[특허]Response mode for control system of piloted craft

National Research Council of Canada

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특허 상세정보

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Response mode for control system of piloted craft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00 B64C-019/00
미국특허분류(USC)	701/003; 244/075.1
출원번호	US-0516381 (2009-12-18)
등록번호	US-8688295 (2014-04-01)
국제출원번호	PCT/CA2009/001866 (2009-12-18)
§371/§102 date	20120615 (20120615)
국제공개번호	WO2011/072362 (2011-06-23)
발명자 / 주소	Ellis, Kristopher Gubbels, Arthur W.
출원인 / 주소	National Research Council of Canada
대리인 / 주소	Davis, Jason
인용정보	피인용 횟수 : 3 인용 특허 : 12

초록
▼

Frequency multiplexed command signaling that permits a single pilot command interface (e.g. control stick) to serve as a multiple response mode interface for piloting a craft conforms with natural interface operation of most pilots. Highly augmented modes receive lower frequency components of the command signaling, and less augmented modes receive higher frequency components. This avoids the requirement for pilots to switch response modes. An embodying control system can be produced by running feedback control loops encoding the respective response modes in parallel, and multiplexing the command signaling to each response mode, filtering each copy of the command signaling respectively according the respective feedback control loop, and then combining the output of each feedback control loop to compute actuation demand.

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청구항
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1. At least one processor encoded with at least two response modes with a first response mode having a higher stability augmentation than a second response mode, the response modes adapted to use command signaling from a pilot command interface of a craft, and orientation and motion feedback from the craft, to generate information that is collectively used to redirect the craft, where the at least one processor is adapted: to receive the command signaling in two parts, a first part having more lower frequency than higher frequency components of the command signaling, and a second part having more higher frequency than lower frequency components of the command signaling; and to process the first part according the first response mode, and the second part according to the second response mode. 2. The at least one processor according to claim 1 further adapted to divide the command signaling into the two parts in dependence on the orientation and motion feedback. 3. The at least one processor according to claim 1 wherein the craft is an aircraft, the orientation and motion feedback are aircraft state data, and the at least two response modes are embodied as separate processes for computing actuator demand. 4. The at least one processor according to claim 3 that provides the components of the command signaling to the separate processes. 5. The at least one processor according to claim 4 wherein the at least one processor includes a respective processor for each of the separate processes. 6. The at least one processor according to claim 4 further comprising a hub for multicasting the command signaling coupled to respective filters, each filter adapted to filter out frequency components of the command signaling that are not sent to the respective process to which the filter is communicatively coupled. 7. The at least one processor according to claim 6 wherein the filters have controllable transmission properties and the at least one processor is further adapted to provide a process for changing the filter properties in response to the aircraft state data. 8. The at least one processor according to claim 3 wherein the at least one processor is further adapted to provide a combining process for combining actuator demand from the respective separate processes to produce a combined control output for redirecting the aircraft. 9. The at least one processor according to claim 8 wherein the combining process is adapted to produce a weighted sum of the actuator demand from the respective separate processes, the weighting applied depending on recent operating conditions of the craft. 10. A method for generating actuator demand for redirecting a craft in response to command signaling from a pilot command interface, and craft orientation and motion feedback, the method comprising: encoding, in one or more processors, at least two response modes of differing stability augmentation;dividing the command signaling into at least two parts by a circuit, wherein a first part has more lower frequency than higher frequency command signaling components, and a second part has more higher frequency than lower frequency command signaling components; andsubmitting the divided parts to respective response modes so that the first part is processed by more highly augmented response modes, and the second part is processed by less augmented response modes, the response modes collectively generating information for determining the actuator demand. 11. The method according to claim 10 wherein dividing the command signaling into the at least two parts is controlled in dependence on the orientation and motion feedback. 12. The method according to claim 10 wherein the craft is an aircraft, the orientation and motion feedback are aircraft state data, and dividing the command signaling comprises multicasting the command signaling to respective filters, and submitting the divided parts comprises forwarding filtered parts of the command signaling to respective feedback control loops for independent processing of the respective filtered parts. 13. The method according to claim 10 further comprising combining control output of the respective response modes to produce a combined control output for redirecting the craft. 14. An aircraft control system comprising: a command interface for generating command signaling;at least one processor defining a first and a second feedback control loop encoding respective first and second response types for deriving flight control output in response to the command signaling, aircraft state data, and flight control laws of the aircraft, the first response type having a lower degree of augmentation than the second response type;a circuit communicatively coupling the at least one processor and the command interface for dividing the command signaling into at least two parts, wherein a first part has more lower frequency than higher frequency command signaling components, and a second part has more higher frequency than lower frequency command signaling components;wherein the at least one processor processes the first part according to the first response type, and the second part according to the second response type. 15. The aircraft control system of claim 14 wherein the aircraft is a rotorcraft, and the response type encoded by one of the feedback control loops is one of: rate damped, attitude command/attitude hold, translational rate command, and position hold. 16. The aircraft control system of claim 14 wherein the aircraft is a fixed wing aircraft and the response type encoded by one of the feedback control loops is based on control of: orientation of a fuselage of the aircraft, or a rate of change thereof, or an acceleration thereof, an airspeed or rate of change thereof, a position over ground, ground speed or a rate of change of ground speed, an altitude, rate of change thereof, or acceleration thereof, or a flight path angle or a rate of change therein. 17. The aircraft control system of claim 14 wherein the circuit permits a controllable frequency bandwidth of the command signaling to be forwarded to the respective feedback control loops, and the aircraft control system further comprises a feedback controller for adjusting the frequency bandwidth forwarded to the respective control loops in dependence on the aircraft state data. 18. The aircraft control system of claim 17 wherein the circuit comprises a hub for multicasting the command signaling to the feedback control loops via respective tunable filters. 19. The method according to claim 10 wherein the circuit is a part of the one or more processors. 20. An aircraft control system comprising: at least one processor encoded with at least two response types of differing stability augmentation, the response types adapted to use command signaling from a pilot interface of the aircraft, aircraft state data, and flight control laws of the aircraft, to generate information that is collectively used to redirect the craft; anda circuit communicatively coupled to the at least one processor for dividing the command signaling into at least two parts, wherein a first part has more lower frequency than higher frequency command signaling components, and the second part has more higher frequency than lower frequency command signaling components; wherein the at least one processor is configured to process the first part according to the first response type, and the second part according to the second response type.

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Response mode for control system of piloted craft

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Response mode for control system of piloted craft

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