Fault tolerant electronic control architecture for aircraft actuation system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/42
G05D-001/00
B64C-009/16
출원번호
US-0780328
(2014-05-29)
등록번호
US-9988139
(2018-06-05)
국제출원번호
PCT/US2014/040032
(2014-05-29)
국제공개번호
WO2014/194097
(2014-12-04)
발명자
/ 주소
Neely, John David
Seely, Stanley Lawrence
White, John Mendenhall
출원인 / 주소
Eaton Intelligent Power Limited
대리인 / 주소
Fishman Stewart PLLC
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback fr
An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.
대표청구항▼
1. A system having a control architecture for an aircraft, comprising: a multi-channel controller including a first channel and a second channel that are redundantly paired with a single physical component of said aircraft, wherein the first and second channels are operationally coupled to alternate
1. A system having a control architecture for an aircraft, comprising: a multi-channel controller including a first channel and a second channel that are redundantly paired with a single physical component of said aircraft, wherein the first and second channels are operationally coupled to alternate between an active operational status and an inactive operational status;the first channel in the active operational status being configured to receive one or more inputs comprising a movement command, to produce an output to control a movement of the single physical component of said aircraft based on the one or more inputs, and to receive feedback from the single physical component respective of the movement of the single physical component, the first channel comprising a fault detection module configured to compare the feedback to the movement command to determine if the first channel is functioning properly; andthe second channel in the inactive operational status being configured for redundant functionality while the first channel is in the active operational status and to receive the one or more inputs of the first channel and, in response to the first channel not functioning properly based on the fault detection module of the first channel, switch to the active operational status to produce an output to control the movement of the single physical component while the first channel switches to the inactive operational status. 2. The system of claim 1, wherein the second channel is in communication with the first channel, further wherein the first channel informs the second channel when the fault detection module determines that the first channel is not functioning properly. 3. The system of claim 1, wherein the single physical component comprises one or more of an electromechanical actuator, a hydraulic actuator, an actuator brake, and a motor brake. 4. The system of claim 3, wherein the single physical component is mechanically coupled with an aircraft flap. 5. The system of claim 1, wherein the fault detection module is a first module, the system further comprising a second module configured to generate the output, wherein the first module is independent of the second module. 6. The system of claim 5, wherein the second module is a processing module. 7. The system of claim 6, wherein the processing module is a first processing module, wherein the second channel comprises a second processing module. 8. The system of claim 1, wherein the feedback is received from a sensor coupled to the single physical component. 9. The system of claim 8, wherein the sensor comprises one or more of a rotary motor position sensor, and an absolute position sensor. 10. The system of claim 1, wherein the second channel is configured to not produce an output to control movement of the single physical component unless the first channel is not functioning properly. 11. A method of controlling a movement of an aircraft component, the method comprising: providing a multi-channel controller including a first channel and a second channel that are redundantly paired with the aircraft component, wherein the first and second channels are operationally coupled to alternate between an active operational status and an inactive operational status;receiving, with the first channel in the active operational status, one or more inputs comprising a movement command;producing, with the first channel, an output to control the movement of the aircraft component based on the one or more inputs,receiving feedback from the aircraft component respective of the movement of the aircraft component;comparing the feedback to the movement command to determine if the first channel is functioning properly; andreceiving, with the second channel in the inactive operational status being configured for redundant functionality while the first channel is in the active operational status, the one or more inputs of the first channel and, in response to the first channel not functioning properly based on a fault detection module of the first channel, switch to the active operational status to produce an output with the second channel to control the movement of the aircraft component while the first channel switches to the inactive operational status. 12. The method of claim 11, wherein the second channel is in communication with the first channel, wherein the method further comprises: receiving, with the second channel and from the first channel, an indication that the first channel is not functioning properly. 13. The method of claim 11, wherein the aircraft component comprises one or more of an electromechanical actuator, a hydraulic actuator, an actuator brake, and a motor brake. 14. The method of claim 11, wherein the feedback is received from a sensor coupled to the aircraft component. 15. The method of claim 14, wherein the sensor comprises one or more of a rotary motor position sensor, and an absolute position sensor. 16. The method of claim 11, wherein producing an output with the second channel to control movement of the aircraft component is only performed if the first channel is not functioning properly. 17. The method of claim 11, wherein comparing the feedback to the command to determine if the first channel is functioning properly is performed by a fault detection module associated with the first channel. 18. The method of claim 17, wherein comparing the feedback to the command to determine if the first channel is functioning properly is also performed by a fault detection module associated with the second channel. 19. A control architecture for an aircraft system, comprising: a multi-channel controller including a first channel and a second channel that are redundantly paired with a single physical component of said aircraft system, wherein the first and second channels are operationally coupled to alternate between an active operational status and an inactive operational status;the first channel comprising: a processing module in the active operational status being configured to receive one or more inputs comprising a movement command and to produce an output to control a movement of the single physical component based on the one or more inputs, anda fault detection module configured to receive feedback from the single physical component respective of the movement of the single physical component and compare the feedback to the movement command to determine if the first channel is functioning properly; andthe second channel in the inactive operational status being configured for redundant functionality while the first channel is in the active operational status and to receive the one or more inputs of the first channel and, in response to the first channel not functioning properly based on the fault detection module of the first channel, switch to the active operational status to produce an output to control the movement of the single physical component while the first channel switches to the inactive operational status. 20. The control architecture of claim 19, wherein the second channel comprises a processing module configured to receive the one or more inputs and to produce an output signal.
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