Многоступенчатая ракета и головной способ отделения отработанных частей

Изобретение относится к ракетной технике и, в частности, к многоступенчатым ракетам. Технический результат – повышение эффективности работы устройства за счет замены действующих ракетных двигателей в процессе полета с отделением отработавших топливных баков без отделения ракетных двигателей. Многоступенчатая ракета содержит корпус с головным обтекателем, за которым последовательно расположены вдоль продольной оси ракеты дополнительный топливный отсек с возможностью его отделения от ракеты, оснащенный дополнительными топливными баками, отсек для полезного груза, топливные баки, связанные с ракетными двигателями. Дополнительный топливный отсек разделен на сегменты с возможностью отделения каждого сегмента от ракеты, с поворотом на расчетный угол относительно оси ракеты и со скоростью, исключающими повреждение ракеты. Сегменты размещены один над другим по продольной оси ракеты. В каждом из сегментов размещены топливные баки и головной обтекатель с устройством, обеспечивающим возможность глушения топливного трубопровода и его разъединения. К ракетным двигателям по продольной и/или поперечной оси ракеты примыкает по меньшей мере одна разгонная отделяемая ступень. Она содержит топливные баки и ракетные двигатели с возможностью потреблять топливо из определенных топливных баков по топливному трубопроводу посредством открытия и закрытия соответствующих клапанов. 2 н. и 7 з.п. ф-лы, 4 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 693 093 C2 (51) МПК F42B 15/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F42B 15/12 (2019.02); F42B 15/12 (2019.02) (21)(22) Заявка: 2017146502, 27.12.2017 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Степанян Ревик Артурович (BY) Дата регистрации: 01.07.2019 (56) Список документов, цитированных в отчете о поиске: RU 2406660 C1, 20.12.2010. RU 06.10.2017 BY A20170377 (43) Дата публикации заявки: 27.06.2019 Бюл. № 18 2532321 С2, 10.11.2014. RU 2149125 С1, ...

Patent RU2017146502A3

ВУ” 2017146502'” АЗ Дата публикации: 17.07.2019 Форма № 18 ИЗ,ПМ-2011 Федеральная служба по интеллектуальной собственности Федеральное государственное бюджетное учреждение ж Я «Федеральный институт промышленной собственности» (ФИПС) ОТЧЕТ О ПОИСКЕ 1. . ИДЕНТИФИКАЦИЯ ЗАЯВКИ Регистрационный номер Дата подачи 2017146502/03(079507) 27.12.2017 Приоритет установлен по дате: [ ] подачи заявки [ ] поступления дополнительных материалов от к ранее поданной заявке № [ ] приоритета по первоначальной заявке № из которой данная заявка выделена [ ] подачи первоначальной заявки № из которой данная заявка выделена [ ] подачи ранее поданной заявки № [Х] подачи первой(ых) заявки(ок) в государстве-участнике Парижской конвенции (31) Номер первой(ых) заявки(ок) (32) Дата подачи первой(ых) заявки(ок) (33) Код страны 1. А20170377 06.10.2017 ВУ Название изобретения (полезной модели): [Х] - как заявлено; [ ] - уточненное (см. Примечания) Многоступенчатая ракета и головной способ отделения отработанных частей Заявитель: Степанян Ревик Артурович, ВУ 2. ЕДИНСТВО ИЗОБРЕТЕНИЯ [Х] соблюдено [ ] не соблюдено. Пояснения: см. Примечания 3. ФОРМУЛА ИЗОБРЕТЕНИЯ: [Х] приняты во внимание все пункты (см. Примечания) [ ] приняты во внимание следующие пункты: [ ] принята во внимание измененная формула изобретения (см. Примечания) 4. КЛАССИФИКАЦИЯ ОБЪЕКТА ИЗОБРЕТЕНИЯ (ПОЛЕЗНОЙ МОДЕЛИ) (Указываются индексы МПК и индикатор текущей версии) Е42В 15/12 (2006.01) 5. ОБЛАСТЬ ПОИСКА 5.1 Проверенный минимум документации РСТ (указывается индексами МПК) Е42В 15/00-15/12, В64С 1/00-1/40 5.2 Другая проверенная документация в той мере, в какой она включена в поисковые подборки: 5.3 Электронные базы данных, использованные при поиске (название базы, и если, возможно, поисковые термины): РУРТ ЕАРАТГУ, Ебрасепе, РАТЕМТЗСОРЕ, Рабеагсв, КОРТО, ОЗРТО 6 ДОКУМЕНТЫ, ОТНОСЯЩИЕСЯ К ПРЕДМЕТУ ПОИСКА Кате- Наименование документа с указанием (где необходимо) частей, Относится к гория* относящихся к предмету поиска пункту формулы № 1 2 3 ...

Двухступенчатая ракета

Полезная модель относится к ракетной технике, в частности к двухступенчатым ракетам, и может быть использована в ракетостроении.Задачей данной полезной модели является создание возможности отделения отработавших конструктивных частей двухступенчатой ракеты в слоях атмосферы и за ее пределами, с максимальным ускорением, без отделения жидкостных ракетных двигателей. Что в свою очередь расширит сферу ее применения, а также даст возможность: более быстрого набора скорости относительно прототипа; увеличить дальность полета ракеты и массу полезного груза относительно ракеты, по отношению к прототипу.Поставленная задача достигается тем, что двухступенчатая содержащая корпус, головной обтекатель, после которого последовательно расположены относительно продольной оси дополнительный топливный отсек с возможностью его отделения от ракеты, оснащенный дополнительными топливными баками; отсек для полезного груза; топливные баки, связанные с ракетными двигателями, причем все топливные баки соединены трубопроводами ...

Launch vehicle and system and method for economically efficient launch thereof

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) 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 (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

STARTING SYSTEM AND METHOD OF STARTING USEFUL LOAD

ВЫСОКОСКОРОСТНОЙ ЛЕТАТЕЛЬНЫЙ АППАРАТ

Изобретение относится к ракетной технике. Высокоскоростной летательный аппарат содержит корпус, выполненный в виде силовой оболочки и теплозащитного покрытия, бортовые системы и полезную нагрузку. Корпус выполнен в виде отсеков, жестко скрепленных между собой. В одном из отсеков расположена полезная нагрузка, занимающая все его свободное пространство. Силовая оболочка отсека корпуса высокоскоростного летательного аппарата является корпусом полезной нагрузки. Изобретение направлено на уменьшение массы. 1 з.п. ф-лы.

IS LAUNCHED BY THE AIRCRAFT, STARTING SYSTEM AND METHOD ECONOMICALLY EFFECTIVE STARTING

Launch vehicle and system and method for economically efficient launch thereof

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.

Многоступенчатая ракета и способ отделения отработанных частей

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2017 146 498 A (51) МПК F42B 15/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2017146498, 27.12.2017 (71) Заявитель(и): Степанян Ревик Артурович (BY) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): Степанян Ревик Артурович (BY) 11.08.2017 BY A20170298 Адрес для переписки: 220100, Белоруссия, г. Минск, ул. Цнянская, 17, кв. 36, Степанян Р.А. Стр.: 1 A 2 0 1 7 1 4 6 4 9 8 R U A (57) Формула изобретения 1. Многоступенчатая ракета, содержащая основной разгонный блок, который представлен корпусом, головным обтекателем, после которого последовательно расположены относительно продольной оси, отсек для полезного груза, топливные баки, связанные с ракетными двигателями основного разгонного блока, причем ракета содержит дополнительные разгонные блоки, представленные дополнительными топливными отсеками, которые соединены с корпусом жесткой связью поперечно продольной оси ракеты, с возможностью их отделения, отличается тем, что дополнительные топливные отсеки разделены на сегменты с возможностью отделения каждого сегмента от ракеты, сегменты размещены один над другим, причем топливные баки размещены в каждом сегменте, верхняя сторона каждого сегмента, является головным обтекателем или содержит головной обтекатель. 2. Многоступенчатая ракета по п. 1, отличающаяся тем, что дополнительные топливные отсеки, содержат ракетные двигатели. 3. Многоступенчатая ракета по п. 1, отличающаяся тем, что некоторые сегменты содержат топливные баки только с окислителем. 4. Многоступенчатая ракета по п. 1, отличающаяся тем, что между сегментами установлена опорная поверхность вышележащего сегмента, содержит по меньшей мере одну точечную связь с вышележащим сегментном, причем опорная поверхность так же имеет жесткую связь с нижележащем сегментом и/или корпусом ракеты с возможностью отделения. 5. Многоступенчатая ракета по п. 1, отличающаяся тем, что головной обтекатель по меньшей мере ...

Многоступенчатая ракета и способ отделения отработанных частей

FIELD: astronautics. SUBSTANCE: invention relates to rocket engineering and particularly to multi-stage rockets and can be used in rocket engineering. Proposed device comprises main acceleration unit represented by case and head fairing. Afterwards, compartment for payload, fuel tanks connected with rocket engines of the main booster unit are arranged in series relative to lengthwise axis. Rocket comprises additional fuel compartments. They are made with possibility of their separation from the main booster unit. At that, additional fuel compartments are divided into segments so that they are arranged one above another along longitudinal axis. In each segment there are fuel tanks. Upper side of each segment is head fairing or comprises head fairing. Every segment is separated from the farthest segment relative to rocket engines of the main booster unit. This is ensured by the possibility of segments displacement during rocket flight at a given angle relative to rocket axis at the speed providing safe rocket flight. EFFECT: technical result is increase in fuel margin due to additional separated fuel tanks without increasing rocket diameter and without adding rocket engines. 12 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 693 122 C2 (51) МПК F42B 15/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F42B 15/12 (2019.02) (21)(22) Заявка: 2017146498, 27.12.2017 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Степанян Ревик Артурович (BY) Дата регистрации: 01.07.2019 (56) Список документов, цитированных в отчете о поиске: ГРАБИН Б. В. и др., Основы 11.08.2017 BY A20170298 (43) Дата публикации заявки: 27.06.2019 Бюл. № 18 (45) Опубликовано: 01.07.2019 Бюл. № 19 конструирования ракет-носителей космических аппаратов, Москва, Машиностроение, 1991, с 14. RU 2406660 C1, 20.12.2010. RU 2149125 С1, 20.05.2000. RU 2331550 С1, 20.08.2008. US 6612522 B1, 02.09.2003. US 6622971 B1, 23.09. ...

Patent RU2017146498A3

7 ВУ"? 2017146498” АЗ Дата публикации: 17.07.2019 Форма № 18 ИЗ,ПМ-2011 Федеральная служба по интеллектуальной собственности Федеральное государственное бюджетное учреждение ж Я «Федеральный институт промышленной собственности» (ФИПС) ОТЧЕТ О ПОИСКЕ 1. . ИДЕНТИФИКАЦИЯ ЗАЯВКИ Регистрационный номер Дата подачи 2017146498/03(07950Т) 27.12.2017 Приоритет установлен по дате: [ ] подачи заявки [ ] поступления дополнительных материалов от к ранее поданной заявке № [ ] приоритета по первоначальной заявке № из которой данная заявка выделена [ ] подачи первоначальной заявки № из которой данная заявка выделена [ ] подачи ранее поданной заявки № [Х] подачи первой(ых) заявки(ок) в государстве-участнике Парижской конвенции (31) Номер первой(ых) заявки(ок) (32) Дата подачи первой(ых) заявки(ок) (33) Код страны 1. А20170298 11.08.2017 ВУ Название изобретения (полезной модели): [Х] - как заявлено; [ ] - уточненное (см. Примечания) Многоступенчатая ракета и способ отделения отработанных частей Заявитель: Степанян Ревик Артурович, ВУ 2. ЕДИНСТВО ИЗОБРЕТЕНИЯ [Х] соблюдено [ ] не соблюдено. Пояснения: см. Примечания 3. ФОРМУЛА ИЗОБРЕТЕНИЯ: [Х] приняты во внимание все пункты (см. Примечания) [ ] приняты во внимание следующие пункты: [ ] принята во внимание измененная формула изобретения (см. Примечания) 4. КЛАССИФИКАЦИЯ ОБЪЕКТА ИЗОБРЕТЕНИЯ (ПОЛЕЗНОЙ МОДЕЛИ) (Указываются индексы МПК и индикатор текущей версии) Е42В 15/12 (2006.01) 5. ОБЛАСТЬ ПОИСКА 5.1 Проверенный минимум документации РСТ (указывается индексами МПК) Е42В 15/00-15/12, В64С 1/00-1/40 5.2 Другая проверенная документация в той мере, в какой она включена в поисковые подборки: 5.3 Электронные базы данных, использованные при поиске (название базы, и если, возможно, поисковые термины): РУРТ ЕАРАТГУ, Ебрасепе, РАТЕМТЗСОРЕ, Рабеагсв, КОРТО, ОЗРТО 6 ДОКУМЕНТЫ, ОТНОСЯЩИЕСЯ К ПРЕДМЕТУ ПОИСКА Кате- Наименование документа с указанием (где необходимо) частей, Относится к гория* относящихся к предмету поиска пункту формулы № 1 2 3 А ...

Многоступенчатая ракета и головной способ отделения отработанных частей

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2017 146 502 A (51) МПК F42B 15/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2017146502, 27.12.2017 (71) Заявитель(и): Степанян Ревик Артурович (BY) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): Степанян Ревик Артурович (BY) 06.10.2017 BY A20170377 Адрес для переписки: 220100, Белоруссия, г. Минск, ул. Цнянская, 17, кв. 36, Степанян Р.А. Стр.: 1 A 2 0 1 7 1 4 6 5 0 2 R U A (57) Формула изобретения 1. Многоступенчатая ракета, содержащая корпус с головным обтекателем, за которым последовательно расположены вдоль продольной оси ракеты дополнительный топливный отсек с возможностью его отделения от ракеты, оснащенный дополнительными топливными баками, отсек для полезного груза, топливные баки, связанные с ракетными двигателями, отличающаяся тем, что дополнительный топливный отсек разделен на сегменты с возможностью отделения каждого сегмента от ракеты, сегменты размещены один над другим вдоль продольной оси ракеты, а в каждом сегменте размещены топливные баки, причем продольно и/или поперечно продольной оси ракеты закреплена по меньшей мере одна разгонная отделяемая ступень, содержащая топливные баки и ракетные двигатели с возможностью потреблять топливо из сегментов по трубопроводу посредством открытия и закрытия соответствующих клапанов. 2. Многоступенчатая ракета по п. 1, отличающаяся тем, что по меньшей мере одни ракетные двигатели выполнены составными, с возможностью отделения части ракетных двигателей. 4. Многоступенчатая ракета по п. 1, отличающаяся тем, что по меньшей мере одни ракетные двигатели выполнены с возможностью изменения степени расширения сопла. 5. Многоступенчатая ракета по п. 1, отличающаяся тем, что верхняя сторона отсека для полезного груза и/или верхняя сторона по меньшей мере одного сегмента выполняет функцию головного обтекателя или содержит головной обтекатель. 6. Многоступенчатая ракета по п. 1, отличающаяся тем, что на внешней ...

Non-explosive target directed reentry projectile

The non-explosive core of a reentry projectile is fixedly positioned within a hollow casing of the projectile at a location maximizing conversion and transfer of kinetic energy to an earth bound target in response to the projectile's impact at a hypersonic velocity and at a steep impact angle to the surface of the earth. The hollow casing is formed of a material capable of withstanding high temperatures, therefore, not requiring any cooling and allowing for the hollow casing to be free of heat transfer medium that might otherwise impede the desired quick release of the core upon impact of the projectile. The core is in the form of a single dense metallic slug having a mass establishing a center of gravity and moments of inertia for the projectile as a kinetic energy warhead corresponding to that of an explosive or nuclear warhead without weapon system modification.

МНОГОСТУПЕНЧАТАЯ РАКЕТА И СПОСОБ ОТДЕЛЕНИЯ ОТРАБОТАННЫХ ЧАСТЕЙ

FIELD: rocketry.SUBSTANCE: invention relates to a multistage rocket and a method for separating spent parts. The creation of multistage missiles with a minimum mass of a light class and a relatively increased value of the payload is an important task. The multistage rocket contains the main booster block, which is represented by a body and a nose fairing. After the nose fairing, the payload compartment, the main fuel tanks, the turbopump assemblies of the liquid propellant rocket engines of the main upper stage, connected with the main fuel tanks, are sequentially located relative to the longitudinal axis. The rocket also contains additional fuel compartments. These compartments are made with the possibility of their attachment by means of controllable detachment units on the main fuel tanks and separation from the main upper stage, and are equipped with a pressurization system and lines. These lines connect additional fuel compartments with the main fuel tanks and are made in the form of pipelines with start-off valves and transfer pumps with drives installed in series on them. The main fuel tanks are connected to additional fuel compartments with the possibility of replacing propellants in the main fuel tanks, as they are depleted, with propellants from additional fuel compartments when the liquid propellant rocket engine is operating. With the complete depletion of fuel components from additional fuel compartments, their separation and separation of stages from the rocket, it is possible not to disturb the regime and the continuity of operation of the liquid-propellant rocket engine due to the depletion of fuel components from the main fuel tank.EFFECT: ensured continuity of the operating parameters of the multifunctional liquid-propellant rocket engine at all stages of the multistage rocket operation, both as part of the first stage and as part of subsequent stages.6 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 748 344 C1 (51) МПК F42B 15/12 (2006.01) B64G ...

Launch vehicle and system and method for economically efficient launch thereof

The present disclosure relates to a launch system, and methods of launching a 5 payload utilizing 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 system can comprise: 1) a launch tube comprising a plurality of conductive layers separated by one or more insulating layers and being configured for transmission of energy therethrough; and 2) an electrical energy source; wherein 10 the launch tube is configured for propulsion of a launch vehicle therethrough, and the launch system is configured to be electroantimagnetic. An electrical energy source also can be provided. 11809219_1 (GHMatters) P101112.AU.2 20250 11013 1020 100 -135 113a / 230130 210 xx 115 220 240 260 113b 112 ...

Launch vehicle and system and method for economically efficient launch thereof

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 5 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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust 10 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 also can be provided. 9406720_1 (GHMatters) P101112.AU.1 20250 11013 1020 100 -135 113a / 230130 210 xx 115 220 240 260 113b 112 ...

Rocket propelled by nuclear energy

Launch vehicle and system and method for economically efficient launch thereof

The present disclosure relates to a launch system, and methods of launching a 5 payload utilizing 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 system can comprise: 1) a launch tube comprising a plurality of conductive layers separated by one or more insulating layers and being configured for transmission of energy therethrough; and 2) an electrical energy source; wherein 10 the launch tube is configured for propulsion of a launch vehicle therethrough, and the launch system is configured to be electroantimagnetic. An electrical energy source also can be provided. 11809219_1 (GHMatters) P101112.AU.2 20250 11013 1020 100 -135 113a / 230130 210 xx 115 220 240 260 113b 112 ...

Launch vehicle and system and method for economically efficient launch thereof

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) 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 (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) 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 (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

Large cross-section interceptor vehicle and method

A vehicle may include a vehicle body maneuverable onto a near collision course with a target and a plurality of inflatable ballutes which, when inflated, extend generally radially from the vehicle body. A controller may cause the ballutes to be inflated prior to an anticipated time of collision with the target. A plurality of explosive charges may be attached to at least some of the ballutes. A detonation controller may be coupled to the controller and to the plurality of explosive charges.

Launch vehicle and system and method for economically efficient launch thereof

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 5 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, and an exhaust nozzle from which the heated propellant expands to provide an exhaust 10 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 also can be provided. 9406720_1 (GHMatters) P101112.AU.1 20250 11013 1020 100 (-135 113a /230 1 210 xx 115 220 240 260 113b 112 ...

Viscous Liquid Monopropellant

This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) 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 (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

Distributed ordnance system, multiple stage ordnance system, and related methods

A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple-stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple-stage ordnance control system and controlling initiation of an energetic material are also disclosed.

Verfahren und Vorrichtung zum Test eines operationellen Marschflugkörpers in verschiedenen Prüfzenarien mittels Betriebsart Wartung

Vorrichtung zum Test eines operationellen Flugkörper bestehend aus • einem Umbilical-Kabel entspr. MIL-STD 1760, • einer Milbus-Steuereinheit ('bus control unit' entspr. MIL-STD 1553) mit Mensch-Maschine-Schnittstelle, • einer RTU-Adressen-Brücken-Schaltung entspr. MIL-STD 1760, • einer aktiven GPS-Antenne inklusive 12 V Gleichspannungs-Versorgung, • einer GPS-Signal-Verlängerung für die Flugkörper-GPS-Antenne • einer schaltbaren 3 × 115 V 400 Hz Spannungs-Quelle, • einem Radarhöhenmesser-Signal-Verzögerer, • einem operationellem Kabel zur Wartungs-Klappe des zu testenden Flugkörpers • einer mit Kühlmittel gefüllten Flasche für den Infrarot-Suchkopf und einem Bildschirm, • einer Einheit zum Missions-Plan-Laden, gekennzeichnet durch folgende Merkmale: a. das Umbilical-Kabel führt nur folgende Signale: Milbus-Kanal A, Milbus-Kanal B, RTU-Adress-Leitungen, 3 × 115 V 400 Hz Leitungen, GPS-Antennen-Signal, b. die RTU-Adressen-Brückenschaltung der Testvorrichtung brückt die RTU-Adress-Leitungen des Umbilical-Kabels so, dass sich für den zu testenden Flugkörper eine RTU-Adresse ergibt, welche unterschiedlich zu den operationell benutzten RTU-Adressen... Device for testing an operational missile consisting of • an umbilical cable according to MIL-STD 1760, A Milbus control unit ('bus control unit' according to MIL-STD 1553) with human-machine interface, • an RTU address bridge circuit according to MIL-STD 1760, • an active GPS antenna including 12 V DC power supply, • A GPS signal extension for the missile GPS antenna A switchable 3 × 115 V 400 Hz voltage source, A radar altimeter signal retarder, • an operational cable to the maintenance flap of the missile under test • a coolant filled bottle for the infrared seeker and a screen, • a mission plan loading unit, characterized by the following features: a. the umbilical cable carries only the following signals: Milbus channel A, Milbus channel B, RTU address lines, 3 × 115 V 400 Hz lines, GPS antenna signal, ...

DISTRIBUTED ORDNANCE SYSTEM, MULTIPLE STAGE ORDNANCE SYSTEM, AND RELATED METHODS

A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple stage ordnance control system and controlling initiation of an energetic material are also disclosed.

Planetary impact defense system

A system for defending a planet having a satellite against impact from an incoming body includes an explosive system and a propulsion system. The explosive system is adapted for deployment on the satellite and detonation thereon with sufficient explosive force to produce at least one ejectum to which is imparted a velocity increment sufficient for the ejectum to exceed the satellite's escape velocity and enter orbit about the planet. The propulsion system is adapted to be secured to at least one ejectum and impart a velocity increment to the ejectum sufficient to leave orbit about the planet and enter an orbit intercepting the incoming body. The system is used in a planetary defense method in which the explosive system is deployed at a deployment site on the satellite and detonated to produce at least one ejectum having a velocity that exceeds the escape velocity of the satellite. The ejectum enters into orbit around the planet, at which time the propulsion system is secured to the ejectum ...

MISSILE INTERCEPTOR

The present invention is a method of interception. When a missile is launched and detected by a satellite, an anti-missile rocket is launched to intercept it. When the anti-missile rocket nears the point of interception, it goes into a turn of about 180 degrees, to reverse its course, and comes in behind the enemy missile, at a speed almost equal to that of the ICBM. In this maneuver, coming in behind the ICBM, it reduces the relative speed of the two rockets from about 13,000 mph to about 50 mph, and allows the interceptor missile to approach the ICBM at a slow speed and easily destroy it.

Launch vehicle and system and method for economically efficient launch thereof

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.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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.

Viscous liquid monopropellant

This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomized and then ignited. The atomization step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidizers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion while doing so.

BALLISTIC TARGET DEFENSE SYSTEM AND METHODS

A method for ballistic target defense including identifying a launched ballistic target having a target launch point, a target launch direction, a target speed, and a target trajectory; launching a target interceptor in a launch direction that is generally the same as the target launch direction and with a speed that is less than the target speed; providing the interceptor with an approximate target intercept trajectory, and accelerating the interceptor at an approximate point of intercept to substantially match the target trajectory. During a relatively long target engagement time, the interceptor has approximately a zero net relative velocity with respect to the target. The interceptor will have a speed change capability sufficient to maneuver the interceptor around and/or in a target object cloud, providing the interceptor with the ability to inspect an object of the object cloud, capture an object of the object cloud, nondestructively engage in object of the object cloud, and/or destructively ...

Verfahren zur Zustandsüberwachung einer intelligenten Waffe und intelligente Waffe

Verfahren zur Zustandüberwachung einer intelligenten Waffe (1), insbesondere eines Marschflugkörpers, mit den Schritten: a) Erzeugen eines ersten Zustandsbilds der Waffe (1) während der Fertigung der Waffe, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe ermittelt und in einem Datenspeicher (10) gespeichert werden; b) Erzeugen von zumindest einem weiteren Zustandsbild der Waffe (1) in einem zeitlichen Abstand zum Erzeugen eines vorherigen Zustandsbilds, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe (1) ermittelt und in einem Datenspeicher (10) gespeichert werden; c) Vergleich der Ergebnisdaten aus Schritt b) mit den Ergebnisdaten aus zumindest einem vorherigen Schritt und Ermittlung von Unterschieden sowie von Trends in den einzelnen Ergebnisdaten; d) Entscheidung über die Restnutzungsdauer und das Wartungserfordernis auf der Grundlage der Ergebnisse aus Schritt c).

DISTRIBUTED ORDNANCE SYSTEM, MULTIPLE STAGE ORDNANCE SYSTEM, AND RELATED METHODS

A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple stage ordnance control system and controlling initiation of an energetic material are also disclosed.

Launch vehicle and system and method for economically efficient launch thereof

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.

Launch vehicle and system and method for economically efficient launch thereof

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.

Device for testing an operational cruise missile, allows testing without performing any irreversible operation

Device for testing an operational cruise missile. An independent claim is also included for testing a cruise missile with the new device.

Method for monitoring the status of an intelligent weapon and intelligent weapon

Ein Verfahren zur Zustandüberwachung einer intelligenten Waffe, insbesondere eines Marschflugkörpers, weist die Schritte auf: a) Erzeugen eines ersten Zustandsbilds der Waffe während der Fertigung der Waffe, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe ermittelt und in einem Datenspeicher gespeichert werden; b) Erzeugen von zumindest einem weiteren Zustandsbild der Waffe in einem zeitlichen Abstand zum Erzeugen eines vorherigen Zustandsbilds, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe ermittelt und in einem Datenspeicher gespeichert werden; c) Vergleich der Ergebnisdaten aus Schritt b) mit den Ergebnisdaten aus zumindest einem vorherigen Schritt und Ermittlung von Unterschieden sowie von Trends in den einzelnen Ergebnisdaten; d) Entscheidung über die Restnutzungsdauer und das Wartungserfordemis auf der Grundlage der Ergebnisse aus Schritt c).

Intelligent weapon's i.e. cruise missile, condition monitoring method, involves comparing resulting data of function test of weapon and determining differences and trends in individual data and remaining duration and maintenance requirement

The method involves producing a condition image of an intelligent weapon (1), where resulting data of a function test of the weapon are stored in a data memory (10). Another condition image of the weapon is produced in a temporal distance to produce a previous condition image, where another resulting data of the test are determined and stored in the memory. The both resulting data are compared, and differences and trends in the individual resulting data are determined. A remaining duration and the maintenance requirement are determined based on results of comparison and determination.

CLUSTER ROCKET MOTOR BOOSTERS

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.

Transmitting system and method for transmitting payload

METHOD FOR PLASMA DYNAMIC CANCELLATION FOR HYPERSONIC VEHICLES

A sensor system and method of reducing plasma-induced communication inhibition for a main antenna includes using auxiliary antennas for detecting a density of plasma that affects operation of the main antenna, and re-orienting an electromagnetic field around the main antenna in response to the density detected to reduce effect of the plasma on the main antenna. The auxiliary antennas are also operable for data link communication and switchable such if the density of the plasma inhibits receipt or sending of signals by one of the auxiliary antennas, another one of the auxiliary antennas may be used for data link communication.

Carrying tools and system and transmitting method thereof

Multi-party missile firing control system

A system under international control is in possession of the firing codes required to launch missiles owned by the parties to the system. Upon a request to the international authority for the release of its firing codes so that it may launch a first strike, the target party is advised of the request and given the opportunity to launch its own missiles first. The system deters first strikes.

Ballistic target defense system and methods

A method for ballistic target defense including identifying a launched ballistic target having a target launch point, a target launch direction, a target speed, and a target trajectory; launching a target interceptor in a launch direction that is generally the same as the target launch direction and with a speed that is less than the target speed; providing the interceptor with an approximate target intercept trajectory; and accelerating the interceptor at an approximate point of intercept to substantially match the target trajectory. During a relatively long target engagement time, the interceptor has approximately a zero net relative velocity with respect to the target. The interceptor will have a speed change capability sufficient to maneuver the interceptor around and/or in a target object cloud, providing the interceptor with the ability to inspect an object of the object cloud, capture an object of the object cloud, nondestructively engage in object of the object cloud, and/or destructively engage in object of the object cloud. Embodiments are also directed to a ballistic target defense system and a ballistic target interceptor.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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.

MISSILE INTERCEPTOR

The present invention is a method of interception. When a missile is launched and detected by a satellite, an anti-missile rocket is launched to intercept it. When the anti-missile rocket nears the point of interception, it goes into a turn of about 180 degrees, to reverse its course, and comes in behind the enemy missile, at a speed almost equal to that of the ICBM. In this maneuver, coming in behind the ICBM, it reduces the relative speed of the two rockets from about 13,000 mph to about 50 mph, and allows the interceptor missile to approach the ICBM at a slow speed and easily destroy it.

Planetary impact defense system

A system for defending a planet having a satellite against impact from an incoming body includes an explosive system and a propulsion system. The explosive system is adapted for deployment on the satellite and detonation thereon with sufficient explosive force to produce at least one ejectum to which is imparted a velocity increment sufficient for the ejectum to exceed the satellite's escape velocity and enter orbit about the planet. The propulsion system is adapted to be secured to at least one ejectum and impart a velocity increment to the ejectum sufficient to leave orbit about the planet and enter an orbit intercepting the incoming body. The system is used in a planetary defense method in which the explosive system is deployed at a deployment site on the satellite and detonated to produce at least one ejectum having a velocity that exceeds the escape velocity of the satellite. The ejectum enters into orbit around the planet, at which time the propulsion system is secured to the ejectum ...

Apparatus for translation of GPS signals to facilitate asset tracking

A method for facilitating real time tracking of an airborne asset via downlink of GPS signals that are usable for determining asset location information from the asset to a ground station may include receiving a first GPS signal and a second GPS signal at a device disposed on the airborne asset and combining the first and second GPS signals to form combined signal responsive to filtration and amplification of the first and second GPS signals. The method may further include employing an overlay analog translation to convert the combined signal into a composite signal at a different frequency than the combined signal, generating a pilot carrier frequency for association with the composite signal, and amplifying the composite signal prior to transmission via the downlink from the airborne asset to the ground station. The pilot carrier frequency and amplitude may be adjustable.

Method and system for analyzing ballistic trajectories

A method for analyzing ballistic trajectories comprises determining invariants for known ballistic objects, defining a reference graph having nodes corresponding to the invariants, and defining a query graph having nodes connected to nodes of the reference graph corresponding to anticipated invariant queries to be made using the query graph. One or more sets of invariants corresponding to trajectories of one or more observed objects are input into the reference graph and traverse through the nodes of the reference graph, leaving a record in the nodes traversed. A query is selected for the query graph corresponding to one or more range of invariants, the query generating a query result identifying the nodes of the reference graph that satisfy the query. Identifying each of the observed objects identified by a record in the identified nodes determines which of the one the observed objects satisfy the query.

Method for monitoring the status of an intelligent weapon and intelligent weapon

Ein Verfahren zur Zustandüberwachung einer intelligenten Waffe, insbesondere eines Marschflugkörpers, weist die Schritte auf: a) Erzeugen eines ersten Zustandsbilds der Waffe während der Fertigung der Waffe, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe ermittelt und in einem Datenspeicher gespeichert werden; b) Erzeugen von zumindest einem weiteren Zustandsbild der Waffe in einem zeitlichen Abstand zum Erzeugen eines vorherigen Zustandsbilds, wobei Ergebnisdaten zumindest eines Funktionstests der Waffe ermittelt und in einem Datenspeicher gespeichert werden; c) Vergleich der Ergebnisdaten aus Schritt b) mit den Ergebnisdaten aus zumindest einem vorherigen Schritt und Ermittlung von Unterschieden sowie von Trends in den einzelnen Ergebnisdaten; d) Entscheidung über die Restnutzungsdauer und das Wartungserfordemis auf der Grundlage der Ergebnisse aus Schritt c).

MULTI-PARTY MISSILE FIRING CONTROL SYSTEM

A system under international control is in possession of the firing codes required to launch missiles owned by the parties to the system. Upon a request to the international authority for the release of its firing codes so that it may launch a first strike, the target party is advised of the request and given the opportunity to launch its own missiles first. The system deters first strikes.

Launch vehicle and system and method for economically efficient launch thereof

本发明涉及一种发射系统(20)、用于该发射系统(20)的运载工具(200)，和利用运载工具(200)和/或发射系统发射有效载荷的方法。本发明可以用于将有效载荷投放到陆地位置、地球轨道位置或轨道外位置。运载工具(200)可以包括有效载荷(240)、推进剂罐(230)、电加热器(220)和排气喷嘴(210)，诸如轻气体(例如，氢气)这样的推进剂在电加热器中被电加热，加热的推进剂从排气喷嘴膨胀出以提供例如为7-16km/sec的排气速度。运载工具可以用于发射系统，该发射系统可以进一步包括由至少一个管(110,130)形成的发射管(100)，该至少一个管(110,130)可以是导电的并且可以与至少一个绝缘体管(120)组合起来。还可以提供电能源(300)。

DISTRIBUTED ORDNANCE SYSTEM, MULTIPLE STAGE ORDNANCE SYSTEM, AND RELATED METHODS

A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple-stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple-stage ordnance control system and controlling initiation of an energetic material are also disclosed.

Cluster rocket motor boosters

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.

Launch vehicle and system and method for economically efficient launch thereof

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.

Missile interceptor

The present invention is a method of interception. When a missile is launched and detected by a satellite, an anti-missile rocket is launched to intercept it. When the anti-missile rocket nears the point of interception, it goes into a turn of about 180 degrees, to reverse its course, and comes in behind the enemy missile, at a speed almost equal to that of the ICBM. In this maneuver, coming in behind the ICBM, it reduces the relative speed of the two rockets from about 13,000 mph to about 50 mph, and allows the interceptor missile to approach the ICBM at a slow speed and easily destroy it.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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.

LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF

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.

RETRACTOR AND CAPTURE MECHANISM FOR A MISSILE ANTENNA COUPLER

Large Cross-Section Interceptor Vehicle and Method

A vehicle may include a vehicle body maneuverable onto a near collision course with a target and a plurality of inflatable ballutes which, when inflated, extend generally radially from the vehicle body. A controller may cause the ballutes to be inflated prior to an anticipated time of collision with the target. A plurality of explosive charges may be attached to at least some of the ballutes. A detonation controller may be coupled to the controller and to the plurality of explosive charges.

Method for plasma dynamic cancellation for hypersonic vehicles

A sensor system and method of reducing plasma-induced communication inhibition for a main antenna includes using auxiliary antennas for detecting a density of plasma that affects operation of the main antenna, and re-orienting an electromagnetic field around the main antenna in response to the density detected to reduce effect of the plasma on the main antenna. The auxiliary antennas are also operable for data link communication and switchable such if the density of the plasma inhibits receipt or sending of signals by one of the auxiliary antennas, another one of the auxiliary antennas may be used for data link communication.

Non-explosive target directed reentry projectile

The non-explosive core of a reentry projectile is fixedly positioned within hollow casing of the projectile at a location maximizing conversion and transfer of kinetic energy to an earth bound target in response to the projectile's impact at a hypersonic velocity and at a steep impact angle to the surface of the earth. The hollow casing is formed of a material capable of withstanding high temperatures, therefore, not requiring any cooling and allowing for the hollow casing to be free of heat transfer medium that might otherwise impede the desired quick release of the core upon impact of the projectile. The core is in the form of a single dense metallic slug having a mass establishing a center of gravity and moments of inertia for the projectile as a kinetic energy warhead corresponding to that of an explosive or nuclear warhead without weapon system modification.

APPARATUS FOR TRANSLATION OF GPS SIGNALS TO FACILITATE ASSET TRACKING

A method for facilitating real time tracking of an airborne asset via downlink of GPS signals that are usable for determining asset location information from the asset to a ground station may include receiving a first GPS signal and a second GPS signal at a device disposed on the airborne asset and combining the first and second GPS signals to form combined signal responsive to filtration and amplification of the first and second GPS signals. The method may further include employing an overlay analog translation to convert the combined signal into a composite signal at a different frequency than the combined signal, generating a pilot carrier frequency for association with the composite signal, and amplifying the composite signal prior to transmission via the downlink from the airborne asset to the ground station. The pilot carrier frequency and amplitude may be adjustable. 1. An apparatus configured to be disposed on an airborne asset to communicate global positioning system (GPS) signals that are usable for determining location information of the asset to a ground station for tracking of the asset , the apparatus comprising:a dual input low noise amplifier configured to receive a first GPS signal and a second GPS signal and combine the first and second GPS signals to form combined signal;a translator module configured to employ analog translation to convert the combined signal into a composite signal at a different frequency than the combined signal; anda power amplifier configured to amplify the composite signal prior to transmission via a downlink from the airborne asset to the ground station,wherein the translator module is configured to generate a pilot carrier frequency to facilitate ground station tracking of the airborne asset, and wherein the pilot carrier frequency is adjustable via a frequency programming module of the translator module.2. The apparatus of claim 1 , wherein the frequency programming module is further configured to enable selection of the ...

Launch vehicle and system and method for economically efficient launch thereof

Launch vehicle and system and method for economically efficient launch thereof

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) 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 (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

Launch means and systems and their economical and efficient launch methods

Launch vehicle, launch system and method of launching a payload

The invention describes a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) and/or the launch system. The invention can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) 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 (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.

Distributed ordnance system, multiple stage ordnance system, and related methods

A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple stage ordnance control system and controlling initiation of an energetic material are also disclosed.

分散型のオードナンスシステム、多段式オードナンスシステム、および関連の方法

发射系统和用于发射有效载荷的方法

公开了发射系统和用于发射有效载荷的方法。发射系统包括：发射管，所述发射管包括由一个或多个绝缘层分隔开的多个导电层，并且配置成用于通过其传输能量；和电能源，其中所述发射管配置成用于推进所述运载工具通过该发射管，并且所述发射系统被配置成是电防磁的。用于发射有效载荷的方法包括：提供发射系统，所述发射系统包括：发射管，所述发射管包括配置成用于通过其传输能量的至少一个管；和电能源，以及以大约2至大约2,000G的加速力将所述运载工具加速通过所述发射管至至少为大约每秒2000米的速度，同时将所述管内的磁场限制成不大于约2特斯拉。