The invention discloses an orbit deploying device for a cubic micro-nano satellite, belongs to the technical field of aerospace, and aims at solving the problems that in the prior art, the bearing capacity is poor, deformation is prone to occurring, the assembly difficulty is large, the distance tolerance between orbits cannot be controlled, and the satellite is damaged due to oscillation in a separation mechanism under the vibration working condition. The device comprises a cabin body and an ejection mechanism arranged in the cabin body; the cabin body at least comprises a cabin door which is arranged at one end of the cabin body and rotationally connected with the cabin body, the cabin door is locked through a closing locking mechanism when being closed relative to the cabin body and is locked through an in-place locking mechanism when being opened, and a wedge-shaped block is arranged on the upper portion and the lower portion of the side, away from the side rotationally connected with the cabin body, of the inner surface of the cabin door respectively; the ejection mechanism comprises a pushing plate in sliding fit with the cabin body and a cylindrical spiral spring arranged between the pushing plate and the other end face of the cabin body, wedge-shaped faces are arranged at the three corners of the inner surface of the pushing plate, and the wedge-shaped faces are matched with wedge-shaped blocks on the cabin door to press the cubesat on the bottom face and the side face of the cabin body.
一种用于立方体微纳卫星的轨道部署器属于航空航天技术领域,目的在于解决现有技术存在的承载能力差、容易变形、装配难度大、轨道与轨道间的距离公差无法控制以及振动工况下卫星在分离机构中振荡导致损坏的问题。本发明包括舱体以及设置在舱体内的弹出机构;舱体至少包括一个设置在舱体一端和舱体转动连接的舱门,舱门相对舱体关闭时,通过关闭锁紧机构锁紧,打开时,通过到位锁定机构锁紧,舱门内表面远离与舱体转动连接的一侧上下分别设置有一个楔形块;弹出机构包括和舱体滑动配合的推动板以及设置在推动板和舱体另一端面之间的圆柱螺旋弹簧,推动板内表面三个角处设置有楔形面,楔形面和舱门上的楔形块配合将立方星压紧在舱体的底面和侧面。
Orbit deploying device for cubic micro-nano satellite
一种用于立方体微纳卫星的轨道部署器
2021-11-26
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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