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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 3197. 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
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: 2
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: 3
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: 4
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: 5
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: 6
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: 7
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: 8
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: 9
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: 10
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: 11
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: 12
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: 13
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: 14
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: 15
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: 16
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: 17
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: 18
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: 19
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: 20
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: 21
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: 22
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: 23
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: 24
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: 25
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: 26
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: 27
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: 28
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: 29
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: 30
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: 31
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: 32
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: 33
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: 34
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: 35
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: 36
13-04-2017 дата публикации

MULTI-AIMING POINT RETICLE AND OPTICAL SCOPE INCORPORATING THE SAME

Номер: US20170102209A1
Автор: BYARS Mike, MEZYNSKI Ryan
Принадлежит: AIRTRONIC USA, LLC

A multi-aiming point reticle for use in an optical scope is described including both range-finding and aiming points. The reticle, and scope incorporating the same, finds special utility for combination with a rocket propelled grenade (RPG) launcher to hit targets at extended distances. A method of operation is also described. 1. A multi-aiming point reticle comprising:a fixed aiming point indicia;a vertical crosshair and a horizontal crosshair, each of the vertical and horizontal crosshair having an optical point of intersection; the point of intersection being below the fixed aiming point indicia;a series of quadrilateral shapes between the fixed aiming point indicia and the point of intersection.2. The multi-aiming point reticle of claim 1 , wherein the vertical crosshair comprises a series of predetermined distance gradients.3. (canceled)4. The multi-aiming point reticle of claim 2 , wherein the vertical crosshair comprises a series of mil gradients and every fifth mil gradient is larger than its adjacent gradient.5. The multi-aiming point reticle of claim 1 , wherein the horizontal crosshair comprises a series of predetermined gradients.6. (canceled)7. The multi-aiming point reticle of claim 5 , wherein the horizontal crosshair comprises a series of mil gradients and every fifth mil gradient is larger than its adjacent gradient.8. The multi-aiming point reticle of claim 1 , wherein the series of quadrilateral shapes comprise a first set of quadrilateral shapes that are uniform in shape and size to each one in the series.)9. The multi-aiming point reticle of claim 8 , wherein the first set of quadrilateral shapes are rectangles.10. The multi-aiming point reticle of claim 9 , wherein the first set of rectangles form a row claim 9 , wherein at least one intersection in the row is directly between the fixed aiming point indicia and the vertical crosshair.11. The multi-aiming point reticle of claim 9 , wherein the first set of rectangles comprise two rows and the ...

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Номер записи: 37
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: 38
05-05-2016 дата публикации

APPARATUS AND METHOD OF GENERATING MOMENTUM USING SUPERCONDUCTING COILS

Номер: US20160123703A1
Автор: KIM Hyung Jun, KIM Jin Sub, Ko Tae Kuk, LEE Ji Ho, Lee Woo Seung, Nam Seok Ho, Park Young Gun
Принадлежит:

The present invention relates to an apparatus of generating momentum which drives an object. The present invention provides a momentum generating apparatus in which a pair of high temperature superconducting coils which are wound in different directions and have different superconducting properties are arranged in parallel and the same current flows in the pair of coils to be in a stable state where magnetic fields generated in the coils are cancelled and an asymmetric current is suddenly applied to the pair of coils through a switching operation to generate a magnetic field and an eddy current is induced in a plate due to the generated magnetic field and the plate is floated using a repulsive force between the magnetic field generated in the plate due to the eddy current and the magnetic field generated in the pair of coils, to instantaneously generate force using a small amount of superconducting coils. 1. A momentum generating apparatus using a superconducting coil , the apparatus comprising:a superconducting unit which includes a pair of a first superconducting coil unit and a second superconducting coil unit which are wound in different directions, have different superconductive properties, and are arranged in parallel;a power supply which supplies an AC power to the superconducting unit; anda switching unit which is connected to the superconducting unit and closes or opens a circuit in accordance with the manipulation,wherein when the switching unit is turned on to connect circuits at both sides of the switching unit, the superconducting unit instantaneously generates a predetermined amount or more of a magnetic field within a predetermined time.2. The apparatus of claim 1 , wherein the first superconducting coil unit and the second superconducting coil unit are high temperature superconductors which are objects whose critical temperature for having a superconductive property is set to a predetermined temperature or higher.3. The apparatus of claim 1 , wherein ...

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Номер записи: 39
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: 40
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: 41
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: 42
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: 43
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: 44
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: 45
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: 46
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: 47
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: 48
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: 49
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: 50
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: 51
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: 52
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: 53
24-06-2021 дата публикации

ROCKET LAUNCH MODULE AND ROCKET LAUNCH VEHICLE

Номер: US20210190452A1
Автор: Jeannot Simon Pierre
Принадлежит:

The present invention relates to a rocket launching module comprising a base frame () comprising at least one rail (); a sliding table () configured to slide substantially vertically on said rail () when driven by at least one electric linear actuator (), and a targeting device () comprising a turntable () on which a pivotable body () is mounted, supporting a rocket support portion (). The sliding table () comprises a platform () configured to receive the turntable () of the targeting device (). 1. Module for rocket launching , comprising:a base frame comprising at least one rail;a sliding table configured to slide substantially vertically on said rail when driven by at least one electric linear actuator, anda targeting device comprising a turntable on which a pivotable body supporting a rocket support portion is mounted;wherein the sliding table comprises one platform that is substantially flat configured to receive the turntable of the targeting device.2. Module for rocket launching according to claim 1 , wherein:the base frame comprises a rectangular shaped frame with four columns, each of the four columns defining a rail;the sliding table comprises a support structure supporting the substantially flat platform;the support frame of the sliding table comprises a plurality of lugs configured to slide into the rails of the frame andthe substantially flat platform of the sliding table comprises an opening which receives the turntable of the targeting device.3. Module for rocket launching according to claim 2 , further comprising two linear actuators arranged at opposite ends of the frame.4. Module for rocket launching according to claim 3 , wherein the actuators are powered by an electric motor.5. Module for rocket launching according to claim 3 , wherein each actuator is powered by an electric motor and is connected to the sliding table by a transition piece.6. Module for rocket launching according to claim 1 , further comprising at least one modular rocket ...

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Номер записи: 54
14-06-2018 дата публикации

Launch vehicle and system and method for economically efficient launch thereof

Номер: US20180162559A1
Автор: Miles R. Palmer
Принадлежит: 8 Rivers Capital LLC

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, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

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Номер записи: 55
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: 56
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: 57
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: 58
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: 59
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: 60
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: 61
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: 62
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: 63
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: 64
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: 65
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: 66
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: 67
27-08-2015 дата публикации

Laser sight for rocket launcher

Номер: US20150241170A1
Автор: Dale Suzuki, Dee SWARTZ, James Mcdonald, Jason KLEIBER, Scott Hartley
Принадлежит: Crimson Trace Corp

Embodiments herein relate to the field of firearm accessories, and, more specifically, to reusable laser sighting devices for rocket launchers and other large weapons, particularly reusable laser sighting devices that allow retrofitting of existing weapons inventory. Some embodiments include a base plate that is configured to be permanently coupled to a rocket launcher, such as the M72 LAW, and a laser module configured to removably couple to the base plate. In various embodiments, the systems disclosed herein permit a the module to be removed from the base plate of a spent rocket launcher, and coupled to the base plate of a new rocket launcher, thereby reducing waste. In various embodiments, the laser module may be factory calibrated with respect to the base plate, and therefore once the base plate has been fixed to the rocket launcher, no field calibrations of the laser module are necessary.

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Номер записи: 68
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: 69
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: 70
26-08-2021 дата публикации

ROCKET ARMAMENT LAUNCHABLE FROM A TUBULAR LAUNCHER WITH AN OUTSIDE LAUNCHER NON-IGNITION SECURING AND MOTOR SEPARATION DURING FLIGHT

Номер: US20210262756A1
Автор: Guller Evgeny, Tal Nadav, Teper Yossi, Ziv Jakov
Принадлежит:

Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight and a method to prevent the ignition of the armaments rocket even in the event of actuation of the armaments pyrotechnic assembly, which normally serves to eject the armament from the launcher and to ignite its rocket motor, wherein the armament comprises a gas dispersion assembly, which when the armament is not encased in the tubular launcher, prevents the ignition of the rocket motor even if the armaments pyrotechnic assembly is actuated; and a cutting and separation assembly that is actuated by the pressure of the rocket motor gases for mechanically cutting a structural connection between the rocket motor and the armaments effective payload and separate them during their flight. 1. A rocket-based armament launchable from a tubular launcher that comprises:an effective payload;a rocket motor that is structurally connected to the effective payload and is adapted from the time of an ignition of the rocket motor to propel the effective payload; anda pyrotechnic assembly that has been adapted, once actuated, to eject the rocket motor and said effective payload from said tubular launcher and to ignite said rocket motor;wherein said rocket armament is characterized in that said armament also comprises:a. a gas dispersion assembly which, when said rocket armament is not encased in the tubular launcher, prevents the ignition of said rocket motor even if said pyrotechnic assembly is actuated; andb. a cutting and separation assembly that is actuated by the pressure of gases from said rocket motor for mechanically cutting the structural connection between the rocket motor and the effective payload and separate the rocket motor and the effective payload during flight.2. The rocket armament of claim 1 , wherein said gas dispersion assembly comprises:a dispersing openings array that is connected to a flow of gas mass-produced by the actuation of ...

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Номер записи: 71
06-09-2018 дата публикации

SYSTEMS AND METHODS FOR IMPROVING EFFICIENCY OF ELECTROANTIMAGNETIC LAUNCHERS

Номер: US20180251237A1
Автор: Hosie Cam, Palmer Miles R.
Принадлежит:

The present disclosure relates launch systems, launch vehicles for use with the launch system, and methods of launching articles utilizing the launch vehicle and/or the launch system. In particular, various improvements for electroantimagnetic launch systems, vehicles, and methods are provided. 1. A method for improving efficiency of an electroantimagnetic launch system , the method comprising:accelerating a launch vehicle through a launch tube by conducting electrical current from a power source through conductors positioned in the launch tube to electrical contacts on the launch vehicle so as to power a propulsion system of the launch vehicle; andsubstantially preventing flow of electrical current in the launch tube other than between the launch tube conductors and the launch vehicle electrical contacts.2. The method of claim 1 , wherein the launch tube comprises a starting end and an exit end claim 1 , wherein the power source is positioned proximate the exit end of the launch tube so as to deliver the electrical current from the exit end toward the starting end claim 1 , and wherein the launch tube comprises a plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle as the launch vehicle accelerates through the launch tube.3. The method of claim 2 , wherein the plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle are selected from the group consisting of solid state switches claim 2 , explosive switches claim 2 , fuses claim 2 , and combinations thereof.4. The method of claim 2 , wherein the plurality of elements that sequentially terminate delivery of the electrical current rearward of the launch vehicle are defined by one or more of the following configurations: time-based switching; controlled by a defined computer algorithm; mechanically triggered; optically triggered.5. The method of claim 1 , comprising forming a sheath of ionization ...

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Номер записи: 72
24-09-2015 дата публикации

Launch Tube Restraint System For Unmanned Aerial Vehicle (UAV)

Номер: US20150267996A1
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 (). 1. An unmanned aerial launch vehicle (UAV) launch apparatus , comprising:a UAV having an exterior surface;an aerial vehicle (AV) tab extending from the exterior surface; and a tab stop configured to hinder travel of the AV tab about the tab stop; and', 'a tab guide configured to position the AV tab for travel about the tab stop., 'a tube containing the UAV, the tube comprising2. The apparatus of claim 1 , wherein the tube comprises an open end and the tab stop is disposed adjacent the open end.3. The apparatus of claim 1 , wherein the tab guide comprises a trough formed in an inner circumferential wall of the tube.4. The apparatus of claim 3 , wherein the tab stop comprises an end of the trough.5. The apparatus of claim 1 , wherein the tab guide extends from an interior side of the tube.6. The apparatus of claim 1 , wherein the tab guide is configured to guide the AV tab axially along the tube.7. The apparatus of claim 3 , wherein the tab guide comprises opposing parallel walls.8. The apparatus of claim 4 , wherein the tab stop comprises an end cap extending between the opposing parallel walls.9. The apparatus of claim 4 , wherein the tab stop comprises a prepeg material extension extending into an interior of the tube.10. The apparatus of claim 1 , further comprising:a cap positioned over the open end, the cap having a cap tab stop extending axially into the interior of the tube adjacent to the tab guide.11. The apparatus of claim 10 , further comprising:a strap extending through the strap guide and restraining the cap.12. The ...

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Номер записи: 73
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: 74
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: 75
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: 76
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: 77
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: 78
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: 79
19-10-2017 дата публикации

RAMP OF CATAPULT

Номер: US20170297740A1
Автор: Lipponen Pentti
Принадлежит: Robonic Ltd Oy

The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage () for fastening an aircraft (). The carriage () is supported on a ramp (). The ramp is formed of one or more ramp elements (-). The ramp element comprises four frame plates, namely two parallel side plates (), a top plate () and a bottom plate (). The frame plates are separate pieces which are connected at fastening points () to each other by means of mechanical fastening elements (). 1. A ramp of a catapult comprising:at least one elongated ramp element;longitudinal first guide surfaces on an upper part of the ramp for supporting a carriage movably on the ramp;and wherein the at least one ramp element comprises two parallel side plates, which are located at a horizontal distance from each other, and further, at least one top plate and at least one bottom plate, which top plate and bottom plate are located at a vertical distance from each other;and further, the frame plates are separate pieces which are connected at fastening points to each other by means of mechanical fastening elements.2. The ramp as claimed in claim I , whereinthe fastening points are provided with fastening openings extending though structures connected at the fastening points;and the fastening openings are provided with the mechanical fastening elements, which are tightened for generating fastening forces.3. The ramp as claimed in claim 1 , wherein the mechanical fastening elements are rivets claim 1 , whereby the ramp element is a riveted structure.4. The ramp as claimed in claim 1 , wherein the mechanical fastening elements are fastening screws.5. The ramp as claimed in claim 1 , wherein the fastening points are provided with adhesive joints in addition to mechanical fastening elements.6. The ramp as claimed in claim 1 , whereinthe fastening points are provided with angle pieces, which are separate pieces relative to the frame plates;and the angle pieces comprise two fastening surfaces, which ...

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Номер записи: 80
19-10-2017 дата публикации

ARRANGEMENT IN CATAPULT

Номер: US20170297741A1
Автор: Lipponen Pentti, Verho Heikki Ilmari
Принадлежит: Robonic Ltd Oy

The invention relates to a launching cylinder of a catapult and to a catapult. The launching cylinder comprises a frame inside which are a pneumatic pressure space for launching purpose and a hydraulic pressure space for returning purpose. The pressure spaces are separated from each other by means of a piston assembly. 1. A launching cylinder of a catapult wherein the launching cylinder comprises:a frame comprising a cylindrical inner space;a piston assembly arranged movably inside the inner space and being connected to a piston rod;a first pressure space and a second pressure space inside the cylindrical inner space of the frame and being separated from each other by means of the piston assembly;and wherein the first pressure space is connectable to a pneumatic circuit for generating launching movement towards a stroke direction of the launching cylinder, and the second pressure space on the side of the piston rod is connectable to a hydraulic circuit for generating return movement opposite to the stroke direction, whereby the launching cylinder is provided with combined pneumatic launching means and hydraulic returning means.2. The launching cylinder as claimed in claim 1 , whereinthe piston assembly comprises radial first sealing means on the side of the first pressure space and radial second sealing means on the side of the second pressure space;the piston assembly is further provided with at least one radial first leakage channel, which is located between the first sealing means and second sealing means;and the piston rod comprises at least one longitudinal second leakage channel a first end portion of which is in connection to the first leakage channel allowing thereby leakage fluids to be conveyed through the second leakage channel away from an area between the sealing means of the piston assembly.3. The launching cylinder as claimed in claim 2 , whereina free end of the piston rod is provided with a first connecting element by means of which the launching ...

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Номер записи: 81
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: 82
26-10-2017 дата публикации

BAFFLED-TUBE RAM ACCELERATOR

Номер: US20170307313A1
Автор: Bruckner Adam P., Hansen Viggo, Higgins Andrew J., Knowlen Carl
Принадлежит:

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 ram accelerator system , the system comprising:a ram accelerator tube with an inner surface and an outer surface;a plurality of baffles disposed on the inner surface of the ram accelerator tube, wherein the plurality of baffles is disposed to form a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube; andan accelerator gun disposed on an input end of the ram accelerator tube, wherein the accelerator gun is positioned to fire a projectile into the ram accelerator tube.2. The ram accelerator system of claim 1 , wherein the plurality of baffles is arranged linearly along the longitudinal axis of the ram accelerator tube.3. The ram accelerator system of claim 1 , wherein the plurality of baffles is arranged into a helix along the longitudinal axis of the ram accelerator tube.4. The ram accelerator system of claim 1 , wherein the ram accelerator tube has an output end opposite the input end claim 1 , and wherein the plurality of baffles is angled toward the output end.5. The ram accelerator system of claim 1 , wherein the ram accelerator tube has an output end opposite the input end claim 1 , and wherein the plurality of baffles is angled toward the input end.6. The ram accelerator system of claim 1 , further comprising a projectile claim 1 , wherein the length of the projectile is greater than the distance between two neighboring baffles in the ram accelerator tube.7. The ram accelerator system of claim 6 , wherein the plurality of baffles in the ram accelerator ...

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Номер записи: 83
08-11-2018 дата публикации

Weapon interface system and delivery platform employing the same

Номер: US20180319498A1
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: 84
03-12-2015 дата публикации

Missile Launcher System

Номер: US20150345900A1
Автор: Bohlmann Thomas E., Flemmings Charles N., Plaia Joseph M., Sisemore Carl L., Wastweet Scott A., Wheater Eric A.
Принадлежит: Chief of Naval Research, Office of Counsel

A missile launcher is provided for ship integration. In particular, the missile launcher affords a simple and safe integration onto a surface, such as a deck of a naval vessel, for example. The missile launcher includes a box launcher to house and launch the missiles and a pedestal to support and orient the box launcher. The box launcher provides protection from the natural environment as well as protection from other threats to the system. The box launcher is designed to enable missiles not normally designed for use in a harsh environment to be used in such an environment. The missile launcher also enables loading of missiles while at sea. The missile launcher can be integrated into naval vessels, land vehicles, fixed locations and other installations, as needed. 1. A missile launch assembly for securing at least one missile within and launching said missile from a corresponding missile canister deployed on a mobile platform , said assembly comprising:a pedestal operable to mount to a surface of the platform; anda launcher box attached to the pedestal, the launcher box providing an environmental seal for the missile canister and the corresponding missile disposed therein.2. The missile launch assembly of claim 1 , further comprising wire rope isolators installed in a shear configuration for securing said launcher box to said pedestal.3. The missile launch assembly of claim 1 , further comprising:a base plate of said launcher box having at least one canister saddle attached thereto, said canister saddle having an indent for receiving the missile canister; anda plurality of upper clamps, each upper clamp independently and removably attaching to said canister saddle to secure the corresponding missile canister thereunder.4. The missile launch assembly of claim 1 , further comprising:an aft plate disposed on an aft end of said launcher box and having an aft end plate hole therethrough, said aft end plate hole aligning with the missile canister; anda forward plate ...

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Номер записи: 85
24-10-2019 дата публикации

FLEXIBLE COVER FOR A MISSILE CONTAINER

Номер: US20190323799A1
Автор: Herquel Pascal, LEROY Bertrand
Принадлежит: MBDA France

A flexible cover includes a main layer made of a first composite material that includes a first woven material and a first elastomer. The flexible cover also includes an auxiliary layer made of a second composite material that includes a second woven material and a second elastomer. The auxiliary layer is secured to a face of the main layer and includes petal-shaped regions that are separated from one another by weakening lines. 1. A flexible cover , configured to be mounted on a missile container and to be pushed open , the flexible cover comprising:a main layer made of a first composite material comprising a first woven material and a first elastomer; andan auxiliary layer made of a second composite material comprising a second woven material and a second elastomer, the auxiliary layer being secured to the main layer, on a first face of the latter, the auxiliary layer comprising petal-shaped regions that are separated from one another by weakening lines, wherein the auxiliary layer is coupled to the main layer by stitches.2. The flexible cover according to claim 1 ,further comprising a second auxiliary layer arranged on a second face of the main layer opposite the first face.3. The flexible cover according to claim 2 ,wherein the first and second auxiliary layers are arranged, with their petal-shaped regions, symmetrically, with respect to a substantially central plane (P) of the main layer.4. The flexible cover according to claim 1 ,wherein at least some of the stitches are arranged along weakening lines.5. The flexible cover according to claim 1 ,wherein at least some of the stitches are arranged transversally to the weakening lines.6. The flexible cover according to claim 1 ,wherein stitches are provided over the entire surface of the petal-shaped regions.7. The flexible cover according to claim 1 ,wherein the weakening lines extend radially from a center portion of the flexible cover.8. The flexible cover according to claim 1 ,wherein at least one of: (1) the ...

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Номер записи: 86
07-11-2019 дата публикации

WEAPON TUBE AND PARTICULARLY TORPEDO TUBE STRUCTURE

Номер: US20190339041A1
Автор: LAMOTTE Arnaud, NIOT Stéphane, RAFFOUX Johan
Принадлежит:

Disclosed is a weapon tube and particularly a torpedo tube structure including a system for holding the weapon in a storage position in the tube, including a clamping mechanism which is connected to the structure and can be moved by an actuator between a closed position for locking an interface part of the weapon in order to lock the weapon in position in the structure and an open position for releasing the interface part and therefore the weapon, the structure includes an elastic unit for soliciting the clamping mechanism in the closed position. 123145662134. A weapon tube , including a weapon () holding system () in the storage position in the tube () , including a clamping mechanism () connected to the structure and movable by actuating means () , between a closed position for blocking an interface part () of the weapon in order to block the latter in position , and an open position for releasing this interface part () and therefore the weapon () , comprising elastic means () for stressing the clamping mechanism () in the closed position.249139. The structure according to claim 1 , wherein the clamping mechanism () includes a closing cylinder () of the clamp and wherein the elastic means () are associated with this cylinder () to push it into the closed position of the mechanism.3139. The structure according to claim 2 , wherein the elastic means comprise a helical spring () placed behind the cylinder () to push the latter.410. The structure according to claim 1 , wherein the actuating means comprise an unlocking lever () that can be manipulated by an operator.5911124. The structure according to claim 2 , wherein the closing cylinder () is associated with a withdrawal chamber () and is connected (at ) to the expulsion of the tube to guarantee the opening of the clamping mechanism () during firing of the weapon.6624. The structure according to claim 1 , wherein the interface part () of the weapon () includes a member fastened thereon and provided with a spherical ...

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Номер записи: 87
29-10-2020 дата публикации

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

Номер: US20200339279A1
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:receiving, by a receiver disposed within a launcher volume of a launcher, wireless communication via one or more RF signals received 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 radio-frequency (RF) permeable material; andcommanding, by the launcher, an unmanned aerial vehicle (UAV) disposed within the launcher volume to enter a standby mode while remaining responsive to received RF signal commands for a full power-up, thereby providing a self-contained launcher-UAV configured to be deployed and left at a prospective launch site for a protracted period of time.2. The method of claim 1 , wherein the self-contained launcher-UAV is configured to be powered up and launched responsive to one or more command signals from an offsite node.3. ...

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Номер записи: 88
06-12-2018 дата публикации

MISSILE CABLE CUTTING SYSTEM

Номер: US20180347942A1
Автор: BAE Minji, KIM Jonghwan, KIM Sanghwa, LEE HaJun
Принадлежит:

A missile cable cutting system includes a tubular housing opened at one end and allowing a missile to be loaded therein, a cable housing fixed to and installed on one surface of the tubular housing and accommodating an umbilical cable protruding from the inside of the missile, a fixing plate installed in the cable housing and allowing the umbilical cable to be inserted between the fixing plate and the cable housing, and a cable cutter installed to be adjacent to the umbilical cable and cutting one side of the umbilical cable when the missile is fired and moved in a traveling direction. 1. A missile cable cutting system comprising:a tubular housing opened at one end and allowing a missile to be loaded therein;a cable housing fixed to and installed on one surface of the tubular housing and accommodating an umbilical cable protruding from the inside of the missile;a fixing plate installed in the cable housing and allowing the umbilical cable to be inserted between the fixing plate and the cable housing; anda cable cutter installed to be adjacent to the umbilical cable and cutting one side of the umbilical cable when the missile is fired and moved in a traveling direction.2. The missile cable cutting system of claim 1 , whereinthe cable housing includes:a first member extending in an outward direction of the tubular housing; anda second member extending from one end of the first member in the traveling direction of the missile along the tubular housing to intersect the extending direction of the first member.3. The missile cable cutting system of claim 2 , whereinthe umbilical cable and the fixing plate are positioned in a mounting portion formed by the first member and the second member.4. The missile cable cutting system of claim 1 , whereina first groove portion is formed in the cable housing such that the fixing plate is slidably inserted and drawn out.5. The missile cable cutting system of claim 4 , whereina second groove portion is formed below the first groove ...

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Номер записи: 89
29-10-2020 дата публикации

Subterranean Well Thrust-Propelled Torpedo Deployment System and Method

Номер: US20200340781A1
Автор: Bouldin Brett, Jervis Michael
Принадлежит:

Provided in some embodiments is a method of deploying a payload in a subterranean well. The method including advancing a torpedo in a first portion of a wellbore of a subterranean well (the torpedo including a body, a fiber-optic (FO) umbilical that is physically coupled to a surface component, and adapted to unspool from the torpedo as the torpedo advances in the wellbore, and an engine adapted to generate thrust to propel the torpedo), and activating the engine to generate thrust to propel advancement of the torpedo within a second portion of the wellbore such that the FO umbilical is disposed in the second portion of the wellbore. 1. A method of deploying a payload in a subterranean well , the method comprising: a body;', 'a fiber-optic (FO) umbilical that is physically coupled to a surface component, configured to unspool from the torpedo as the torpedo advances in the wellbore, and configured to facilitate communication between the torpedo and a well control system; and', 'an engine configured to generate thrust to propel advancement of the torpedo in the wellbore;, 'releasing a torpedo into gravity-driven advancement within a first portion of a wellbore of a subterranean well, the torpedo comprisingdetermining that the torpedo has reached a trigger point within the wellbore; andactivating, in response to determining that the torpedo has reached the trigger point within the wellbore, the engine to generate forward thrust to propel the torpedo within a second portion of the wellbore such that the FO umbilical is disposed in the second portion of the wellbore, and the torpedo comes to rest in a deployment location within the wellbore.2. A method of deploying a fiber-optic payload in a subterranean well , the method comprising: a body;', 'a fiber-optic (FO) umbilical that is physically coupled to a surface component, and configured to unspool from the torpedo as the torpedo advances in the wellbore; and', 'an engine configured to generate thrust to propel the ...

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Номер записи: 90
14-11-2019 дата публикации

LAUNCHING ARRANGEMENT FOR A MISSILE FOR INTERCEPTING ALIEN DRONES

Номер: US20190346241A1
Автор: METZ Franco, METZ Manuel
Принадлежит:

The invention relates to a launching arrangement () for a missile () for intercepting alien drones, wherein the launching arrangement () comprises a launch container () with an opening (), wherein the missile () is or can be arranged within the launch container (). 1291293031130161. Launching arrangement () for a missile () for intercepting alien drones , wherein the launching arrangement () comprises a launch container () with an opening () , wherein the missile () is or can be arranged within the launch container () , characterised in that the missile () comprises a propeller drive () in a bow area of the missile ().2303231303237373732130. Launching arrangement according to the preceding claim , characterised in that the launch container () is fitted with a cover () closing the opening () , wherein the launch container () and the cover () are connected to one another via an actuatable closing mechanism () , wherein when the closing mechanism () is actuated , the closing mechanism () releases the cover () and the missile () can leave the launch container ().33713932371. Launching arrangement according to any one of the preceding claims , characterised in that the closing mechanism () is coupled to on-board electronics of the missile () via a connecting line () , wherein a signal to open the cover () can be sent to the closing mechanism () via the on-board electronics of the missile ().43034134. Launching arrangement according to any one of the preceding claims , characterised in that the launch container () comprises at least one , in particular a plurality of guide elements () , wherein the missile () is guided by the guide elements ().529404037. Launching arrangement according to any one of the preceding claims , characterised in that the launching arrangement () comprises a power supply () , wherein the power supply () feeds the electrically actuatable closing mechanism ().61219181599159151. Launching arrangement according to any one of the preceding claims , ...

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Номер записи: 91
31-12-2015 дата публикации

STOWABLE EFFECTOR LAUNCH SYSTEM

Номер: US20150377586A1
Автор: Anderson Chad V., Gin Brian A., JR. Charles E., Kurtis James M., MORGAN, Szlemko Emile M.
Принадлежит:

An effector launch system includes a stowable effector launcher housing having a housing panel configured for coupling with a vehicle, and one or more receptacle brackets movably coupled with the housing panel. The one or more receptacle brackets include one or more effector launcher sockets. The launch system further includes one or more effector launchers. Each effector launcher includes an effector received within an adapter housing. The stowable effector launcher housing is movable between deployed and stowed configurations. In the deployed configuration the one or more receptacle brackets extend from the housing panel and the one or more effector launchers are received within the one or more effector launcher sockets. In the stowed configuration the one or more effector launchers are removed from the one or more effector launcher sockets and the one or more receptacle brackets are stowed along the housing panel. 1. An effector launch system comprising: a housing panel configured for coupling with a vehicle, and', 'one or more receptacle brackets movably coupled with the housing panel, the one or more receptacle brackets including one or more effector launcher sockets;, 'a stowable effector launcher housing includingone or more effector launchers, each effector launcher includes an effector received within an adapter housing; and in the deployed configuration the one or more receptacle brackets extend from the housing panel and the one or more effector launchers are received within the one or more effector launcher sockets, and', 'in the stowed configuration the one or more effector launchers are removed from the one or more effector launcher sockets and the one or more receptacle brackets are stowed along the housing panel., 'wherein the stowable effector launcher housing is movable between a deployed configuration and a stowed configuration2. The effector launch system of claim 1 , wherein in the stowed configuration the one or more effector launcher sockets ...

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Номер записи: 92
22-12-2016 дата публикации

LAUNCHING APPARATUS FOR UNDERWATER PAYLOAD

Номер: US20160372999A1
Автор: MATSUI Hiroyoshi
Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

Provided is a launching apparatus capable of efficiently obtaining water pressure sufficient for launching an underwater payload, including a launch tube, a conduit including a first end portion and a communicating portion communicating with the launch tube, a plurality of conduit coils to axially aligned in a first region between the first end portion and the communicating portion, a plurality of main circuits passing an electric current through respective conduit coils, and a main-circuit control section. The main-circuit control section controls operation of the main circuits to pass electric currents through the conduit coils to generate an axial first magnetic field in the conduit and thereby cause an axial second magnetic field in a moving object, thereby moving the moving object in an advance direction toward a second end portion. 1. An apparatus for launching an underwater payload with water pressure , the launching apparatus for underwater payloads comprising:a launch tube in which an underwater payload is loaded;a conduit including a first end portion, which is one of axially opposite ends, and a communicating portion located in a position separate from the first end portion and communicating with the launch tube, the conduit being filled with water;a plurality of conduit coils disposed around the conduit in a first region between the communicating portion and the first end portion, the plurality of conduit coils aligned axially of the conduit;a plurality of main circuits configured to pass an electric current through the conduit coils, respectively, so as to generate an axial first magnetic field in the conduit;a main-circuit control section configured to control an operation of each of the plurality of main circuits; anda moving object disposed in the conduit and including a magnetic material or an induction coil, the moving object being configured to move in the conduit in an advance direction from the first end portion toward the communicating portion ...

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Номер записи: 93
21-11-2019 дата публикации

LAUNCHER DEVICE AND LAUNCHER BATTERY

Номер: US20190353453A1
Автор: Bittner Markus, LEIDENBERGER THOMAS
Принадлежит:

A launcher device for launching ammunition or weapons provided with primers, contains a plurality of launch tubes combined so as to form a launcher battery. Each of the launch tubes is loaded with ammunition or a weapon, and each of the launch tubes is closed off by a cover. A device is provided for detecting damage to the covers closing off the launch tubes. 1. A launcher device for launching ammunition or weapons provided with primers , the launcher device comprising:covers;a plurality of launch tubes combined so as to form a launcher battery, each of said launch tubes is loaded with the ammunition or a weapon, and each of said launch tubes is closed off by one of said covers; anda detector for detecting damage to said covers closing off said launch tubes.2. The launcher device according to claim 1 , wherein said detector is configured to detect an incidence of light into a respective one of said launch tubes resulting from damage to one of said covers.3. The launcher device according to claim 2 ,further comprising a control and/or display device disposed external to said launch tubes; andwherein said detector has sensor elements for detecting the incidence of light, at least one of said sensor elements is disposed in each of said launch tubes, said sensor elements communicate with said control and/or display device.4. The launcher device according to claim 2 ,further comprising a control and/or display device disposed external to said launch tubes;wherein said detector has sensor elements for detecting the incidence of light, at least one of said sensor elements is disposed in each of said launch tubes; andfurther comprising optical waveguides, one of said optical waveguides is disposed or inserted in each of said launch tubes, said optical waveguide is connected to said at least one sensor element for detecting the incidence of light, said at least one sensor element communicates with said control and/or display device.5. The launcher device according to claim 4 ...

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Номер записи: 94
20-12-2018 дата публикации

SYSTEMS AND TECHNIQUES FOR LAUNCHING A PAYLOAD

Номер: US20180362191A1
Автор: Russell Mark C.
Принадлежит:

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile. 1. A start gun system for accelerating a projectile to ram speed comprising: a start tube configured to selectively inject a pressurant;', 'a control system configured to control staged injection of the pressurant along the start tube; and, 'a distributed injection system comprisinga movable diaphragm configured to increase the relative velocity of the projectile in a medium.2. The start gun system of claim 1 , wherein the movable diaphragm is configured to move towards the projectile through the start tube.3. The start gun system of claim 1 , wherein the selective injection of the pressurant comprises injection into the start gun tube through one or more of gas baffles claim 1 , high speed valves claim 1 , or diaphragms.4. The start gun system of claim 1 , further comprising an onsite distribution system configured to claim 1 , upon request of a user claim 1 , select and load into the start gun system a projectile claim 1 , and launch the selected and loaded projectile.5. The start gun system of claim 1 , further comprising a ram accelerator coupled to the distributed injection system and the moveable diaphragm claim 1 , wherein the ram accelerator is disposed in an underground facility claim 1 , a floating system claim 1 , or a flying vehicle.6. A multiple projectile launch system comprising:a plurality of launch mechanisms configured to accelerate a respective projectile each;a first control system configured to coordinate the acceleration of the respective projectiles in the respective plurality of ...

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Номер записи: 95
29-12-2016 дата публикации

Launch system for a guided missile and a guided missile for such a launch system

Номер: US20160377375A1
Автор: Jörg Lutzenberger, Stefan Lehmann
Принадлежит: MBDA Deutschland GmbH

The present embodiment relates to a guided missile launch system comprising a launch tube with a guided missile space for receiving a guided missile and with a cartridge space for receiving a blank cartridge, further comprising a handle piece mountable on the launch tube and separable from the launch tube, the handle piece having a striking pin system for firing the blank cartridge.

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Номер записи: 96
12-11-2020 дата публикации

SYSTEM AND APPARATUS FOR LAUNCHING A MISSILE

Номер: US20200355465A1
Автор: GERNERT Heribert, MAYER Anja
Принадлежит: MBDA Deutschland GmbH

A launch apparatus for launching a missile includes a launching tube extending in a longitudinal direction. The launching tube has an outlet opening at a first end. An acceleration device arranged in the region of a second end of the launching tube includes a gas generator to generate a gas mass flow, and a bag formed from a textile fabric. The bag is coupled to a diffuser of the gas generator via an end opening and inflates longitudinally by the gas mass flow generated by the gas generator to accelerate the missile. The bag has a gas permeability within a range of between 10 l dmminand 30 l dmmin. When inflated, a cross section of the bag alternatively or additionally tapers from the end opening to a minimal cross section along the longitudinal direction and increases in size to an end opposite the end opening. 11. Launch apparatus () for launching a missile (F) , having:{'b': 10', '11', '10, 'a launching tube () extending in a longitudinal direction (L) for accommodating the missile (F), which launching tube has an outlet opening () at a first end (A); and'}{'b': 2', '10', '10', '20', '21', '22', '20', '21', '20', '21, 'sup': −2', '−1', '−2', '−1, 'an acceleration device () that is arranged in the region of a second end (B) of the launching tube () and has a gas generator () that can be activated to generate a gas mass flow, and a bag () formed from a textile fabric, which bag is coupled to a diffuser () of the gas generator () via an end opening (A) and can be inflated along the longitudinal direction (L) by the gas mass flow that can be generated by means of the gas generator () to accelerate the missile (F), the bag () being gas permeable within a range of between 10 l dmminand 301 dmmin.'}2121. Launch apparatus () according to claim 1 , characterised in that the textile fabric of the bag () defines the gas permeability within a range of between 10 l dmminand 30 l dmmin.312123. Launch apparatus () according to claim 1 , characterised in that the bag () has one ...

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Номер записи: 97
19-11-2020 дата публикации

Multi-Mission Munition Adapter

Номер: US20200363159A1
Автор: Brindle Doug
Принадлежит:

A multi-mission munition adapter for an aircraft may be configured to attach to a hardpoint and hold a plurality of munitions, such as missiles and bombs. A top of the multi-mission munition adapter may have suspension lugs configured to attach to a hardpoint on an aircraft. Sides of the multi-mission munition adapter may have one or more launcher attachment fittings configured to attach missile launchers. A bottom of the multi-mission munition adapter may have one or more munitions ejector hangers configured to attach air-to-ground munitions ejectors. The adapter may comprise an electrical system that permits an aircraft to communicate with and/or power all functions of the bomb rack, missile launchers, and the weapons employed. 1. A multi-mission munition adapter , comprising:a main body;a first missile launcher attachment fitting on a left side of the main body;a second missile launcher attachment fitting on a right side of the main body;at least one pair of hangers on a bottom side of the main body and configured to receive a munitions ejector; anda smart weapons interface connector, on the bottom side of the main body, configured to be connected to the munitions ejector via a cable.2. The multi-mission munition adapter of claim 1 , wherein the smart weapons interface connector is configured to receive a break-away connector.3. The multi-mission munition adapter of claim 1 , further comprising:one or more aircraft suspension lugs attached to the main body, wherein the main body is configured to be attached, via the one or more aircraft suspension lugs, to one or more aircraft hardpoints.4. The multi-mission munition adapter of claim 3 , wherein the one or more aircraft suspension lugs are sized to hold a weight of at least twelve thousand pounds.5. The multi-mission munition adapter of claim 1 , further comprising:at least one electrical connector on the main body, wherein the at least one electrical connector is on a top side of the main body.6. The multi- ...

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Номер записи: 98
10-12-2020 дата публикации

MUNITIONS INTERFACE ADAPTER

Номер: US20200386515A1
Автор: Cantine Christopher Hugh, Kemp Steven L., Pfund Robert P.
Принадлежит:

A munitions interface adapter including a rail adapter body. A plurality of mounting shoes may be coupled to the rail adapter body, and configured to mechanically couple the rail adapter body to a munitions rail of an installed munitions interface. A fire control connector may be configured to communicatively couple with an installed munitions fire control system. An adapter control interface may be included for adapting fire control signals from the installed munitions fire control system to an adapted munitions fire control signals. One or more adapted munitions deployment fixtures may be positioned on the rail adapter body. The one or more adapted munitions deployment fixtures are configured to retain and deploy one or more adapted munitions. 1. A munitions interface adapter comprising:a rail adapter body;a plurality of mounting shoes coupled to the rail adapter body, and configured to mechanically couple the rail adapter body to a munitions rail of an installed munitions interface;a fire control connector configured to communicatively couple with an installed munitions fire control system;an adapter control interface for adapting fire control signals from the installed munitions fire control system to an adapted munitions fire control signals; andone or more adapted munitions deployment fixtures positioned on the rail adapter body, the one or more adapted munitions deployment fixtures configured to retain and deploy one or more adapted munitions.2. The munitions interface adapter according to claim 1 , wherein the installed munitions interface includes an AGM-114 guided missile interface.3. The munitions interface adapter according to claim 2 , wherein the installed munitions interface includes one or more of ah M299 launcher and an M310 launcher.4. The munitions interface adapter according to claim 1 , wherein the plurality of mounting shoes are configured to slidingly receive the rail adapter body on a rail system of the installed munitions interface.51. The ...

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Номер записи: 99
20-05-2013 дата публикации

Device and method to retain shell in weapon barrel charged from breech

Номер: RU2482418C2
Автор: Кари РЕУНАМЯКИ, Пекка НИЕМИ
Принадлежит: Патриа Лэнд Энд Армамент Оу

FIELD: weapons and ammunition. SUBSTANCE: method to retain a shell in a weapon barrel is carried out due to a device for retention of a shell (1) in a weapon barrel charged from a breech of a weapon, comprising a support unit (4), equipped with a board edge (15). The support unit (4) is fixed on a tail assembly of the shell (1) with the help of one or more adhesive materials. EFFECT: improved retention of a shell in a mortar barrel. 18 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 482 418 (13) C2 (51) МПК F41F 1/06 (2006.01) F42B 30/10 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010135800/11, 30.01.2009 (24) Дата начала отсчета срока действия патента: 30.01.2009 (72) Автор(ы): РЕУНАМЯКИ Кари (FI), НИЕМИ Пекка (FI) (73) Патентообладатель(и): ПАТРИА ЛЭНД ЭНД АРМАМЕНТ ОУ (FI) R U Приоритет(ы): (30) Конвенционный приоритет: 31.01.2008 FI 20085075 (43) Дата публикации заявки: 10.03.2012 Бюл. № 7 2 4 8 2 4 1 8 (45) Опубликовано: 20.05.2013 Бюл. № 14 (56) Список документов, цитированных в отчете о поиске: RU 2178138 С2, 10.01.2002. US 4763577 А, 16.08.1988. GB 2105813 А, 30.03.1983. RU 2282136 С2, 20.08.2006. GB 2251290 А, 01.07.1992. 2 4 8 2 4 1 8 R U (86) Заявка PCT: FI 2009/050081 (30.01.2009) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 31.08.2010 (87) Публикация заявки РСТ: WO 2009/095543 (06.08.2009) Адрес для переписки: 119146, Москва, а/я 33, И.В. Журавлевой (54) УСТРОЙСТВО И СПОСОБ ДЛЯ УДЕРЖАНИЯ СНАРЯДА В СТВОЛЕ ОРУДИЯ, ЗАРЯЖАЕМОГО С КАЗЕННОЙ ЧАСТИ (57) Реферат: Изобретения относятся к способу и устройству для удержания снаряда в стволе орудия. Способ удержания снаряда в стволе орудия осуществляется за счет устройства для удержания снаряда (1) в стволе орудия, заряжаемого с казенной части орудия, содержащего опорный узел (4), снабженный бортовой кромкой (15). Опорный узел (4) закреплен на хвостовом оперении снаряда (1) при помощи одного или более клейких материалов. ...

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Номер записи: 100