摘要
为了弥补高空空气动力不足的情况下,导弹机动性能下降的缺点,在导弹飞行末端引入直接力控制,采用直接力/气动力复合控制。直接力控制的关键问题是点火逻辑的确定,对轨控发动机点火时机与分配策略进行了研究,按照使用最少资源提供最大调偏能力的原则,采用离线规划在线分段查表的方法给出了两种可行的发动机点火逻辑,一种是固定分配模式,另一种是动态分配模式。并对两种模式下的点火时间以及调偏误差进行了分析。由计算结果可以看出,在导弹飞行末端引入直接力控制,配合合适的点火逻辑,可以迅速有效地调整脱靶量,使导弹实现与目标直接碰撞。
In order to compensate the deficient air power at high altitude, the paper introduces the direct lateral force and adopts direct lateral force and aerodynamic coefficient for Blended - Control. Because the key problem of direct lateral force control is the establishment of fire logic, the balance between fire timing and assigning strategies is researched. Based on the principle of providing the most adjusting capacity of biased error by the least resource, the paper introduces the offline layout and online subsection checking table ways, and presents two feasible ways of using system of side force to adjust miss distance in the terminal flying phase of the guided missile, one way is the immobile allotment mode, another way is the mobile allotment mode. The firing time and biased error under the two modes are analyzed. According to the simulation result, in the terminal flying phase of the guided missile, using direct lateral force control can efficiently adjust the miss distance, and make the guided missile collide with the target directly.
出处
《计算机仿真》
CSCD
北大核心
2009年第3期99-102,共4页
Computer Simulation
关键词
拦截弹
直接力
复合控制
轨控发动机
Intercept missile
Direct lateral force
Blended- control
Trajectory control engine
