Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/16
B64C-013/18
출원번호
US-0121458
(2009-10-05)
등록번호
US-8523102
(2013-09-03)
국제출원번호
PCT/US2009/059548
(2009-10-05)
§371/§102 date
20110329
(20110329)
국제공개번호
WO2010/096104
(2010-08-26)
발명자
/ 주소
Shue, Shyhpyng Jack
Corrigan, John James
Bird, Eric Thomas
Wood, Tommie Lynn
Ewing, Alan Carl
출원인 / 주소
Textron Innovations Inc.
대리인 / 주소
Walton, James E.
인용정보
피인용 횟수 :
6인용 특허 :
2
초록▼
A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration
A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.
대표청구항▼
1. A reconfigurable flight control system for reconfiguring flight control of an aircraft in response to a failure, the aircraft having flight control actuators and sensors, the reconfigurable flight control system comprising: a control law that is software-implemented and configured to automaticall
1. A reconfigurable flight control system for reconfiguring flight control of an aircraft in response to a failure, the aircraft having flight control actuators and sensors, the reconfigurable flight control system comprising: a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix;a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator, the reconfiguration management tool comprising: a risk factor tool for calculating a risk factor, the risk factor being used for determining whether reconfiguration is necessary;wherein the risk factor is an empirical representation of a control authority of the aircraft, such that a degradation in the control authority effects the risk factor; anda sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during the reconfiguring flight control of the aircraft in response to the failure;wherein the mixing/mapping matrix is configured to mix the usage of the flight control actuators in response to a failing of the failed actuator by employing a first independent actuator system at a first percentage and employing a second independent actuator system at a second percentage, such that the combination of the first independent actuator system and the second independent actuator system produces a desired aircraft flight control response that takes into consideration the failed actuator;wherein the mixing/mapping matrix is configured to continuously change the first percentage and the second percentage to optimize flight control of the aircraft in response to the failed actuator. 2. The reconfigurable flight control system according to claim 1, wherein the risk factor takes into consideration a control power level. 3. The reconfigurable flight control system according to claim 1, wherein the reconfiguration management tool further comprises: an authority for dictating a symmetric control actuator arrangement so as to position a non-failed actuator in a same position as a failed actuator, the non-failed actuator and the failed actuator being symmetric actuators such that symmetric positioning of the non-failed actuator and the failed actuator provides aerodynamic stability to the aircraft. 4. The reconfigurable flight control system according to claim 1, wherein the reconfiguration management tool further comprises: a fault/fail detection tool for detecting a failure of at least one of the flight control sensors and actuators. 5. The reconfigurable flight control system according to claim 1, wherein the reconfiguration management tool is configured for determining whether reconfiguration is necessary based upon a quantity of separate actuator failures. 6. The reconfigurable flight control system according to claim 1, wherein the sensor management tool comprises: a Kalman filter for interpreting a data from the flight control sensors on the aircraft. 7. The reconfigurable flight control system according to claim 1, wherein the sensor management tool is configured to interpret data from the sensors on the aircraft, and provide the interpreted data to a fault/failure detection tool and the reconfiguration management tool. 8. The reconfigurable flight control system according to claim 1, wherein the first independent actuator system uses a differentiate collective power such that a first rotor produces a higher amount of thrust than a second rotor, and wherein the second independent actuator system uses a left and right aircraft flap differential, such that the first independent actuator system and the second independent actuator system act jointly to achieve an aircraft yawing control of the aircraft. 9. The reconfigurable flight control system according to claim 1, wherein the aircraft is a quad tilt rotor. 10. The reconfigurable flight control system according to claim 1, wherein the aircraft is a tilt rotor aircraft. 11. The reconfigurable flight control system according to claim 1, wherein the smoothing any transient conditions that may occur during reconfiguration by the sensor management tool involves the employment of a fader, the fader being used to gradually convert positioning of at least one failed actuator and positioning of at least one reconfigured actuator. 12. The reconfigurable flight control system according to claim 11, wherein the fader is configured to prevent a high amplitude feedback in front of an input side by implementation of a fade block installation. 13. An aircraft comprising: flight control actuators;a fuselage having a forward wing and an aft wing;a first rotor rotatably attached to a left side of the forward wing;a second rotor rotatably attached to a right side of the forward wing;a third rotor rotatably attached to a left side of the aft wing;a fourth rotor rotatably attached to a right side of the aft wing;at least one left forward flap and at least one right forward flap on the forward wing;at least one left aft flap and at least one right aft flap on the aft wing; anda reconfigurable flight control system for selectively reconfiguring involvement of the first rotor, the second rotor, the third rotor, the fourth rotor, the at least one left forward flap, the at least one right forward flap, the at least one left aft flap, and the at least one right aft flap, during a failure of any of the rotors and the flaps, the reconfigurable flight control system comprising: a risk factor tool for calculating a risk factor, the risk factor being used for determining whether reconfiguration is necessary;wherein the risk factor is an empirical representation of a control authority of the aircraft, such that a degradation in the control authority effects the risk factor;a mixing/mapping matrix configured to mix the usage of the flight control actuators in response to the failure of any of the rotors and the flaps by employing a first independent actuator system at a first percentage and employing a second independent actuator system at a second percentage, such that the combination of the first independent actuator system and the second independent actuator system produces a desired aircraft flight control response that takes into consideration the failure of any of the rotors and the flaps;wherein the mixing/mapping matrix is configured to continuously change the first percentage and the second percentage to optimize flight control of the aircraft in response to the failure of any of the rotors and the flaps;wherein the aircraft is configured for flying in an airplane mode wherein the first, second, third, and fourth rotors are rotated to be in a generally horizontal position;wherein the aircraft is configured for flying in a helicopter mode wherein the first, second, third, and further rotors are rotated to be in a generally horizontal position. 14. The aircraft according to claim 13, wherein the reconfigurable flight control system is configured to generate a yawing control of the aircraft while in the airplane mode by selectively differentiating a collective power in the first, second, third, and fourth rotors, in any combination so as to produce a desired differential in thrust between the left side and right side of the aircraft. 15. The aircraft according to claim 13, wherein the reconfigurable flight control system is configured to generate a pitching control of the aircraft while in the airplane mode by selectively actuating the left forward flap, the right forward flap, the left aft flap, and the right aft flap in any combination so as to produce a desired differential of lift between the forward wing and the aft wing of the aircraft. 16. The aircraft according to claim 13, wherein the reconfigurable flight control system is configured to selectively trim and sync a healthy actuator to a same position to that of a failed actuator, when the healthy actuator and the failed actuator are of symmetric positions on the aircraft. 17. A method of automatically reconfiguring flight control of an aircraft, comprising: detecting a failure of an actuator;determining whether reconfiguration is necessary based upon a risk factor, the risk factor is an empirical representation of a control authority of the aircraft, such that a degradation in the control authority effects the risk factor;seamlessly transferring flight control authority from a failed actuator to a back-up actuator; andmanaging the transfer of flight control authority to a back-up actuator with a sensor management tool so as to smooth any transient conditions that may otherwise occur. 18. The method according to claim 17, further comprising; mixing and mapping the use of actuators by continuously changing the percentage usage of each actuator on the aircraft. 19. The method according to claim 17, further comprising: implementing a symmetric control actuator arrangement so as to position a non-failed actuator in a same position as a failed actuator, the non-failed actuator and the failed actuator being symmetric actuators such that symmetric positioning of the non-failed actuator and the failed actuator provides aerodynamic stability to the aircraft.
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이 특허에 인용된 특허 (2)
Urnes, Sr., James M.; Hood, Mark B., Method and system for in-flight fault monitoring of flight control actuators.
Shue, Shyhpyng Jack; Corrigan, John James; Bird, Eric Thomas; Wood, Tommie Lynn; Ewing, Alan Carl, Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws.
Shue, Shyhpyng Jack; Corrigan, John James; Bird, Eric Thomas; Wood, Tommie Lynn; Ewing, Alan Carl, Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws.
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