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水平定点着落再入返回飞行器对再入角、再入点至着落点的纵程和横程有较严格的要求,飞行器侧向机动能力决定最大横程误差和可返回时机。为设计满足上述要求的飞行轨迹,提出了一种离轨时机及制动策略计算方法。根据再入轨迹分析和着落点经纬度,估计再入轨道最优升交点地理经度;利用横程误差计算返回圈升交点地理经度范围,并推算升交点地理经度优选离轨时机;通过地固系下再入角估计惯性系下速度倾角,由再入点经纬高和速度倾角推算离轨制动时刻及速度增量,由迭代修正生成离轨制动策略,并经算例仿真验证。
Horizontal fixed landing and reentry of the reentry vehicle to the reentry angle, reentry point to the landing point of the longitudinal and horizontal have more stringent requirements, the aircraft lateral maneuverability determines the maximum horizontal error and return timing. In order to design a flight path that meets the above requirements, a method of calculating the derailment timing and braking strategy is proposed. According to the re-entry trajectory analysis and the latitude and longitude of the landing point, the geo-longitude of the re-entry orbit optimal ascending point is estimated; the geo-longitude range of the ascending point of the return circle is calculated by using the horizontal error and the geo-longitude of the ascending point is estimated; The reentry angle estimates the velocity dip under the inertial system. The latitude and longitude of the reentry point and the velocity dip are used to calculate the detrack braking moment and the velocity increment. The detrack correction strategy is generated by the iterative correction. The simulation results show the simulation results.