CAJ | 학술논문

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。
추종제도공격활동목표시시선선전속도수탄목접근회축보증대，제도말단대란절기과재화쾌속성수구고，탄체가용과재교소시탈파량대，난이괄응저성본제도계통응용。위제고추종제도공격활동목표적제도정도，제출일충비례적분추종제도방법。이론분석표명저충제도방법재보증추종오차은정적동시，가유효감소시선선전속도，강저료제도말단대탄체수용과재화쾌속성적요구，능명현제고추종제도적정도。대불동속도활동목표적공격방진결과증실료연구결론적정학성。
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.