IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0874657
(2010-09-02)
|
등록번호 |
US-8604741
(2013-12-10)
|
우선권정보 |
FR-09 04272 (2009-09-08) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
▼
A monitoring and control device for an aircraft actuator includes a control module, delivering control signals for the actuator and position signals for the actuator determined according to control messages received from a piloting management system of the aircraft, and at least one first position s
A monitoring and control device for an aircraft actuator includes a control module, delivering control signals for the actuator and position signals for the actuator determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning the position of the actuator, and a monitoring module, delivering position signals for the actuator and receiving the control signals received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor. The control and monitoring modules are capable of assessing the consistency of the signals processed therein and of controlling accordingly a power supply and disabling module of the actuator.
대표청구항
▼
1. A monitoring and control device for an aircraft actuator, comprising: a control module, delivering control signals for the actuator and position signals for the actuator respectively determined according to control messages received from a piloting management system of the aircraft, and at least
1. A monitoring and control device for an aircraft actuator, comprising: a control module, delivering control signals for the actuator and position signals for the actuator respectively determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning a position of the actuator,a monitoring module, delivering actuator position signals and simultaneously receiving the control messages received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor,said control and monitoring modules being capable of assessing a consistency of the signals processed therein and of controlling accordingly an actuator power supply and a disabling module, the actuator being moved by a brushless electric motor, the first position sensor being a Hall-effect type sensor supplying information concerning a rotational positioning of a rotor of the motor, the position of the actuator being determined by the control module based on an initial position datum supplied by the monitoring module,the control module comprising a first simulation module receiving the control messages received from the piloting management system of the aircraft, and simulating a behavior of the actuator and generating a first actuator virtual position signal. 2. The monitoring and control device according to claim 1, in which the initial position datum is supplied to the control module when the monitoring and control device for an actuator is started up. 3. The monitoring and control device according to claim 1, in which the second position sensor is an actuator position sensor. 4. The monitoring and control device according to claim 1, the control module further comprising: an actuation module controlling the actuator via the power supply and disabling module,a first position processing module processing the data originating from the first position sensor and generating and sending to the actuation module a first signal representative of the position of the actuator. 5. The monitoring and control device according to claim 4, in which the monitoring module comprises a second position processing module processing the data originating from the second position sensor and generating a second signal representative of the position of the actuator. 6. The monitoring and control device according to claim 1, in which the monitoring module comprises a second simulation module receiving the control messages received from the piloting management system of the aircraft, and simulating the behavior of the actuator and generating a second actuator virtual position signal. 7. The monitoring and control device according to claim 1, comprising a first comparator, the output of which changes from one nominal logic level to the other if the first actuator virtual position signal differs from the first signal representative of the position of the actuator by a value greater than a first determined threshold. 8. The monitoring and control device according to claim 7, comprising a second comparator, the output of which changes from one nominal logic level to the other if a control signal received by the control module differs from the control signal received simultaneously by the monitoring module by a value greater than a second determined threshold. 9. The monitoring and control device according to claim 8, comprising a third comparator, the output of which changes from one nominal logic level to the other if the second actuator virtual position signal differs from the second signal representative of the position of the actuator by a value greater than a third determined threshold. 10. The monitoring and control device according to claim 9, comprising a fourth comparator, the output of which changes from one nominal logic level to the other if the first signal representative of the position of the actuator differs from the second signal representative of the position of the actuator by a value greater than a fourth determined threshold. 11. The monitoring and control device according to claim 1, in which the power supply and disabling module comprises: a power supply module powered by a main power supply voltage, and processing the power supply signal to generate the power supply signals for the various modules forming the monitoring and control device;a power distribution module, generating, on the basis of the information supplied by the actuation module, a modulated signal to control the motor, and responsible for freezing or disabling the actuator in the event of failure, detected on the basis of a summary logic signal dependent at least on the logic level of the outputs of the comparators. 12. The monitoring and control device according to claim 11, in which the power supply and disabling module comprises, on the main power supply line, a power breaker, a first current measuring device, in series with which is arranged a power bridge, the power bridge comprising a top switch in series with a bottom switch and generating the modulated control signal for the motor, the power breaker and said switches being controlled by said summary logic signal. 13. The monitoring and control device according to claim 12, in which the power breaker, the switches and the motor are controlled via logic switchers: a first logic switcher controlling the power breaker, and being maintained by a dynamic signal of determined frequency,a second logic switcher controlling the switches, and being maintained by a dynamic signal of determined frequency,a third logic switcher controlling the activation of the modulated control signal for the motor. 14. The monitoring and control device according to claim 13, in which the motor is a brushless-type motor with three windings, the top switch and the bottom switch each being formed by three field-effect transistors respectively associated with each winding of the motor. 15. The monitoring and control device according to claim 11, in which the summary logic signal is also conditioned by logic results of correct operation tests on the modules forming the monitoring and control device. 16. The monitoring and control device according to claim 13, in which the freezing or disabling of the actuator is also controlled by logic disabling signals from the flight management system. 17. The monitoring and control device according to claim 1, in which the control module and the monitoring module are implemented in at least one programmable logic circuit. 18. The monitoring and control device according to claim 17, in which the control module is implemented in a first programmable logic circuit, and the monitoring module is implemented in a second programmable logic circuit. 19. The monitoring and control device according to claim 18, in which the control module and the monitoring module are associated with one and the same power supply circuit. 20. The monitoring and control device according to claim 18, in which the control module and the monitoring module are each associated with a dedicated power supply circuit. 21. The monitoring and control device according to claim 1, in which the control module, the monitoring module, the actuator, the position sensors and the power supply and disabling module are integrated in one physical module.
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