靶带式激光微推力器微推力输出对纳星平台的姿态影响分析

Analysis of attitude influence of nano-satellite platform by micro thrust output of fuel tape micro laser thruster

激光微推力器由于比冲高、推力水平低、体积功耗低、简单可靠等优点逐渐成为微纳星可负担的起的动力系统选择之一。针对固体靶带式激光微推力器推力输出过程中,由于阵列式激光器点火位置、点火顺序对纳星平台姿态影响问题,建立了基于激光烧蚀力矩的卫星姿态动力学方程,仿真分析姿态角和角速度随时间变化关系。仿真结果表明:在微推力器激光点火顺序可分为两边对称且连续输出和两边对称且间隔输出两种情况下,两种模式对纳星姿态影响存在差异,但无论激光烧蚀力矩由大到小输出或由小到大,力矩对称且连续输出对姿态影响最小,为应用于微纳星姿态稳定控制奠定基础。

Laser micro-thruster has become one of the affordable power system options for micro-nanosatellites due to its high specific impulse,low thrust level,small size,low power consumption and high reliability.In view of the influence of laser ignition position and ignition sequence on the attitude of nano-satellite platform during the thrust output of solid fuel tape laser micro-thruster,the attitude dynamics equation based on laser ablation moment was established,and the relationship between attitude angle and its angular velocity with time was simulated and analyzed.The simulation results show that,the laser ignition sequence of micro thruster can be divided into two kinds:symmetrical on both sides and continuous output and symmetrical on both sides and spacing output,the effects of the two modes on the attitude of the nano-satellite are different.However,whether the laser ablation moment was from large to small or from small to large,the moment symmetrical and continuous output has the least impact on the attitude.This lays the foundation for the application of attitude stability control of micro-nano-satellite.