大惯量太阳翼展开锁定冲击地面测试方法OA

To address the difficulties in accurately predicting deployment-locking impacts of large-inertia solar arrays and the insufficient consistency between ground tests and on-orbit conditions,a ground testing method integrating gravity unloading,velocity compensation,and multi-dimensional impact measurement was proposed.Based on the principle of energy conservation,counterweights were employed to compensate for energy losses caused by the work of non-conservative forces such as friction and aerodynamic resistance,thereby ensuring consistency between ground and on-orbit conditions in deployment time,terminal velocity,and locking impact loads.A two-link dynamic model was established,and an integrated measurement system incorporating vision-based motion measurement,strain measurement,and six-axis force measurement was developed.Test results of a 120 kg-class solar array showed that the proposed method effectively reproduced the 15 s on-orbit deployment process.The maximum impact force in the y direction was measured as 280 N,and the peak impact torque about the z axis was measured as 412 N·m.The deviation between simulation and experimental results was 2.4%,and the repeatability deviation was less than 5%.These results show that the impact energy is primarily transferred along the tangential deployment direction and dissipated through deformation of the root hinge.The proposed method provides technical support for high-fidelity ground verification of deployment-locking impacts of large-inertia solar arrays.