System and method for configuring a direct lift control system of a vehicle
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0457499
(2012-04-27)
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등록번호 |
US-8712606
(2014-04-29)
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발명자
/ 주소 |
- Beaufrere, Henry Llewellyn
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
2 |
초록
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A system and methods for configuring a direct lift control system of a vehicle are presented. A plurality of fly-by-wire control surfaces is provided, and fly-by-wire control surface deflection commands of the fly-by-wire control surfaces are scheduled. The fly-by-wire control surfaces are symmetric
A system and methods for configuring a direct lift control system of a vehicle are presented. A plurality of fly-by-wire control surfaces is provided, and fly-by-wire control surface deflection commands of the fly-by-wire control surfaces are scheduled. The fly-by-wire control surfaces are symmetrically actuated based on the fly-by-wire control surface deflection commands such that a fluid dynamic lift of the vehicle is modulated without using a short-period pitch control.
대표청구항
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1. A direct lift control system of a vehicle comprising: a plurality of fly-by-wire control surfaces;a control surface direct lift control schedule operable to generate a plurality of fly-by-wire control deflection commands based on preprogrammed degrees of deflection of the fly-by-wire control surf
1. A direct lift control system of a vehicle comprising: a plurality of fly-by-wire control surfaces;a control surface direct lift control schedule operable to generate a plurality of fly-by-wire control deflection commands based on preprogrammed degrees of deflection of the fly-by-wire control surfaces; andan actuator configured to symmetrically actuate the fly-by-wire control surfaces based on the fly-by-wire control surface deflection commands such that a fluid dynamic lift of the vehicle is modulated without using a short-period pitch control such that a flight path of the vehicle is controlled by the direct lift control system,wherein the fly-by-wire control surfaces comprise fly-by-wire spoilers, and the fly-by-wire control surface deflection commands comprise fly-by-wire spoiler deflection commands. 2. The system of claim 1, wherein the vehicle comprises an aircraft, and the control surface direct lift control schedule comprises a fly-by-wire spoiler direct lift control schedule operable to direct each of the fly-by-wire spoilers to deflect according to the preprogrammed degrees of deflection respectively. 3. The system of claim 2, wherein the fly-by-wire spoilers are coupled to a wing of the aircraft. 4. The system of claim 3, further comprising a force transducer located on a control wheel column of the aircraft and operable to generate a force transducer signal in response to receiving a column force from the control wheel column. 5. The system of claim 4, wherein the force transducer signal is shaped to obtain a direct lift command to retain a same pilot action applied via the column force to flare with the direct lift system that is applied with the short-period pitch control, thereby alleviating pilot training. 6. The system of claim 5, wherein the fly-by-wire control deflection commands are generated based on the direct lift command. 7. The system of claim 5, wherein the fly-by-wire spoiler deflection commands are scheduled such that a change in aerodynamic lift of the aircraft is maximized while ensuring no adverse pitching moment is generated and a tail buffet is minimized. 8. The system of claim 2, wherein the fly-by-wire spoilers are operable to actuate such that the direct lift control system is configured in an event of a jammed elevator. 9. The system of claim 2, wherein the fly-by-wire spoilers are actuated such that an approach and a landing are performed without the short-period pitch control. 10. The system of claim 1, wherein the short-period pitch control comprises at least one control surface selected from the group consisting of an elevator, a stabilator, a tailplane, and a trim tab. 11. A method for configuring a direct lift control system of a vehicle comprising: providing a plurality of fly-by-wire control surfaces;scheduling a plurality of fly-by-wire control surface deflection commands of the fly-by-wire control surfaces based on preprogrammed degrees of deflection of the fly-by-wire control surfaces;symmetrically actuating the fly-by-wire control surfaces based on the fly-by-wire control surface deflection commands such that a fluid dynamic lift of the vehicle is modulated without using a short-period pitch control; andcontrolling a flight path of the vehicle by the direct lift control system,wherein the fly-by-wire control surfaces comprise a plurality of fly-by-wire spoilers, and the fly-by-wire control surface deflection commands comprise a plurality of fly-by-wire spoiler deflection commands. 12. The method of claim 11, wherein the vehicle comprises an aircraft. 13. The method of claim 12, further comprising coupling the fly-by-wire spoilers to a wing of the aircraft. 14. The method of claim 12, further comprising: generating a force transducer signal from a force transducer located on a control wheel column of the aircraft in response to receiving a column force from the control wheel column; andshaping the force transducer signal to provide a direct lift command to retain a same pilot action applied via the column force to flare with the direct lift control system that is applied with the short-period pitch control, thereby alleviating pilot training. 15. The method of claim 12, further comprising scheduling the fly-by-wire spoiler deflection commands such that a change in aerodynamic lift of the aircraft is maximized while ensuring no adverse pitching moment is generated and a tail buffet is minimized. 16. The method of claim 12, configuring the direct lift control system in an event of a jammed elevator by symmetrically actuating the fly-by-wire spoilers based on the fly-by-wire spoiler deflection commands. 17. The method of claim 12, further comprising performing an approach and a landing by symmetrically actuating the fly-by-wire spoilers without using the short-period pitch control. 18. The method of claim 11, wherein the short-period pitch control comprises at least one control surface selected from the group consisting of: an elevator, a stabilator, a tailplane, and a trim tab. 19. A method of operating an aircraft comprising a direct lift control system, the method comprising: activating the direct lift control system comprising a plurality of fly-by-wire spoilers if an elevator is jammed;performing an approach and a landing by symmetrically actuating the fly-by-wire spoilers based on a plurality of fly-by-wire spoiler deflection commands such that an aerodynamic dynamic lift of the aircraft is modulated without using a short-period pitch control, the fly-by-wire spoiler deflection commands generated based on preprogrammed degrees of deflection of the fly-by-wire control surfaces; andcontrolling a flight path of the aircraft by the direct lift control system. 20. The method of claim 19, further comprising generating the fly-by-wire spoiler deflection commands by: generating a force transducer signal from a force transducer located on a control wheel column of the aircraft in response to receiving a column force from the control wheel column;shaping the force transducer signal to provide a direct lift command to retain a same pilot action applied via the column force to flare with the direct lift control system that is applied with the short-period pitch control, thereby alleviating pilot training;providing a fly-by-wire spoiler direct lift control schedule based on the direct lift command;scheduling the fly-by-wire spoiler deflection commands based on the direct lift command such that a change in aerodynamic lift of the aircraft is maximized while ensuring no adverse pitching moment is generated and a tail buffet is substantially minimized; andgenerating the fly-by-wire spoiler deflection commands.
이 특허에 인용된 특허 (2)
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Martorella Romeo P. (Dix Hills NY), Aircraft precision approach control system.
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Frosch Robert A. Administrator of the National Aeronautics and Space Administration ; with respect to an invention of ( Oakhurst NJ) Tisdale ; Sr. Henry F. (Oakhurst NJ) Kelley Wendell W. (Newport Ne, Velocity vector control system augmented with direct lift control.
이 특허를 인용한 특허 (1)
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Beaufrere, Henry L., System and method for configuring a direct lift control system of a vehicle.
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