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空地导弹采用具有角度约束的弹道成型制导律攻击目标时,制导需要包含剩余飞行时间信息。针对传统的剩余飞行时间的估计算法精度不高问题,结合空地导弹采用弹道成型制导末段弹道的飞行特性,对剩余飞行时间的算法进行优化。同时,分析了在空地导弹常用制导方式下,估计算法的工程实现,仿真验证优化算法具有较高的精度及工程应用性。
When space-to-air missiles target a target using ballistic guidance with angle constraints, the guidance needs to include information on the remaining flight time. Aiming at the problem of low precision of the traditional estimation algorithm of remaining flight time, the algorithm of remaining flight time is optimized by combining the flight characteristics of the ballistic missile with ballistic guidance at the last stage. At the same time, the paper analyzes the engineering realization of the estimation algorithm under the guidance methods commonly used in air-to-ground missiles. The simulation verification algorithm has high accuracy and engineering applicability.