CAJ | 학술논문

为了实现椭圆形悬挂轨道，文中以航天器相对运动动力学模型为基础，对椭圆形悬挂轨道的控制策略进行了分析研究。根据悬挂轨道的定义，通过理论分析和推导，得到了悬挂星在椭圆悬挂轨道上运行时所需要的控制加速度，并对其进行了数值仿真。仿真结果表明：控制加速度曲线平滑，易于实现和控制，且仿真结果与泛开普勒轨道所需的控制加速度一致，椭圆形悬挂轨道实现方法正确可行。
위료실현타원형현괘궤도，문중이항천기상대운동동역학모형위기출，대타원형현괘궤도적공제책략진행료분석연구。근거현괘궤도적정의，통과이론분석화추도，득도료현괘성재타원현괘궤도상운행시소수요적공제가속도，병대기진행료수치방진。방진결과표명：공제가속도곡선평활，역우실현화공제，차방진결과여범개보륵궤도소수적공제가속도일치，타원형현괘궤도실현방법정학가행。
Based upon analyzing the relative motion dynamics model of spacecraft,an elliptical orbit hovering method was presented.According to the definition of hovering orbit,theoretical dynamic analysis of the hovering orbit was conducted,the acceleration requirements during the hovering process were deduced,and the corresponding simulations were conducted.The simulation results show that control acceleration curves are smooth enough to realize orbit control,and the results and their analysis show preliminarily that the method is in agreement with the method in Ref.9,and thus is plausibly correct and feasible.