IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0910584
(2004-08-04)
|
등록번호 |
US-7252270
(2007-08-07)
|
우선권정보 |
IL-157261(2003-08-05); IL-163002(2004-07-13) |
발명자
/ 주소 |
|
출원인 / 주소 |
- Israel Aircraft Industries, Ltd.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
16 인용 특허 :
28 |
초록
▼
System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system including a missile support coupled with the missile, and a foldable control-surface mechanism coupled with the missile su
System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system including a missile support coupled with the missile, and a foldable control-surface mechanism coupled with the missile support, the foldable control-surface mechanism being in a folded position before ejecting the missile support and the missile from the flying vehicle, the foldable control-surface mechanism moving from a folded position to an operational position after ejecting the missile support and the missile from the flying vehicle, wherein the foldable control-surface mechanism maneuvers the missile and the missile support to a predetermined orientation suitable for launching the missile, wherein the missile support is decoupled from the missile when the missile and the missile support are at the predetermined orientation, and wherein the missile is launched after reaching the predetermined orientation.
대표청구항
▼
The invention claimed is: 1. System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system comprising: a missile support coupled with said missile; and a foldable control-surface mech
The invention claimed is: 1. System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system comprising: a missile support coupled with said missile; and a foldable control-surface mechanism coupled with said missile support, said foldable control-surface mechanism being in a folded position before ejecting said missile support and said missile from said flying vehicle, said foldable control-surface mechanism moving from a folded position to an operational position after ejecting said missile support and said missile from said flying vehicle, said foldable control-surface mechanism maneuvering said missile and said missile support to a predetermined upward orientation suitable for launching said missile, a release controller including an orientation detector, the orientation detector being coupled with said missile support to detect when said missile and said missile support reach said predetermined upward orientation; and at least one release mechanism coupled with said release controller, wherein said at least one releasable mechanism couples said missile with said missile support before said missile and said missile support reach said predetermined upward orientation, and wherein said at least one releasable mechanism decouples said missile from said missile support, according to a signal received from said release controller, after said missile and said missile support reach said predetermined upward orientation, and wherein said missile is launched after decoupling from said missile support. 2. The system according to claim 1, wherein said foldable control-surface mechanism comprises at least two control surfaces. 3. The system according to claim 2, wherein at least one of said at least two control surfaces can be folded within said missile support. 4. The system according to claim 2, wherein at least one of said at least two control surfaces can be folded external to said missile support. 5. The system according to claim 2, wherein at least one of said at least two control surfaces is in form of an airfoil. 6. The system according to claim 2, wherein said foldable control-surface mechanism further comprises: a positioning controller; and at least one positioning actuator coupled with said at least two control surfaces and with said positioning controller, wherein said at least one positioning actuator moves said at least two control surfaces from said folded position to said operational position, according to a signal received from said positioning controller. 7. The system according to claim 6, wherein the type of said at least one positioning actuator is selected from the list consisting of: variable displacement; and constant displacement. 8. The system according to claim 6, wherein the type of said positioning controller is selected from the list consisting of: timer; processor; and another orientation detector. 9. The system according to claim 6, wherein said foldable control-surface mechanism further comprises a first communication interface coupled with said positioning controller, wherein said positioning controller communicates wirelessly with a remote controller via said first communication interface and a second communication interface, said second communication interface is coupled with said remote controller, and wherein said at least one positioning actuator moves said at least two control surfaces from said folded position to said operational position, according to a signal received from said remote controller. 10. The system according to claim 2, wherein said foldable control-surface mechanism further comprises: a maneuvering controller; and at least one maneuvering actuator coupled with said at least two control surfaces and with said maneuvering controller, wherein said at least one maneuvering actuator moves said at least two control surfaces according to a signal received from said maneuvering controller, to maneuver said missile and said missile support to said predetermined orientation. 11. The system according to claim 10, wherein the type of said at least one maneuvering actuator is selected from the list consisting of: hydraulic; pneumatic; and electric. 12. The system according to claim 1, wherein the contour of said missile support is selected from the list consisting of: polygon; closed curve; and a combination of at least one line and at least one curve. 13. The system according to claim 1, further comprising at least one ejection parachute coupled with said missile support, wherein said at least one ejection parachute ejects said missile support and said missile from said flying vehicle. 14. The system according to claim 1, further comprising at least one ejection element coupled with said missile support and with said flying vehicle, wherein said at least one ejection element ejects said missile support and said missile from said flying vehicle. 15. The system according to claim 14, wherein the type of said at least one ejection element is selected from the list consisting of: hydraulic; pneumatic; electric; and mechanical. 16. The system according to claim 1, further comprising an exposed control-surface mechanism, said exposed control-surface mechanism comprising at least one exposed control surface, wherein said exposed control-surface mechanism maneuvers said missile and said missile support. 17. The system according to claim 16, wherein said exposed control-surface mechanism is selected from the list consisting of: movable; and stationary. 18. Method for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the method comprising the procedures of: ejecting said missile and a missile support from inside of said flying vehicle, said missile being coupled with said missile support; moving a control-surface mechanism from a folded position to an operational position, said control-surface mechanism being coupled with said missile support; rolling said missile support about a longitudinal axis of said missile support; maneuvering said missile support and said missile, by said control-surface mechanism, to a predetermined upward orientation suitable for launching said missile; detecting when said missile and said missile support reach said predetermined upward orientation; decoupling said missile from said missile support after said missile and said missile support reach said predetermined upward orientation; and activating the propulsion system of said missile to launch said missile. 19. The method according to claim 18, further comprising a preliminary procedure of carrying said missile and said missile support by said flying vehicle, to said launch region for launching said missile at said launch region. 20. The method according to claim 18, further comprising a procedure of activating at least one ejection parachute, before performing said procedure of ejecting, said at least one ejection parachute being coupled with said missile support. 21. The method according to claim 18, further comprising a procedure of activating at least one ejection element, before performing said procedure of ejecting, said at least one ejection element being coupled with said missile support and with said flying vehicle. 22. The method according to claim 18, further comprising a procedure of uncoupling at least one ejection parachute from said missile support, after performing said procedure of ejection. 23. The method according to claim 18, wherein said ejection procedure is performed while a missile direction from an aft section of said missile to a fore section of said missile, is substantially along a flying direction of said flying vehicle. 24. The method according to claim 18, wherein said ejection procedure is performed while a missile direction from an aft section of said missile to a fore section of said missile, is substantially opposite a flying direction of said flying vehicle. 25. The method according to claim 18, wherein said moving procedure is performed according to a signal received from a positioning controller. 26. The method according to claim 18, wherein said rolling procedure is performed by a foldable control-surface mechanism. 27. The method according to claim 18, wherein said rolling procedure is performed by an exposed control-surface mechanism. 28. The method according to claim 18, wherein said rolling procedure is performed by at least two maneuvering elements. 29. The method according to claim 18, wherein said maneuvering procedure is performed according to a signal received from a maneuvering controller. 30. The method according to claim 18, wherein said maneuvering procedure is performed while said control-surface mechanism is stationary relative to said missile support. 31. The method according to claim 18, wherein said maneuvering procedure is performed while said control-surface mechanism is moving relative to said missile support. 32. System for launching a missile from a launch region within the atmosphere of a planet, the missile being carried to the launch region by a flying vehicle while the missile is coupled externally with the flying vehicle, the system comprising: a missile support coupled with said missile and with said flying vehicle, said missile support and said missile being located outside of said flying vehicle, said missile support being decoupled from said flying vehicle when said flying vehicle is at said launch region; and a control-surface mechanism coupled with said missile support, said control-surface mechanism maneuvering said missile and said missile support to a predetermined upward orientation suitable for launching said missile, a release controller including an orientation detector, the orientation detector being coupled with said missile support to detect when said missile and said missile support reach said predetermined upward orientation; and at least one release mechanism coupled with said release controller, wherein said at least one releasable mechanism couples said missile with said missile support before said missile and said missile support reach said predetermined upward orientation, and wherein said at least one releasable mechanism decouples said missile from said missile support, according to a signal received from said release controller, after said missile and said missile support reach said predetermined upward orientation, and wherein said missile is launched after decoupling from said missile support. 33. The system according to claim 32, wherein said missile is located between said missile support and a fuselage of said flying vehicle. 34. The system according to claim 32, wherein said missile support is located between said missile and a fuselage of said flying vehicle. 35. The system according to claim 32, wherein said missile support is coupled with an upper portion of a fuselage of said flying vehicle. 36. The system according to claim 32, wherein said missile support is coupled with a lower portion of a fuselage of said flying vehicle. 37. The system according to claim 32, wherein said missile support is coupled with a wing of said flying vehicle. 38. The system according to claim 32, wherein said control-surface mechanism comprises at least two control surfaces. 39. The system according to claim 38, wherein said at least two control surfaces can be folded within said missile support. 40. The system according to claim 38, wherein said at least two control surfaces can be folded external to said missile support. 41. The system according to claim 38, wherein said at least two control surfaces are in a folded position before decoupling said missile support from said flying vehicle, and wherein said at least two control surfaces move from said folded position to an operational position, when said missile support is no longer coupled with said flying vehicle. 42. The system according to claim 38, wherein at least one of said at least two control surfaces are in an operational position, both before and after decoupling said missile support from said flying vehicle. 43. The system according to claim 38, wherein at least one of said at least two control surfaces are coupled with said missile support, at a location relative to a direction of flight of said flying vehicle, said location being selected from the list consisting of: aft; fore; and middle. 44. The system according to claim 38, wherein at least one of said at least two control surfaces are in form of an airfoil. 45. The system according to claim 38, wherein at least one of said at least two control surfaces are in form of a substantially flat plate. 46. The system according to claim 38, wherein at least one of said at least two control surfaces are selected from the list consisting of: movable; and stationary. 47. The system according to claim 38, wherein said control-surface mechanism further comprises: a positioning controller; and at least one positioning actuator coupled with said at least two control surfaces and with said positioning controller, and wherein said at least one positioning actuator moves said at least two control surfaces from a folded position to an operational position, according to a signal received from said positioning controller. 48. The system according to claim 47, wherein the type of said at least one positioning actuator is selected from the list consisting of: variable displacement; and constant displacement. 49. The system according to claim 47, wherein the type of said positioning controller is selected from the list consisting of: timer; processor; and another orientation detector. 50. The system according to claim 47, wherein said control-surface mechanism further comprises a first communication interface coupled with said positioning controller, wherein said positioning controller communicates wirelessly with a remote controller via said first communication interface and a second communication interface, said second communication interface is coupled with said remote controller, and wherein said at least one positioning actuator moves said at least two control surfaces from said folded position to said operational position, according to a signal received from said remote controller. 51. The system according to claim 38, wherein said control-surface mechanism further comprises: a maneuvering controller; and at least one maneuvering actuator coupled with at least one of said at least two control surfaces and with said maneuvering controller, and wherein said at least one maneuvering actuator moves at least one of said at least two control surfaces according to a signal received from said maneuvering controller, to maneuver said missile and said missile support to said predetermined orientation. 52. The system according to claim 51, wherein the type of said at least one maneuvering actuator is selected from the list consisting of: hydraulic; pneumatic; and electric. 53. The system according to claim 32, wherein the contour of said missile support is selected from the list consisting of: polygon; closed curve; and a combination of at least one line and at least one curve. 54. The system according to claim 32, further comprising a disengagement mechanism, wherein said disengagement mechanism couples said missile support with said flying vehicle, when said flying vehicle is flying toward said launch region, and wherein said disengagement mechanism decouples said missile support from said flying vehicle, when said flying vehicle is at said launch region. 55. The system according to claim 54, wherein the type of said disengagement mechanism is selected from the list consisting of: hydraulic; pneumatic; pyrotechnic; electric; and mechanical. 56. Method for launching a missile from a launch region within the atmosphere of a planet, the missile being carried to the launch region by a flying vehicle while the missile is coupled externally with the flying vehicle, the method comprising the procedures of: decoupling a missile support from said flying vehicle, said missile support coupling said missile with said flying vehicle, while said flying vehicle is flying toward said launch region; maneuvering said missile support and said missile, by a control-surface mechanism coupled with said missile support, to a predetermined upward orientation suitable for launching said missile; detecting when said missile and said missile support reach said predetermined upward orientation; decoupling said missile from said missile support after said missile and said missile support reach said predetermined upward orientation; and activating the propulsion system of said missile to launch said missile. 57. The method according to claim 56, further comprising a preliminary procedure of carrying said missile and said missile support by said flying vehicle, to said launch region for launching said missile at said launch region. 58. The method according to claim 56, further comprising a preliminary procedure of coupling said missile support with said flying vehicle, such that said missile is located between said missile support and a fuselage of said flying vehicle. 59. The method according to claim 56, further comprising a preliminary procedure of coupling said missile support with said flying vehicle, such that said missile support is located between said missile and a fuselage of said flying vehicle. 60. The method according to claim 59, further comprising a procedure of rolling said missile support about a longitudinal axis of said missile support, before performing said procedure of maneuvering. 61. The method according to claim 60, wherein said rolling procedure is performed by a control-surface mechanism coupled with said missile support. 62. The method according to claim 60, wherein said rolling procedure is performed by at least two maneuvering elements coupled with said missile support. 63. The method according to claim 62, wherein said at least two maneuvering elements are selected from the list consisting of: micro-rocket motor; thruster; and pressurized-gas operated system. 64. The method according to claim 56, further comprising a preliminary procedure of coupling said missile support with an upper portion of a fuselage of said flying vehicle. 65. The method according to claim 56, further comprising a preliminary procedure of coupling said missile support with a lower portion of a fuselage of said flying vehicle. 66. The method according to claim 56, further comprising a preliminary procedure of coupling said missile support with a wing of said flying vehicle. 67. The method according to claim 56, further comprising a procedure of moving a control-surface mechanism from a folded position to an operational position, before performing said procedure of maneuvering, said control-surface mechanism being coupled with said missile support. 68. The method according to claim 56, further comprising a preliminary procedure of folding a control-surface mechanism within said missile support, said control-surface mechanism being coupled with said missile support. 69. The method according to claim 56, further comprising a preliminary procedure of folding a control-surface mechanism external to said missile support, said control-surface mechanism being coupled with said missile support. 70. The method according to claim 56, wherein said maneuvering procedure is performed while a control-surface mechanism is stationary relative to said missile support, said control-surface mechanism being coupled with said missile support. 71. The method according to claim 56, wherein said maneuvering procedure is performed while a control-surface mechanism is moving relative to said missile support, said control-surface mechanism being coupled with said missile support.
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