航天器弹性附件伸展动力学研究

利用动量矩定理推导出带伸展弹性板航天器的姿态动力学方程，在弹性板等速伸展的情况下，导出板的振动与伸展运动耦合微分方程，航天器姿态运动与板的伸展运动、振动耦合微分方程，通过龙格－库搭积分法得出了数值解，结果表明：弹性板等速伸展时，其振动的振幅随板长度的增长而增大，航天器姿态角速度随板长度的增长而减少。弹性板等速率越大，板振动的振幅越大。

DEPLOYMENT DYNAMICS OF ELASTIC APPENDAGES OF A SPACECRAFT

The attitude dynamic equations of a spacecraft with deploying elastic plates are obtained by using the theorem of moment of momentum.When elastic plates deploy at uniform velocity the coupled differential equations of vibration and deploying motion are obtained and the coupled differential equations of attitude motion,deploying motion and vibration are obtained.By using Runge Kutta method the numerical results are obtained.The results show that as the length of the elastic plates increase,the amplitudes of vibration increase,but the attitude angular velocity decreases.The results also show that as the speed of deployment increase,the amplitudes of vibration increase.