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Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Применить Всего найдено 3667. Отображено 100.
03-07-2018 дата публикации

Крышка отсека корабельной пусковой установки

Номер: RU0000181015U1
Автор: Владимир Пантилеймонович Манько, Фариз Хакимянович Хасанов, Юрий Леонидович Заболотный
Принадлежит: АО "Научно-производственное предприятие "Старт" им. А.И. Яскина"

Полезная модель относится к вооружению, конкретно, к бронированным крышкам пусковых установок (ПУ), может быть использована в корабельных установках вертикального пуска. Технической задачей является упрощение бронезащиты крышки, снижение ее массы и стоимости, повышение эффективности.Корабельная ПУ содержит раму 1. Рама включает отсеки 3. Крышка отсека содержит корпус 4, соединенный с рамой при помощи торсиона 5. На корпусе сверху закреплен бронелист 8 (далее - лист). Лист 8 изготовлен из вторичного титанового сплава. Внешняя сторона листа 8 упрочнена по специальной технологии до твердости и вязкости конструкционной брони. Лист 8 закреплен с зазором относительно корпуса крышки при помощи соединителей в виде болтов 13 и дистанционных втулок 9. Для защиты крышки от электрокоррозии соединители снабжены электроизолирующими прокладками 14.Как показали испытания, бронированная крышка в виде разнесенной конструкции из титанового броневого листа и стального корпуса, соединенных между собой с зазором, обеспечивает требуемую броневую защиту отсека ПУ от пуль и осколков. При этом крышка имеет сниженную массу и стоимость в сравнении с аналогами. 3 з.п. ф-лы, 3 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 181 015 U1 (51) МПК B63G 1/00 (2006.01) F41F 3/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B63G 1/00 (2006.01); F41F 3/04 (2006.01) (21)(22) Заявка: 2017115272, 28.04.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): АО "Научно-производственное предприятие "Старт" им. А.И. Яскина" (RU) 03.07.2018 (56) Список документов, цитированных в отчете о поиске: RU 2557123 C1, 20.07.2015. RU (45) Опубликовано: 03.07.2018 Бюл. № 19 1 8 1 0 1 5 R U 2090820 C1, 20.09.1997. RU 2572424 C1, 10.01.2016. US 5062345 A1, 05.11.1991. EP 935118 B1, 20.04.2005. US 6230604 B1, 15.05.2001. (54) КРЫШКА ОТСЕКА КОРАБЕЛЬНОЙ ПУСКОВОЙ УСТАНОВКИ (57) Реферат: Полезная модель относится к ...

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Номер записи: 1
02-08-2018 дата публикации

Катушка для безынерционной размотки кабеля

Номер: RU0000182066U1
Автор: Аркадий Анатольевич Хлапов, Владимир Яковлевич Геча, Дмитрий Владимирович Геча, Татьяна Александровна Хлапова, Эдуард Яковлевич Геча
Принадлежит: ЗАО "Московское техническое бюро"

Полезная модель относится к конструкциям безынерционных катушек с оптическим или электрическим кабелем, предназначенных для телеуправления движущимися объектами в воде, воздухе и безвоздушном пространстве, а также для передачи информации между ними. Задачей, решаемой заявленной полезной моделью, является создание относительно простой конструкции безынерционной катушки без приклеивания витков кабеля, которая позволит минимизировать габаритные размеры блоков, предназначенных для ее размещения, с обеспечением надежной безынерционной размотки оптического кабеля (при необходимости, также - электрического и комбинированного) без ухудшения его характеристик передачи. Технический результат достигается тем (фиг. 2), что вал катушки выполнен полым, передняя щека представляет собой тело вращения и содержит направляющую область, выполненную в виде «воронки» и расположенную соосно с валом катушки, конец кабеля, предназначенный для соединения с подвижным относительно катушки объектом, заведен через направляющую область передней щеки в вал катушки и выведен из него через отверстие в опорной щеке, расположенное соосно с валом, минимальный радиус кривизны внешнего профиля передней щеки (R1) катушки, а также профиля направляющей воронки (R2) составляет не менее 20 диаметров кабеля, поверхность передней щеки катушки, соприкасающаяся с разматываемым кабелем, обработана таким образом, что обеспечивается минимальный коэффициент трения между щекой катушки и кабелем, намотка катушки является «полной» - по всей высоте щеки катушки, соприкасающейся с разматываемым кабелем. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 182 066 U1 (51) МПК F42B 15/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F42B 15/04 (2006.01) (21)(22) Заявка: 2017143604, 13.12.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: 02.08.2018 (73) Патентообладатель(и): ЗАО "Московское техническое бюро" (RU) (45) Опубликовано: 02.08.2018 Бюл. № 22 ...

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Номер записи: 2
04-10-2021 дата публикации

Боевая машина тяжелой огнеметной системы

Номер: RU0000206960U1
Автор: Александр Петрович Болдырев, Александр Сергеевич Клещёв, Борис Иванович Еременко, Денис Александрович Пронкин, Игорь Эдуардович Лобов
Принадлежит: Акционерное общество "Омский завод транспортного машиностроения"

Полезная модель относится к боевой реактивной технике, а конкретно к боевым машинам тяжелой огнеметной системы, выполненным на танковом шасси и предназначенным для транспортировки, наведения на цель и пусков неуправляемых реактивных снарядов, и использования в различных видах наступательного и оборонительного боя в качестве средства огневой поддержки.Боевая машина реактивной системы залпового огня (БМ РСЗО) на шасси базового танка, содержащая корпус, на погонном устройстве которого закреплена поворотная платформа с установленной на ее выносных кронштейнах пусковой установкой, боевое отделение, расположенное в поворотной платформе, с рабочими местами командира и наводчика, рабочее место механика-водителя, размещенное в корпусе шасси, надгусеничные полки, передние и задние аутригеры, систему постановки дымовой завесы, систему электроснабжения. Привод вертикального наведения пусковой установки, выполненный так, что верхний носовой лист корпуса, правая и левая надгусеничные полки оборудованы комплексом встроенной динамической защиты (ВДЗ).Техническим результатом полезной модели является повышение защиты экипажа и внутреннего оборудования БМ-1 от современных БПС и кумулятивных средств поражения (ПТУР и РПГ). РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 206 960 U1 (51) МПК F41F 3/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F41F 3/04 (2021.08) (21)(22) Заявка: 2021117069, 11.06.2021 (24) Дата начала отсчета срока действия патента: Дата регистрации: 04.10.2021 (45) Опубликовано: 04.10.2021 Бюл. № 28 2 0 6 9 6 0 R U (54) Боевая машина тяжелой огнеметной системы (57) Реферат: Полезная модель относится к боевой реактивной технике, а конкретно к боевым машинам тяжелой огнеметной системы, выполненным на танковом шасси и предназначенным для транспортировки, наведения на цель и пусков неуправляемых реактивных снарядов, и использования в различных видах наступательного и оборонительного боя в качестве средства огневой ...

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Номер записи: 3
16-02-2012 дата публикации

Mobile missile launch system and method thereof

Номер: US20120036987A1
Автор: Alasani Prasad Goud, Atul Gupta, Bimal Gautam, Paras Ram, Ravindra Sudhakar Khire, Sanjay Kumar, Shreedhar Aravind Katti, Siddalingappa Guruprasad, Tushar Kant Santosh, Vikas Narayan Waghmare
Принадлежит: Director General Defence Res and Dev Organization Ministry of Defence Government of India

The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle ( 14 ) having a chassis structure adapted to carry the launch system; a mounting frame ( 16 ) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame ( 16 ); plurality of canisters ( 43 ) mounted onto said beam ( 22 ) and plurality of missiles ( 11 ) ensconced within the canisters ( 43 ); plurality of containers ( 42 ) enclosing said canisters ( 43 ) and are connected to the saddles ( 32, 34 ) for linear movement; plurality of resting units ( 27 ) abutting to rear end of the canisters ( 43 ) and are adapted to move linearly to transfer reaction forces from said missiles ( 11 ) to ground.

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Номер записи: 4
15-03-2012 дата публикации

Method for releasing an unmanned missile from a carrier aircraft

Номер: US20120061507A1
Автор: Christine Stumpp, Michael Grabmeier
Принадлежит: LFK Lenkflugkoerpersysteme GmbH

Unmanned missile and method for releasing the unmanned missile from a carrier aircraft, in which the missile has an autonomous flight control device that acts on control devices of the missile. The method includes adjusting vertical rudders and elevators of the missile into a neutral position in which a respective rudder angle is 0°, separating electrical and mechanical connections between the missile and the carrier aircraft, and detecting, via sensors of the missile, that the separating has occurred. The method also includes activating the autonomous flight control device and automatically controlling the missile with the flight control device and the control devices based upon correction flight condition variables caused by a prevailing downwash between the missile and the carrier aircraft, and automatically controlling the missile with the flight control device and the control devices based on data stored in at least one storage device on the missile.

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Номер записи: 5
22-03-2012 дата публикации

Submersible transport and launch canister and methods for the use thereof

Номер: US20120068010A1
Автор: David E. Bossert, Jeffrey N. Zerbe, Ray Sampson
Принадлежит: Raytheon Co

Embodiments of a method for deploying an airborne object are provided utilizing a submersible transport and launch canister of the type that includes a pressure vessel in which the airborne object is stored and a cap which sealingly engages the pressure vessel. In one embodiment, the method includes the steps of positioning an end portion of the pressure vessel above the surface level of a body of water, opening the cap, and launching the airborne object from the pressure vessel while in the body of water.

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Номер записи: 6
19-04-2012 дата публикации

Method of intercepting incoming projectile

Номер: US20120091253A1
Автор: Garrett L. Hall, Henri Y. Kim, James H. Dupont, James M. Cook, Richard D. Loehr, William N. Patterson
Принадлежит: Raytheon Co

A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.

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Номер записи: 7
21-06-2012 дата публикации

Self-Contained Munition Gas Management System

Номер: US20120152090A1
Автор: Daniel A. Skurdal, John Snediker
Принадлежит: Lockheed Martin Corp

An apparatus is disclosed that is a self-contained gas management system (hereinafter “GMS”) that accommodates individual canisters of highly energetic small munitions, but is not so limited. By decoupling the gas management system for a given munition from an adjacent munition, the risk of downing a multi-pack launcher or munition adapter is reduced. Thermal wear, overheating, restrained firing and aft closure debris can be isolated through the separation of gas management systems. In addition, the GMS allows for ease of replenishment and maintenance of a given sub-cell of a multi-pack system. The GMS works with existing munitions and canisters without the need to modify them. Each GMS is dimensioned to fit the canistered munition it receives as well as the launch system with which it is used. The illustrative GMS comprises a plenum, and a first and a second uptake structure. The plenum receives the exhaust from the canistered munition when the munition fires. The plenum is fluidically coupled to the first and second uptake structures. The uptake structures in the illustrative embodiment receive the missile exhaust from the plenum and vent the exhaust to the atmosphere. In the illustrative embodiment, the first and second uptake structures are disposed along opposite sides of the canistered munition, flanking it.

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Номер записи: 8
06-06-2013 дата публикации

MISSILE CANISTER

Номер: US20130139676A1
Автор: Bowen Bryan, Kavanagh Terence Edward, MACHELL Anthony, Turner Dennis George
Принадлежит: MBDA UK LIMITED

The invention covers a missile canister () for accommodating a missile () along a longitudinal axis (L) of the canister. The canister comprises a plurality of generally planar longitudinal wall portions () connected together to form a tubular vessel having a polygonal cross-section. The interconnecting portions () between wall sections () are generally flexible so that when a missile () is launched the bending moment at the interconnecting portions () generated by the increase of pressure in the vessel is substantially less than the bending moment () generated at the wall portions (). The interconnecting portions () allow relative angular deflection between adjacent wall portions () at respective interconnecting portions () when said missile () is launched. 1. A missile canister for accommodating a missile along a longitudinal axis of the canister , the canister comprising a plurality of generally planar longitudinal wall portions connected together to form a tubular vessel having a polygonal cross-section , the interconnecting portions between wall sections are generally flexible so that when a missile is launched the bending moment at the interconnecting portions generated by the increase of pressure in the vessel is substantially less than the bending moment generated at the wall portions.2. A missile canister as claimed in claim 1 , wherein the interconnecting portions allow relative angular deflection between adjacent wall portions at respective interconnecting portions when a missile is launched.3. A missile canister as claimed in claims 1 , wherein the interconnecting portions generally simply support the wall portions therebetween.4. A missile canister as claimed in claim 1 , wherein the interconnecting portions comprise a thin wall section relative to the thickness of the wall portions.5. A missile canister as claimed in claim 1 , wherein the interconnecting portions have relatively high tensile strength in a hoop direction and relatively low compressive ...

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Номер записи: 9
21-11-2013 дата публикации

Kinematic Mount

Номер: US20130305584A1
Автор: Cosentino Timothy
Принадлежит:

A mounting device for use with a firearm comprising: (a) a first frame; (b) a second frame, where the first frame and the second frame collectively include a first sphere and a second sphere, where the first frame and the second frame collectively include a first receiver configured to restriction motion of the first sphere in at least one degree of freedom, where the first frame and the second frame collectively include a second receiver configured to restriction motion of the second sphere in at least one degree of freedom, and where the first frame and the second frame collectively include a projection and a lock configured to engage the projection and: (a) restrict motion of the first sphere in a degree of freedom not restricted by the first receiver, and (b) restrict motion of the second sphere in a degree of freedom not restricted by the second receiver. 1. A mounting device for use with a firearm comprising:a first frame;a second frame;wherein the first frame and the second frame collectively include a first sphere and a second sphere;wherein the first frame and the second frame collectively include a first receiver configured to restriction motion of the first sphere in at least one degree of freedom;wherein the first frame and the second frame collectively include a second receiver configured to restriction motion of the second sphere in at least one degree of freedom;wherein the first frame and the second frame collectively include a projection and a lock configured to engage the projection and: (a) restrict motion of the first sphere in a degree of freedom not restricted by the first receiver, and (b) restrict motion of the second sphere in a degree of freedom not restricted by the second receiver.2. The mounting device of claim 1 , wherein:the first frame includes the first sphere and the second sphere; and,the second frame include the first receiver and the second receiver.3. The mounting device of claim 1 , wherein:the first frame includes the first ...

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Номер записи: 10
06-03-2014 дата публикации

VESSEL OF THE TYPE COMPRISING AT LEAST ONE SHAFT FOR RECEIVING AT LEAST ONE MISSILE-LAUNCHING CONTAINER

Номер: US20140060296A1
Автор: Armbrust Marie Anne, Bruneau Herve, Monteil Dominique, Seguinot Didier
Принадлежит: DCNS

Vessel of the type comprising at least one shaft for receiving at least one missile-launching container (), characterised in that the launching container () is received in the shaft with controlled lateral and axial clearance; the upper portion of the side wall of the container is provided with means for centring/guiding same in the shaft; and the lower end includes a container-bearing base () associated with a supporting base () of the vessel by means of shock-filtering set-point damping means (). 1. Vessel of the type comprising at least one shaft for receiving at least one missile-launching container , wherein the launching container is received in the shaft with controlled lateral and axial clearance; the upper portion of the side wall of the container is provided with means for centring/guiding same in the shaft; and the lower end includes a container-bearing base associated with a supporting base of the vessel by means of shock-filtering set-point damping means.2. Vessel according to claim 1 , wherein the shaft and the container have vertical axes.3. Vessel according to claim 1 , wherein the guiding/centring means comprise stops in shock-absorbing material.4. Vessel according to claim 1 , wherein the set-point damping means comprise damping organs connected with pretensioned set-point break strips that are mounted between the bases.5. Vessel according to claim 4 , wherein the damping means comprise at least one damping assembly with metal windings.6. Vessel according to claim 5 , wherein the damping means comprise at least two damping assemblies with metallic windings arranged symmetrically on either side of the container.7. Vessel according to claim 5 , wherein the metal windings are in the form of at least one coil spring organ arranged lying flat between the bases claim 5 , with its opposite edges engaged in openings for corresponding connection lugs of the bases.8. Vessel according to claim 4 , wherein each break strip includes two portions of strip ...

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Номер записи: 11
20-03-2014 дата публикации

Method and Apparatus for Launch Recoil Abatement

Номер: US20140076134A1
Автор: SCHROEDER Wayne K.
Принадлежит: LOCKHEED MARTIN CORPORATION

Recoil forces of a launched missile and the moment force imposed on the launch platform can be reduced by use of a recoil abatement element in communication with a launch tube. The recoil abatement element includes at least one nozzle configured to receive therethrough exhaust gasses from a missile when launched. The nozzle can be canted or otherwise configured to direct the exhaust gasses in a desired direction to thereby offset moment force imposed on the platform by the exhaust gasses. 1. A device for reducing recoil forces of a launched missile comprising:a missile launch tube;a recoil abatement element in communication with the launch tube, the recoil abatement element including at least one nozzle configured to receive therethrough exhaust gasses from a missile.2. The device of wherein the nozzle is configured to direct exhaust gasses in a desired direction.3. The device of wherein the recoil abatement element includes a center element configured to contain objects ejected from a missile.4. The device of further in including a surface for attaching to a platform claim 1 , wherein the platform is an aircraft claim 1 , a landcraft claim 1 , a watercraft claim 1 , or a ground positioned platform.5. The device of wherein the nozzle includes at least four nozzles.6. The device of wherein the nozzle is a continuous or nearly continuous opening of 360 degrees circumference.7. The device of wherein the recoil abatement element is formed at least in part of a material selected from the group consisting essentially of aluminum claim 1 , steel claim 1 , a composite material claim 1 , and ceramic.8. The device of wherein the nozzle incudes a throat configured to restrict flow of gasses passing through the throat.91. The device of wherein the device is configured such that gasses pass through the throat at a velocity of about Mach .10. A method of launching a missile comprising:receiving exhaust gasses from a missile in a cavity;directing the exhaust gasses to a nozzle; ...

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Номер записи: 12
02-01-2020 дата публикации

Missile for intercepting alien drones

Номер: US20200003530A1
Автор: Franco METZ, Manuel METZ
Принадлежит: RHEINMETALL AIR DEFENCE AG, Skysec GmbH

The invention relates to a missile (1) for intercepting alien drones (21), comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1) and the weights (15) can be ejected from the missile (1). The capturing of the alien drone is improved by the fact that the capturing net (9) can be ejected by a first means and the weights (15) can be ejected by a second means, wherein the weights (15) and the capturing net (9) can be ejected at different times from the missile (1).

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Номер записи: 13
10-01-2019 дата публикации

ADAPTER FOR COUPLING A GRENADE LAUNCHER TO A HANDGUARD

Номер: US20190011219A1
Автор: MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

Mounting system operable to couple a grenade launcher to a firearm, the mounting system including a rail system operable to be coupled to a firearm, the rail system comprising at least one rail that is mounted on an underside of a barrel of the firearm that is opposite to sights mounted on an upperside of the barrel. The mounting system includes a front lug that is coupled to the barrel in front of the rail system and aligned with the at least one rail. Additionally, the mounting system includes a grenade launcher rail that is operable to be coupled to the grenade launcher and a lug adapter operable to be coupled to the grenade launcher rail and the front lug. 1. A mounting system operable to couple a grenade launcher to a firearm , the mounting system comprising:a rail system operable to be coupled to a firearm, the rail system comprising at least one rail that is mounted on an underside of a barrel of the firearm that is opposite to sights mounted on an upperside of the barrel;a front lug that is coupled to the barrel in front of the rail system and aligned with the at least one rail;a grenade launcher rail that is operable to be coupled to the grenade launcher; andan lug adapter operable to be coupled to the grenade launcher rail and the front lug.2. The mounting system of claim 1 , wherein a first and second flanges of a rail base of the lug adapter are partially received by the grenade launcher rail and operably couple the lug adapter to the grenade launcher rail.3. A lug adapter operable to couple a grenade launcher rail to a front lug of a firearm claim 1 , the lug adapter comprising:a rail base that is operable to be received by a grenade launcher rail, the rail base having a first end and a second end, the second end being opposite the first end, the rail base forming an opening near the first end, the opening being operable to receive a set screw;a housing protruding from the rail base at the second end and extending towards the first end, the housing ...

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Номер записи: 14
03-02-2022 дата публикации

Light Trigger

Номер: US20220034616A1
Автор: Dorothy Devine Burdine, Lavada Sue Pitts
Принадлежит: Area Denial Systems LLC

A firearm has a trigger shield configured as a protective loop surrounding a first and second switch of the firearm. Each switch actuates the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. Further, the firearm has an emitter mounted on the trigger shield that propagates a light beam to a receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges.

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Номер записи: 15
03-02-2022 дата публикации

Light Trigger

Номер: US20220034617A1
Автор: Burdine Dorothy Devine, Pitts Lavada Sue
Принадлежит: Area Denial Systems, LLC

A firearm has a trigger shield configured as a protective loop surrounding a first and a second switch of the firearm, each switch actuates the function of the firearm when activated by a finger to start the firing process, and the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. The firearm has at least three receivers on the protective loop and at least three beam windows on the protective loop aligned with the three receivers. Further, the firearm has an emitter outside of the protective loop, the emitter propagates a beam of light to a beam splitter, and the beam splitter propagates three beams of light one beam to each of the three beam windows, the three beams of light are incident on one of the respective receivers. Also, when a finger activates one of the switches, the firearm activates, and when the finger breaks one of the beams of light, the firearm discharges. 1. A firearm , comprising:a trigger shield configured as a protective loop surrounding a first and a second switch of the firearm, each switch configured to actuate the function of the firearm when activated by a finger to start or stop the firing process, the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop;at least three receivers on the protective loop; an emitter outside of the protective loop, the emitter configured to propagate a beam of light to a beam splitter, and the beam splitter propagates three fire beams of light, one fire beam to each of the three beam windows, the three beams of light incident on one of the respective receivers;', 'wherein when a finger activates one of the switches, the firearm activates, and when the finger breaks one of the fire beams of light, the firearm discharges., 'at least three beam windows on the protective loop aligned with the three receivers;'}2. The firearm of claim 1 , wherein the finger moves to block or ...

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Номер записи: 16
03-02-2022 дата публикации

Light Trigger

Номер: US20220034618A1
Автор: Burdine Dorothy Devine
Принадлежит: Area Denial Systems, LLC

A firearm has an emitter that propagates a light beam to a receiver and at least two finger position beams that propagate horizontally along the firearm on either side of a switch that provides detection of a position of a finger when the finger blocks and unblocks the finger position beam. Further, when only one finger position beam is blocked, this indicates improper positioning of the finger placing the firearm into a non-dischargeable condition. 1. A firearm , comprising:an emitter that propagates a light beam to a receiver;at least two finger position beams that propagate along the firearm on either side of a switch that provides detection of a position of a finger when the finger blocks and unblocks the finger position beam;wherein when only one finger position beam is blocked, this indicates improper positioning of the finger placing the firearm into a non-dischargeable condition.2. The firearm of claim 1 , wherein the finger moves to block or unblock the light beam by flexion or extension.3. The firearm of claim 1 , wherein the trigger is mounted on a shield.4. The firearm of claim 1 , wherein the emitter is in alignment with the receiver and a beam emitted from the emitter is incident upon the receiver.5. The firearm of claim 1 , wherein the shield may vary in shape claim 1 , vertical or horizontal orientation claim 1 , width claim 1 , and slope.6. The firearm of claim 1 , wherein the trigger comprises one or more of a shield claim 1 , a switch claim 1 , an emitter claim 1 , and a receiver. This application claims priority to and is a divisional of U.S. Pat. No. 10/962,320 entitled Light Trigger and filed on December , , which is incorporated herein by reference in its entirety.An optical firearm trigger is disclosed, revealing means and methods of initiating discharge of a firearm without the use of a mechanical trigger. In this manner the grip of the firearm will not change due to the mechanical loading required to pull the trigger further alleviating the ...

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Номер записи: 17
17-01-2019 дата публикации

MISSILE CANISTER GATED OBTURATOR

Номер: US20190017780A1
Автор: Miller Mark J., Woods Peter C.
Принадлежит:

Apparatus and methods relating to a missile canister that utilizes a variable obturator assembly. The variable obturator assembly can include a plurality of gates that adjust based upon canister pressure at a base plate. In a maximum pressure situation experienced during successful missile egress from the canister, one or more of the gates can open in response to canister flyout pressure so as to increase flow area through the base plate, thereby reducing canister pressure. In a restrained firing scenario, the plurality of gates remain closed thereby preventing missile exhaust gases from flow up past the base plate which could lead to heating of a rocket motor and warhead. The variable obturator assembly can have multiple individual gates that are mounted to the base plate with a hinge assembly, with the gates held in a closed position against the base plate with a spring assembly. 1. A method for reducing canister pressure when firing a missile from a vertical launch system , the method comprising:mounting a missile within a canister, said canister comprising a forward end and an aft end and a central axis extending from the forward end to the aft end, said forward end disposed approximate a missile nose while the aft end is disposed proximate a missile exhaust nozzle;attaching an obturator plate to the canister approximate the nozzle;positioning at least one obturator gate on the said obturator plate, said obturator gate in a closed position prior to firing and transitionable to an open position after firing the missile; andfiring the missile;wherein firing the missile creates a flyout pressure that opens the obturator gate to increase the opening size of the obturator plate, said increase in obturator opening size reduces the shell pressure.2. The method for reducing canister pressure of further including attaching the obturator gate to the obturator plate by a hinge assembly.3. The method for reducing canister pressure of wherein the hinge assembly has a spring ...

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Номер записи: 18
24-01-2019 дата публикации

SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE

Номер: US20190023415A1
Автор: Andryukov Alexander, McNeil John, Miralles Carlos Thomas, Su Guan H.
Принадлежит:

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. 1. A system comprising:a launcher having a launcher volume defined by a continuous launcher wall, the launcher wall having radio-frequency (RF) permeability; anda receiver disposed within the launcher volume, the receiver receiving wireless communication via one or more RF signals received wirelessly through the launcher wall.2. The system of further comprising:a transmitter disposed within the launcher volume, the transmitter transmitting wireless communication via one or more RF signals transmitted wirelessly through the launcher wall.3. The system of further comprising:an unmanned aerial vehicle (UAV) disposed within the launcher volume.4. The system of claim 1 , wherein the receiver further comprises an RF antenna disposed within the launcher volume.5. The system of claim 1 , wherein the receiver is in communication with an external communications node claim 1 , ...

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Номер записи: 19
23-01-2020 дата публикации

VEHICLE DEVICE SEPARATION SYSTEM WITH TELESCOPING PISTON SPRINGS

Номер: US20200025513A1
Автор: Bopp Jayson Kahle, Kavalar Brian R., Streib Stephen A., Wright Philip
Принадлежит:

An ejector system for ejecting/separating a store, such as a weapon, from a launch platform includes a pair of spring assemblies that each include nested springs that are contained in a housing when the spring assemblies are in a compressed configuration. To separate the store from the aircraft the spring assemblies each move from the initial compressed configuration to an extended configuration, using the potential energy stored in the springs when compressed. The extension of the springs extends the springs mostly out of the spring assembly housings, extending telescoped sleeves of the spring assemblies. The extension of the spring assemblies provides a safe and steady way of separating the store from the launch platform, while having the advantages of being reusable, low cost and low weight, not producing any debris, and providing a softer push than may be produced by other separation mechanisms, such as the use of pyrotechnic devices. 1. An ejector system for separating a store from a launch platform , the ejector system comprising:spring assemblies that engage different portions of the store;wherein the spring assemblies have a compressed position when the store is mechanically coupled to the launch platform;wherein the spring assemblies extend from the compressed position to an extended position to separate the store from the launch platform; andwherein each of the spring assemblies includes at least two nested springs.2. The system of claim 1 , wherein claim 1 , for each of the spring assemblies claim 1 , the at least two nested springs includes a pair of nested coil springs claim 1 , an inner spring and an outer spring.3. The system of claim 2 , wherein the outer spring has a larger wire diameter than that of the inner spring.4. The system of claim 2 , wherein the outer spring has a larger spring constant than that of the inner spring.5. The system of claim 2 , wherein each of the spring assemblies further includes a nesting device that mechanically engages ...

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Номер записи: 20
01-02-2018 дата публикации

Torpedo Power Cable Guide System

Номер: US20180031148A1
Автор: Allan Laperche, Angelo Di Biasio, Michael D Cullinane, William P Barker
Принадлежит: Individual

A guide system for securing a torpedo pre-set power cable to move within a torpedo tube is provided. The guide system includes a longitudinal keeper and a guide assembly. The longitudinal keeper secures the power cable and includes a protrusion. A channel of the guide assembly connects to a Torpedo Mount Dispenser such that the channel receives the protrusion with the keeper sliding within and along a length of the channel. An alternate channel connects to a torpedo tube land and is configured to pivot to a stowed position and a deployed position where the channel is configured to receive the protrusion of the keeper such that the keeper slides within and along a length of the channel. When using each of the channels, the power cable can move within the torpedo tube when the protrusion of the keeper with the secured power cable slides within each channel.

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Номер записи: 21
17-02-2022 дата публикации

Light Trigger

Номер: US20220049916A1
Автор: Burdine Dorothy Devine, Pitts Lavada Sue
Принадлежит: Area Denial Systems, LLC

A firearm has a trigger shield that is a protective loop surrounding a first and second switch of the firearm and the switches actuate the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. The protective loop is vertically aligned having the first and second switches on respective shorter sides of the protective loop. The firearm further has a first emitter mounted on the trigger shield that propagates a first light beam to a first receiver mounted on an opposite side of the trigger shield and a second emitter mounted on the trigger shield that propagates a second light beam to a second receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges. 1. A firearm , comprising:a trigger shield configured as a protective loop surrounding a first, second, third, and fourth switch of the firearm, the switches configured to actuate the function of the firearm when activated by a finger to start the firing process, the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop, the protective loop is vertically aligned having the first and second switches on respective shorter sides of the protective loop, the third switch is on a third side and the fourth switch is on a fourth side of the protective loop and the third and fourth switches are on the longer sides of the protective loop;a first emitter mounted on the trigger shield that propagates a first light beam to a first receiver mounted on an opposite side of the trigger shield;a second emitter mounted on the trigger shield that propagates a second light beam to a second receiver mounted on an opposite side of the ...

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Номер записи: 22
17-02-2022 дата публикации

333Light Trigger

Номер: US20220049917A1
Автор: Dorothy Devine Burdine, Lavada Sue Pitts
Принадлежит: Area Denial Systems LLC

A firearm has a trigger shield configured as a protective loop surrounding at least one switch and the at least one switch actuates the function of the firearm when activated by a finger to start the firing process. The firearm further has at least one receiver, at least one position beam emanating horizontally that determines a position of a finger by the finger blocking or not blocking the position beam, and at least one emitter that propagates a beam of light, the beam of light incident on the at least one receiver. Further, when a finger activates the switch, the firearm activates, and when the finger breaks the beam of light, the firearm discharges.

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Номер записи: 23
17-02-2022 дата публикации

THROWING DEVICE WITH TWO-STAGE PROPULSION SYSTEM

Номер: US20220049928A1
Автор: HUANG JIAN-LIN
Принадлежит:

The present disclosure provides a throwing device with a launcher and a propulsion system. The propulsion system comprises a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system. The launcher comprises: a tube for containing the propulsion system; and a trigger for triggering the ignition cartridge. A screw hole is in center of a bottom of the first chamber; nozzles are located around the screw hole; and a collar with a hole fixed in the bottom of the first chamber, wherein the ignition cartridge is fixed in the screw hole by the collar. The ignition cartridge comprises an explosive primer, and the launcher further comprises a firing pin triggered by the trigger to hit the explosive primer. 1. A throwing device , comprising:{'claim-text': ['a first section comprising a first chamber containing a first propellant, and an ignition cartridge for igniting the first propellant;', 'a second section that is connected to the first section and comprises a second chamber containing a second propellant; and', 'a retardant set between the first propellant and the second propellant for delaying the combustion from the first propellant to the second propellant; and'], '#text': 'a propulsion system comprising:'}{'claim-text': ['a tube for containing the propulsion system; and', 'a trigger for triggering the ignition cartridge.'], '#text': 'a launcher comprising:'}2. The throwing device of claim 1 , further comprising:a screw hole in center of a bottom of the first chamber;nozzles around the screw hole; anda collar with a hole fixed in the screw hole,wherein the ignition cartridge is fixed in the screw hole by the collar.3. The throwing device of claim 2 , wherein the ignition cartridge comprises an explosive primer claim 2 , and the launcher further comprises a firing pin triggered by the trigger to hit the explosive primer.4. The throwing device of claim 3 , wherein the ignition ...

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Номер записи: 24
17-02-2022 дата публикации

TWO-STAGE PROPULSION SYSTEM

Номер: US20220049935A1
Автор: HUANG JIAN-LIN
Принадлежит:

The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system. 1. A propulsion system , comprising:a first section including a first chamber containing a first propellant;a second section connected to the first section, the second section including a second chamber containing a second propellant; anda retardant set between the first propellant and the second propellant for delaying combustion from the first propellant to the second propellant, the retardant set including a dish with holes in a bottom, the dish containing a third propellant, the dish and the third propellant being covered by a mesh.2. The propulsion system of claim 1 , wherein the third propellant has a low regression rate.3. The propulsion system of claim 1 , wherein the third propellant includes Sorbitol claim 1 , Potassium Nitrate claim 1 , and Iron Oxide.4. The propulsion system of claim 2 , wherein the third propellant includes Sorbitol claim 2 , Potassium Nitrate claim 2 , and Sodium Bicarbonate.5. The propulsion system of claim 4 , wherein a ratio of the Sodium Bicarbonate to the Sorbitol and the Potassium Nitrate in the third propellant is about 15 to 100 in weight.6. The propulsion system of claim 4 , wherein a ratio of the Sorbitol to the Potassium Nitrate in the third propellant is about 35 to 65 in weight.7. A propulsion system claim 4 , comprising:a first section including a first chamber containing a first propellant;a second section connected to the first section, the second section including a second chamber containing a second propellant; anda retardant set between the first propellant and the second propellant for delaying combustion from the first propellant to the second propellant,wherein the retardant set includes a third propellant and a dish with holes in a bottom for containing the third propellant, the third propellant ...

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Номер записи: 25
24-02-2022 дата публикации

DEVICE FOR EXTRACTING A LARGE-CALIBER PROJECTILE JAMMED IN A WEAPON BARREL

Номер: US20220057157A1
Автор: Multon Patrick, Pipart Romain
Принадлежит: NEXTER SYSTEMS

A device, and method for using the device, for extracting a large-caliber projectile jammed in a barrel of a weapon including a solid body having a diameter smaller than the caliber of the barrel and intended to be introduced into the barrel at the muzzle of the latter and then released in the barrel in order to impact, by inertia, the jammed projectile. The device is at least two radially expandable locking means, each able to move between a locked position in which it is applied radially against the inner wall of the barrel and a released position in which it is not applied against the barrel, the passage of the locking means from one position to the other by an expansion means, the device includes a translation means enabling a first locking means to be translated axially to a second locking means. 1. An extraction device for extracting a large-caliber projectile jammed in a barrel of a weapon , the extraction device comprising a solid body , the solid body having a diameter smaller than the caliber of the barrel and the solid body being intended to be introduced into the barrel at a muzzle of the barrel and then to be released in the barrel in order to impact by inertia the projectile jammed in the barrel , the extraction device being characterized in that the extraction device comprises at least two radially expandable locking means , each able to move between a locked position in which the locking means is applied radially against an inner wall of the barrel and a released position in which the locking means is not applied against the barrel , the passage of the locking means from one position to the other being provided by an expansion means , the extraction device comprising a translation means enabling a first one of the locking means to be translated axially with respect to a second one of the locking means.2. The extraction device according to claim 1 , characterized in that each locking means comprises a toroidal chamber made of elastic plastic material ...

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Номер записи: 26
16-02-2017 дата публикации

Rocket Extraction Device and Method

Номер: US20170045323A1
Автор: Gainer Michael Harvey
Принадлежит: United States Government, as Represented by the Secretary of the Army

A rocket extraction device and method is disclosed. In one embodiment, the device comprises an upper and a lower casing; an interior cutout in each of the upper and lower casings, the interior cutouts having contours matching exterior surface contours of a rocket fuze; an upper fuze clamp and a lower fuze clamp disposed respectively within the upper and lower casings, each upper and lower fuze clamp having interior surface contours matching exterior surface contours of the rocket fuze; a clamp adjustment screw onto which the upper fuze clamp is mountable; an adjustment wheel mountable at the exterior end of the clamp adjustment screw by which the clamp adjustment screw and the upper fuse clamp are movable to secure the upper and lower fuze clamps to the fuze and force the fuze into the contours of the lower fuze clamp and the interior cutout of the lower casing to lock the fuze into the rocket extraction device. There is an eyebolt or similar type device mountable to the exterior of the rocket extraction device, to which force is applied to remove a rocket from a storage tube. In another embodiment, the method comprises attaching the rocket extraction device securely to a fuze on a rocket and pulling on the rocket extraction device to remove the rocket from a storage tube. 1. A rocket extraction device comprising:An upper and a lower casing;An interior cutout in each said upper and lower casing, said interior cutouts matching exterior surface contours of a rocket fuze;An upper fuze clamp and a lower fuze clamp disposed respectively within said upper and lower casings, each having interior surface contours matching said exterior surface contours of said rocket fuze;A clamp adjustment screw disposed through said upper fuze clamp;An adjustment wheel mountable at an exterior end of said clamp adjustment screw by which said clamp adjustment screw and said upper fuse clamp are movable; andAn eyebolt type device fixedly mountable to an exterior of said rocket extraction ...

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Номер записи: 27
26-02-2015 дата публикации

Multiple Missile Carriage and Launch Guidance Module

Номер: US20150053073A1
Автор: Kalms William, Snediker John-Nathan Russell
Принадлежит: LOCKHEED MARTIN CORPORATION

A multiple missile carriage and launch guidance module comprising a plurality of missile launch rails that are each configured to carry and guide the launch of a missile and are carried on a common missile carriage wall in respective positions and orientations allowing for missile carriage and launch from the rails. 1. A multiple missile carriage and launch guidance module comprising:a plurality of missile launch rails, each rail being configured to carry and guide the launch of a missile; anda common missile carriage wall carrying the plurality of missile launch rails in respective positions and orientations allowing for missile carriage and launch from the rails.2. A multiple missile carriage and launch guidance module as defined in in which the rails are distributed between and carried by opposite-facing front and back sides of the carriage wall.3. A multiple missile carriage and launch guidance module as defined in in which the carriage wall comprises a carriage wall core defined by generally parallel spaced-apart front and back structural skins of the carriage wall configured to cooperate in the carriage and distribution of missile carriage loads.4. A multiple missile carriage and launch guidance module as defined in in which the carriage wall comprises filler disposed between the front and back structural skins.5. A multiple missile carriage and launch guidance module as defined in in which the module includes:at least one sprinkler nozzle carried by the carriage wall and configured to emit fluid in a direction and manner that suppresses missile exhaust flame; andsprinkler piping connected at an outlet end to the sprinkler nozzle and connectable at an inlet end to a fluid source, the sprinkler piping being configured to provide a fluid pathway from a fluid source through the carriage wall core and carriage wall structural skin for a fluid to the sprinkler nozzles.6. A multiple missile carriage and launch guidance module as defined in in which the sprinkler ...

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Номер записи: 28
13-02-2020 дата публикации

Extended Drone Range

Номер: US20200047894A1
Автор: Bruno Jocelyn
Принадлежит:

This disclosure generally relates to the use of solid fuel rockets with drone aircraft. Solid fuel tanks can be mounted to a Drone, for example, the underside of the drone. They may be built similar to guided missiles and once they complete their task they may detach from the drone and, in embodiments, equipped with all components found on guided missiles, i.e., guidance Section, control section, wings and fins, they may return to point of origin. In other embodiments, they may be deployed as missiles or remain attached to the drone. 1. A drone aircraft comprising:engines; andone or more solid fuel rockets.2. The drone aircraft of claim 1 , wherein the one or more solid fuel rockets comprise:a guidance section;a solid fuel core,a control section including wings, andfins.3. The drone aircraft of claim 2 , wherein the one or more solid fuel rockets further comprises:a section for expendable fuel;a section for fuel reserved for missile use; andan armament compartment.4. The drone aircraft of claim 1 , wherein the one or more solid fuel rockets are attached to the underside of the drone aircraft.5. The drone aircraft of claim 1 , wherein there are two solid fuel rockets.6. A method of flying the drone aircraft of claim 1 , comprising:launching the drone using the solid fuel rockets;flying the drone aircraft some distance using the solid fuel rockets.7. The method of claim 6 , wherein the solid fuel rockets power the drone until all expendable solid fuel is used.8. The method of claim 7 , wherein the solid fuel rockets are deployed as missiles.9. The method of claim 6 , further comprising:detaching the solid fuel rockets from the drone after the flying of some distance and turning on the drone engines;returning the solid fuel rockets to the vicinity of the point of origin, or some other location, for re-use.10. The method of claim 9 , wherein the solid fuel rockets return to the vicinity of the point of origin for re-use.11. The method of claim 9 , wherein the solid fuel ...

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Номер записи: 29
14-02-2019 дата публикации

TORPEDO LAUNCHING TUBE AND NAVAL PLATFORM COMPRISING AT LEAST ONE SUCH TUBE

Номер: US20190049216A1
Автор: LAMOTTE Arnaud, PELISSIER Cyril, Roy Philippe
Принадлежит:

Disclosed is an ordinance-launching tube, including a rear door and an expulsion circuit between a source of pressurized fluid and the tube, and provided with a unit for closing this circuit having an actuator that can be maneuvered by an operator in order to permit the expulsion, the actuator being associated with a detector for the presence of the rear door in the tube-closing position and with a lock for this rear door in the tube-closing position, which can be actuated via a bolt that the operator can move between a first position preventing expulsion and a second position permitting expulsion when the door is in the closing position and locked. The bolt includes an abutment movable between a position blocking the actuator in position to prevent expulsion, and a position releasing the actuator so that they may be actuated by the operator, and thus permit expulsion. 11245120212322622422427282930312121. An ordinance-launching tube () , of the type comprising a rear door () and an expulsion circuit () between a source of pressurized fluid () and the tube () , and provided with means for closing this circuit that comprise actuating means ( , ) that can be maneuvered by an operator in order to permit the expulsion , these actuating means being associated with means for detecting () the presence of the rear door () in the tube-closing position and with means for locking () this rear door () in the tube-closing position , which can be actuated via a bolt () that the operator can move between a first position preventing expulsion and a second position permitting expulsion when the door () is in the closing position and locked , wherein the bolt () comprises abutment means ( , , , , ) that can be moved between a position blocking the actuating means () in position in order to prevent expulsion , and a position releasing these actuating means () so that they may be actuated by the operator , and thus permit expulsion.222321. The ordinance-launching tube according to claim ...

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Номер записи: 30
14-02-2019 дата публикации

RAPID VISUAL AND PHYSICAL MULTIPLE TOLERANCES AND ALIGNMENTS VERIFICATION STRUCTURE ASSEMBLY AND RELATED METHODS

Номер: US20190049241A1
Автор: Broe Kevin Michael, Halter Mark, Mowery Steven, Mullis Tyler
Принадлежит: NSWC CRANE

Various embodiments of this disclosure relates to a methods and related apparatuses for rapidly and visually determining and verifying multiple interface alignments of parts within a system. In particular, embodiments of the invention are directed to methods and related apparatuses enabling rapid visual determining and verifying multiple interface alignments of parts within at least one first system interface part that cooperatively engage with at least one second system's interface part each having at least one system-sub-system assembly alignment datum that requires the at least one first and second system's interface parts cooperatively and engagingly align within multiple respective tolerances of alignment. 2. A VSA system as in claim 1 , said first and second alignment keys each further comprising:a protrusion which is disposed into said third and fourth apertures;a body, which fits inside said third and fourth apertures when said first and second alignment keys are inserted through said third and fourth apertures;a knob, which facilitates gripping of said first and second alignment keys when said first and second alignment keys are inserted or removed from said third and fourth apertures.3. A VSA system as in claim 1 , further comprising: first and second opposing surfaces on a body;', 'a protrusion located on said second surface of said body wherein said protrusion is shaped substantially similar to said third recessed surface and extends outward from said second surface of said body at a distance slightly more than the maximum height tolerance range., 'wherein said height range verification tool comprises, 'a height range verification tool;'}4. A method of verifying structure alignments comprising:providing a position sensitive article (PSA) that includes a body formed with a first PSA body side, a second PSA body side opposing the first side, a first PSA body end, and a second PSA body end that is formed opposing the first PSA body end, the PSA body further ...

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Номер записи: 31
25-02-2016 дата публикации

PAYLOAD LAUNCHER AND AUTONOMOUS UNDERWATER VEHICLE

Номер: US20160054097A1
Автор: Gordon, JR. Robert P., LEWIS Martin C., SYLVIA Russell M., WHALEN Mark E.
Принадлежит:

A payload launch system is described that provides one launch solution suitable for multiple applications. A payload, such as a UAV, is launched from a sealed launch tube using compressed gas or other energy source. The launch tube can be used to transport and protect the payload from harsh environments for extended periods prior to launch. 1. A payload launch system , comprising:a launch tube defining a launch chamber, a cap releasably secured to the launch tube and closing an open end of the launch chamber;a payload and sabot disposed within the launch chamber, the payload is connected to the sabot; andan energy source in the launch tube that can be selectively applied to the payload and sabot to launch the payload from the launch chamber.2. The payload launch system of claim 1 , wherein the energy source comprises a source of compressed gas.3. The payload launch system of claim 2 , wherein the source of compressed gas comprises a compressed gas storage chamber fluidly separated from the launch chamber by a valve that is positioned to selectively place the compressed gas storage chamber in fluid communication with the launch chamber.4. The payload launch system of claim 1 , wherein the payload is an unmanned aerial vehicle.5. The payload launch system of claim 1 , further comprising a stowed claim 1 , deployable lift bag in the launch tube.6. The payload launch system of claim 1 , further comprising a controller electronics assembly in the launch tube claim 1 , the controller electronics assembly includes a tilt sensor.7. The payload launch system of claim 1 , further comprising a propulsion mechanism connected to the launch tube that propels the launch tube.8. The payload launch system of claim 7 , wherein the propulsion mechanism comprises a propeller; and further comprising a motor connected to the propeller claim 7 , and one or more the batteries providing power to the motor.9. The payload launch system of claim 1 , further comprising a stop mechanism in the ...

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Номер записи: 32
04-03-2021 дата публикации

AIRCRAFT ARMAMENT SYSTEM CONTROL ELECTRONICS

Номер: US20210063114A1
Автор: Broadhead David J., Deininger Gregory J., Featherston Katherine
Принадлежит:

A computer implemented method for integrating a platform, different stores, and/or carriage racks is implemented in an electronics control system that is communicatively couplable to each of the platform, the different stores, and/or the carriage racks. The computer implemented method includes defining parameters for a plurality of predetermined electrical interfaces for predetermined platforms, stores, and carriage racks, and message sets corresponding thereto, identifying electrical interfaces of the platform, at least one store and/or at least one carriage rack based on the defined parameters, communicating different messages between the platform, the store and/or the carriage rack without affecting an Operational Flight Program (OFP) of the platform, with each communication between the platform, and the store and/or the carriage rack being independent, translating messages between the platform and the store and/or the carriage rack, and controlling operation of the carriage rack and/or the store based on the messages. 1. A computer implemented method for integrating a platform , different stores , and/or carriage racks , wherein the computer implemented method is implemented in an electronics control system that is communicatively couplable to each of the platform , the different stores , and/or the carriage racks , the computer implemented method comprising:defining parameters for a plurality of predetermined electrical interfaces for predetermined platforms, stores, and carriage racks, and message sets that correspond to the predetermined platforms, stores, and carriage racks;identifying electrical interfaces of the platform, at least one store of the different stores and/or at least one carriage rack of the carriage racks to be integrated based on the defined parameters;communicating different messages between the platform, the at least one store and/or the at least one carriage rack without affecting an Operational Flight Program (OFP) of the platform, ...

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Номер записи: 33
28-02-2019 дата публикации

AIRCRAFT

Номер: US20190061920A1
Автор: Yoshimoto Minoru
Принадлежит:

An aircraft configured to drop an object to be dropped includes a body, a cavity provided in the body and opening on the bottom face of the body, and a gas supply part that blows gas from vertically above to a blowing position on the object to be dropped detachably mounted in the cavity. The blowing position is a position on a side closer to the nose of the aircraft with respect to the center of gravity of the object to be dropped. 1. An aircraft configured to drop an object to be dropped , the aircraft comprising:a body;a cavity provided in the body, the cavity opening on a bottom face of the body; anda gas supply part configured to blow gas from vertically above to a blowing position on the object to be dropped detachably mounted in the cavity, the blowing position being a position on a side closer to a nose of the aircraft with respect to the center of gravity of the object to be dropped.2. The aircraft according to claim 1 , wherein the gas supply part blows an airflow having a vertically downward component onto the object to be dropped when the object to be dropped is dropped vertically downward from the cavity.3. The aircraft according to claim 1 , whereinthe gas supply part has an inlet opening part that opens in the bottom face of the body on a side closer to the nose of the aircraft with respect to the cavity, an outlet opening part that opens in a vertically upper side of the cavity with respect to the object to be dropped in the cavity, and a gas supply channel that communicates the inlet opening part and the outlet opening part with each other, andthe gas supply part takes in air flowing along the bottom face from the inlet opening part, and blows, from the outlet opening part, the air taken in onto the object to be dropped.4. The aircraft according to claim 3 , wherein the gas supply part further has an inlet wall part that is provided between the inlet opening part and the cavity claim 3 , and protrudes from the bottom face of the body.5. The aircraft ...

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Номер записи: 34
28-02-2019 дата публикации

WEAPON LAUNCHING TUBE STRUCTURE, AND NAVAL PLATFORM COMPRISING AT LEAST ONE STRUCTURE OF SAID TYPE

Номер: US20190063872A1
Автор: LAMOTTE Arnaud, LAVOIX Laurent, RAFFOUX Johan
Принадлежит:

A weapon launching tube structure, and in particular a torpedo launching tube structure, includes a tube inside which weapon guiding slides are mounted at regular intervals around the weapon. The slides are made from a single slide blank obtained by an extrusion process. 125262728292627282920. A weapon launching tube structure () , comprising a tube inside which weapon guiding slides ( , , , ) are mounted at regular intervals around the weapon , wherein the slides ( , , , ) are made from a single slide blank () obtained by an extrusion process.220. The structure according to claim 1 , wherein the slide blank () is obtained by an aluminum extrusion process.32021222324. The structure according to claim 1 , wherein the slide blank () has a section with a curved profile () to marry the contour of the weapon claim 1 , at each end of this profile claim 1 , a bent portion ( claim 1 , ) for bearing on the inner wall of the tube claim 1 , and in its intermediate portion claim 1 , a withdrawn foot ().424222320. The structure according to claim 3 , wherein the withdrawn foot () is provided asymmetrically between the bent bearing portions ( claim 3 , ) of the blank ().5252627282926272829. The structure according to claim 1 , wherein the tube () includes four slides ( claim 1 , claim 1 , claim 1 , ) claim 1 , including two lateral lower slides ( claim 1 , ) and two lateral upper slides ( claim 1 , ).6302829. The structure according to claim 5 , further comprising claim 5 , in its upper part claim 5 , at least one access hatch () to means forming an interface of the weapon claim 5 , wherein cutouts are formed in the upper slides ( claim 5 , ) at this hatch claim 5 , between a bent bearing portion on the inner wall of the tube and the withdrawn foot.7313235. The structure according to claim 1 , wherein covers ( claim 1 , claim 1 , ) are provided to close the open ends of the slides.8262728293325. The structure according to claim 1 , wherein the slides ( claim 1 , claim 1 , claim 1 ...

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Номер записи: 35
11-03-2021 дата публикации

SET-BACK ROCKET MOTOR IGNITOR FOR SHOULDER-FIRED ROCKETS

Номер: US20210071976A1
Автор: GRYMONPRE David, MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

A rocket motor ignitor assembly that may be used in a shoulder-fired rocket system. The rocket motor ignitor assembly may include a delay ignitor operable to ignite a rocket motor propellant, a stab firing pin operable to activate the delay ignitor by contacting the delay ignitor, and a biasing element coupled with the stab firing pin. The stab firing pin may have a length to diameter ratio greater than two, as well as relief grooves allowing air to vent past the stab firing pin as it travels toward the delay ignitor to activate it. The rocket motor ignitor assembly may also include a guide stop to limit penetration of the stab firing pin into the delay ignitor. 1. A rocket motor ignitor assembly comprising:a delay ignitor operable to ignite a rocket motor propellant;a stab firing pin operable to activate the delay ignitor by contacting the delay ignitor; anda biasing element coupled with the stab firing pin,wherein the delay ignitor is operable to ignite the rocket motor propellant after a predetermined amount of time upon contact by the stab firing pin;wherein the biasing element is biased to space apart the stab firing pin and the delay ignitor when the rocket motor assembly is in a pre-fired condition and the stab firing pin is operable to contact the delay ignitor when the rocket motor assembly is in a firing condition.2. The rocket motor ignitor assembly according to claim 1 , wherein the stab firing pin has a length and a diameter claim 1 , the length to diameter ratio being greater than 2.3. The rocket motor ignitor assembly according to claim 2 , wherein the stab firing pin length to diameter ratio is greater than 2.5.4. The rocket motor ignitor assembly according to claim 2 , wherein the stab firing pin length to diameter ratio is greater than 3.5. The rocket motor ignitor assembly according to claim 1 , wherein the stab firing pin comprises one or more relief grooves operable to vent air around the edge of the stab firing pin.6. The rocket motor ignitor ...

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Номер записи: 36
11-03-2021 дата публикации

COMPOSITE ROCKET LAUNCHER

Номер: US20210071988A1
Автор: MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

A projectile launch system includes a longitudinally extending launch tube having an inner bore formed therethrough. The launch tube having a metal liner and a composite overwrap, and a firing pin aperture formed in the longitudinally extending launch tube. A firing pin sleeve can be coupled with the metal liner and extend through at least a portion of the firing pin aperture, and a receiver including a launch control system. 1. A projectile launch system comprising:a longitudinally extending launch tube having an inner bore formed therethrough, the launch tube having a metal liner and a composite overwrap formed over the metal liner;a firing pin aperture formed in the longitudinally extending launch tube;a firing pin sleeve coupled with the metal liner and extending through at least a portion of the firing pin aperture; anda receiver including a launch control system.2. The projectile launch system of claim 1 , wherein the metal liner is a nickel liner and/or nickel alloy.3. The projectile launch system of claim 1 , further comprising a nozzle within the inner bore claim 1 , the nozzle coupled with the metal liner.4. The projectile launch system of claim 3 , wherein the nozzle is brazed to the metal liner.5. The projectile launch system of claim 1 , wherein the metal liner is formed from a forward metal liner and an aft metal liner claim 1 , the forward metal liner and the aft metal liner having a nozzle disposed therebetween.6. The projectile launch system of claim 5 , wherein the forward metal liner and the aft metal liner are brazed to the nozzle.7. The projectile launch system of claim 1 , further comprising an accessory rail.8. The projectile launch system of claim 1 , wherein the composite overwrap is coupled with the metal liner by an adhesive.9. The projectile launch system of claim 1 , wherein the launch tube has gaps between the metal liner and the composite overwrap claim 1 , wherein the metal liner expands into the gaps after actuation of a projectile. ...

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Номер записи: 37
19-03-2015 дата публикации

ACTUATION SYSTEM AND METHOD FOR MISSILE CONTAINER DOORS

Номер: US20150075357A1
Автор: Bixby Dylan Foster, Bugge John F.
Принадлежит: Raytheon Company

A missile container sealing assembly includes an end cap capable of sealing an end of a container for a missile, and one or more linkage assemblies for controllably opening the end cap. The end cap has a frame portion that defines an opening for a missile and is mountable to the end of the missile container, and a door portion that includes one or more doors that close and seal the opening in the frame portion. Each linkage assembly is associated with a respective one of the one or more doors, for opening the doors relative to the frame portion. Moreover, each linkage assembly includes a link that transmits a force ahead of the leading end of the missile to open the doors and permit the missile's egress through the opening. 1. A missile container sealing assembly , comprising: 'the end cap having a frame portion that defines an opening for a missile at an end of a container and is mountable to an end of a missile container, and a door portion that includes one or more doors that close and seal the opening in the frame portion, each door being hingedly mounted to the frame portion; and', 'an end cap capable of sealing an end of a container for a missile,'} 'where the first link is pivotally connected to the guide track at a location removed from the connection between the first link and the second link, and the first link being mounted for sliding movement relative to and along the guide track, the first link further including a surface against which a force can be applied to move the connection between the first link and the guide track along the guide track and to transfer a force to the second link and the door to cause the door to open.', 'where each linkage assembly includes a first link, a second link pivotally connected to the first link and to the door at a location removed from the connection to the first link, and a guide track,'}, 'one or more linkage assemblies, each linkage assembly being associated with a respective one of the one or more doors, for ...

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Номер записи: 38
07-03-2019 дата публикации

THIN-WALLED CONICAL STRUCTURES

Номер: US20190071189A1
Автор: Hilliard Donald Bennett
Принадлежит:

The present invention relates broadly to a process and apparatus in field of thin-walled structures possessing high strength-to-weight ratio, and particularly to mirror structures utilizing corrugated, or similarly structured, predominantly hollow-core panel structures; and, even more particularly, heat collector structures utilized for concentration of radiant heat. The disclosed invention relates to an optical element utilized for concentrating radiation, and more particularly, high-concentration, reflective concentrators that are constructed from discrete conical concentrators utilizing flexible high-reflectance layers that are produced by roll-to-roll manufacturing. In its first preferred embodiment, the disclosed optical element preferably comprises a quasi-parabolic, multi-frustum, concentration optic. 1. A hollow-core sandwich structure with sheet-like facing having a conical aspect , comprising:a.) a first frustum-shaped conical structure;b.) a second frustum-shaped conical structure disposed in concentric relation to the first structure;c.) a roughly conical, corrugated structure comprising periodically spaced thin-sheet layers disposed in a space defined between the first frustum-shaped conical structure and second frustum-shaped conical structure; and,d.) fastening means, the fastening means fastening the first frustum-shaped conical structure to a first side of the corrugated structure, the fastening means fastening the second frustum-shaped conical structure to a second side of the corrugated structure, the second side roughly opposing the first side.2. A process for forming a substantially hollow-core , conical structural component , including the steps:a.) forming a roughly cylindrical structure comprising periodically spaced layers of a thin-sheet material;b.) separating the preform into a plurality of roughly conical structures, the roughly conical structures having an interior side, the roughly conical structures having an exterior side opposite ...

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Номер записи: 39
07-03-2019 дата публикации

Payload Launching Apparatus and Method

Номер: US20190072362A1
Автор: Strocchia-Rivera Stephen Tomás
Принадлежит:

A method and device are provided for launching a payload from water, including a launching tube having inside walls, outside walls, a top and an inlet at the tube bottom, with the tube bottom anchored to the bottom water surface. The tube includes a convergent tubular nozzle or neck that is an inlet to the bottom and an outlet open at the top. A gate valve blocking the inlet is opened by remote control signals; or by an explosive plug blocking the inlet removed by an explosion initiated by remote control. The launching tube loaded with a payload and empty of water is installed in water with the inlet deep below the top positioned above the water surface. 1. A method for launching a payload from a body of water , which has a top surface and a bottom surface , by the steps comprising:providing a launching tube for launching said payload from said body of water with said launching tube having an inside wall, an outside wall, a tube top and a tube bottom;providing an inlet at said tube bottom and an outlet open at said tube top;providing a flow blocking device at said inlet operable by remote control signals;providing an actuation device for sending said remote control signals to control said flow blocking device;installing said tube in said body of water with said tube top extending above said top surface, and with said tube bottom located deep in said body of water below said top surface; andoperating said actuation device for sending a remote control signal to open said flow blocking device.2. The method of including providing a support secured below said payload to inside walls of said tube for supporting said payload above said flow blocking device.3. The method of including anchoring said launching tube to said bottom surface and thereby providing means for supporting said launching tube in said body of water.4. The method of including providing a power supply for both said flow blocking device and said actuation device.5. The method of wherein said flow blocking ...

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Номер записи: 40
05-03-2020 дата публикации

MUNITIONS RACK WITH STRUCTURAL ELEMENT AND INSERTABLE EJECTORS

Номер: US20200072587A1
Автор: Bailey Robert A., Deherdt Jessica R., Erdmann James T., Guerrero Armando, McMahon Roy P., Streib Stephen A.
Принадлежит:

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s). 1. A munitions rack comprising:a munitions rack structure that includes a pair of longitudinal ribs defining a longitudinally-extending central recess and a pair of longitudinal-extending side recesses on opposite respective sides of the longitudinally-extending central recess, with the longitudinal ribs between the longitudinally-extending central recess and respective of the longitudinally-extending side recesses; andmunitions ejectors;wherein multiple of the munitions ejectors are in each of the side recesses.2. The munitions rack of claim 1 , where the side recesses include a forward port pocket claim 1 , a forward starboard pocket claim 1 , an aft port pocket claim 1 , and an aft starboard pocket.3. The munitions rack of claim 1 , wherein the ribs extend a majority of a length of the munitions rack.4. The munitions rack of claim 1 , wherein the ribs extend at least two-thirds of a length of the munitions rack5. The munitions rack of claim 1 , wherein the ribs extend at least 90% of a length of the munitions rack structure.6. The munitions rack of claim 1 , wherein the munitions rack structure ...

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Номер записи: 41
31-03-2022 дата публикации

Deep sea pressure based projectile launching system

Номер: US20220099408A1
Автор: Ahmed Hamza, Faizan Mirza, Fatima Arifa, Fatima Aroush, Haque Ashaz, Khan Omar Farooq, Khan Zayd, Nouiouat Abdullah, Rizwan Mirza, Sheikh Abdurraheem, Siddiqui Rida, Zubair Wafiqah
Принадлежит:

A projectile launching apparatus for launching projectile with the pressure exerted by the seawater. The projectile launching apparatus includes a large barrel launch, a piston, one or more piston stoppers, plurality of hinged doors, piston locks, and a plurality of water pump is available at bottom of the barrel to generate pressure and help to launch the projectile, wherein the assembly for the projectile is less expensive than present systems, lighter in weight, and of less complexity. 1) A projectile launching apparatus for launching a projectile , wherein the launching apparatus comprises a barrel to engage the projectile , wherein the barrel comprises a source of pressurized water to propel the projectile , the apparatus comprising:a. a barrel having a housing which includes a collecting unit for pressurized water,b. an inlet to said collector unit and hinged doors as an outlet from said collector unit said inlet and said outlet being separate;c. said housing further comprising a piston, wherein a projectile is available on the piston;d. a water pump connected to the inlet of the collector unit, wherein the pump is connected for and capable of pumping water into said collector unit at a pressure sufficient to launch a rocket projectile; ande. a pair of piston stopper connected to the barrel in order to stop the piston while allowing the projectile to launch.2) The launcher of further comprising an orientation Sensitive Safety Switch to prevent the launcher from being actuated in an undesired orientation.3) The launcher of further comprising a dual-engine connected with the projectile claim 1 , wherein after launched from the projectile launching apparatus claim 1 , the fuel engine use the fuel to allow to reach the high position.4) The launcher of further comprising pressure gauge means for indicating the fluid pressure within the collecting unit.5) The launcher of claim 1 , wherein the water pump is placed at bottom of the barrel positioned within the launch ...

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Номер записи: 42
12-03-2020 дата публикации

LAUNCH TUBE AND METHOD OF LAUNCHING FLYING OBJECT

Номер: US20200080817A1
Автор: IEKI Katsunori, MIHARA Chiyako
Принадлежит:

A launch tube of a flying object 1 has a tube a plurality of rails and a plurality of guides The tube stores the flying object The plurality of rails are fixed on an inner wall of the tube to touch the flying object The plurality of guides are provided on the inner wall of the tube A first guide of the plurality of guides is provided to touch the flying object and evacuates from a region of movement of the flying object when the flying object 1 moves to leave the first guide. 1. A launch tube comprising:a tube configured to store a flying object;a plurality of rails fixed to an inner wall of the tube and configured to contact the flying object; anda plurality of guides provided on the inner wall of the tube,wherein a first guide of the plurality of guides:is provided to contact with flying object; andto evacuate from a movement region of the flying object when the flying object moves to leave the first guide.2. The launch tube according to claim 1 , wherein the first guide comprises:a supporter configured to contact with the flying object when guiding the flying object;an arm configured to support the supporter and provided to protrude from the inner wall of the tube; anda biasing device configured to support the arm to be rotatable;wherein the biasing device:biases the arm to a first direction to push the supporter against the flying object, when the supporter contacts with the flying object; androtates the arm to the first direction to move the supporter toward the inner wall of the tube when the flying object leaves the supporter.3. The launch tube according to claim 2 , wherein the supporter touches a protruding section extending to a progressing direction of the flying object.4. The launch tube according to claim 2 , wherein the supporter touches a dorsal fin of the flying object claim 2 , andwherein the biasing device rotates the arm to move the supporter to a tip direction of the dorsal fin, when the dorsal fin leaves the supporter.5. The launch tube ...

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Номер записи: 43
05-05-2022 дата публикации

IMPROVEMENTS IN AND RELATING TO OPERATING A MUNITIONS SYSTEM

Номер: US20220135226A1
Автор: BOWDEN-PETERS Edwin John William, Cook Ben
Принадлежит:

The invention relates to a method of determining the relative positions of components of a munitions system, the munitions system comprising a first component () and at least one second component (). The method comprises monitoring the output of a resonant circuit () provided on a first component (), the resonant circuit () having a resonant frequency, detecting a change in the output due to a change in the resonant frequency caused by a change in the relative positions of the first component () and the at least one second component (), and using the detected change to determine that the at least one second component () has moved relative to the first component ().

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Номер записи: 44
26-06-2014 дата публикации

MISSILE CONTAINER AND METHOD OF OPERATING A MISSILE CONTAINER

Номер: US20140174283A1
Автор: KEMPAS HAGEN
Принадлежит: DIEHL BGT DEFENCE GMBH & CO. KG

A missile container has a container housing, a container roof, at least one canister for holding a missile which, in a storage position, is disposed on the container housing, and a movement mechanism for moving the canister from the storage position into an operating position. The elements arranged in the interior of the container housing are protected against external weather influences. In the operating position, the canister is held at least partially outside the container housing by the movement mechanism and the container roof is closed and shields a container interior against the outside. 1. A missile container , comprising:a container housing and a container roof;at least one canister for supporting a missile arranged in a storage position in said container housing; anda movement mechanism for moving said at least one canister from the storage position into an operating position;said movement mechanism holding said at least one canister at least partially outside said container housing in the operating position, and said container roof being closed and outwardly shielding a container interior when said at least one canister is in the operating position.2. The missile container according to claim 1 , wherein said container roof is formed with a passage opening and said movement mechanism projects through said passage opening the operating position and when said container roof closes a roof opening claim 1 , and wherein said passage opening is closed by a roof flap when said movement mechanism is moved out of said passage opening.3. The missile container according to claim 2 , wherein said roof flap and said movement mechanism are disposed with respect to each other such that said movement mechanism presses on said roof flap by moving into the operating position.4. The missile container according to claim 1 , wherein said container roof has at least one roof wing resting on said container housing.5. The missile container according to claim 4 , wherein said roof ...

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Номер записи: 45
05-04-2018 дата публикации

Autonomous Flight Termination System and Method

Номер: US20180094903A1
Автор: DeJong Michelle V.
Принадлежит:

An autonomous flight termination system for terminating vehicle flight after the vehicle is launched from an aircraft includes a global positioning system (GPS) receiver; a termination unit selected from a cut-off switch connected to terminate vehicle flight when actuated, and a switch connected to detonate an explosive on the vehicle; a system controller for receiving a first signal indicating separation of the vehicle from the aircraft and a second signal from the GPS receiver to calculate an actual vehicle trajectory, and for sending a third signal to actuate the termination unit to terminate the flight of the vehicle when the actual vehicle trajectory is determined to be outside the safety bounds of a mission-planned flight trajectory; and a failsafe controller connected to receive operational data of the system controller, and to actuate the termination unit when the operational data indicates that the system is in an error state. 1. An autonomous flight termination system for terminating a vehicle flight after the vehicle is launched from an aircraft , the system comprising:a first global positioning system (GPS) receiver for determining a position of the vehicle during the vehicle flight relative to the Earth;a first termination unit selected from a first cut-off switch connected to terminate the vehicle flight when actuated, and a first switch connected to detonate an explosive on the vehicle;a system controller for receiving a first signal from the aircraft indicating separation of the vehicle from the aircraft and a second signal from the first GPS receiver to calculate an actual vehicle trajectory, and for sending a third signal to actuate the first termination unit to terminate the flight of the vehicle when the actual vehicle trajectory is determined by the system controller to be outside predetermined safety bounds of a mission-planned flight trajectory for the vehicle; anda failsafe controller connected to receive operational data of the system ...

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Номер записи: 46
16-04-2015 дата публикации

AIRCRAFT MISSILE LAUNCHER COVER

Номер: US20150101478A1
Автор: Carpenter Daryl D., Cowin Aaron Ross, DiDomenico Daniel, Heller Mike, Huhman Samuel Jerome, Jakubowski, JR. Richard Raymond, JR. Thaddeus M., Keller Cory Gordon, Kreutzman, Palmer Todd J., Paruleski David Michael, Schoen Steven Michael, Sisti Gregory M.
Принадлежит: The Boeing Company

A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher. 1. A cover for a rail missile launcher comprising: a flightworthy cover adapted for removably mounting on the rail missile launcher and for reducing a radar cross section of the missile launcher.2. The cover of claim 1 , wherein the cover is shaped to reflect a radar signal transmitted by a radar transmitter away from the radar transmitter.3. The cover of claim 1 , wherein the cover is adapted to absorb a radar signal transmitted by a radar transmitter.4. The cover of claim 3 , wherein an outer surface of the cover comprises a radar absorbent material.5. The cover of claim 3 , wherein the cover comprises a radar absorbent material.6. The cover of claim 1 , wherein the rail missile launcher has a launch rail claim 1 , the cover further comprising: a hanger for mounting the cover on the launch rail.7. The cover of claim 6 , wherein the launch rail has a guide track and the hanger is adapted to slidably engage the guide track.8. The cover of claim 1 , wherein the cover comprises:a forward section;an aft section; anda splice joint connecting the forward section to the aft section.9. The cover of claim 1 , further comprising: a grounding element connected to the launcher;', 'a cover terminal connected to the cover; and, 'a grounding mechanism for dissipating precipitation static, the grounding mechanism comprisinga wire connecting the cover terminal to the grounding element.10. The cover of claim 1 , wherein ...

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Номер записи: 47
16-04-2015 дата публикации

ROCKET LAUNCH TOWER

Номер: US20150101479A1
Автор: Essbaum Alexander Dankwart
Принадлежит:

A rocket launch tower is provided, including: a vertical support structure including two or more guide towers defining a vertical shaft between the two or more guide towers, each guide tower including one or more pulleys engaging one or more cables; a platform located within the vertical shaft and connected to the one or more cables; a drive mechanism that applies a force to the one or more cables to accelerate the platform along a trajectory within the vertical shaft; one or more sensors collecting data regarding the position of the platform along the trajectory within the vertical shaft and communicating the platform position data to a controller, the controller in communication with an acceleration control system including one or more brakes acting on the platform; wherein the controller causes the acceleration control system to actively correct the platform acceleration towards an intended platform acceleration. 1. A rocket launch tower comprising:a vertical support structure including two or more guide towers defining a vertical shaft between the two or more guide towers, each guide tower including one or more pulleys engaging one or more cables;a platform located within the vertical shaft and connected to the one or more cables;a drive mechanism that applies a force to the one or more cables to accelerate the platform along a trajectory within the vertical shaft;one or more sensors collecting data regarding the position of the platform along the trajectory within the vertical shaft and communicating the platform position data to a controller, the controller in communication with an acceleration control system including one or more brakes acting on the platform;wherein, the controller compares the platform position data received from the sensors to an intended platform acceleration and in response to receipt of platform position data indicating the platform acceleration has deviated from the intended platform acceleration, the controller causes the acceleration ...

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Номер записи: 48
13-04-2017 дата публикации

DEBRIS CONTROL APPARATUS

Номер: US20170102204A1
Автор: BYARS Mike, MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

Debris control apparatus for a rocket propelled grenade launcher including a plug configured to be inserted into an opening at a rear end of a tube assembly of the rocket propelled grenade launcher, the plug forming an aperture at about the center thereof. A front cover configured to be coupled with a front end of the rocket propelled grenade launcher and configured to cover an inlet, at the front end, that receives a rocket propelled grenade. The front cover is configured to provide cross-hairs and the aperture cooperating to provide, when a target is provided down range at a predetermined distance, a bore sight with the cross-hairs and the front cover and plug cooperatively, when installed, seal the rocket propelled grenade launcher assists in preventing ingress of debris. 1. A debris control apparatus for a rocket propelled grenade launcher comprising:a plug configured to be inserted into an opening at a rear end of a tube assembly of the rocket propelled grenade launcher, the plug forming an aperture at about the center thereof;a front cover configured to be coupled with a front end of the rocket propelled grenade launcher and configured to cover an inlet, at the front end, that receives a rocket propelled grenade;wherein the front cover is configured to provide cross-hairs and the aperture cooperating to provide, when a target is provided down range at a predetermined distance, a bore sight with the cross-hairs and the front cover and plug cooperatively, when installed, seal the rocket propelled grenade launcher assists in preventing ingress of debris.2. The debris control apparatus as recited in claim 1 , wherein the aperture has a diameter that is sized based on the length of the rocket propelled grenade launcher so as to provide the appropriate field of view for the bore sight.3. The debris control apparatus as recited in claim 1 , wherein the plug is configured to be ejected from the rocket propelled grenade launcher upon firing of the rocket propelled ...

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Номер записи: 49
10-07-2014 дата публикации

DEVICE FOR ATTACHMENT TO A PROFILED RAIL

Номер: US20140190061A1
Автор: Griffin Todd
Принадлежит: RM Equipment, Inc.

A device for selective affixation to a profiled rail is generally provided. The device generally includes a body and a clamp assembly operatively supported thereby. The body has an upper portion characterized by first and second opposing and spaced apart sidewall segments. The first sidewall segment has a profiled rail receiving surface and the second sidewall segment has a channeled face. The clamp assembly includes a clamping block adapted for advancement toward the profiled rail receiving surface of the first sidewall segment of the upper body portion, a portion of the clamping block pivotingly received by the channeled face of the second sidewall segment of the upper body portion so as to operatively self-seat the clamping block with a profiled rail interposed between the first sidewall segment and the clamping block of the clamp assembly upon advancement thereof. 1. A device for selective affixation to a profiled rail , the device comprising:a. a body having an upper portion characterized by a first sidewall segment and a second sidewall segment, said second sidewall segment opposite and spaced apart from said first sidewall segment, said first sidewall segment having a profiled rail receiving surface, said second sidewall segment having a channeled face; and,b. a clamp assembly operatively supported by said upper portion of said body for clamped engagement with a received profiled rail, said clamp assembly comprising a clamping block adapted for advancement toward said profiled rail receiving surface of said first sidewall segment of said upper portion of said body, a portion of said clamping block pivotingly received by said channeled face of said second sidewall segment of said upper portion of said body so as to operatively self-seat said clamping block with a profiled rail interposed between said first sidewall segment and said clamping block of said clamp assembly upon advancement thereof.2. The device of wherein said clamp block is biasingly spaced apart ...

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Номер записи: 50
07-05-2015 дата публикации

Guidance Section Connector Interface for Advanced Rocket Launchers

Номер: US20150122113A1
Автор: Hlavek Michael R., McMahon Roy P.
Принадлежит: Raytheon Company

A guidance section connector interface system operable with smart or guided rockets to be launched from a rocket launcher comprising a rocket connector of a rocket in electronic communication with a guidance system of a guidance head of the rocket, a connector saver, and a launcher connector of a rocket launcher. The connector saver can be configured to connect the rocket connecter to the launcher connector. The connection between the connector saver and the rocket connector is configured to release upon launching the rocket, wherein the connector saver remains connected to the launcher connector to protect the launcher connector from the extreme conditions within the rocket launcher at launch. 1. A guidance section connector interface system operable with a rocket launcher for facilitating electrical communication between a rocket and the rocket launcher , the guidance section connector interface system comprising:a rocket connector in electrical communication with a guidance system of a rocket;a connector saver coupled to the rocket connector to provide a first connection; anda launcher connector supported about a rocket launcher, and in electrical communication with a control system, wherein the connector saver is coupled to the launcher connector upon insertion of the rocket into the rocket launcher to provide a second connection,wherein the rocket connector, the connector saver and the launcher connector connect together to facilitate electrical communication between the rocket and the rocket launcher,wherein, upon launch of the rocket from the rocket launcher, the first connection releases, and the second connection remains connected, causing the connector saver to remain connected to the launcher connector.2. The system of claim 1 , wherein the connector saver comprises a receiver portion that operates to guide the launcher connector into correct alignment with the connector saver and the rocket connector during connection of the launcher connector and the ...

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Номер записи: 51
04-05-2017 дата публикации

Weapon interface system and delivery platform employing the same

Номер: US20170121020A1
Автор: John P. Volpi, Joseph Edward Tepera, Steven D. Roemerman
Принадлежит: Lone Star IP Holdings LP

A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto.

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Номер записи: 52
25-08-2022 дата публикации

ARMING APPARATUS

Номер: US20220267003A1
Автор: Murray Steven Robert
Принадлежит: BAE SYSTEMS plc

There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming connector coupled with the linking connector and a first fuze input of the store; wherein each of the first attachment system and the second attachment system comprises: an arming unit; a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector coupled with the linking connector and the store. 1200204: An arming apparatus () for a store () , the apparatus comprising:{'b': 202', '202, 'i': a', 'b, 'a first attachment system () and a second attachment system ();'}{'b': 208', '202', '202, 'i': a', 'b, 'a linking connector () coupled with the first attachment system () and the second attachment system (); and'}{'b': 210', '208', '214', '204, 'an arming connector () coupled with the linking connector () and a first fuze input () of the store ();'}{'b': 202', '202, 'i': a', 'b, 'wherein each of the first attachment system () and the second attachment system () comprises{'b': '220', 'an arming unit ();'}{'b': 224', '220', '208, 'a first frangible connector () coupled with the arming unit () and the linking connector (); and'}{'b': 226', '208', '204, 'a second frangible connector () coupled with the linking connector () and the store ().'}2200232204234202b: The apparatus () according to claim 1 , comprising a gag rod wire () coupled with the store () and a second fuze input () via the second attachment system ().3200202202228228208204abab: The apparatus () according to claim 1 , wherein each attachment system ( claim 1 , ) comprises a safety connector ( claim 1 , ) coupled with the linking connector () and the store ().4200228228210ab: The apparatus () according to claim 3 , wherein the length of the safety connector ( claim 3 , ) is longer than the length of the arming ...

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Номер записи: 53
25-04-2019 дата публикации

METHOD AND APPARATUS FOR LAUNCH CONTROL PACKET PROCESSING

Номер: US20190120596A1
Автор: LEE Jae Yob, MIN Joon Ki, OH Jino
Принадлежит:

A launch control system relates to a method and apparatus for launch control packet processing that is provided in the launch control system and configured to allow interworking between a plurality of firing control systems and the launch control system. The launch control system comprises a plurality of operation equipments, a system control device, and control the plurality of operation equipments, a launch control packet processing unit, a control signal distribution device, and a status display device. 1. A launch control system comprising:a plurality of operation equipments used for launch control of a guided weapon;a system control device configured to communicate with a plurality of firing control systems for controlling a firing sequence of the guided weapon and a plurality of test equipments, and control the plurality of operation equipments;a launch control packet processing unit configured to generate, when an interworking start event linked to any one of the plurality of firing control systems begins, one or more first packets to be transmitted to said any one of the firing control systems and one or more second packets that are expected to be received from said any one of the firing control systems based on an interface control document (ICD), and configured to analyze, when a third packet received by the system control device and said one or more second packets are compared and there is a packet matched with the third packet among said one or more second packets, information included in the third packet or information included in the packet matched with the third packet to allow the system control device to transmit said one or more first packets to the firing control systems based on the information, or allow the system control device to control the operation equipments based on the information;a control signal distribution device configured to interface signals between the system control device and the test equipments; anda status display device ...

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Номер записи: 54
31-07-2014 дата публикации

Payload deployment system and method

Номер: US20140208927A1
Автор: Bradley M. Gaul, Darren C. Smith, Derek S. Wall, Donald P. Cox, Michael D. Stokes, Michael J. Holt, Robert W. Knox, Scott G. Martin
Принадлежит: Raytheon Co

A payload deployment system includes a mount for receiving one or more payload modules that each include one or more payloads to be deployed. The payload modules also each include a sleeve, with the one or more payloads are in one or more openings in the sleeve. The payloads may be contained in respective containers, such as hermetically-sealed containers, that are in the openings. The electrical coupling may be wireless coupling, for transferring electrical power to the payload module(s), and for communication, such as networked communication, between the mount and the one or more payload modules. The wireless coupling may be inductive coupling that involves overlap of inductive elements such as wire coils. The payload deployment system may also include one or more translators for translating commands and/or other communications between the one or more payload modules and a platform to which the payload deployment system is coupled.

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Номер записи: 55
10-05-2018 дата публикации

MARKSMAN LAUNCHER SYSTEM ARCHITECTURE

Номер: US20180128573A1
Автор: Anderson Chad V., Gin Brian A., Kulbacki Mary L., Le Huy, Szlemko Emile M., Ueberschar David P., Wahl Ryan P.
Принадлежит:

An effector launching system includes an environment that has external components located within the environment. The effector launching system may include a modular controller located in the environment of an effector launching system and the external components may be located in the environment externally to the modular controller for executing an effector launching sequence. The modular controller may include a core processor module that is configured to execute a plurality of different effector launching sequences using the external components and a plurality of converting modules that each have an electro-mechanical interface and is connectable between the core processor module and one of the external components. The plurality of converting modules are configured to send and receive data with the core processor module and the plurality of external components. 1. A modular controller located in an environment of an effector launching system that has external components located in the environment externally to the modular controller for executing an effector launching sequence , the modular controller comprising:a core processor module that is configured to execute a plurality of different effector launching sequences using the external components; anda plurality of converting modules that each have an electro-mechanical interface and is connectable between the core processor module and one of the external components,wherein the plurality of converting modules are configured to send and receive data with the core processor module and the plurality of external components.2. The modular controller of claim 1 , wherein at least one of the plurality of converting modules includes an adapter for converting data from the core processor module to readable data for the external components.3. The modular controller of claim 2 , wherein the adapter is an effector adaptor that includes a mechanical support for holding an effector.4. The modular controller of claim 2 , ...

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Номер записи: 56
11-05-2017 дата публикации

GAS GENERATORS, LAUNCH TUBE ASSEMBLIES INCLUDING GAS GENERATORS, AND RELATED SYSTEMS AND METHODS

Номер: US20170131070A1
Автор: Dunaway James D.
Принадлежит:

A gas generator includes a housing sized and configured to be located within a launch tube for a projectile. The housing defines a first propellant chamber; at least a second propellant chamber comprising a ring situated concentrically around the first propellant chamber; an expansion chamber; at least one first aperture between the first propellant chamber and the expansion chamber; and at least one second aperture between the at least a second propellant chamber and the expansion chamber. The gas generator also includes at least one propellant within each of the first propellant chamber and the at least a second propellant chamber of the housing; and a pyrotechnic delay connecting the first propellant chamber and the second propellant chamber. A launch tube assembly includes a tube containing at least one projectile and a gas generator. Related methods of launching a projectile are also disclosed. 1. A gas generator for use in launching a projectile , comprising: a first propellant chamber;', 'at least a second propellant chamber comprising a ring situated concentrically around the first propellant chamber;', 'an expansion chamber;', 'at least one first aperture between the first propellant chamber and the expansion chamber; and', 'at least one second aperture between the at least a second propellant chamber and the expansion chamber;, 'a housing sized and configured to be located within a launch tube for the projectile, the housing definingat least one propellant within each of the first propellant chamber and the at least a second propellant chamber of the housing; anda pyrotechnic delay connecting the first propellant chamber and the at least a second propellant chamber.2. The gas generator of claim 1 , wherein the at least one first aperture and the at least one second aperture comprise a plurality of first apertures and a plurality of second apertures.3. The gas generator of claim 1 , further comprising a burst foil between at least one of the first ...

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Номер записи: 57
07-08-2014 дата публикации

Projectile-Deployed Countermeasure System

Номер: US20140216290A1
Автор: Williams Timothy L., YEE DENNIS
Принадлежит: The Boeing Company

Systems and methods described herein provide for the protection of personnel within vehicles and structures from rocket-propelled grenades and other incoming threats. According to one aspect of the disclosure provided herein, a countermeasure system includes an interceptor vehicle configured to stow and launch an expandable countermeasure. The countermeasure may have a flexible body with attached deployment mechanisms that expand the flexible body into the path of an incoming threat to capture the threat. 1. A countermeasure system , comprising:an interceptor vehicle comprising a propulsion system and a countermeasure compartment, the interceptor vehicle configured for launch from a countermeasure launcher; anda countermeasure comprising a flexible receiving body and configured for detachable stowage within the countermeasure compartment of the interceptor vehicle.2. The countermeasure system of claim 1 , wherein the interceptor vehicle comprises a rocket or a missile having an exhaust nozzle claim 1 , wherein the countermeasure compartment surrounds at least a portion of the exhaust nozzle.3. The countermeasure system of claim 1 , further comprising a threat detection and launch control system operative to detect an incoming threat and to launch the interceptor vehicle to intercept the incoming threat.4. The countermeasure system of claim 3 , wherein the threat detection and launch control system comprises:a detection system operative to detect the incoming threat; anda controller operative to guide the interceptor vehicle to the incoming threat.5. The countermeasure system of claim 4 , wherein the interceptor vehicle comprises:a plurality of detachable panels encompassing the countermeasure compartment; andan electronics system operative to release the detachable panels to deploy the countermeasure,wherein the controller is further operative to provide countermeasure deployment information to the electronics system corresponding to the release of the plurality of ...

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Номер записи: 58
04-06-2015 дата публикации

Umbilical cable disconnect

Номер: US20150153135A1
Автор: Paul A. Merems
Принадлежит: Raytheon Co

An umbilical cable disconnect device is disclosed. The umbilical cable disconnect device includes a base having an opening configured to receive an umbilical cable, a cutter extending into the opening of the base, and a spacer component disposed in the opening between the cutter and the umbilical cable. The spacer component maintains separation of the cutter and the umbilical cable prior to disconnect of the umbilical cable. The cutter is operable to penetrate the spacer component in response to displacement of the disconnect device relative to the umbilical cable to facilitate cutting of the umbilical cable by the cutter to disconnect the umbilical cable.

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Номер записи: 59
21-08-2014 дата публикации

Dispenser pod

Номер: US20140230636A1
Автор: Matthew MacDonald Morrison, Robert Harry Schilder
Принадлежит: US Department of Navy

A dispenser pod, which includes a dispenser chassis with a first chassis end, a second chassis end and a chassis chamber, a first chassis end cover for covering the first chassis end, a second chassis end cover for covering the second chassis end, a launch system, and at least one sway brace. The first chassis end cover has at least one expendable passageway for accepting an expendable launch canister such that the expendable launch canister can enter the chassis chamber. The launch system is for expelling the expendable launch canister from the chassis chamber and through the expendable passageway. The at least one sway brace is for securing the expendable launch canister within the chassis chamber.

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Номер записи: 60
21-08-2014 дата публикации

WEAPON INTERFACE SYSTEM AND DELIVERY PLATFORM EMPLOYING THE SAME

Номер: US20140230637A1
Автор: Roemerman Steven D., Tepera Joseph Edward, Volpi John P.
Принадлежит: Lone Star IP Holdings, LP

A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto. 1. A weapon interface system coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system , comprising:a translation interface configured to provide an interface between said electrical interconnection system and an inductive power and data circuit; anda weapon coupler, coupled to said translation interface and including a weapon interface and an inductive coil, configured to provide an inductive coupling to said weapon system to provide mission information thereto.2. The weapon interface system as recited in wherein said weapon system includes a canister with at least one weapon therein claim 1 , said weapon coupler extending coaxially about said canister.3. The weapon interface system as recited in wherein said weapon coupler is formed from a flexible and substantially planar material and located within a flat spring adapter of said rack system.4. The weapon interface system as recited in wherein said weapon coupler further comprises a spacer claim 1 , a shield claim 1 , and a protection layer.5. The weapon interface system as recited in wherein said spacer is a Teflon spacer.6. The weapon interface system as recited in wherein said protection layer is a spring steel layer.7. The weapon interface system as recited in wherein said weapon coupler further comprises a spacer claim 1 , and a spring steel layer.8. The weapon ...

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Номер записи: 61
07-05-2020 дата публикации

SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE

Номер: US20200140120A1
Автор: Andryukov Alexander, McNeil John, Miralles Carlos Thomas, Su Guan H
Принадлежит:

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. 1. A method comprising:transmitting, by a transmitter disposed within a launcher volume of a launcher, wireless communication via one or more RF signals transmitted wirelessly through a launcher wall of the launcher, wherein the launcher volume is defined by the launcher wall, and wherein the launcher wall comprises a continuous radio-frequency (RF) permeable material.2. The method of further comprising:receiving, by a receiver disposed within the launcher volume of the launcher, wireless communication via one or more RF signals received wirelessly through the launcher wall of the launcher.3. The method of claim 2 , wherein the received one or more RF signals are received by an RF antenna disposed within the launcher volume.4. The method of further comprising:transmitting, by an external communications node, the one or more RF signals received by the receiver ...

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Номер записи: 62
11-06-2015 дата публикации

CLUSTER ROCKET MOTOR BOOSTERS

Номер: US20150159587A1
Автор: Alkema Michael S., Facciano Andrew B., Gonzalez Juan, Moore Robert T.
Принадлежит: Raytheon Company

A projectile for firing from a launcher includes a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage. The propulsion stage may further include a central booster about which the non-axisymmetric boosters are arranged. 1. A projectile for firing from a launcher , the projectile comprising:a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage.2. The projectile of claim 1 , further including a central booster about which the non-axisymmetric boosters are arranged.3. The projectile of claim 2 , wherein the central booster is axisymmetric.4. The projectile of claim 2 ,wherein the non-axisymmetric boosters each have a booster outer wall; andwherein the booster outer walls each include an arcuate wall portion of the respective booster outer wall corresponding to a curvature of the central booster.5. The projectile of claim 1 ,wherein the non-axisymmetric boosters each have a booster outer wall;wherein the booster outer walls each include a planar wall portion; andwherein the non-axisymmetric boosters abut one another at the planar wall portions.6. The projectile of claim 1 , further including a binding material wrapped about the non-axisymmetric boosters.7. The projectile of claim 2 , as part of a projectile system claim 2 ,wherein the projectile system also includes a projectile outer launch canister; andwherein the projectile is at least partially interior to the projectile outer launch canister.8. A projectile propulsion stage comprising:contiguous boosters arranged about a longitudinal axis of the propulsion stage; anda binding material wrapped about the contiguous boosters; andwherein at least one of the contiguous boosters is non-axisymmetric.9. The projectile propulsion stage of claim 8 , wherein longitudinally-extending portions of each of the contiguous boosters are integral parts of a unitary body of boosters.10. The projectile propulsion stage of ...

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Номер записи: 63
17-06-2021 дата публикации

BAFFLED-TUBE RAM ACCELERATOR

Номер: US20210180893A1
Автор: Bruckner Adam P., Hansen Viggo, Higgins Andrew J., Knowlen Carl
Принадлежит: UNIVERSITY OF WASHINGTON

A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube. 1. A method of fabrication comprising:providing a first hollow cylinder; andinserting a second hollow cylinder into the first hollow cylinder, wherein the second hollow cylinder is perforated with uniformly spaced holes along the longitudinal axis of the second hollow cylinder, and wherein the uniformly spaced holes in the second hollow cylinder are capped by an inner surface of the first hollow cylinder to form baffles, wherein the first hollow cylinder and the second hollow cylinder form a ram accelerator tube.2. The method of claim 1 , further comprising forming the second hollow cylinder prior to inserting the second hollow cylinder into the first hollow cylinder.3. The method of claim 2 , wherein forming the second hollow cylinder includes using at least one of fused deposition modeling claim 2 , fused filament fabrication claim 2 , robocasting claim 2 , electron beam melting claim 2 , laminated object manufacturing claim 2 , selective laser sintering claim 2 , direct metal laser sintering claim 2 , or selective laser melting.4. The method of claim 2 , wherein forming the second hollow cylinder includes creating the uniformly spaced holes that extend entirely through the second hollow cylinder.5. The method of claim 2 , wherein forming the second hollow cylinder includes forming the uniformly spaced holes arranged into a helix along the longitudinal axis of the second hollow cylinder.6. The method of claim 5 , wherein the helix includes a double helix.7. The method of claim 1 , wherein forming the ...

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Номер записи: 64
28-08-2014 дата публикации

Attachment Firing Apparatus

Номер: US20140237883A1
Автор: Hosz Christian
Принадлежит: STEYR MANNLICHER GMBH

An attachment firing apparatus, in particular a grenade launcher, for mounting on the barrel of a firearm, having an anchoring part that can be fixedly mounted on the firearm and having a support part that can be detachably connected to the anchoring part via a coupling, a launch tube in the support part being openable and closable relative to a breech, wherein the coupling is locked in the closed position of the launch tube and breech and can be opened in the open position of the launch tube and breech. 1. An attachment firing apparatus comprising:an anchoring part that can be fixedly mounted on a barrel of a firearm,a support part detachably connected to the anchoring part via a coupling,the support part mounting a launch tube and a breech movably between an open and a closed position relative to one another,wherein the coupling is locked in said closed position and can be opened in said open position.2. The attachment firing apparatus according to claim 1 , wherein the launch tube is mounted in the support part such that said launch tube can be pivoted out with respect to the breech claim 1 , and the launch tube locks the coupling when pivoted in.3. The attachment firing apparatus according to claim 1 , wherein the coupling locked in said closed position by a locking member claim 1 , which is mounted movably in the support part and which is blocked in said closed position by at least one of the launch tube and the breech.4. The attachment firing apparatus according to claim 3 , wherein the launch tube can be pivoted out with respect to the breech and blocks the locking member when pivoted in.5. The attachment firing apparatus according to claim 1 , wherein the coupling is a plug-and-slide coupling.6. The attachment firing apparatus according to claim 1 , wherein the attachment firing apparatus is a single-shot grenade launcher. The present invention relates to an attachment firing apparatus, in particular a grenade launcher, for mounting on the barrel of a ...

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Номер записи: 65
28-08-2014 дата публикации

FLOAT SUPPORT MEMBER FOR ROCKET LAUNCHER

Номер: US20140238223A1
Автор: STRAHL Erik
Принадлежит: Amphenol Corporation

A float support member that comprises a base for mounting to an object, primary linkages rotatably coupled by a primary pin defining a primary movable pin point that moves both in a lateral direction and a transverse direction, and secondary linkages rotatably coupled to said primary linkages, respectively, by first and second secondary pins, respectively. The first and second secondary pins define first and second secondary movable pin points, respectively, that each move both in a lateral direction and a transverse direction. The first and second secondary linkages being rotatably coupled to the base by first and second stationary pins, respectively, defining first and second stationary pin points, respectively. The position of the primary movable pin point in both the lateral and transverse directions depends on the position of both of the first and second secondary moveable pin points in both the lateral and transverse directions and vice versa. 1. A float support member , comprising:a base for mounting to an object;first and second primary linkages rotatably coupled by a primary pin, said primary pin defining a primary movable pin point that moves both in a lateral direction and a transverse direction transverse to said lateral direction;first and second secondary linkages rotatably coupled to said first and second primary linkages, respectively, by first and second secondary pins, respectively, said first and second secondary pins defining first and second secondary movable pin points, respectively, that each move both in a lateral direction and a transverse direction transverse to said lateral direction,said first and second secondary linkages being rotatably coupled to said base by first and second stationary pins, respectively, defining first and second stationary pin points, respectively,wherein the position of said primary movable pin point in both the lateral and transverse directions depends on the position of both of said first and second secondary ...

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Номер записи: 66
08-06-2017 дата публикации

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

Номер: US20170158356A1
Автор: Brown, JR. Glenn William, Palmer Miles R.
Принадлежит:

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided. 1. A launch vehicle adapted for high velocity delivery of a payload , the launch vehicle comprising:a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust; andone or more electrical conductors configured to direct flow of electrical current from an external source to the electrical heater.2. The launch vehicle according to claim 1 , further comprising an expansion nozzle in fluid communication with the exiting exhaust from the electrical heater.3. The launch vehicle according to claim 1 , wherein the electrical heater is a resistive heater.4. The launch vehicle according to claim 3 , wherein the resistive heater comprises at least one electrically heated porous cylinder inside a containment vessel.5. The launch vehicle according to claim 4 , wherein the electrically heated porous cylinder comprises carbon walls.6. The launch vehicle according to claim 5 , wherein ...

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Номер записи: 67
07-06-2018 дата публикации

IMPROVEMENTS IN AND RELATING TO CARRYING A MUNITION ON A MUNITION LAUNCHER PLATFORM

Номер: US20180156571A1
Автор: BOWDEN-PETERS Edwin John William
Принадлежит: MBDA UK LIMITED

In a method of carrying a munition on a munition launcher platform, the munition launcher platform is provided with a data tag activator and a data tag reader. A munition is attached to the munition launcher platform, the munition being provided with a data tag. An activation signal is transmitted from the data tag activator to the data tag. As a result of receiving the activation signal, the data tag returns a data response to the data tag reader. The receiving of the data response provides the munition launcher platform with an indication that the munition is still attached to the munition launcher platform. 1. A method of carrying a munition on a munition launcher platform , the method comprising:providing the munition launcher platform with an data tag activator and a data tag reader;attaching a munition to the munition launcher platform, the munition being provided with an data tag; andtransmitting an activation signal from the data tag activator to the data tag, such that, as a result of receiving the activation signal, the data tag returns an data response to the data tag reader, the receiving of the data response providing the munition launcher platform with an indication that the munition is still attached to the munition launcher platform.2. The method of claim 1 , wherein the data response received by the data tag reader indicates data of the munition attached to the munition launcher platform and the method comprises:using the data to ascertain one or more launch parameters that the munition launcher platform is to apply in launching the munition.3. A method of carrying a munition on a munition launcher platform claim 1 , the method comprising:providing the munition launcher platform with a data tag;attaching a munition to the munition launcher platform, the munition being provided with a data tag activator and an data tag reader; andtransmitting an activation signal from the data tag activator to the data tag, such that, as a result of receiving the ...

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Номер записи: 68
14-05-2020 дата публикации

Modular Weapon Carriage and Deployment (MWCD) System

Номер: US20200148355A1
Автор: Provenza Jerry
Принадлежит:

A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts. 1. A modular weapon carriage and deployment (MWCD) system comprising:a strongback structure mountable to an aircraft;left and right guide struts that have respective upper ends attached to the strongback structure in spaced lateral positions, extending downward in a parallel arrangement, wherein each guide strut comprising a vertically-extending engaging surface; and a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation; and', 'a locking mechanism that controllably locks to the corresponding engaging surface of one of the left and right guide struts., 'left and right suspension modules engageable to opposite lateral sides of a first airborne store, each suspension module comprising2. The MWCD system of claim 1 , wherein the left and right guide struts extend vertically sufficiently to receive a second airborne store in vertical alignment with the first airborne store.3. The MWCD system of claim 1 , wherein strongback structure extends longitudinally sufficiently to receive a second airborne store.4. The MWCD system of claim 1 , wherein:each guide strut comprises at least one of a fore and aft toothed rack; and ...

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Номер записи: 69
14-05-2020 дата публикации

Airborne Store Ejection Using Selectable Force Gas Generator

Номер: US20200148356A1
Автор: Provenza Jerry
Принадлежит:

An airborne store support assembly includes an ejector housing assembly that receives a fluid-actuated ejector piston. Extension of the piston pushes apart an airborne store from an aircraft for separation after release. A selectable force gas generator (SFGG) includes a total number of more than one gas-generating unit in fluid communication with the ejector housing assembly to actuate the fluid-actuated ejector piston with a selected amount of force. A communication interface in communication with the SFGG supplies at least one firing signal that causes a selected subset of the more than one gas-generating unit that corresponds to the selected amount of force that is dynamically determined by a controller based on flight parameters of at least one of an attitude, a rate of motion, and a rate of acceleration of the aircraft. 1. An airborne support assembly comprising:a first ejector housing assembly coupled to a selected one of: (i) an airborne store; and (i) an aircraft;a first fluid-actuated ejector piston received for movement in the first ejector housing assembly and having a distal end abutting for contact the other one of: (i) the airborne store; and (ii) the aircraft;a first selectable force gas generator (SFGG) comprising more than one gas-generating unit in fluid communication with the first ejector housing assembly to actuate the first fluid-actuated ejector piston with a first selected amount of force to eject the airborne store;an initiator in communication with the first SFGG and that supplies at least one firing signal that causes a first selected subset of the more than one gas-generating unit that corresponds to the first selected amount of force;a first signal switching matrix that selectively communicatively couples the firing signal from the initiator to one or more of the more than one gas-generating unit;a device interface coupled to the initiator, the first signal switching matrix, and at least one sensor that dynamically detects one or more ...

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Номер записи: 70
08-06-2017 дата публикации

METHOD AND SYSTEM FOR PLANNING AND LAUNCHING A PLURALITY OF MISSILES TO BE INCLUDED IN THE SAME MISSION

Номер: US20170160057A1
Автор: HAUGEN Rune Andre, LOWE Kare, SKULLESTAD Age Johan, STRAUME Terje
Принадлежит:

A method for planning and launching two or more missiles, to be included in the same mission, and where this is done from one or more aircraft in such a way that the missiles arrive at same target approximately at the same time without interfering with each other on the way to the target. The planning of the mission is performed by sending a set of identical mission data to the missiles prior to launch; letting each missile be assigned a unique identity, letting each missile calculate identical trajectories and a unique offset to this, in one or more of four dimensions, where a resulting offset trajectory is unique for each missile and based on the identical mission data and unique identity, and launching the missiles included in the same mission. 1. A method for planning a mission and launching two or more missiles , to be included in the same mission , from one or more aircraft in such a way that the missiles arrive at the same target approximately at the same time without interfering with each other on the way to the target , wherein that planning of the mission is performed by:sending a set of identical mission data, MD, to said missiles prior to launch;letting each missile be assigned a unique identity, ID;letting each missile calculate identical main trajectories and trajectories with a unique offset to the main trajectory in one or more of four dimensions, where a resulting offset trajectory is unique for each missile and is based on said identical mission data, MD, and the unique identity, ID;{'b': '10', 'launching the missiles () to be included in the same mission, and where each missile follow a unique trajectory.'}2. The method according to claim 1 , wherein the mission data are sent to each missile via an umbilical.3. The method according to claim 1 , wherein the mission data are sent to each missile wirelessly.4. The method according to claim 1 , wherein the unique identity is extracted from the unique number of a weapon station holding each missile.5. ...

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Номер записи: 71
23-06-2016 дата публикации

PAYLOAD LAUNCH SYSTEM AND METHOD

Номер: US20160178317A1
Автор: Durrance Taylor, Huber Keith, JR. Charles M., Mark Earl, Nowell, Powell David, Sizemore Tanner
Принадлежит: Sparton Corporation

A payload launch system includes a launch tube, payload, rocket tube, pressurized motor assembly, and control system. The motor assembly has a launch actuator and an accumulator housing containing compressed gas. The accumulator housing defines a vent opening having a closure. The control system transmits an actuation signal to the actuator in response to a launch request signal to open the closure and cause a discharge of pressure into the launch tube. This causes the rocket tube to launch from the launch tube to a threshold altitude in a single gaseous thrust phase. A method includes deploying a launch system, transmitting a launch actuation signal to the launch actuator via a control system, and opening a closure to allow compressed gas to enter the launch tube, thereby launching the rocket tube from the launch tube to a threshold altitude in the single gaseous thrust phase. 1. A payload launch system comprising:a cylindrical outer launch tube having a longitudinal axis;a payload;a rocket tube containing the payload, wherein the rocket tube is contained within the outer launch tube;a pressurized motor assembly held stationary within the outer launch tube, wherein the pressurized motor assembly includes a launch actuator and an accumulator housing containing a volume of compressed gas and defining a vent opening having a closure; anda control system in communication with the launch actuator;wherein the control system is configured to transmit a launch actuation signal to the launch actuator in response to a launch signal to thereby open the closure of the vent opening and thereby cause a discharge of the compressed gas from the actuator housing into the outer launch tube via gaseous thrust from the pressurized motor assembly, thereby translating the rocket tube along the longitudinal axis and launching the rocket tube from the outer launch tube.2. The launch system of claim 1 , further comprising tether material connecting the rocket tube to the outer launch tube ...

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Номер записи: 72
23-06-2016 дата публикации

MISSILE CANISTER GATED OBTURATOR

Номер: US20160178318A1
Автор: Miller Mark J., Woods Peter C.
Принадлежит:

Apparatus and methods relating to a missile canister that utilizes a variable obturator assembly. The variable obturator assembly can include a plurality of gates that adjust based upon canister pressure at a base plate. In a maximum pressure situation experienced during successful missile egress from the canister, one or more of the gates can open in response to canister flyout pressure so as to increase flow area through the base plate, thereby reducing canister pressure. In a restrained firing scenario, the plurality of gates remain closed thereby preventing missile exhaust gases from flow up past the base plate which could lead to heating of a rocket motor and warhead. The variable obturator assembly can have multiple individual gates that are mounted to the base plate with a hinge assembly, with the gates held in a closed position against the base plate with a spring assembly. 1. A missile canister for a vertical launch missile system , said canister comprising a forward end and an aft end , said forward end disposed approximate a missile nose while the aft end is disposed proximate a missile exhaust nozzle , the canister comprisinga canister shell,a canister forward closure disposed at said forward end,a canister aft closure disposed at said aft end,an obturator plate mounted forward of the canister aft closure, wherein said obturator plate defines a central opening sized to accommodate the missile exhaust nozzle and at least one peripheral obturator opening covered by at least one obturator gate, the obturator opening disposed between the canister shell and the central opening.2. The missile canister of wherein the obturator plate is adjacent at its periphery to the canister shell.3. The missile canister of wherein the obturator plate includes multiple peripheral obturator openings.4. The missile canister of wherein the obturator plate includes 6 peripheral obturator openings.5. The missile canister of wherein the obturator gate is sized to cover more than ...

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Номер записи: 73
22-06-2017 дата публикации

Casing with liquid dispenser

Номер: US20170173616A1
Автор: Andrey Kapranov, Tiziano Rocca
Принадлежит: INNOVANTIX GMBH, Niceway Creation Ltd

The present invention relates to a casing for a mobile electronic device, the casing including a dispenser, which includes a spraying unit and a reservoir, wherein the dispenser can be moved from a secure position to at least one dispensing position.

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Номер записи: 74
15-07-2021 дата публикации

Accommodation and Deployment Device for Payloads on a Flying Machine

Номер: US20210214081A1
Автор: Ralf Schlüter
Принадлежит: Airbus Defence and Space GmbH

A device for accommodating and deploying at least one payload on a flying machine includes at least one housing. The housing includes at least two opposite first side surfaces which extend over at least a portion of a length of a payload to be accommodated. The payload to be accommodated is releasably held between the two first side surfaces of the housing. The housing is at least partially arranged in a cavity on an outer surface of a flying machine. The cavity includes at least one outwardly open first opening, and the housing can be at least partially moved out of the cavity for deploying and/or receiving the payload to be accommodated.

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Номер записи: 75
15-07-2021 дата публикации

Extraction Pole Assembly for Extracting Projectiles from a Bore

Номер: US20210215449A1
Автор: Eliason Douglas J., Lewis Parker, SCOTT Mark A.
Принадлежит:

An extraction system for removing an object from a bore, the extraction system comprising an extraction pole assembly comprising a plurality of extraction poles, each extraction pole having a proximal end and a distal end; and a plurality of centering couplers, each centering coupler of the plurality of centering couplers comprising a partial spherical outer surface sized to complement a diameter of the bore, a proximal end configured to couple to a distal end of an extraction pole, and a distal end configured to couple to a proximal end of the extraction pole. The extraction pole assembly can be operable with a press assembly comprising a clamp configured to secure to the structure having the bore, and an extendable member configured to provide an input force to an extraction pole of the extraction pole assembly. 1. An extraction pole assembly for facilitating removal of an object from a bore , the extraction pole assembly comprising:a first extraction pole having a distal end and a proximal end;a second extraction pole having a distal end and a proximal end; and a spacer comprising a partial spherical outer surface sized to complement an inner diameter of the bore; and', 'an axial bar extending from the spacer, the axial bar comprising a proximal end coupled to the distal end of the first extraction pole and a distal end coupled to the proximal end of the second extraction pole., 'a centering coupler comprising2. The extraction pole assembly of claim 1 , wherein the spacer comprises claim 1 , at least in part claim 1 , a material having a low coefficient of friction and the axial bar comprises a rigid material.3. The extraction pole assembly of claim 2 , wherein the material having a low coefficient of friction comprises nylon and the rigid material comprises a metal.4. The extraction pole assembly of claim 1 , further comprising a centering coupler adapter comprising:a second spacer having a central aperture and a partial spherical outer surface sized to ...

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Номер записи: 76
05-07-2018 дата публикации

LAUNCH TUBE RESTRAINT SYSTEM FOR UNMANNED AERIAL VEHICLE (UAV)

Номер: US20180186474A1
Автор: Rodriguez Marcos Henry, Su Guan H.
Принадлежит:

An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV having an exterior surface, an aerial vehicle (AV) tab extending from the exterior surface, a tube containing the UAV, the tube including a tab stop configured to controllably hinder travel of the AV tab past the tab stop, and a pair of opposing tab guides configured to position the AV tab for travel over the tab stop. 120-. (canceled)21. An unmanned aerial launch vehicle (UAV) launch apparatus , comprising:a tube, wherein the tube has an open end;a cap positioned over the open end of the tube;a strap extending through at least one strap guide and restraining the cap;wherein the strap extends around the entire tube; anda gas generator configured to provide a launching force wherein the launching force is at least sufficient to enable the UAV to translate axially out of the tube.22. The apparatus of claim 21 , wherein the strap extends over a top of the cap.23. The apparatus of claim 21 , wherein the strap extends through at least one strap guide.24. The apparatus of claim 23 , wherein the at least one strap guide includes at least one of: a top strap guide disposed on the cap and a bottom strap guide disposed distal from the open end of the tube.25. The apparatus of claim 21 , wherein the strap has a first attachment at a first end of the strap and a second attachment at a second end of the strap claim 21 , and wherein the first attachment is detachably coupled to the second attachment.26. The apparatus of claim 25 , wherein the first attachment and the second attachment are buckles.27. The apparatus of claim 25 , wherein the strap claim 25 , first attachment claim 25 , and second attachment have sufficient strength to prevent forceful escape of a UAV through the open end of the tube by holding the cap in place over the open end of the tube.28. The apparatus of claim 21 , wherein the strap remains connected to the at least one strap guide when the cap is removed from the open ...

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Номер записи: 77
07-07-2016 дата публикации

FIRING DEVICE FOR FIRING CARTRIDGE AMMUNITION

Номер: US20160195362A1
Автор: HUBER Florian, KITTL Wolfgang, Krebs Michael, MALTAN Johannes
Принадлежит: RHEINMETALL WAFFE MUNITION GMBH

The invention relates to a firing device () for firing cartridge ammunition () comprising a case head (), which has on its outer circumference at least one peripheral, groove-shaped depression (). In order to achieve secure arrestment of the ammunition () in the firing device () when the firing device () is loaded from the muzzle end, the invention proposes that the firing device () comprises a head piece () and a tubular ammunition receiving-device () that is secured on the front side of the head piece (), wherein the ammunition receiving-device () is arranged such that it can be moved axially in the direction of the head piece () against the pressure of a restoring element (). In this case, the head piece () includes an annular guiding element (), which extends axially into the ammunition receiving-device () and has multiple guiding openings (), which extend through the wall () of the guiding element () and are in each case of a form that is angled from the outer side of the guiding element () in the direction of the opening () of the ammunition receiving-device (). Locking elements () are movably arranged in the guiding openings () and, on the side thereof that is facing away from the ammunition receiving-device () are acted upon by spring elements () in such a way that, when the firing device () is loaded, the locking elements () are pressed by the spring elements () into the groove-shaped depression () in the ammunition (). For unloading the ammunition (), the locking elements are pressed out from the groove-shaped depression () in the ammunition () into the guiding openings () of the guiding element () by axially moving the ammunition receiving-device () towards the head piece (). 12203. A firing device for firing cartridge ammunition () with a case head () , having on its outer circumference at least one circumferential , groove-shaped depression () , with the features:{'b': 1', '4', '5', '4, 'a) The firing device () comprises a head piece () and a tubular ...

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Номер записи: 78
13-07-2017 дата публикации

RETRACTING HOOKS ASSEMBLY

Номер: US20170197716A1
Автор: Grygla Michael S., Kerns Keith A., Taylor Bill K.
Принадлежит:

A fastening system with a rotatable fastener that may secure an aircraft store to an aircraft and may rotate to reduce a drag coefficient of the aircraft store. Reducing the drag coefficient of the aircraft store may increase fuel efficiency of the aircraft store by requiring less energy to propel the aircraft store at a given speed or acceleration. 1. A fastening system for securing an expendable aircraft store to an aircraft , including:a housing that forms part of the expendable aircraft store, the housing extending along a longitudinal axis;a first fastener rotatably connected to the housing, wherein the first fastener is rotatable about a first fastening axis; anda second fastener rotatably connected to the housing opposite the first fastener relative to the longitudinal axis of the housing, wherein the second fastener is rotatable about a second fastening axis, and wherein the second fastener is rotatable about a portion of the second fastening axis that is laterally offset from the longitudinal axis opposite the first fastening axis;wherein each fastener includes an engagement section for securing the respective fastener to a mechanical interface of the aircraft, each engagement section being radially outward of the respective fastening axis; andwherein each fastener is rotatable from an open position, where the respective engagement section is engageable with the mechanical interface of the aircraft, to a closed position that reduces a drag coefficient of the fastening system compared to the open position.2. The fastening system of claim 1 , wherein each fastener includes a leg for distributing load when the respective fastener is in the open position.3. The fastening system of claim 2 , wherein the housing includes a longitudinally-extending support with a leg-bearing surface for distributing load received from each leg when the respective fastener is open.4. The fastening system of claim 3 , wherein the bearing surface includes an adjustable-leg-bearing ...

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Номер записи: 79
30-07-2015 дата публикации

THREAT SIMULATING SYSTEM

Номер: US20150211831A1
Автор: Perkal Hagai, Tamir Gabriel
Принадлежит:

A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising: (1) a Static Pyrotechnic Unit (SPTU) and a support stand; (2) a system of Short Range Simulating Rocket (SRSR) and a rocket launching apparatus; and (3) a control system that activates said Static Pyrotechnic Unit in (1) and said system SRSR in (2). When the Static pyrotechnic Unit is ignited, the resulting flash has an IR wavelength and multi spectral emission, intensity and time duration that simulate the initial flash created by a shoulder missile. When the Short Range Simulating Rocket is fired, the resulting radiation has an IR wavelength and multi spectral emission, intensity and time duration that simulates the radiation trail emitted from a fired shoulder missile. The flash created by the Static pyrotechnic Unit, and the trail emission of the Short Range Simulating Rocket are detected by the target survivability detection equipment, enabling the target to take protective measures. 1. A system for evaluating aircraft/watercraft/battle-vehicle survivability equipment comprising the following:(1) a Static Pyrotechnic Unit (SPTU) and a support stand on which said Static pyrotechnic Unit is positioned, said support stand comprising a base and insulating board connected by a telescopic pole, said insulating board has wires for igniting the SPTU, and said SPTU is coated with a flammable material/compound for electrical ignition;(2) a system of Short Range Simulating Rocket (SRSR) and a rocket launching apparatus, said Short Range Simulating Rocket comprising a front section which comprises a pyrotechnic flare material, a back section which comprises a propellant, a rocket engine, and stabilizing fins, and in between the front section and the back section, there is a safety mechanism that enables/disables the activation of the SRSR, said launching apparatus comprising a tripod that can change azimuth and elevation and pedestal on top of which a launch tube is mounted; and( ...

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Номер записи: 80
21-07-2016 дата публикации

REUSABLE LASER SIGHTING DEVICE ADAPTER FOR ROCKET LAUNCHER

Номер: US20160209174A1
Автор: Hartley Scott, Hoblitt Jeff, McDonald James, Suzuki Dale, Swartz Dee
Принадлежит: CRIMSON TRACE INC.

Disclosed herein are reusable adapters for sighting devices for rocket launchers and other large weapons, particularly mounting adapters for reusable sighting devices that allow retrofitting of existing weapons inventory. Some embodiments include an adapter that includes a laser sighting device mount coupled to a mounting bracket, wherein the mounting bracket is configured to register to and align with one or more housing features of the rocket launcher. In various embodiments, the adapter also includes a strap member configured to secure and immobilize the adapter in position on the rocket launcher. In various embodiments, the laser sighting device mount may be factory calibrated with respect to the adapter, and therefore once the adapter has been mounted on the rocket launcher, no field calibrations of the laser sighting device are necessary. 1. A laser sighting device mounting adapter for a rocket launcher comprising:a mounting bracket having a top surface and a bottom surface, the bottom surface forming a void for receiving an iron sight, the void comprising a first registration surface positioned to contact a first side of the iron sight and a second registration surface positioned to contact a second side of the iron sight when the mounting bracket is coupled to the rocket launcher;a laser sighting device mount coupled to the mounting bracket; wherein the laser sighting device mount detachably couples to a laser sighting device; anda strap configured to immobilize the mounting bracket on a muzzle of the rocket launcher, wherein coupling the mounting bracket to the rocket launcher aligns the laser sighting device mount with the rocket launcher for accurate sighting without additional calibration.2. (canceled)3. The laser sighting device mounting adapter of claim 1 , wherein the mounting bracket further comprises a third registration surface positioned to contact a top surface of the iron sight when the mounting bracket is coupled to the rocket launcher.4. The ...

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Номер записи: 81
27-06-2019 дата публикации

Baffled-tube ram accelerator

Номер: US20190195579A1
Автор: Adam P. Bruckner, Andrew J. Higgins, Carl Knowlen, Viggo HANSEN
Принадлежит: UNIVERSITY OF WASHINGTON

A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube.

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Номер записи: 82
20-07-2017 дата публикации

COMBINED LAUNCH AND STORAGE TUBE FOR MISSILE

Номер: US20170205193A1
Автор: Lemire Gary M., Teetzel James W.
Принадлежит:

A dual purpose missile storage and launch tube device includes a tubular housing and a front cover removably covering a first end of the tubular housing, the first end defining an opening for firing a missile. A rear cover assembly removably covers a second end of the tubular housing opposite the first end. A safety mechanism is attached to the tubular housing and includes a sliding member extending through a longitudinal passageway formed in the safety mechanism. A forward portion of the sliding member engages the front cover. A rearward portion of the sliding member engages a fastener locking the rear cover assembly onto the tubular housing. The rearward portion of the sliding member is disengaged from the fastener when the front cover is removed from the first end of the tubular housing for unlocking the rear cover assembly from the tubular housing. 1. A dual purpose missile storage and launch tube device , comprising:a tubular housing;a front cover removably covering a first end of the tubular housing, the first end defining an opening for firing a missile;a rear cover assembly removably covering a second end of the tubular housing, the second end opposite the first end;a safety mechanism attached to the tubular housing, the safety mechanism including a sliding member extending through a longitudinal passageway formed in the safety mechanism;wherein a forward portion of the sliding member engages the front cover;wherein a rearward portion of the sliding member engages a first fastener locking the rear cover assembly onto the tubular housing when the front cover is attached to the first end of the tubular housing; andwherein the rearward portion of the sliding member is disengaged from the first fastener when the front cover is removed from the first end of the tubular housing for unlocking the rear cover assembly from the tubular housing.2. The device of claim 1 , further comprising:a spring member disposed within the longitudinal passageway urging the sliding ...

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Номер записи: 83
28-07-2016 дата публикации

Multi-launcher firearm

Номер: US20160216066A1
Автор: Wei Yanwei
Принадлежит:

A multi-launcher firearm includes a firearm body comprising a plurality of ammunition launchers for storing different types of ammunitions having different ranges in the respective ammunition launchers, an input device connected to the firearm body for receiving a designation inputted by a user, and a controller mounted on the firearm body and respectively connected to each ammunition launcher for receiving the designation from the input device and then controlling the ammunition launcher correspondent to the designation to launch out the ammunition stored therein. The ammunition in each ammunition launcher comprises a plurality of rocket projectiles. All the rocket projectiles stored in the ammunition launcher share an identical diameter. 1. A multi-launcher firearm , comprising:different types of ammunitions having different ranges;a firearm body comprising a plurality of ammunition launchers for storing said different types of ammunitions in said respective ammunition launchers;an input device connected to said firearm body for receiving a designation inputted by a user; anda controller mounted on said firearm body and respectively connected to each said ammunition launcher for receiving the designation from said input device and then controlling said ammunition launcher correspondent to the designation to launch out said ammunition stored therein.2. The multi-launcher firearm claim 1 , as recited in claim 1 , wherein said ammunition comprises a rocket projectile; said controller comprises an igniting device connected to said rocket projectile claim 1 , for igniting said rocket projectile under the designation of the user claim 1 , so as to reduce a total weight and reduce a recoil force brought by launching said ammunition.3. The multi-launcher firearm claim 2 , as recited in claim 2 , wherein said ammunition further comprises a plurality of rocket projectiles which are connected head to tail to form a chain; said igniting device comprises a plurality of ...

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Номер записи: 84
28-07-2016 дата публикации

MISSILE SYSTEM INCLUDING ADS-B RECEIVER

Номер: US20160216073A1
Автор: BONEN Uri
Принадлежит: ISRAEL AEROSPACE INDUSTRIES LTD.

The disclosure presents at least one example of a missile system, method, and/or computer program product. The missile system may, for example, include a radar, an Automatic Dependent Surveillance Broadcast (“ADS-B”) receiver, a missile launcher, and a control station. The missile system may, for example, be configured to handle various situations such as when only ADS-B data relating to an airborne entity is available, only radar data relating to the airborne entity is available or both ADS-B data and radar data relating to the airborne entity are available. The missile system, may, for example, be a surface to air missile system. 1. A missile method comprising ,determining that Automatic Dependent Surveillance Broadcast (“ADS-B”) data relating to an airborne entity was obtained;determining whether or not radar data relating to the airborne entity was obtained;determining whether or not to command missile launch against the airborne entity; andif determined not to command missile launch, then refraining from commanding missile launch against the airborne entity.2. The method of claim 1 , wherein if radar data relating to the airborne entity was not obtained claim 1 , then said determining whether or not to command missile launch against the airborne entity includes determining that a missile should not be launched against the airborne entity.3. The method of claim 1 , wherein said determining whether or not radar data relating to the airborne entity was obtained includes:determining whether or not radar data was obtained; andif radar data was obtained, then determining whether or not said radar data pertains to the airborne entity at least partly based on comparing position data included in said radar data with position data included in said ADS-B data.4. The method of claim 1 , further comprising: if determined to command missile launch claim 1 , then commanding missile launch against the airborne entity.5. The method of claim 1 , wherein if determined that radar ...

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Номер записи: 85
25-06-2020 дата публикации

RAIL-LAUNCHING MUNITION RELEASE

Номер: US20200200506A1
Автор: Bailey Robert A., Campbell David R., Traylor James, Wright Philip C.
Принадлежит:

A rail launch mechanism and method for launching a payload is configured to release payload lugs of a payload from a platform. A rack for launching a payload includes multiple rails that separately engage lugs in the respective payload of the rails, and a force actuator for launching the payload by accelerating the payload along the rails, causing the lugs to separate from the respective rails. A launching system for launching the payload from the platform may include a rail, at least one payload release shoe that carries a payload lug along the rail, and a force actuator for accelerating the payload release shoe such that inertia of the payload causes the payload lug to be released from the payload release shoe. 1. A rack for launching a payload , the rack comprising:multiple rails that separately engage payload lugs received in respective of the rails; anda force actuator for launching the payload by accelerating the payload along the rails, causing the payload lugs to separate from the respective rails.2. The rack according to claim 1 , wherein the multiple rails are parallel and offset from one another in a perpendicular direction relative to a length of the rack.3. The rack according to claim 2 , wherein the multiple rails are offset by a distance between 2 and 13 centimeters.4. The rack according to claim 1 , wherein the force actuator is in-line with one of the multiple rails and offset relative to another one of the multiple rails.5. The rack according to claim 1 , wherein the multiple rails have a stepped arrangement that ascends along a length of the rack opposite the force actuator.6. The rack according to claim 1 , further comprising a frame having a base claim 1 , wherein the multiple rails are offset relative to the base and the force actuator is in-line with one of the multiple rails which is farther away from the base relative to another one of the multiple rails.7. The rack according to claim 1 , wherein the multiple rails are vertically offset and ...

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Номер записи: 86
02-08-2018 дата публикации

FLEXIBLE COVER FOR A MISSILE CONTAINER

Номер: US20180216912A1
Автор: Herquel Pascal, LEROY Bertrand
Принадлежит: MBDA France

A flexible cover comprising at least one, so-called composite, layer, formed from a composite material consisting of at least one fabric and at least one elastomer and a flat metal blade secured to the composite layer by elastomer and comprising pre-cut lines for fragilisation of the flexible cover, the pre-cut lines being arranged so as to create areas in the form of petals, the composite layer and the metal blade being designed so as to return to an initial position once the flexible cover has been opened. 1. A flexible seal that is intended to be mounted on a missile container and is capable of opening under a thrust , the flexible seal comprising:at least one composite layer made of a composite material that includes at least one fabric and at least one elastomer; andat least one flat metal sheet, rigidly connected to said composite layer by the elastomer and including pre-cut lines of weakness in the flexible seal, the pre-cut lines being arranged so as to create petal-shaped regions.2. The flexible seal according to claim 1 , wherein the at least one composite layer includes two composite layers arranged on either side of the metal sheet.3. The flexible seal according to claim 1 , further comprising an anti-friction covering on a surface intended to be positioned towards the interior of the container.4. The flexible seal according to claim 1 , wherein the pre-cut lines are arranged radially with respect to the center of the flexible seal.5. The flexible seal according to claim 1 , wherein said at least one composite layer and the metal sheet are arranged such that at least some of the pre-cut lines of the metal sheet are parallel to at least one direction of the thread of the fabric of the composite material of the composite layer.6. The flexible seal according to claim 1 , wherein the metal sheet is a single part in which said pre-cut lines are made.7. The flexible seal according to claim 1 , wherein the metal sheet comprises recesses for receiving a portion ...

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Номер записи: 87
17-08-2017 дата публикации

LAUNCH APPARATUS AND VEHICLE

Номер: US20170233047A1
Автор: Lambertus Detlef
Принадлежит:

The invention relates to a launch apparatus for an Unmanned Underwater Vehicle—in particular, for an Autonomous Underwater Vehicle or for a Remotely Operated Vehicle—with a launching tube having an inner wall and an outlet, and the Unmanned Underwater Vehicle contained within the launching tube, whereby the Unmanned Underwater Vehicle has a vehicle casing with a vehicle casing inhomogeneity, such that an ejection of the Unmanned Underwater Vehicle causes different contact loads between the vehicle casing and the inner wall, whereby the Unmanned Underwater Vehicle has a detachable compensating form, which is designed in such a way that the vehicle inhomogeneity is compensated, such that the result is a combination of the Unmanned Underwater Vehicle and the detachable compensating form, the combination whereof, when ejected, causes a substantially more uniform contact load to occur between the combination and the inner wall. 1. A launch apparatus for an unmanned underwater vehicle , said launch apparatus comprising a launching tube having an inner wall and an outlet , the unmanned underwater vehicle contained within the launching tube , the unmanned underwater vehicle having a vehicle casing , the vehicle casing having inhomogeneity , the unmanned underwater Vehicle having a detachable compensating form configured to compensate for the vehicle inhomogeneity so that when a combination comprised of the unmanned underwater vehicle having the detachable compensating form is ejected from the launch tube , a substantially more uniform contact load between the combination and the inner wall occurs in comparison to the different contact load that would occur when the unmanned underwater vehicle without the detachable form is ejected from the launch tube.2. The launch apparatus according to claim 1 , wherein the launch apparatus further comprises a relay facility arranged on the inside of the launch tube claim 1 , the relay facility movable to an outlet medium when the ...

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Номер записи: 88
16-07-2020 дата публикации

ROCKET MOTOR WITH COMBUSTION PRODUCT DEFLECTOR

Номер: US20200225002A1
Автор: Dryer Richard, Hitner John M., Smallwood David A., Summers Matt H., Villarreal James Kendall
Принадлежит:

A missile includes a rocket motor that has a flow deflector in an expansion region of the rocket motor's nozzle. The flow deflector diverts flow of combustion products away from a safe region that is aft of the missile. The safe region protects an operator of a launcher used to fire the missile, such as a shoulder-fired launcher, from harm caused by the combustion products. The flow deflector may be small enough such that it does not significantly adversely affect the performance of the rocket motor. The presence of the flow diverter may allow for the rocket motor to be started sooner in the flight of the missile, or at a distance closer to the operator, while still keeping the operator safe. The flow deflector and supporting structure, such as struts, may be additively manufactured with at least an aft part of the nozzle, as a continuous single-piece part. 1. (canceled)2. The rocket motor of claim 5 , wherein the flow deflector is conical.3. The rocket motor of claim 5 , wherein the flow deflector has a wedge shape.4. The rocket motor of claim 5 , wherein the flow deflector has a maximum extent of at least 3.2 mm (0.125 inches).5. A rocket motor comprising:a fuel element;a converge-diverge nozzle through which combustion products from the burning of the fuel element pass; anda flow deflector along a centerline of an expansion region of the nozzle;wherein the flow deflector deflects away from the centerline combustion products from the burning of the fuel;wherein the flow deflector is attached to an inner wall of a diverge portion of the nozzle, with the diverge portion defining the expansion region; andwherein an upstream end of the flow deflector is in the diverge portion of the nozzle.6. The rocket motor of claim 5 , further comprising struts that attach the inner wall and the flow deflector together.7. The rocket motor of claim 6 , wherein the flow deflector claim 6 , the struts claim 6 , and at least part of the diverge portion are a single unitary additively- ...

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Номер записи: 89
01-08-2019 дата публикации

EJECTOR RACK

Номер: US20190233108A1
Автор: Elnekave David, MELAMED Gil, WEISSMAN Ilan
Принадлежит:

The presently disclosed subject matter is directed to devices for carrying and releasing stores from a vehicle, such as ejector racks for carrying and releasing a store with respect to an air vehicle. 1. A support and release device for releasably supporting a store , the store having at least one lug for enabling selective removable engagement of the store with respect to the device , the support and release device comprising: a lug engagement release system, comprising a hook element;', 'an actuator system, operatively coupled to the lug engagement release system; and', 'a safety system comprising a safety lock, said safety lock being configured for selectively coupling or uncoupling with respect to at least the lug engagement release system to alternately provide a coupled mode and a decoupled mode, respectively,, 'a housing accommodating the lug engagement release system is configured for alternately providing:', 'an engaged configuration, in which the lug engagement release system is capable of being in an engaged relationship with respect to the lug via said hook element, and', 'a disengaged configuration, in which the lug engagement release system is selectively disengaged with respect to the lug, responsive to selective operation of the actuator system wherein the actuator system selectively provides pressurized gas to said lug engagement release system, concurrent with the safety lock being in uncoupled mode;, 'wherein in the coupled mode the safety lock is coupled with respect to the lug engagement release system such as to prevent the lug engagement release system, in the engaged configuration, from providing the disengaged configuration, irrespective of operation of the actuator system; and', 'in the decoupled mode the safety lock is decoupled with respect to the lug engagement release system enabling the lug engagement release system to provide the disengaged configuration from the engaged configuration responsive to operation of the actuator system; ...

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Номер записи: 90
15-09-2016 дата публикации

Tube to bulkhead bonded joint design

Номер: US20160265877A1
Автор: Jack W. Reany, Keith A. Elkins, Orlando L. Mijares
Принадлежит: Raytheon Co

A tube to bulkhead joint is provided. The joint includes a bulkhead defining an aperture and comprising an interior facing sidewall at the aperture, a tubular element, which is insertible into the aperture, the tubular element including an end sized to fit into the aperture and slotted to form multiple deflectable fingers, and adhesive disposable between at least the multiple deflectable fingers and the interior facing sidewall of the aperture.

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Номер записи: 91
15-08-2019 дата публикации

LOW-SHOCK SEPARATION DEVICE

Номер: US20190249951A1
Автор: Cha Jeong-Min, Kim Dong-Jin, KIM Nam-Choon, KIM Zaeill, LEE Yeung-Jo
Принадлежит:

A low-shock separation device is characterized in that an internal locking structure is unlocked and a bolt is separated by operating a specific part of components thereof using high pressure that is generated by combustion of powder. 1. A low-shock separation device comprising:a housing having open top and bottom and an internal receiving space;a cylinder disposed in the receiving space through the top of the housing and having a top hole and a bottom hole communicating with the top hole and larger in cross-sectional area than the top hole;a housing cap fitted in a space between the housing and the cylinder and closing the top of the housing;a piston disposed in the bottom hole of the cylinder;a pressure cartridge partially inserted in the top hole and closing an upper end of the top hole; anda bolt partially inserted in the bottom hole through the bottom of the housing, closing a lower end of the bottom hole, and kept in the bottom hole by a holder,wherein a passage attenuating a collision between the cylinder and the housing cap is formed by filling a space between the cylinder and the housing cap with high pressure gas, and the passage is formed when the cylinder is moved toward the pressure cartridge by high pressure that is generated when the pressure cartridge is operated.2. The device of claim 1 , wherein the passage has a first passage formed around a side of the cylinder and a second passage having a first end communicating with the top hole of the cylinder and a second end extending from a top to a side of the piston to communicate with the first passage of the cylinder.3. The device of claim 2 , wherein the first passage is formed at a position where the first passage can communicate with the second passage when the cylinder is moved.4. The device of claim 1 , comprising a deformable portion formed on the housing cap claim 1 , restricting movement of the cylinder before the pressure cartridge is operated claim 1 , and primarily absorbing shock by ...

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Номер записи: 92
14-09-2017 дата публикации

MULTIPLE MISSILE AND BOMB CARRIAGE SYSTEM

Номер: US20170259919A1
Автор: Binkholder Ryan, Foster John K., Jakubowski, JR. Thaddeus M.
Принадлежит:

A multiple advanced missile and bomb ejector rack carriage system employs a carriage mountable to an air to ground (AG) bomb release unit (BRU) on an aircraft pylon. A single MIL-STD- electrical interface is integral to the carriage and has a first power connection and first signal connection. Onboard carriage avionics are supported within the carriage and connected to the MIL-STD- electrical interface. The onboard carriage avionics are adapted to receive communications from an aircraft central computer through the first power connection and first signal connection and provide store specific communications independent of specific original aircraft wiring to at least one ejector and store. 1. A multiple advanced missile and bomb ejector rack carriage system comprising:a carriage mountable to an air to ground (AG) bomb release unit (BRU) on an aircraft pylon;a single MIL-STD-1760 electrical interface integral to the carriage having at least a first power connection and at least a first signal connection;onboard carriage avionics supported within the carriage and connected to the MIL-STD-1760 electrical interface, said onboard carriage avionics adapted to receive communications from an aircraft central computer through the at least a first power connection and at least a first signal connection and provide store specific communications to at least one ejector and store.2. The multiple advanced missile and bomb ejector rack carriage system as defined in claim I wherein the at least one ejector comprises an advanced missile and bomb ejection rack (AMBER) and the store is selected from the set of universal armament interface (UAI) air to air (AA) stores , non-UAI AA stores , and air to ground (AG) stores.3. The multiple advanced missile and bomb ejector rack carriage system as defined in wherein the at least one ejector comprises an AA launcher (LAU) claim 1 ,4. The multiple advanced missile and bomb ejector rack carriage system as defined in claim I wherein the at least ...

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Номер записи: 93
06-08-2020 дата публикации

SELF-DEFENSE WEAPONS POD SYSTEMS AND METHODS FOR AIRCRAFT

Номер: US20200247540A1
Автор: Jones Ryan D., Powell Rayner R.
Принадлежит: The Boeing Company

A self-defense weapons pod system for an aircraft. The self-defense weapons pod system includes a housing containing at least one missile in a non-deployed state, and threat detection sensors coupled to the housing. The threat detection sensors are configured to detect an incoming threat. The missile(s) is configured to be deployed to neutralize the incoming threat. 1. A self-defense weapons pod system for an aircraft , the self-defense weapons pod system comprising:a housing containing at least one missile in a non-deployed state, wherein the at least one missile comprises a plurality of fins coupled to a main body, and an engine within the main body; andthreat detection sensors directly secured to the housing, wherein the threat detection sensors are configured to detect an incoming threat, and wherein the at least one missile is configured to be deployed to neutralize the incoming threat.2. The self-defense weapons pod system of claim 1 , further comprising a threat defense control unit in communication with the threat detection sensors and the at least one missile.3. The self-defense weapons pod system of claim 2 , wherein the threat defense control unit is contained within the housing.4. The self-defense weapons pod system of claim 2 , wherein the threat defense control unit is configured to output a threat neutralization signal to the at least one missile in response to receiving one or more incoming threat detection signals from the threat detection sensors claim 2 , and wherein the threat neutralization signal deploys the at least one missile.5. The self-defense weapons pod system of claim 4 , wherein the threat defense control unit automatically outputs the threat neutralization signal in response to receiving the one or more threat detection signals.6. The self-defense weapons pod system of claim 1 , wherein the at least one missile comprises four forwardly-oriented missiles and four rearwardly-oriented missiles.7. The self-defense weapons pod system of ...

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Номер записи: 94
13-09-2018 дата публикации

Launched air vehicle system

Номер: US20180257792A1
Автор: Thomas William Smoker
Принадлежит: Lockheed Martin Corp

A launch canister for ejection from a submerged launch platform, the launch canister being adapted for ejection in a direction substantially along a first axis of the launch canister and comprising: an enclosure for carrying a UAV; a nose cap releasably located in a launch opening at a forward end of the launch canister; a launch mechanism for driving a UAV carried in the enclosure out of the launch canister through the launch opening in a direction substantially along said first axis; and a water surface sensor for detecting when the nose cap of the canister broaches the surface of the water; wherein the launch canister is configured to, on the water surface sensor detecting that the nose cap of the canister has broached the surface of the water, immediately release the nose cap and initiate the launch mechanism to drive a UAV carried in the enclosure out of the launch canister through the launch opening.

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Номер записи: 95
14-10-2021 дата публикации

Light Trigger

Номер: US20210318089A1
Автор: Dorothy Devine Burdine, Lavada Sue Pitts
Принадлежит: Area Denial Systems LLC

A firearm has a trigger shield configured as a protective loop surrounding a first and second switch of the firearm. Each switch actuates the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. Further, the firearm has an emitter mounted on the trigger shield that propagates a light beam to a receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges.

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Номер записи: 96
05-10-2017 дата публикации

CARRIAGE FOR ROCKET LAUNCH SYSTEM

Номер: US20170284768A1
Автор: Carraha Kimberly A., Chin Howard M.
Принадлежит:

A carriage for use in a rocket launch system for cooperating with an electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage has traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage. 1. A carriage for transporting a rocket for use in a rocket launch system , the rocket launch system having a set of rocket transport lines extending between a low altitude and a high altitude , a set of electric power lines extending between a low altitude and a high altitude and lighter-than-air balloons connected to sets of rocket transport lines and the set of electric power lines for holding the rocket transport lines and electric power lines at respective altitudes extending between the low altitude and the high altitude , said carriage comprising:a multi-sided cross section; anda set of traction wheels for engaging said rocket transport lines and rotating to convey said carriage along said rocket transport lines.2. A carriage according to wherein said set of traction wheels is electrically powered claim 1 , each traction wheel of said set of traction wheels engaging said electric power lines for deriving electric power from said electric power lines when said carriage is at a low altitude for transporting said carriage to a higher altitude.3. A carriage according to wherein said carriage further comprises receptacles for being used to lift said respective carriages into components of the rocket launch system.4. A carriage according to wherein said ...

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Номер записи: 97
27-08-2020 дата публикации

HOUSING INTENDED TO BE ARRANGED ON A VEHICLE AND WEAPON SYSTEM COMPRISING SUCH A HOUSING

Номер: US20200271414A1
Автор: BRUN Michel, DESCATOIRE Xavier, Vincent Virginie
Принадлежит: NEXTER SYSTEMS

A housing intended to be arranged on a vehicle, in particular a military vehicle, and having a substantially parallelepiped shape including a front wall and a rear wall that each includes at least one bore for allowing air to flow inside the housing. At least one of the front or rear walls carries a plate, arranged outside the housing and at a distance from said wall, the housing further including at least one first slot allowing air to pass between the plate and the wall in question, and at least one second slot constituted by the gap between a lateral edge of the plate and said wall. The invention also concerns a weapon system including at least one missile launcher arranged in such a housing. 1. A housing intended to be arranged on a vehicle and having a substantially parallelepiped shape comprising a front wall , a rear wall , a lower wall , an upper wall and two side walls , the front and rear walls each comprising at least one bore for allowing air to flow inside the housing , wherein at least one of the front or rear walls carries a plate which is arranged outside the housing and at a distance from said wall , the at least one bore of the wall in question being located at the vicinity of an upper edge of said wall , the housing further comprising at least one first slot allowing air to pass between the plate and the wall in question , the slot being located at the vicinity of a lower edge of said wall , the plate also having at least one second dimension that is less than that of said wall in question such that there is at least one second slot constituted by the gap between a lateral edge of the plate and said wall , the housing comprising at least one sheet metal closing the gap between the plate and the wall at an upper edge and at at least one lateral edge of the wall in question.2. The housing according to claim 1 , wherein the at least one first slot is carried by the plate and provided at the vicinity of a lower edge of the plate.3. The housing ...

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Номер записи: 98
12-09-2019 дата публикации

1-TO-N MUNITIONS ADAPTER FOR AN AIRBORNE PLATFORM

Номер: US20190277603A1
Автор: Hild Walter Hunter, Livingstone Abel
Принадлежит:

A 1-to-N munitions adapter that includes a physical launcher interface, a physical munitions interface, and electronic control circuitry. The physical launcher interface is operable to connect the 1-to-N munitions adapter to a single munition launcher that is i) configured and arranged to carry and launch a single munition of a first type, and ii) integrated to an airborne platform. The physical munitions interface is operable to connect the 1-to-N munitions adapter to multiple munitions of a second type. The 1-N munitions adapter i) emulates a control interface of a single munition of the first type to the single munition launcher, in part by identifying the 1-to-N munitions adapter to the single munition launcher as a single munition of the first type, and ii) selectively controls the release of munitions of the second type while the airborne platform is in flight in response to signals received from the single munition launcher. 1. A 1-to-N munitions adapter for an airborne platform , comprising:a physical launcher interface that is configured and arranged to mechanically and electrically connect the 1-to-N munitions adapter to a single munition launcher that is i) configured and arranged to carry and launch a single munition of a first type, and ii) integrated to an airborne platform;a physical munitions interface that is configured and arranged to mechanically and electrically connect the 1-to-N munitions adapter to a plurality of munitions of a second type; and emulate a control interface of a single munition of the first type to the single munition launcher, at least in part by identifying the 1-to-N munitions adapter to the single munition launcher as a single munition of the first type, and', 'selectively control the release of multiple ones of a plurality of munitions of the second type that are carried by the 1-to-N munitions adapter while the airborne platform is in flight in response to signals received from the single munition launcher., 'electronic ...

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Номер записи: 99
19-10-2017 дата публикации

MOUNTING BASE AND RINGS FOR MOUNTING AN OPTICAL SCOPE TO A ROCKET PROPELLED GRENADE (RPG) LAUNCHER

Номер: US20170299331A1
Автор: BYARS Mike, JOZAITIS Eric, MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

An optical scope mounting system is disclosed including a back-sloped base mount and a pair of rings, to cooperate with the base mount, for positioning an optical scope laterally of the weapon on which it is mounted. The optical mounting system finds utility on rocket propelled grenade (RPG) launchers. The back-sloped base mount creates a divergence between the centerline of the bore of the RPG launcher and the line of sight through the optical scope. 1. An optical scope mounting system for a rocket propelled grenade (RPG) launcher , the system comprising:a rail mount, the rail mount having a lower surface shaped to be complementary to an exterior surface of the barrel of the RPG launcher and to be mounted over and in-line with a bore of the RPG barrel,the rail mount having an upper surface to accept a pair of rings configured to receive the optical scope;a pair of rings, each ring of the pair of rings having a base configured to engage with the rail mount and a portion to receive the optical scope; andwherein the rail mount is shaped so as to be back sloped in a direction opposite to a muzzle of the bore.2. The optical scope mounting system according to claim 1 , wherein a connecting portion of the rings between the base and the portion to receive the optical scope is shaped to position the optical scope offset from claim 1 , and laterally of claim 1 , the bore of the RPG.3. The optical scope mounting system according to claim 1 , wherein the upper surface of the rail mount has a Picatinny configuration.4. The optical scope mounting system according to claim 1 , wherein the rail mount has a dovetail portion.5. The optical scope mounting system according to claim 4 , wherein the base of the rings have a shape to engage the dovetail of the base.6. The optical scope mounting system according to claim 5 , wherein the shape on the base of the rings is adjustable so as to clamp on the dovetail of the base.7. The optical scope mounting system according to claim 2 , ...

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Номер записи: 100