[특허]Multi-position landing gear

The Boeing Company

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특허 상세정보

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Multi-position landing gear

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-025/14 B64C-025/36 B64C-025/52 B64C-025/66 B64C-029/00
출원번호	US-0562934 (2014-12-08)
등록번호	US-9731816 (2017-08-15)
발명자 / 주소	Harris, III, John H. Newman, Daniel I.
출원인 / 주소	The Boeing Company
대리인 / 주소	Walters & Wasylyna LLC
인용정보	피인용 횟수 : 0 인용 특허 : 11

초록

A multi-position landing gear for an aircraft may include a first landing skid disposed on a bottom side of the aircraft, and a second landing skid disposed on one of a top side or the bottom side of the aircraft, wherein the first landing skid and the second landing skid are rotatable relative to the aircraft.

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1. A multi-position landing gear for an aircraft comprising: a first landing skid disposed on a bottom side of said aircraft; anda second landing skid disposed on one of a top side or said bottom side of said aircraft,wherein said first landing skid and said second landing skid are rotatable relative to said aircraft, andwherein rotation of said first landing skid relative to said aircraft and said second landing skid relative to said aircraft transitions an orientation of said aircraft from an approximately vertical orientation to an approximately horizontal orientation and from said approximately horizontal orientation to said approximately vertical orientation. 2. The multi-position landing gear of claim 1 wherein said first landing skid is rotatably coupled to said aircraft about a first axis of rotation perpendicular to a longitudinal axis of said aircraft, and wherein said second landing skid is rotatably coupled to said aircraft about a second axis of rotation perpendicular to said longitudinal axis of said aircraft. 3. The multi-position landing gear of claim 1 further comprising skid actuator mechanisms operably coupled to said first landing skid and said second landing skid to rotate said first landing skid and said second landing skid relative to said aircraft. 4. The multi-position landing gear of claim 1 wherein said first landing skid is spaced away from said second landing skid along a longitudinal axis of said aircraft. 5. The multi-position landing gear of claim 1 wherein said first landing skid comprises a range of rotation of approximately between 180-degrees and 200-degrees. 6. The multi-position landing gear of claim 1 wherein said second landing skid comprises a range of rotation of approximately between 250-degrees and 270-degrees. 7. The multi-position landing gear of claim 1 wherein said first landing skid and said second landing skid each comprises a U-shaped bar. 8. The multi-position landing gear of claim 1 wherein said first landing skid and said second landing skid each comprises an H-shaped bar. 9. The multi-position landing gear of claim 1 wherein said first landing skid and said second landing skid each comprises one of a U-shaped bar or an H-shaped bar. 10. The multi-position landing gear of claim 1 further comprising taxiing devices removably coupled to said first landing skid and said second landing skid. 11. An aircraft comprising: a fuselage comprising a longitudinal axis, a top side and a bottom side;wings extending from said fuselage;at least one engine coupled to at least one of said fuselage and said wings;a first landing skid rotatably coupled to said bottom side of said fuselage; anda second landing skid rotatably coupled to one of said top side or said bottom side of said fuselage,wherein controlled rotation of said first landing skid about said bottom side of said aircraft and said second landing skid about said one of said top side or said bottom side of said aircraft transitions an orientation of said aircraft from an approximately vertical orientation to an approximately horizontal orientation and from said approximately horizontal orientation to said approximately vertical orientation. 12. The aircraft of claim 11 further comprising skid actuator mechanisms operably coupled to said first landing skid and said second landing skid to rotate said first landing skid about a first axis of rotation perpendicular to said longitudinal axis and said second landing skid about a second axis of rotation perpendicular to said longitudinal axis. 13. The aircraft of claim 11 wherein said aircraft further comprises a forward end and a longitudinally opposed aft end, wherein said second landing skid is positioned proximate said aft end of said aircraft, and wherein said first landing skid is spaced away from said second landing skid toward said forward end. 14. The aircraft of claim 11 wherein said first landing skid comprises a range of rotation of approximately between 180-degrees and 200-degrees, and wherein said second landing skid comprises a range of rotation of approximately between 250-degrees and 270-degrees. 15. The aircraft of claim 11 wherein said first landing skid and said second landing skid each comprises one of a U-shaped bar or an H-shaped bar. 16. The aircraft of claim 11 further comprising at least one of a first recess formed in said bottom side of said fuselage to receive said first landing skid; and a second recess formed in one of said top side or said bottom side of said fuselage to receive said second landing skid. 17. A method for transitioning an aircraft between a plurality of orientations, said method comprising: positioning said aircraft in one of an approximately vertical orientation or an approximately horizontal orientation supported by a multi-position landing gear, said multi-position landing gear comprising a first landing skid disposed on a bottom side of said aircraft and a second landing skid disposed on one of a top side or a bottom side of said aircraft, wherein said first landing skid and said second landing skid are rotatable relative to said aircraft;when in said approximately vertical orientation, rotating said first landing skid and said second landing skid relative to said aircraft to transition said aircraft from said approximately vertical orientation to said approximately horizontal orientation; andwhen in said approximately horizontal orientation, rotating said first landing skid and said second landing skid relative to said aircraft to transition said aircraft from said approximately horizontal orientation to said approximately vertical orientation. 18. The method of claim 17 further comprising positioning said aircraft in at least one intermediate orientation between said approximately vertical orientation and said approximately horizontal orientation in response to at least one of rotating said first landing skid relative to said aircraft and rotating said second landing skid relative to said aircraft. 19. The method of claim 17 further comprising adjusting an angle of said aircraft in response to at least one of rotating said first landing skid relative to said aircraft and rotating said second landing skid relative to said aircraft. 20. The method of claim 17 further comprising adjusting a height of said aircraft in response to at least one of rotating said first landing skid relative to said aircraft and rotating said second landing skid relative to said aircraft.

이 특허에 인용된 특허 (11)

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Multi-position landing gear

초록

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Multi-position landing gear

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이 특허에 인용된 특허 (11)

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IPC 상세정보(version : 201201)

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