IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0282792
(2002-10-28)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
47 인용 특허 :
6 |
초록
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Methods and apparatuses for controlling aircraft devices with multiple actuators. An apparatus in accordance with one embodiment of the invention includes a first actuator coupled to a first power system having a first probability of failure, the first actuator being coupleable to at least one movea
Methods and apparatuses for controlling aircraft devices with multiple actuators. An apparatus in accordance with one embodiment of the invention includes a first actuator coupled to a first power system having a first probability of failure, the first actuator being coupleable to at least one moveable component of an aircraft system. The apparatus can further include a second actuator coupled to a second power system having a second probability of failure less than the first. The second actuator can be operatively coupled to the first actuator and can be coupleable to the at least one moveable component, for example, to operate simultaneously with the first actuator. A second force applied by the second actuator can be less than a first force applied by the first actuator. Accordingly, the second power source can be reduced in size by virtue of the reduced probability of failure for the first power system.
대표청구항
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1. An apparatus for controlling an aircraft system having at least one moveable device, the apparatus comprising:a first power system having a first probability of failure;a second power system having a second probability of failure greater than the first probability of failure;a first actuator coup
1. An apparatus for controlling an aircraft system having at least one moveable device, the apparatus comprising:a first power system having a first probability of failure;a second power system having a second probability of failure greater than the first probability of failure;a first actuator coupled to the first power system, the first actuator being coupleable to the at least one moveable device of the aircraft system, the first actuator being configured to apply a first force to the at least one moveable device; anda second actuator coupled to the second power system, the second actuator being operatively coupled to the first actuator and the at least one moveable device of the aircraft system, the second actuator being configured to apply a second force to the at least one moveable device, the second force being less than the first force. 2. The apparatus of claim 1 wherein the first power system includes a plurality of busses coupled to one or more electrical power generators. 3. The apparatus of claim 1 wherein the first actuator is configured to apply the first force simultaneously with the second actuator applying the second force during normal operation. 4. The apparatus of claim 1 wherein the first actuator includes an electrically powered actuator and wherein the second actuator includes a hydraulically powered actuator. 5. The apparatus of claim 1 wherein the first power system includes an electrical power system and the second power system includes a hydraulic power system. 6. The apparatus of claim 1, further comprising the aircraft system. 7. The apparatus of claim 1, further comprising the aircraft system, and wherein the aircraft system includes a moveable flight control surface. 8. The apparatus of claim 1 wherein the first power system has a probability of failure of about 10 −7 or less. 9. The apparatus of claim 1 wherein the second power system has a probability of failure of about 10 −5 . 10. The apparatus of claim 1, further comprising a third actuator operatively coupled to the first and second actuators. 11. The apparatus of claim 1 wherein the first force and the second force together are sufficient to operate the moveable device over a normal operating range, and wherein the first force or the second force above alone is sufficient to operate the moveable device over a reduced operating range. 12. The apparatus of claim 1 wherein the first actuator includes an electrically driven motor coupled to a hydraulic pump. 13. The apparatus of claim 1 wherein the second actuator includes a valve coupleable to a supply of hydraulic fluid pressurized by one or more aircraft engines or electrical pumps. 14. The apparatus of claim 1 wherein the second actuator weighs less than it would if it were sized and configured to apply a third force approximately equal to the first force. 15. An apparatus for controlling an aircraft system having at least one moveable device, the apparatus comprising:first power means for generating power, the first power means having a first probability of failure;first actuator means for moving the at least one moveable device, the first actuator means being coupled to the first power means and coupleable to the at least one moveable device to apply a first force to the at least one moveable device;second power means for generating power, the second power means having a second probability of failure greater than the first probability of failure; andsecond actuator means for moving the at least one moveable device, the second actuator means being coupled to the second power means and operatively coupled to the first actuator means and being coupleable to the at least one moveable device to apply a second force to the at least one moveable device, the second force being less than the first force. 16. The apparatus of claim 15 wherein the first actuator means are configured to apply the first force simultaneously with the second actuator means applying the second force du ring normal operation. 17. The apparatus of claim 15 wherein the first actuator means include an electrically powered actuator and wherein the second actuator means include a hydraulically powered actuator. 18. The actuator of claim 15 wherein the first power means includes a plurality of busses coupled to one or more electrical generators and wherein the second power means include a hydraulic power system. 19. The apparatus of claim 15, further comprising the aircraft system. 20. The apparatus of claim 15, further comprising the aircraft system, and wherein the aircraft system includes a moveable flight control surface. 21. The apparatus of claim 15 wherein the first power means have a probability of failure of about 10 −7 or less. 22. The apparatus of claim 15 wherein the second power means have a probability of failure of about 10 −5 . 23. The apparatus of claim 15, further comprising third actuator means operatively coupled to the first and second actuator means. 24. The apparatus of claim 15 wherein the first force and the second force together are sufficient to operate the at least one moveable device over a first operating range, wherein the first force alone is sufficient to operate the at least one movable device over a second operating range narrower than the first, and wherein the second force alone is sufficient to operate the at least one moveable device over a third operating range narrower than the second operating range. 25. The apparatus of claim 15 wherein the first actuator means include an electrically driven motor coupled to a hydraulic pump. 26. The apparatus of claim 15 wherein the second actuator means include a valve coupleable to a supply of hydraulic fluid pressurized by an aircraft engine. 27. The apparatus of claim 15 wherein the second actuator means have a weight that is less than a weight of another actuator means having a comparable design and configured to apply a third force approximately equal to the first force. 28. An aircraft, comprising:a system having at least one moveable component;a first power system having a first probability of failure;a second power system having a second probability of failure greater than the first probability of failure;a first actuator coupled to the at least one moveable device and the first power system, the first actuator being configured to apply a first force to the at least one moveable device; anda second actuator operatively coupled to the first actuator and the at least one moveable device and the second power system, the second actuator being configured to apply a second force to the at least one moveable device, the second force being less than the first force. 29. The aircraft of claim 28 wherein the at least one moveable device includes at least a portion of an aircraft flight control surface device. 30. The aircraft of claim 28 wherein the first actuator is configured to apply the first force simultaneously with the second actuator applying the second force during normal operation. 31. The aircraft of claim 28 wherein the first actuator includes an electrically powered actuator and wherein the second actuator includes a hydraulically powered actuator. 32. The apparatus of claim 28 wherein the first power system has a probability of failure of about 10 −7 or less. 33. The aircraft of claim 28 wherein the second power system has a probability of failure of about 10 −5 . 34. The aircraft of claim 28 wherein the first force and the second force together are sufficient to operate the moveable device over a normal operating range when the first and second actuators operate simultaneously, and wherein the first and second forces are each sufficient to operate the moveable device over a reduced operating range when each of the first and second actuators operates without the other. 35. The aircraft of claim 28 wherein the first actuator includes an electrically driven motor coupled to a hydraulic pump. 36. The aircraft of c laim 28 wherein the second actuator includes a valve coupleable to a supply of hydraulic fluid pressurized by an aircraft engine. 37. An aircraft system, comprising:a moveable flight control surface;an electrical power system having a first probability of failure;an electrically powered first actuator coupled to the electrical power system and the moveable flight control surface, the first actuator being configured to apply a first force to the moveable flight control surface;a hydraulic power system having a second probability of failure greater than the first probability of failure; anda hydraulically powered second actuator operatively coupled to the hydraulic power system, the first actuator and the moveable flight control surface, the second actuator being configured to apply a second force to the at least one component simultaneously with the first actuator applying the first force, the second force being less than the first force. 38. The system of claim 37 wherein the electrical power system has a probability of failure of about 10 −7 or less and wherein the hydraulic power system has a probability of failure of about 10 −5 . 39. The system of claim 37 wherein the first force and the second force together are sufficient to operate the moveable component over a normal operating range, and wherein each of the first and second forces alone is sufficient to operate the moveable component over a reduced operating range. 40. A method for manufacturing an aircraft system having at least one moveable device, the method comprising:coupling a first actuator to the at least one moveable device of the aircraft system and a first power system, the first power system having a first probability of failure, the first actuator being configured to apply a first force to the at least one moveable device; andoperatively coupling a second actuator to the first actuator, the at least one moveable device of the aircraft system, and a second power system, the second power system having a second probability of failure greater than the first probability of failure, the second actuator being configured to apply a second force to the at least one moveable device, the second force being less than the first force. 41. The method of claim 40 wherein coupling the first actuator includes coupling the first actuator to apply the first force simultaneously with the second actuator applying the second force during normal operation. 42. The method of claim 40 wherein coupling the first actuator includes coupling an electrically powered actuator to an electrical power system and wherein coupling the second actuator includes coupling a hydraulically powered actuator to a hydraulic power system. 43. The method of claim 40 wherein coupling the first actuator includes coupling the first actuator to a first power system having a probability of failure of about 10 −7 or less. 44. The method of claim 40 wherein coupling the second actuator includes coupling the second actuator to a second power system having a probability of failure of about 10 −5 . 45. The method of claim 40, further comprising operatively coupling a third actuator to the first and second actuators. 46. The method of claim 40, further comprising selecting the first and second actuators to apply a first force and a second force which together are sufficient to operate the moveable device over a normal operating range, and wherein each of the first and the second forces alone is sufficient to operate the moveable device over a reduced operating range. 47. The method of claim 40, further comprising selecting the first actuator to include an electrically driven motor coupled to a hydraulic pump. 48. The method of claim 40, further comprising selecting the second actuator to include a valve coupleable to a supply of hydraulic fluid pressurized by an aircraft engine. 49. The method of claim 40, further comprising selecting the second actuator to have a weight that is le ss than a weight of another actuator having a comparable design and configured to apply a third force approximately equal to the first force. 50. A method for manufacturing an aircraft system, comprising:coupling an electrically powered first actuator to a moveable device of an aircraft flight control surface assembly and to an electrical power system, the electrical power system having a first probability of failure, the first actuator being configured to apply a first force to the moveable device; andoperatively coupling a hydraulically powered second actuator to the first actuator, the moveable device, and a hydraulic power system, the hydraulic power system having a second probability of failure greater than the first probability of failure, the second actuator being configured to apply a second force to the moveable device simultaneously with the first actuator applying the first force, the second force being less than the first force. 51. The method of claim 50 wherein coupling the first actuator to a moveable device of an aircraft flight control system includes coupling the first actuator to at least one of an aileron, a flap, an elevator and a canard surface. 52. A method for operating an aircraft system, comprising:applying a first force to at least one moveable device of the aircraft system via a first actuator powered by a first power system having a first probability of failure;applying a second force to the at least one moveable device via a second actuator powered by a second power system having a second probability of failure greater than the first probability of failure, wherein applying the second force includes applying the second force simultaneously with applying the first force, and wherein the second force is less than the first force; andif the first actuator fails, applying only the second force to the at least one moveable device. 53. The method of claim 52 wherein applying the first force to the at least one moveable device includes applying the first force to at least one of an aileron, a flap, an elevator and a canard surface. 54. The method of claim 52 wherein applying the first force via the first actuator includes applying the first force via an electrically powered actuator, and wherein applying the second force via the second actuator includes applying the second force via a hydraulically powered actuator. 55. The method of claim 52 wherein applying the first force via a first actuator includes applying the first force via a first actuator powered by a first power source having a probability of failure of about 10 −7 or less. 56. The method of claim 52 wherein applying the second force via a second actuator includes applying the second force via a second actuator powered by a second power source having a probability of failure of about 10 −5 . 57. The method of claim 52, further comprising applying a third force to the at least one moveable device via a third actuator operatively coupled to the moveable device and the first and second actuators. 58. The method of claim 52 wherein applying the first force and the second force simultaneously includes applying the first and second forces at a level sufficient to operate the moveable device over a normal operating range, and wherein the applying only the first force or the second force includes applying the first force or the second force at a level sufficient to operate the moveable device over a reduced operating range. 59. The method of claim 52 wherein applying the first force via the first actuator includes applying the first force via an electrically driven motor coupled to a hydraulic pump. 60. The method of claim 52 wherein applying the second force via the second actuator includes applying the second force via a valve coupleable to a supply of hydraulic fluid pressurized by an aircraft engine.
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