CAJ | 학술논문

针对轨道轰炸飞行器(OBV)的过渡段轨道设计与制导技术进行了讨论.在初始点位置、再入点位置和再入角固定的前提下,根据冲量假设和二体理论设计了固定时间转移轨道,其实质在于制动点位置和制动速度的确定.为了消除设计偏差,提出了一种基于虚拟再入点补偿的有限推力制导方案,并简要分析了关机点参数的选取原则.对于耗尽关机的动力系统,通过运用能量管理技术实现了多余燃料的耗散.仿真结果验证了上述方法的有效性.
침대궤도굉작비행기(OBV)적과도단궤도설계여제도기술진행료토론.재초시점위치、재입점위치화재입각고정적전제하,근거충량가설화이체이론설계료고정시간전이궤도,기실질재우제동점위치화제동속도적학정.위료소제설계편차,제출료일충기우허의재입점보상적유한추력제도방안,병간요분석료관궤점삼수적선취원칙.대우모진관궤적동력계통,통과운용능량관리기술실현료다여연료적모산.방진결과험증료상술방법적유효성.
The technique of transition trajectory planning and guidance for orbital bombing vehicle was discussed in this paper. On condition that initial location, reentry location and velocity inclination were constrained, a time-fixed transfer orbit was designed based on impulse hypothesis and two-body theory, which is substantial for deciding braking position and braking velocity. Then a scheme of limited thrust guidance with virtual reentry point compensation was put forward to eliminate planning error and the selection of shutdown parameter was analyzed briefly. For some power system with depleted shutdown, the redundant fuel could be dissipated by using energy management approach. Simulation results show effectiveness of the presented method .