火星环绕器环火轨道的角动量管理方法  

Angular Momentum Management Method for Mars Rover on Mars Orbit

作　　者：信思博[1] 顾强[1] 郑艺裕 赵训友 XIN Sibo;GU Qiang;ZHENG Yiyu;ZHAO Xunyou(Shanghai Institude of Satellite Engineering,Shanghai 200240,China)

机构地区：[1]上海卫星工程研究所,上海200240

出　　处：《空间控制技术与应用》2021年第1期8-14,共7页Aerospace Control and Application

基　　金：国家自然科学基金青年基金资助项目(51305327)。

摘　　要：针对中国首次火星探测的任务需求和规划,结合环绕器质量特性和布局构型以及大椭圆轨道特性,分析了环绕器在环火飞行阶段所受的重力梯度力矩和光压力矩规律.空间干扰力矩累积导致飞轮转速上升,影响姿态机动能力,需要喷气卸载.为减少喷气卸载次数,在满足系统任务的基础上,设计了姿态偏置方案,利用光压力矩和重力梯度力矩相互抵消减少角动量累积.通过仿真表明该方法可以将空间干扰力矩累积量减少70%,节约卸载喷气的燃料消耗,延长航天器寿命.According to the mission requirements and planning of the first China mission exploration,the gravity gradient torque and solar pressure torque are investigated by considering the orbiter mass property,configurations,and the highly eccentric orbit.The accumulation of the disturbance torques can increase the rotational speed of the flywheels and finally decrease the attitude maneuver capability.Therefore,the momentum unloading utilizing active thrust forces are usually required.To reduce the number of the momentum unloading,a method based on attitude bias is developed to achieve the canceling effect of gravity gradient torque and solar pressure torque.The numerical simulation results indicate that the accumulation of the disturbance torques can reduce to 70 percent,making a contribution to saving on fuel and promoting longer life of the spacecraft.

关 键 词：火星探测器 空间力矩 角动量 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]