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研究了约束再入点地理位置的再入飞行器离轨问题规划方法。再入飞行器的离轨轨道设计受到飞行器当前轨道状态和再入点参数的约束,基于轨道飞行原理,建立了冲量模型下离轨制动参数和再入点参数的关系,分析了最优离轨的推力施加原则;在考虑地球自转的前提下,针对约束再入点经纬度的问题,研究了利用非线性规划优化方法确定有限推力模型下离轨点位置的策略,同时给出了符合燃料最优目标的离轨制动参数;最后探讨了一般情况下初始轨道不满足离轨要求时,为满足星下点约束而进行的轨道机动施加策略。
The method of derailment planning of reentry vehicle with restraint reentry location is studied. The design of the orbit of the reentry vehicle is constrained by the current state of the orbit and the reentry point parameters of the reentry vehicle. Based on the principle of orbital flight, the relationship between the deaeration parameters and the reentry point parameters under the impulse model is established. Under the premise of considering the rotation of the earth, aiming at the problem of latitude and longitude of the reentry point, the strategy of using the nonlinear programming optimization method to determine the position of the de-ionization point under the finite thrust model is studied. At the same time, The target de-orbit braking parameters are discussed. Finally, the tactics of orbital maneuver applied to meet the under-star point constraints are discussed when the initial orbit does not meet the requirements of derailment.