[특허]Vehicle control systems and corresponding sizing methods

The Boeing Company

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특허 상세정보

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Vehicle control systems and corresponding sizing methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-005/10 B64C-005/00 B64C-009/00 G06F-007/00
미국특허분류(USC)	701/003; 244/090.R; 244/225; 244/229
출원번호	US-0770256 (2004-02-02)
등록번호	US-7424350 (2008-09-09)
발명자 / 주소	Speer,Thomas E.
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 7 인용 특허 : 222

초록
▼

Vehicle control systems and methods for sizing such systems are disclosed. In one embodiment of the invention, an actuator mechanism capability is selected, at least one operating requirement is selected, and the required number, size, and locations of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined. In another embodiment, a set of control laws is selected, at least one operating requirement is selected, and the number size, and location of a plurality of control surfaces needed to satisfy the at le...

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I claim: 1. A portion of a vehicle control system, comprising: at least one external fluid flow body having a forward portion with a first flow surface, a second flow surface facing opposite the first flow surface, and a trailing edge at a juncture of the first flow surface and the second flow surface, the trailing edge having a span extending from a first trailing edge tip to a second trailing edge tip; a plurality of control surfaces, each having at least a portion aft of the trailing edge of the external fluid flow body, the control surfaces being movable relative to the at least one external fluid flow body to control forces and moments on the external fluid flow body by interacting with an adjacent flow field; and a plurality of electro hydraulic actuator mechanisms, each having an approximately identical control capability, wherein the control capability includes approximately identical maximum actuation rate and approximately identical maximum actuation force, at least one actuator mechanism being coupled to each of the control surfaces to actively position the control surfaces in response to command signals, wherein the plurality of actuator mechanisms are the only actuator mechanisms coupled to the control surfaces to actively move the control surfaces in response to the command signals. 2. The system of claim 1 wherein the control surfaces are distributed across at least approximately the entire span of the trailing edge. 3. The system of claim 1 wherein the control surfaces are installed on an aircraft and wherein at least one of the control surfaces can be positioned to cause the aircraft to roll, increase a drag of the aircraft, or both. 4. The system of claim 1 wherein the control capability includes a maximum actuation rate. 5. The system of claim 1 wherein the control capability includes a maximum actuation force. 6. The system of claim 1 wherein the control capability includes a maximum actuation rate and a maximum actuation force. 7. The system of claim 1 wherein the actuator mechanisms each include a single actuator. 8. The system of claim 1 wherein the actuator mechanisms each include at least two actuators. 9. The system of claim 1 wherein the actuator mechanisms each include a hydraulic actuator. 10. The system of claim 1 wherein at least one of the control surfaces is coupled to two actuator mechanisms. 11. The system of claim 1 wherein the external fluid flow body includes an airfoil coupled to an aircraft and wherein the span is noncontinuous, with a first span portion extending from the first trailing edge tip to a first portion of the aircraft and a second span portion extending from a second portion of the aircraft to the second trailing edge tip, and wherein the plurality of control surfaces are distributed across at least approximately the entire first span portion and the entire second span portion. 12. The system of claim 1 wherein the at least one external fluid flow body includes an airfoil, the airfoil extending through an aircraft fuselage, the span being noncontinuous, with a first span portion extending from the first trailing edge tip to a first side of the aircraft fuselage and a second span portion extending from a second side of the aircraft fuselage to the second trailing edge tip, and wherein the control surfaces are distributed across at least approximately the entire first span portion and the entire second span portion. 13. The system of claim 1 wherein the at least one external fluid flow body includes a forward portion of a wing coupled to an aircraft, the forward portion of the wing having a trailing edge, the span extending from a first trailing edge tip of the forward portion of the wing to a second trailing edge tip of the forward portion of the wing, and wherein the plurality of control surfaces are distributed across at least approximately the entire span. 14. The system of claim 1 wherein the control surfaces include control surfaces on both sides of a vehicle longitudinal axis, and wherein the plurality of actuator mechanisms includes multiple actuator mechanisms having an approximately identical control capability and located on the same side of the vehicle longitudinal axis. 15. An aircraft, comprising: a fuselage; a forward wing portion, the forward wing portion having a leading edge and a trailing edge, the trailing edge of the forward wing portion having a span extending from a first trailing edge tip to a second trailing edge tip; a plurality of control surfaces, each having at least a portion positioned aft of the trailing edge, the control surfaces being distributed across at least approximately the entire span of the trailing edge, the control surfaces being movable relative to the forward wing portion to control forces and moments on the forward wing portion by interacting with an adjacent flow field; and a plurality of electro hydraulic actuator mechanisms, each having an approximately identical control capability, wherein the control capability includes approximately identical maximum actuation rate and approximately identical maximum actuation force, each actuator mechanism being coupled to a control surface to actively position the corresponding control surface in response to command signals, wherein the plurality of actuator mechanisms are the only actuator mechanisms coupled to the control surfaces to actively move the control surfaces in response to the command signals. 16. The system of claim 15 wherein the span is noncontinuous and includes a first span portion extending from the first trailing edge tip to a first side of the fuselage and a second span portion extending from a second side of the fuselage to a second trailing edge tip, and wherein the multiple control surfaces are distributed across at least approximately the entire first span portion and the entire second span portion. 17. The system of claim 15 wherein the forward wing portion includes a forward portion of a supercritical airfoil, and wherein at least one of the control surfaces is coupled to the forward portion of the supercritical airfoil, the at least one control surface being configured to change a physical characteristic of a slot, defined by the forward portion of the supercritical airfoil and the at least one control surface, as the at least one control surface is actively positioned. 18. The system of claim 15 wherein the control surfaces include control surfaces on both sides of a longitudinal axis of the fuselage, and wherein the plurality of actuator mechanisms includes multiple actuator mechanisms having an approximately identical control capability and located on the same side of the longitudinal axis of the fuselage.

이 특허에 인용된 특허 (222)

이 특허를 인용한 특허 피인용횟수: 7

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Vehicle control systems and corresponding sizing methods

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이 특허에 인용된 특허 (222)

이 특허를 인용한 특허 피인용횟수: 7

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Vehicle control systems and corresponding sizing methods

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이 특허에 인용된 특허 (222)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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