摘要
提供了弹道导弹弹道设计的一种快速迭代方法和模型。这种方法与惯用迭代方法相比,其优点是将落地点射程偏差和方位角偏差的二元迭代分解成两个一元迭代,这样不仅可大大提高弹道迭代的收敛速度,而且可以满足任何需求的迭代精度指标。大量仿真结果验证了这种方法的有效性。
A rapid iteration algorithm adapting to ballistic missile trajectory design is presented. Comparing the old iteration algorithm, the rapid iteration algorithm is which decomposes binary variable iteration, which include the hit-point range error iteration and hit-point azimuth error iteration, to be two unary iterations. The algorithm would not only accelerate trajectory convergence, but also meet any iterative accuracy index. The algorithm validity is proved by a great deal of simulation results.
出处
《飞行力学》
CSCD
北大核心
2007年第2期75-77,共3页
Flight Dynamics
关键词
弹道导弹
弹道设计
迭代
ballistic missile
trajectory design
iteration
