摘要
追踪制导攻击活动目标时视线旋转速度随弹目接近会逐步增大,制导末端对拦截器过载和快速性需求高,弹体可用过载较小时脱靶量大,难以适应低成本制导系统应用。为提高追踪制导攻击活动目标的制导精度,提出一种比例积分追踪制导方法。理论分析表明这种制导方法在保证追踪误差稳定的同时,可有效减少视线旋转速度,降低了制导末端对弹体需用过载和快速性的要求,能明显提高追踪制导的精度。对不同速度活动目标的攻击仿真结果证实了研究结论的正确性。
Pursuit guidance is widely used in low cost weapon systems. Usually, the command acceleration compu-ted in pursuit guidance is proportional to tracking error. When this guidance method is used for attacking non-sta-tionary targets, the line of sight rate will gradually increase with decreasing range between the missile and the tar-get. This means that the line of sight angle goes faster near the point of impact, and inevitably a higher control effort on missiles is required. Consequently, the miss distance is far bigger if the missile has the lower capability in nor-mal control directions. To solve these problems, a modified pursuit guidance scheme, called proportional plus inte-gral pursuit guidance, is proposed. In this new guidance law, the integral term of the tracking error is introduced in the command computation and the two term control scheme （ proportional plus integral pursuit guidance） is formed. The main advantage of the integral term is that it can efficiently depress the line of sight rate, thus reducing the re-quirement on missile control effort and improving the guidance precision significantly. The conclusions are further confirmed by the simulations and the performance comparisons for two types of moving targets in an air to ground in-tercept scenario.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2014年第2期303-308,共6页
Journal of Northwestern Polytechnical University
关键词
导弹
制导
追踪制导
追踪误差
acceleration, electronic guidance systems, errors, flight control systems, air to surface missiles, tar- gets, two term control systems
pursuit guidance, tracking errors
