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Time-to-go weighted optimal trajectory shaping guidance law 总被引:2,自引:0,他引:2
For maneuvering target,the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based on the time-to-go weighted function.Based on the same cost function,the closed-form solutions of the guidance law were derived when the initial displacement of missile,final impact angle,heading error and target maneuver was introduced into the lag-free guidance system.To validate the closed-form solutions,the simulation of the lag-free system was done and the simulation results exactly matched the closed-form solutions and only when the exponent is greater than zero,the final acceleration approaches to zero. 相似文献
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基于扩展卡尔曼滤波器,提出一种捷联导引头刻度尺参数辨识方法。首先,简化了在比例导引制导律作用下捷联导引头系统的非线性模型。之后,根据该非线性模型,推导扩展卡尔曼滤波方程组,并在参数估计处利用泰勒展式将其线性化。最后,在以上条件下对制导系统的稳定性进行理论分析与研究。通过数学仿真对该刻度尺参数辨识方法加以验证,仿真结果表明:应用该方法,可以快速、准确的估计捷联导引头刻度尺参数,并且有效提高了在稳定性方面制导系统对导引头刻度尺系数误差的容忍度,使系统更具鲁棒性。 相似文献
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为研究导引头量测误差引起的落角约束制导系统制导精度问题,引入扩展的落角约束最优制导律,考虑导引头视线角速率零位误差、视线角零位误差和导引头探测器角噪声,利用无量纲化方法和伴随函数法对制导精度进行研究。研究结果表明:当无量纲末导时间大于15时,由视线角零位误差引起的脱靶量基本收敛到0,落角误差收敛到稳态值;大的导航系数有利于消除视线角速率零位误差对制导系统的影响;导航系数越大,探测器角噪声引起的稳态脱靶量/落角误差也越大;提高导引头的响应比提高驾驶仪的响应更有利于提高制导精度。 相似文献