AIRCRAFT LANDING GEAR

To simplify a structure of an aircraft landing gear including a steering mechanism.SOLUTION: A landing gear 1 includes a shock strut 2 having a cylinder 3 and a piston 4, and a wheel 5 supported by the piston. The shock strut has a steering mechanism 21 for rotating the wheel around a strut shaft Z...

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Bibliographic Details
Main Authors MASAMURA SHINNOSUKE, TADA KAZUO
Format Patent
LanguageEnglish
Japanese
Published 28.07.2023
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary:To simplify a structure of an aircraft landing gear including a steering mechanism.SOLUTION: A landing gear 1 includes a shock strut 2 having a cylinder 3 and a piston 4, and a wheel 5 supported by the piston. The shock strut has a steering mechanism 21 for rotating the wheel around a strut shaft Z together with the piston, and a power source of the steering mechanism is an electric motor 6 having a rotor 61 and a stator 62, and the rotor and the stator are coaxial with the strut shaft.SELECTED DRAWING: Figure 1 【課題】ステアリング機構を備えた航空機の着陸装置の構造を簡略にする。【解決手段】着陸装置１は、シリンダ３とピストン４とを有するショックストラット２と、ピストンに支持された車輪５と、を備え、ショックストラットは、車輪を、ピストンと共に、ストラット軸Ｚを中心に回動させるステアリング機構２１を有し、ステアリング機構の動力源は、回転子６１と固定子６２とを有する電気モータ６であり、回転子及び固定子は、ストラット軸と同軸である。【選択図】図１
Bibliography:Application Number: JP20220005487