[특허]Control linkage for T-tail aircraft elevator surfaces

Hawker Beechcraft Corporation

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Control linkage for T-tail aircraft elevator surfaces

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/04 B64C-013/00 B64C-009/00 B64C-003/38 B64C-003/00 B64C-005/10 B64C-005/00 F16C-007/00
미국특허분류(USC)	244/225; 244/220; 244/087; 244/090.R; 244/099.2; 074/579.R; 074/585; 074/580
출원번호	US-0003788 (2004-12-02)
등록번호	US-7331548 (2008-02-19)
발명자 / 주소	Simkulet,Michael W.
출원인 / 주소	Hawker Beechcraft Corporation
대리인 / 주소	O'Keefe, Egan, Peterman & Enders LLP
인용정보	피인용 횟수 : 6 인용 특허 : 29

초록
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Systems and methods for implementing control linkages that may be employed to produce synchronous motion in two adjacent controlled devices controlled by a common input. In one example implementation, a semi-rigid modified constant velocity (CV) joint control linkage may be provided that is laterally self-stabilizing. The modified constant velocity CV joint control linkage may include an input push rod assembly that is self-aligning, deflectable and of an adjustable length. The CV joint may be configured with a central cage that is allowed to skew to all...

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What is claimed is: 1. A control linkage mechanism for producing synchronous motion in two adjacent elevator surfaces of a T-tail aircraft, comprising: a first universal joint yoke assembly configured for coupling to control a first one of said adjacent elevator surfaces of a T-tail aircraft that is rotatably attached to a horizontal stabilizer of a tail assembly of said aircraft; a second universal joint yoke assembly configured for coupling to control a second one of said adjacent elevator surfaces of a T-tail aircraft that is rotatably attached to a horizontal stabilizer of said tail assembly of said aircraft; a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly; and an input push rod assembly having a first end coupled to said central cage and a self aligning second end configured for coupling to a control input device; wherein said first universal joint yoke assembly is configured to rotate in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage; and wherein said adjacent elevator surfaces are swept elevator surfaces of a T-tail aircraft having hinge lines that are skewed relative to each other; wherein said first universal joint assembly comprises two first yoke uprights attached by a first cross bolt extending between said two first yoke uprights at a right angle to a hinge line of said first one of said adjacent elevator assemblies; and wherein said second universal joint assembly comprises two second yoke uprights attached by a second cross bolt extending between said two second yoke uprights at a right angle to a hinge line of said second one of said adjacent elevator assemblies. 2. The control linkage mechanism of claim 1, further comprising a push rod deflection mechanism configured to laterally deflect said input push rod assembly. 3. The control linkage mechanism of claim 2, wherein said push rod deflection mechanism comprises a lockable eccentric cam assembly, said lockable eccentric cam assembly being configured to deflect said input push rod assembly laterally about a rod deflection pivot point. 4. The control linkage mechanism of claim 1, wherein said self aligning second end comprises a self-aligning rod end bearing. 5. The control linkage mechanism of claim 1, wherein said first universal joint assembly comprises two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle; wherein said second universal joint yoke assembly comprises two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle; wherein said central cage is coupled between said first hinge axle of said first universal joint yoke assembly and said second hinge axle of said second universal joint yoke assembly; and wherein said first universal joint yoke assembly is configured to rotate about said first hinge axle in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate about said second hinge axle in multiple planes relative to said central cage. 6. A dual elevator system for an aircraft having a vertical stabilizer and a horizontal stabilizer attached to said vertical stabilizer, said dual elevator system comprising: a first elevator assembly, said first elevator assembly having a first elevator surface and a first elevator hinge, said first elevator hinge being rotatably attached to said horizontal stabilizer of said aircraft; a second elevator assembly, said second elevator assembly having a second elevator surface and a second elevator hinge, said second elevator hinge being rotatably attached to said horizontal stabilizer of said aircraft; and a modified constant velocity joint control linkage mechanism that comprises: a first universal joint yoke assembly having a yoke axle coupled to said first elevator hinge, a second universal yoke assembly having a yoke axle coupled to said second elevator hinge, a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly, and an input push rod assembly having a first end coupled to said central cage and a self-aligning second end coupled to a control lever, said control lever being fixedly attached to said vertical stabilizer of said aircraft. 7. The dual elevator system of claim 6, wherein said aircraft is a T-tail aircraft; and wherein said horizontal stabilizer is supported by said vertical stabilizer. 8. The dual elevator system of claim 7, further comprising a push rod deflection mechanism configured to laterally deflect said input push rod assembly to impart a rotational offset between a hinge line of said first elevator hinge and a hinge line of said second elevator hinge; and wherein said self-aligning second end of said input push rod assembly is configured to absorb deflection of said input push rod assembly. 9. The dual elevator system of claim 8, wherein said push rod deflection mechanism comprises a lockable eccentric cam assembly, said lockable eccentric cam assembly being configured to deflect said input push rod assembly laterally about a rod deflection pivot point. 10. The dual elevator system of claim 6, wherein no stabilizing linkage is attached between said input push rod assembly and said vertical stabilizer. 11. The dual elevator system of claim 6, wherein said self-aligning second end of said input push rod assembly is configured to allow aeroelastic rocking motion between said horizontal stabilizer and said vertical stabilizer through said modified constant velocity joint control linkage mechanism. 12. The dual elevator system of claim 6, wherein said first universal joint yoke assembly is configured to rotate in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage. 13. The method of claim 6, wherein said first and second elevator assemblies are swept elevator assemblies having hinges that are skewed relative to each other; wherein said yoke axle of said first universal joint yoke assembly is coupled at a right angle to said first elevator hinge; and wherein said yoke axle of said second universal joint yoke assembly is coupled at a right angle to said second elevator hinge. 14. A method for inducing synchronous motion of two adjacent controllable devices, comprising: providing a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being coupled at a right angle to a first one of said controllable devices; providing a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being coupled at a right angle to a second one of said controllable devices; providing a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, said cross connection comprising a third hinge axle between said first and second hinge axles and being adjustable to produce differential motion between said first and second controllable devices; providing a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle between said first and second hinge axles, and a second end configured for coupling to receive a single input control motion; and inducing said synchronous motion in said first and second controllable devices in response to said single input control motion received at said third hinge axle of said cross connection; wherein said synchronous motion is induced by providing control motion to said first controllable device through said first rotational joint, and providing control motion to said second controllable device to said second controllable device through said second rotational joint; and wherein said two adjacent controllable devices comprise dual elevator surfaces of a T-tail aircraft. 15. The method of claim 14, wherein said first and second rotational joints each comprise a universal joint yoke assembly. 16. The method of claim 15, wherein said first rotational joint comprises a rigid universal joint yoke assembly; and wherein said second rotational joint comprises a semi-rigid universal joint assembly. 17. The method of claim 14, wherein said input push rod assembly comprises a push rod deflection mechanism configured to laterally deflect said input push rod assembly. 18. A method of installing a modified constant velocity joint control linkage mechanism in an existing dual elevator system of an aircraft having a vertical stabilizer and a horizontal stabilizer attached to said vertical stabilizer, said method comprising: providing an aircraft having an existing dual elevator system and original control system for same, said existing dual elevator system having a vertical stabilizer and a horizontal stabilizer attached to said vertical stabilizer; and retrofitting said aircraft by replacing one or more components of said original control system with said modified constant velocity joint control linkage mechanism in the following manner: providing said modified constant velocity joint control linkage mechanism that comprises: a first universal joint yoke assembly, a second universal yoke assembly, a central cage coupled between said first universal joint yoke assembly and said second universal joint yoke assembly, and an input push rod assembly having a first end coupled to said central cage and a self-aligning second end; attaching said first universal joint yoke assembly to a first elevator hinge of a first elevator assembly of said elevator system, said first elevator hinge being rotatably attached to said horizontal stabilizer of said aircraft; attaching said second universal yoke assembly to a second elevator hinge of a second elevator assembly of said elevator system, said second elevator hinge being rotatably attached to said horizontal stabilizer of said aircraft; and attaching said self-aligning second end of said input push rod to a control lever of said elevator assembly; wherein said first universal joint yoke assembly is configured to rotate in a single plane relative to said central cage; and wherein said second universal joint yoke assembly is configured to rotate in multiple planes relative to said central cage. 19. The method of claim 18, wherein said input push rod assembly further includes a length adjustment mechanism; and wherein said method further comprises using said length adjustment mechanism to adjust the length of said input push rod assembly so as to adjust the position of respective elevator surfaces of said first and second elevator assemblies relative to a position of said control lever. 20. The method of claim 19, wherein said input push rod assembly further includes a push rod deflection mechanism; and wherein said method further comprises using said push rod deflection mechanism to laterally deflect said input push rod assembly so as to adjust position of respective elevator surfaces of said first and second elevator assemblies relative to each other. 21. The method of claim 18, wherein said original control system comprises elevator control horns, an input control link and a torque knee; and wherein said method comprises replacing said elevator control horns, input control link and torque knee with said modified constant velocity joint control linkage mechanism. 22. The method of claim 18, wherein said first and second elevator assemblies are swept elevator assemblies having hinges that are skewed relative to each other; wherein each of said first and second yoke assemblies comprises a yoke axle; and wherein said method further comprises attaching said yoke axle of said first universal joint yoke assembly at a right angle to said first elevator hinge, and attaching said yoke axle of said second universal joint yoke assembly at a right angle to said second elevator hinge. 23. A method for inducing synchronous motion of two adjacent controllable devices, comprising: providing a first rotational joint comprising two first yoke uprights with a first yoke axle disposed therebetween and a first hinge axle oriented at a right angle to said first yoke axle, said first yoke axle being coupled at a right angle to a first one of said controllable devices; providing a second rotational joint comprising two second yoke uprights with a second yoke axle disposed therebetween and a second hinge axle oriented at a right angle to said second yoke axle, said second yoke axle being coupled at a right angle to a second one of said controllable devices; providing a cross-connection coupled between said first and second hinge axles of said first and second rotational joints, said cross connection comprising a third hinge axle between said first and second hinge axles and being adjustable to produce differential motion between said first and second controllable devices; providing a self-aligning input push rod assembly having a first end coupled to said cross connection at said third hinge axle between said first and second hinge axles, and a second end configured for coupling to receive a single input control motion; and inducing said synchronous motion in said first and second controllable devices in response to said single input control motion received at said third hinge axle of said cross connection; wherein said synchronous motion is induced by providing control motion to said first controllable device through said first rotational joint, and providing control motion to said second controllable device to said second controllable device through said second rotational joint; and wherein said first yoke axle is coupled at a right angle to a hinge line of said first one of said controllable devices; wherein said second yoke axle is coupled at a right angle to a hinge line of said second one of said controllable devices; and wherein said hinge line of said first one of said controllable devices is skewed relative to said hinge line of said second one of said controllable devices. 24. The method of claim 23, wherein said first and second rotational joints each comprise a universal joint yoke assembly. 25. The method of claim 24, wherein said first rotational joint comprises a rigid universal joint yoke assembly; and wherein said second rotational joint comprises a semi-rigid universal joint assembly. 26. The method of claim 23, wherein said two adjacent controllable devices comprise dual elevator surfaces of a T-tail aircraft. 27. The method of claim 23, wherein said input push rod assembly comprises a push rod deflection mechanism configured to laterally deflect said input push rod assembly.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 6

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Control linkage for T-tail aircraft elevator surfaces

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Control linkage for T-tail aircraft elevator surfaces

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