小卫星三轴稳定模式下的有限推力轨道转移  

LOW THRUST ORBITAL TRANSFER OF SMALLSATELLITE UNDER 3-AXIS ATTITUDESTABILIZATION MODE

作　　者：荆武兴[1] 吴瑶华[1] 王学孝[1] 杨涤[1] 

机构地区：[1]哈尔滨工业大学,哈尔滨150001

出　　处：《中国空间科学技术》1996年第5期51-57,共7页Chinese Space Science and Technology

摘　　要：由搭载方式发射的小卫星,通常需要变轨才能进入自己的工作轨道。这种变轨一般由小推力发动机执行,传统的冲量变轨方法存在较大局限性。文章研究了在小推力作用下,小卫星由椭圆停泊轨道进入共面圆工作轨道的点火信息求解方法;给出对地定向三轴稳定模式下和俯仰角偏置三轴稳定模式下的变轨控制仿真结果;提供了对任务设计有参考价值的结论。Small satellite launched together with a main satellite often needs orbital maneuvers to enter its working orbit.The orbital maneuvers are implemented bysmall thrusters. Burning information under low thrust is studied for a small satellite transfering from a elliptic parking orbit to its circular working orbit. Horizontal thrust strategy and constant pitch angle thrust strategy are simulated, and conclusions useful for flight mission design are presented.

关 键 词：轨道转移 小推力 三轴稳定 小型 卫星 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程] V448.231