The invention relates to the technical field of spacecraft low-gravity environment simulation tests, in particular to a spacecraft mass center unloading and attitude adaptation device and method.The device comprises a cross beam, a first vertical rod, a second vertical rod, a first Z-direction adjusting column, a second Z-direction adjusting column, a first X-direction adjusting base, a second X-direction adjusting base and an adapter base; the cross beam is used for being detachably connected with a low-gravity system sling; the upper end of the first vertical rod is rotationally connected with one end of the beam through a first rotating shaft; the upper end of the second vertical rod is rotationally connected with the other end of the cross beam through a second rotating shaft, one side of the adapter seat is detachably connected with the first X-direction adjusting seat, and the other side of the adapter seat is detachably connected with the second X-direction adjusting seat; the cross beam, the first vertical rod, the second vertical rod and the adapter form a parallelogram-like structure, and the change of the mass center position of the spacecraft is adapted through X, Y and Z three-direction adjustment, so that the requirements that the spacecraft is laterally inclined by +/-60 degrees and pitching by +/-180 degrees relative to the horizontal position are met, and the attitude change of the spacecraft is adapted while the mass center of the spacecraft is unloaded.
本申请涉及航天器低重力环境模拟试验技术领域,尤其涉及航天器质心卸载与姿态适应装置及方法,装置包括横梁、第一竖杆、第二竖杆、第一Z向调节柱、第二Z向调节柱、第一X向调节座、第二X向调节座以及转接座,横梁用于与低重力系统吊索可拆卸连接;第一竖杆上端通过第一转轴与横梁的一端转动连接;第二竖杆上端通过第二转轴与横梁的另一端转动连接,转接座的一侧与第一X向调节座可拆卸连接,另一侧与第二X向调节座可拆卸连接;使横梁、第一竖杆、第二竖杆及转接座形成类平行四边形结构,通过X、Y、Z三向调节适应航天器质心位置的变化,从而满足航天器相对于水平位置侧倾±60°,俯仰±180°,对航天器质心卸载同时适应其姿态变化。
Spacecraft centroid unloading and attitude adaptation device and method
航天器质心卸载与姿态适应装置及方法
15.04.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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