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Небесная энциклопедия

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

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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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 7. Отображено 7.
09-02-2022 дата публикации

Symmetric roll divergence

Номер: GB0002597843A
Автор: STEVE HOLSTINE [US], KASSIDY L CARSON [US], CASEY ANDREW STRIBRNY [US], NICHOLAS KERSI CHARLES BHARUCHA [US]
Принадлежит:

An ejection seat 320 for an aircraft comprising a base, a divergence rocket 324 attached to the base of the ejection seat and a compensation rocket 326 attached to the base of the ejection seat. A method of controlling an ejection seat is claimed where the divergence rocket is fired first followed by the compensation rocket. The divergence rocket may be oriented to produce a divergence roll moment about a roll axis of the ejection seat. The compensation rocket may be orientated to produce a compensation roll moment about the roll axis. The compensation roll moment may be opposite the divergence roll moment. The divergence and compensation rockets may be located either side of a main ejection rocket 322.

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Номер записи: 1
30-03-2022 дата публикации

Parachute assemblies with elastomeric inserts

Номер: GB0002599213A
Автор: STEVE HOLSTINE [US], KASSIDY L CARSON [US], JOHN HAMPTON [US]
Принадлежит:

A parachute assembly 116 has a first elastomeric insert 130 coupled between a first portion 122a and a second portion 122b of a suspension line. Preferably, the insert has a first segment 230a and a second segment 230b located within the suspension line; a third segment 230c, external to the line between the first and second segments; a fourth segment 230d, external to the line from the first segment to one end of the insert; and a fifth segment 230e, external and extending from the second segment to the other insert end. The fourth segment may be coupled to the line by an adhesive or heat bonding, or include a crimp or knot to block it from moving into the line. Also claimed is a parachute assembly with a canopy 120 with a number of suspension lines with the elastomeric inserts. Also claimed is a method of testing a parachute assembly by deploying the canopy and increasing tensile load applied to a suspension line coupled to the canopy, stretching the elastomeric insert.

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Номер записи: 2
09-02-2022 дата публикации

Deployable overhead protection assembly and methods of use for canopy fragilization system

Номер: GB0002597845A
Автор: STEVE HOLSTINE [US], NATHAN EISCHEID [US], BRADLEY MASTROLIA [US], JOHN HAMPTON [US], NEIL CROSS [US], KASSIDY L CARSON [US], IAN WALTER HAAS [US], PATRICK EMMETT HYDE [US], AARON H KEENE [US], CYLE TEAL [US], JOHN WADE [US]
Принадлежит:

A deployable overhead protection assembly(201,fig2A) with a base 210 pivotally coupled to an ejection seat headrest, a first stabiliser 220 extending from a first side of the base and a second stabiliser 230 extending from a second side of the base where the stabilisers extend forward a first distance from the headrest when deployed. A mitt 240 coupled to the base and disposed laterally between the first and second stabiliser, the mitt extending forward a second distance. The forward end of the mitt acting as a tertiary breaker for the canopy. A canopy fragilization system for an aircraft ejection system including a sharp breaker 250 disposed on a first side of the ejection seat as a primary breaker for the canopy and a blunt breaker 260 disposed on a second side as a secondary breaker. A method for fragilizing a canopy of an aircraft including; exerting a first impulse on the canopy with a primary breaker, a second impulse with a secondary breaker and a third impulse with a tertiary breaker ...

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Номер записи: 3
02-02-2022 дата публикации

Deployable overhead protection assembly and methods of use for canopy fragilization system

Номер: GB0002597609A
Автор: STEVE HOLSTINE [US], NATHAN EISCHEID [US]
Принадлежит:

A deployable overhead protection assembly 201 with a base 210 pivotally coupled to an ejection seat headrest, a first stabiliser 220 extending from a first side of the base and a second stabiliser 230 extending from a second side of the base. The first and second stabilisers have first 222 and second 232 breakers located distal to the base of the stabilisers. A mitt (240,fig2B) coupled to the base and disposed laterally between the first and second stabiliser. Also claimed is a canopy fragilization system for an aircraft ejection system including a sharp breaker 250 disposed on a first side of the ejection seat as a primary breaker for the canopy and a blunt breaker 260 disposed on a second side as a secondary breaker. A method for fragilizing a canopy of an aircraft including; exerting a first impulse on the canopy with a sharp breaker, a second impulse with a blunt breaker, third impulse with the first tertiary breaker and a fourth impulse with the second tertiary breaker. There may be ...

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Номер записи: 4
03-08-2022 дата публикации

Ejection mode verification system

Номер: GB0002603263A
Автор: STEVE HOLSTINE [US], TRISTAN LIKES [US], JOHN HAMPTON [US]
Принадлежит:

A system, for verifying ejection mode, has a first ejection seat, a second ejection seat, and a controller 302. The controller is configured command an indicator 304 to turn on or off in response to comparing a desired ejection mode with a selected ejection mode. Also claimed is an ejection mode verification system (fig.1A,100) has a controller which commands an indicator to turn on or off in response to comparing a desired ejection mode for an aircraft received via a user detection system 412 with a selected ejection mode for the aircraft received via an ejection mode selector 402. Also claimed is an object containing a programme to cause a processor to compare a received desired ejection mode of an ejection system having a first pilot (fig.1a,52) in a first ejection seat (fig.1a,16) and a second ejection seat (fig.1a,20) which is either empty, has a second pilot (fig.1a,56), or has a non-pilot, with a received selected ejection mode of the ejection system.

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Номер записи: 5
24-08-2022 дата публикации

Drogue parachute assemblies with elastomeric insert sleeves

Номер: GB0002603978A
Автор: STEVE HOLSTINE [US], KASSIDY L CARSON [US], JOHN HAMPTON [US]
Принадлежит:

A multi-staged drogue parachute assembly comprising a suspension line with a primary length 121 and a secondary length 122, wherein an elastomeric insert 230 is coupled between two portions 122a, 122b of the secondary length, and a sleeve 200 coupled to the primary length has an interior volume defined by first and second sleeve sections (200a, 200b, Figure 6B) within which the first and second portions of the secondary length are located. An ejection seat may use the parachute assembly, wherein a riser (160, Figure 2A) couples the ejection seat to the suspension line. A bundling line 135 coupled to the suspension line such that the secondary length is secured may be cut by a cutter to release the secondary length. The primary length may be attached to the sleeve by threading. The elastomeric insert may have first and second segments (230a, 230b, Figure 7) located within an internal volume of the suspension line and joined by a third segment (230c) external to the suspension line. In use ...

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Номер записи: 6
30-11-2022 дата публикации

Dual input actuator for an output device

Номер: GB0002607148A
Автор: STEVE HOLSTINE [US], KASSIDY L CARSON [US], JEFFREY BENJAMIN [US], JOHN HAMPTON [US], LUIS G INTERIANO [US]
Принадлежит:

An output device and/or an output device assembly configured to be initiated in response to different types of input is provided. The output device 100 comprises a housing 110 defining a chamber 112 and a moveable member 120 which is configured to undergo activation movement within the chamber 112 to produce an output. The output device 100 is configured such that the activation movement can be initiated in response to two different types of input. For example, the two different types of input may be mechanical force via a sear pin 130 and fluid pressure via an inlet 114. The output device 100 may be able to receive either form of input and convert either input into the desired output.

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Номер записи: 7