The invention provides an aircraft engine nacelle pressure relief door assembling structure which comprises a pressure relief door supporting frame (1) installed on an engine nacelle and provided with a supporting frame side plate (11). The pressure relief door (2) is provided with a pressure relief door side plate (22); the shaft pin (3) is connected with the supporting frame side plate (11) and the pressure relief door side plate (22) so that the pressure relief door (2) can rotate around the shaft pin (3); the limiting structure (4) is used for limiting the rotating angle range of the pressure relief door (2) around the shaft pin (3); and the damping device (5) is used for generating a damping effect on rotation after the pressure relief door (2) rotates around the shaft pin (3) to be opened to a preset angle.
本发明提供了一种飞行器发动机短舱泄压门装配结构,该泄压门装配结构包括:安装于发动机短舱上的泄压门支撑框架(1),泄压门支撑框架(1)具有支撑框架侧板(11);泄压门(2),泄压门(2)具有泄压门侧板(22);轴销(3),轴销(3)分别与支撑框架侧板(11)和泄压门侧板(22)连接以使泄压门(2)能够围绕轴销(3)转动;限位结构(4),限位结构(4)用于限定泄压门(2)围绕轴销(3)转动的角度范围;以及阻尼装置(5),用于在泄压门(2)围绕轴销(3)转动开启至预设定角度后对转动产生阻尼作用。
Aircraft engine nacelle pressure relief door assembly structure
飞行器发动机短舱泄压门装配结构
2025-05-27
Patent
Electronic Resource
Chinese
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