[특허]Active dihedral control system for a torisionally flexible wing

AeroVironment Inc.

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Active dihedral control system for a torisionally flexible wing

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/38 B64C-017/00 B64C-003/42 B64C-003/52 B64C-015/02 B64C-039/02 B64C-039/10 B64D-027/24 B64D-031/06 H04B-007/185
출원번호	US-0804988 (2010-08-02)
등록번호	US-9120555 (2015-09-01)
발명자 / 주소	Kendall, Greg T. Lisoski, Derek L. Morgan, Walter R. Griecci, John A.
출원인 / 주소	AeroVironment Inc.
대리인 / 주소	Aagaard, Esq., Eric J.
인용정보	피인용 횟수 : 0 인용 특허 : 58

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A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each oth...

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1. A flying wing aircraft, comprising: a laterally extending wing having a spanwise axis; wherein the wing has high torsional flexibility about the spanwise axis;a plurality of independently actuatable control surfaces; wherein the control surfaces are spaced apart along the span of the wing and connected thereto;a plurality of sensors connected to the wing; anda control system programmed to actively control the plurality of control surfaces based upon structural information data received from the plurality of sensors; wherein the control system independently actuates the control surfaces to alter local lift of wing portions at the location of each control surface in order to alter the dihedral of the wing. 2. The flying wing aircraft of claim 1, wherein the wing comprises a plurality of interconnected wing segments. 3. The flying wing aircraft of claim 1, wherein each control surface is a pitch-control device mounted on a boom extending aft from a trailing edge of the wing. 4. The flying wing aircraft of claim 1, wherein the plurality of sensors include at least one of a vertical wing bending sensor, a fore-and-aft wing bending sensor, and/or a wing torsion sensor. 5. The flying wing aircraft of claim 1, further comprising: a plurality of motors connected to the wing; anda plurality of propellers connected to the motors; wherein the control system independently controls the thrust of the plurality of motors in order to alter fore-and-aft bending of the wing in order to alter fore-and-aft wing loads between the motors. 6. The flying wing aircraft of claim 5, wherein each control surface is a pitch-control device mounted on a boom extending aft from a trailing edge of the wing; and wherein one of the plurality of motors and propellers is connected to a leading edge of the wing at the spanwise location of each of said booms. 7. The flying wing aircraft of claim 1, wherein the control surfaces comprise fixed and controllable horizontal surfaces. 8. The flying wing aircraft of claim 1, further comprising: a plurality of solar cells connected to the wing;wherein the solar cells provide power to the aircraft for flight. 9. An aircraft, comprising: a fuselage;a laterally extending wing having a spanwise axis; wherein the wing has high torsional flexibility about the spanwise axis;a plurality of independently actuatable control surfaces; wherein the control surfaces are spaced apart along the span of the wing and connected thereto;a plurality of sensors connected to the wing; anda control system programmed to actively control the plurality of control surfaces based upon structural information data received from the plurality of sensors; wherein the control system independently actuates the control surfaces to alter local lift of wing portions at the location of each control surface in order to alter the dihedral of the wing. 10. The aircraft of claim 9, wherein the wing comprises a plurality of interconnected wing segments. 11. The aircraft of claim 9, wherein each control surface is a pitch-control device mounted on a boom extending aft from a trailing edge of the wing. 12. The aircraft of claim 9, wherein the plurality of sensors include at least one of a vertical wing bending sensor, a fore-and-aft wing bending sensor, and/or a wing torsion sensor. 13. The aircraft of claim 9, further comprising: a plurality of motors connected to the wing; anda plurality of propellers connected to the motors; wherein the control system independently controls the thrust of the plurality of motors in order to alter fore-and-aft bending of the wing in order to alter fore-and-aft wing loads between the motors. 14. The aircraft of claim 13, wherein each control surface is a pitch-control device mounted on a boom extending aft from a trailing edge of the wing; and wherein one of the plurality of motors and propellers is connected to a leading edge of the wing at the spanwise location of each of said booms. 15. The aircraft of claim 9, wherein the control surfaces comprise fixed and controllable horizontal surfaces. 16. The aircraft of claim 9, further comprising: a plurality of solar cells connected to the wing; wherein the solar cells provide power to the aircraft for flight. 17. A method of controlling an aircraft comprising the steps of: providing an aircraft having: a laterally extending wing having a spanwise axis; wherein the wing has high torsional flexibility about the spanwise axis;a plurality of independently actuatable control surfaces; wherein the control surfaces are spaced apart along the span of the wing and connected thereto;a plurality of sensors connected to the wing;a control system programmed to actively control the plurality of control surfaces based upon structural information data received from the plurality of sensors; andindependently actuating the control surfaces to alter local lift of wing portions at the location of each control surface to alter the dihedral of the wing. 18. The method of controlling an aircraft according to claim 17, wherein the wing has a large aspect ratio and a constant chord length; wherein the high torsional flexibility, large aspect ratio, and constant chord length cause the wing to develop a substantial dihedral angle at the wingtips in flight, further comprising the steps of: directing outboard control surfaces to actuate downwardly;directing inboard control surfaces to actuate upwardly; anddeflecting the wing in the spanwise direction to reduce and/or eliminate wing dihedral. 19. The method of controlling an aircraft according to claim 18, further comprising the step of: directing outboard control surfaces to actuate downwardly;directing inboard control surfaces to actuate upwardly; anddeflecting the wing in the spanwise direction to produce a negative dihedral. 20. The method of controlling an aircraft according to claim 17, further comprising the steps of: independently actuating the plurality of independently actuatable control surfaces to alter the local lift of wing portions to deflect the wing into a W-shape or M-shape along the spanwise axis.

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Active dihedral control system for a torisionally flexible wing

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Active dihedral control system for a torisionally flexible wing

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이 특허에 인용된 특허 (58)

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