[특허]Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor

Eurocopter

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특허 상세정보

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Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/50
미국특허분류(USC)	244/006; 244/017.11; 416/142
출원번호	US-0375707 (2003-02-27)
우선권정보	FR-0003013 (2002-03-11)
발명자 / 주소	Romani, Michel Cayol, Marcel
출원인 / 주소	Eurocopter
대리인 / 주소	Sturm & Fix LLP
인용정보	피인용 횟수 : 10 인용 특허 : 6

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To fold/unfold blades of a rotor, at least one variable-length linear actuator is removably attached to two blades locked in the flight position. A first blade is unlocked, and the actuator is actuated to vary its length and bear against the other blade which remains locked. This causes the first blade to pivot about its pivot axis and move to a folded position where it is again locked. The other blade is then unlocked and the actuator once again actuated but this time bearing against the first blade. In this way the other blade pivots into the folded position where it is again locked. The two locked folded blades may be connected to each other by a link rod. Rotors with three blades, four blades, five and six blades can be folded/unfolded with only two actuators. angential thrusters are arranged to selectively produce a tangential thrust vector, wherein the tangential thrust vector is tangential to the axial thrust to control rotation of the vehicle around the axial thrust vector. 11. A system as in claim 10 wherein the at least two tangential thrusters, each further comprise at least one mass expulsion device. 12. The system of claim 1 wherein the thrust vector controller operates synchronously with the at least one reaction control system. 13. The system of claim 1 wherein the at least one reaction control system is combined with the thrust vector controller. 14. The system of claim 13 wherein the combined at least one reaction control system and thrust vector controller provides simultaneous attitude control of torque applied by the main thrust generator and a rotation of the main thrust generator thrusting subsystem. 15. The system of claim 1 wherein the at least one reaction control system responds to signals with a relatively fast band pass to control short-term dynamic disturbance and the thrust vector controller is adapted to reposition an engine thrust vector. 16. The system of claim 1 wherein the thrust vector controller eliminates principal rocket attitude disturbance. 17. The system of claim 1 wherein the thrust vector controller controls slow dynamical motions and the at least one reaction control system controls rapid dynamical motions. 18. An attitude control system for controlling momentum vector force about a center of gravity of a rocket, the rocket having a central axis, the system comprising: a main propulsion nozzle having a main propulsion axis, the main propulsion nozzle disposed aft of the center of gravity; a main chamber providing a propelling gas to said main propulsion nozzle; a reaction control system, wherein the reaction control system is disposed forward of the center of gravity, wherein the reaction control system comprises a plurality of radial nozzles, wherein the plurality of radial nozzles are selectively and independently controlled; at least aerodynamic vane, the at least one aerodynamic vane having a leading edge, wherein the leading edge is positioned in the direction of travel; and a synchronizer for controlling an angle of attack of the at least one controllable aerodynamic vane and the plurality of radial nozzles. 19. An attitude control system as in claim 18, wherein the propelling gas is generated by gas generating means for generating said propelling gas selected from the group consisting of liquid propellant, solid propellant, steam and compressed gas. 20. An attitude control system as in claim 18, wherein the plurality of radial nozzles are symmetrically arranged around the periphery of the body in a common plane, wherein the common plane is at a right angle to the central axis. 21. The apparatus as set forth in claim 18, wherein the plurality of radial nozzles are arranged in non-common planes around the periphery of the body, wherein the non-common planes are at right angles to the central axis. 22. The apparatus as set forth in claim 18, wherein the plurality of radial nozzles are mounted flush with an outer surface of the body. 23. The apparatus as set forth in claim 18, wherein the plurality of radial nozzles comprises at least two straight radial nozzles. 24. The apparatus as set forth in claim 23, wherein the plurality of radial nozzles further comprises at least one tangentially canted radial nozzle, wherein the force generated by the at least one tangentially canted radial nozzle is orthogonal with respect to the central axis. 25. A rocket controller, the rocket controller disposed within a rocket, the rocket having forward and aft sections, a central axis, and a dynamic center of gravity, wherein the rocket controller comprises: at least one first thrust generator, wherein the at least one first thrust generator is located aft of the dynamic center of gravity; at least one first thrust vector controller, wherein the at least one first thrust vector controller controls the at least one first thrust generator; at least one second thrust generator, wherein the at least one second thrust generator is located forward of the dynamic center of gravity; and at least one second thrust vector controller, wherein the at least one second thrust vector controls the at least one second thrust generator. 26. A rocket controller as in claim 25 wherein the at least one second thrust vector controller is synchronized with the at least one first thrust vector controller. 27. A rocket controller as in claim 25, wherein the at least one first thrust generator comprises thrust propelling gas, wherein the thrust propelling gas is generated by gas generating means for generating said propelling gas selected from the group consisting of liquid propellant, solid propellant, steam and compressed gas. 28. A rocket controller as in claim 25, wherein the at least one second thrust generator comprises thrust propelling gas, wherein the thrust propelling gas is generated by gas generating means for generating said propelling gas selected from the group consisting of liquid propellant, solid propellant, steam and compressed gas. 29. A rocket controller as in claim 25, wherein the at least one second thrust generator comprises a plurality of radial nozzles, wherein the plurality of radial nozzles are symmetrically arranged around the rocket periphery in a common plane, wherein the common plane is at a right angle to the central axis. 30. A method for synchronizing forward and aft thrust vector control for a body traveling in a fluid, the body for minimizing fluid resistance and having forward and aft sections, primary thrust generator disposed in the aft section, and a secondary thrust generator disposed in the forward section, the method comprising the steps of: initiating the primary thrust generator; calculating a dynamic center of gravity for the traveling body; calculating a principal thrust axis generated by the primary thrust generator; determining an offset between the principal thrust axis and the dynamic center of gravity; and adjusting the offset to a predetermined value. 31. A method as in claim 30 wherein the step of adjusting the offset to the predetermined value further comprises the steps of: calculating a torque required to adjust the offset to the predetermined value; initiating the secondary thrust generator to apply the calculated torque; and steering the primary thrust generator to adjust the offset to the predetermined value. 32. A method as in claim 30 wherein the step of initiating the secondary thrust generator further comprises the step of adjusting a duty cycle of the secondary thrust generator. 33. A program storage device readable by a machine, tangibly embodying a program of instructions executable by the machine to perform method steps for synchronizing forward and aft thrust vector control for a body traveling in a fluid, the body for minimizing fluid resistance and having forward and aft sections, a primary thrust generator disposed in the aft section, and a secondary thrust generator disposed in the forward section, said method steps comprising: initiating the primary thrust generator; calculating a dynamic center of gravity for the traveling body; calculating a principal thrust axis generated by the primary thrust generator; determining an offset between the principal thrust axis and the dynamic center of gravity; and adjusting the offset to a predetermined value, wherein the step of adjusting the offset further comprises the steps of: calculating a torque required to adjust the offset to the predetermined value; initiating the secondary thrust generator to apply the calculated torque; and steering the primary thrust generator to adjust the offset to the predetermined value.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 10

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특허 상세정보

Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor

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이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 10

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Method and apparatus for folding/unfolding the blades of a rotary-wing aircraft rotor

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이 특허에 인용된 특허 (6)

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