激光微推力器作用下纳星轨道半长轴简化计算方法

Simplified method for calculating semi-major axis under laser micro-thruster for nano-satellite

针对激光微推力器微小推力作用下纳星轨道转移问题,利用摄动方程提出一种切向推力同面轨道转移的半长轴简化计算方法。分析了地球非球形、大气阻力和太阳光压等主要摄动因素对该方法的影响,并与各种摄动下纳星运动方程直接积分的轨道变化情况进行了对比,验证了简化计算方法的有效性和应用条件。仿真对比结果表明:在轨道高度300 km以上,纳星在百微牛量级的切向推力作用下,可以采用简化计算方法获得轨道高度机动能力;对于纳星任务设计阶段,太阳光压摄动可以忽略,大气阻力摄动在500 km以上可以不予考虑,地球非球形摄动影响特性与其他卫星类似。

In order to solve the problem of orbit transfer of the nano-satellite under the action of microthrust of laser micro-thruster,a simplified semi-major axis calculation method for in-plane orbit transfer under the tangential thrust was proposed by using perturbation equation.The influence of the main perturbation factors such as the non-spherical perturbation,the atmospheric perturbation and solar pressure perturbation on the method was analyzed.And the orbital changes of the direct integration of the motion equation under various perturbations were compared with the results from the simplified method.The validity and application conditions of the simplified method was verified.The simulation results show that the orbit maneuverability for nano-satellites can be obtained by simplified calculation method under the tangential thrust of the order of 100μN at orbital altitude above 300 km.What is more,for nano-satellite mission design stage,the solar pressure perturbation can be ignored,the atmospheric drag perturbation can be ignored above orbital altitude of 500 km,and the influence characteristics of non-spherical perturbation are similar to those of other satellites.