摘要
为解决微纳卫星在机动变轨过程中受到侧向干扰力矩的问题,选择自旋稳定的方式,降低卫星速度指向偏差.考虑到质量变化以及喷气阻尼力矩的影响,建立恒定推力下无轴向扭矩的微纳卫星自旋推进模型,得到角速度、欧拉角、角动量以及角速度和欧拉角最大值的解析解.应用实例进行数值分析,结果表明:所求得的解析解精度较高;在发动机点火过程中,侧向角速度和欧拉角呈周期性变化,其中侧向角速度振幅越来越小;角动量矢量指向曲线为一圆形,圆形的半径近似等于卫星速度增量指向偏差;高速自旋的微纳卫星动不平衡特性对卫星自旋机动过程影响较小;微纳卫星的外形越接近于圆盘状,卫星速度增量指向偏差越小,变轨精度越高.
To solve the problem of transverse torques on micro-nano satellites during orbital maneuver,the spinstabilized method was selected to reduce velocity pointing error. Considering the effects of mass variation and jet damping,the spinning thrusting satellite model which subjected to constant force and zero axial torque was established. After that,the analytic solutions for angular velocity,angular momentum,asymptotic limits of angular velocity and Euler angle were obtained. The example was simulated and the results show that the analytic solutions are highly accurate. Besides,the transverse angular velocity and Euler angle are changing periodically,and the amplitude of transverse angular velocity decreases as the time is increasing. What＇s more,the curve of angular momentum vector pointing is a circle,and the radius is nearly equal to the satellite velocity increment pointing error. Also,the dynamic unbalance characters of the micro-nano satellite under high spin rate have little influence on the spinning maneuver process. As the micro-nano satellite becomes more disklike,the velocity increment pointing error can be decreased,and the accuracy of the orbit maneuver is raised.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2018年第1期127-133,共7页
Journal of Harbin Institute of Technology
基金
南京理工大学自主科研专项(30916011101)
关键词
微纳卫星
自旋推进
解析解
角动量
速度增量
micro-nano satellite
spinning thrusting
analytic solutions
angular momentum
velocity increment
