IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0305430
(2005-12-15)
|
등록번호 |
US-7445182
(2008-11-04)
|
우선권정보 |
DE-10 2004 063 116(2004-12-23) |
발명자
/ 주소 |
|
출원인 / 주소 |
- EADS Space Transportation GmbH
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
An apparatus for ejecting a flying body such as a payload recovery container from a spacecraft includes a first ring to be releasably engaged with the flying body, a second ring to be secured to the spacecraft, and tension cables extending between and interconnecting the two rings. Cable winding dev
An apparatus for ejecting a flying body such as a payload recovery container from a spacecraft includes a first ring to be releasably engaged with the flying body, a second ring to be secured to the spacecraft, and tension cables extending between and interconnecting the two rings. Cable winding devices mounted on at least one of the rings are spring-biased to wind-up the cables. The flying body is inserted through the open inner diameter of the second ring, and the first ring is separated from and rotated relative to the second ring, so that the cables extend helically along the outer circumference of the flying body. Holding and guide elements on the second ring hold and guide the flying body. When the holding elements are released, the cables are retracted by the cable winding devices, whereby the flying body is rotated and translationally ejected through the second ring.
대표청구항
▼
What is claimed is: 1. An apparatus for ejecting a spin-stabilized flying body from a spacecraft, said apparatus comprising: a first ring element to be releasably engaged with the flying body; a second ring element to be secured to the spacecraft, wherein said second ring element has an open inner
What is claimed is: 1. An apparatus for ejecting a spin-stabilized flying body from a spacecraft, said apparatus comprising: a first ring element to be releasably engaged with the flying body; a second ring element to be secured to the spacecraft, wherein said second ring element has an open inner diameter corresponding to or larger than an outer diameter of a portion of the flying body to allow the portion to be inserted through said open inner diameter of said second ring element; a plurality of cable winding devices mounted on at least one of said first and second ring elements; a plurality of tension cables extending between and interconnecting said first and second ring elements, wherein each respective one of said tension cables has one cable end thereof connected to and selectively wound-up on a respective one of said cable winding devices mounted on one of said ring elements and another cable end thereof connected to the other of said ring elements not having said respective cable winding device mounted thereon; a plurality of holding elements mounted on said second ring element and adapted to selectively hold the flying body; and a plurality of guide elements mounted on said second ring element and adapted to position and guide the flying body within said open inner diameter of said second ring element. 2. The apparatus according to claim 1, wherein all of said cable winding devices are mounted on said second ring element, and each one of said tension cables respectively has said another cable end thereof connected to said first ring element. 3. The apparatus according to claim 1, wherein said cable winding devices are spring-loaded cable winding devices 4. The apparatus according to claim 1, wherein said cable winding devices comprise no active powered drive. 5. The apparatus according to claim 1, wherein each one of said cable winding devices respectively comprises a cable winding spool and a torsion spring connected to and rotationally biasing said cable winding spool. 6. The apparatus according to claim 1, further comprising a respective locking pin arranged respectively on each respective one of said cable winding devices and adapted to selectively lock and release a cable winding operation of said respective cable winding device. 7. The apparatus according to claim 1, wherein said cable winding devices are distributed equidistantly from one another around a circumference of said one of said ring elements on which said cable winding devices are mounted. 8. The apparatus according to claim 1, wherein said plurality of cable winding devices comprises at least four of said cable winding devices, and said plurality of tension cables comprises at least four of said tension cables. 9. The apparatus according to claim 1, wherein said plurality of cable winding devices includes a total of exactly eight of said cable winding devices, and said plurality of tension cables includes a total of exactly eight of said tension cables. 10. The apparatus according to claim 1, wherein said tension cables are wire cables. 11. The apparatus according to claim 1, wherein said tension cables provide the only interconnection between said first and second ring elements. 12. The apparatus according to claim 1, wherein said holding elements comprise selectively actuatable magnetic actuators or solenoids. 13. The apparatus according to claim 1, wherein said guide elements comprise roller balls that are freely rotatably supported in ball sockets and that face radially inwardly in said open inner diameter of said second ring element. 14. The apparatus according to claim 1, wherein said cable winding devices are mounted on said second ring element, and wherein said holding elements and said guide elements are respectively arranged on said second ring element circumferentially between respective neighboring ones of said cable winding devices. 15. The apparatus according to claim 1, comprising at least four of said holding elements and at least four of said cable winding devices respectively arranged alternating with one another around a circumference of said second ring element. 16. The apparatus according to claim 1, expressly excluding all explosive devices and explosive materials. 17. The apparatus according to claim 1, which is selectively configurable in a loaded state and an unloaded state, wherein: in said loaded state, said first and second ring elements are axially displaced apart and rotated relative to one another, with said tension cables pulled out of said cable winding devices and extending helically along a cylindrical contour between said first and second ring elements, and in said unloaded state, said first and second ring elements are contacting one another or immediately close together and are not rotated relative to one another, with said tension cables wound-up in or on said cable winding devices, and with said another cable ends thereof extending linearly to the other of said ring elements. 18. The apparatus according to claim 1, further comprising catch elements arranged on said first ring element and adapted to releasably engage receiver recesses of the flying body. 19. A spacecraft system comprising a spacecraft having an ejection bay therein, a flying body that is received in said ejection bay and that is to be ejected in a spin-stabilized manner out of said ejection bay, and an ejection apparatus that is arranged in said ejection bay of said spacecraft and that is adapted to eject said flying body with a translation motion and a rotation motion out of said ejection bay, wherein said ejection apparatus comprises: a first ring element releasably engaged with the flying body; a second ring element secured to the spacecraft, wherein said second ring element has an open inner diameter corresponding to or larger than an outer diameter of a cylindrical portion of the flying body that is inserted through said open inner diameter of said second ring element; a plurality of cable winding devices mounted on said second ring element; a plurality of tension cables extending between and interconnecting said first and second ring elements, wherein each respective one of said tension cables has a first cable end thereof connected to said first ring element and a second cable end thereof connected to and selectively wound-up on a respective one of said cable winding devices; a plurality of holding elements mounted on said second ring element and selectively holding the flying body; and a plurality of guide elements mounted on said second ring element and positioning and guiding the flying body within said open inner diameter of said second ring element.
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