卫星太阳帆板展开的动力学仿真分析与应用

Dynamic simulation and application of deployable mechanism of satellite solar panels

研究了卫星帆板展开对整星姿态的影响,优化了展开策略.对单块帆板的展开进行了理论建模,得到了转动角度和时间关系的解析解;结合某卫星工程实际对单块帆板进行了ADAMS动力学仿真,建立了更接近实际的ADAMS模型和参数设置.通过搭建的单块帆板展开试验机构进行展开试验,测得了驱动力矩、阻力矩等参数,并对理论模型和ADAMS模型进行了参数修正.修正后的结果显示理论计算、仿真和试验结果相差在5％以内.对于10.6 kg帆板而言,驱动力矩每增加0.09 N·m,展开时间缩短0.4～0.5 s,冲击载荷相应增加400 N左右.修正过的ADAMS模型可应用于整星帆板展开动力学分析,得到不同展开策略对卫星姿态影响的大小,为展开模式的选择、姿态精确控制提供参考依据.

The impact of a satellite panel deployment on satellite attitudes was researched and deploy- ment strategies were optimized. A theoretical model for deployment of a single solar panel was estab- lished to obtain the analytical solution of the rotation angle changed with time. Combined with the practical application of a satellite project, the ADAMS dynamics of the single solar panel was simula- ted, and a new ADAMS model approximate to an actual situation and parameter settings were per- formed. Through deployment test of single solar panel deployment mechanism, the drive moment and resistance moment were obtained to correct the theoretical model and ADAMS model. The correction results show that the difference among theoretical calculation, simulation and test results is within 5~. For a 10.6 kg panel, deployment time has been shorten by 0.4--0.5 s and the impact load aug- mented about 400 N with each increase of 0.09 N ~ m of drive moment. The revised ADAMS model can be applied to deployment dynamic analysis of satellite panels and can obtain the effect of different deployment strategies on satellite attitudes. Obtained results provide credible references for selection of deployment patterns and precise controls.