【摘要】 为了解决卫星制导炮弹的制导问题,进行了考虑着地角、脱靶量和控制能量等多约束条件的最优制导律设计.在制导炮弹的制导阶段,弹目运动学模型是时变的系统,最优制导律的设计涉及到困难的变参数微分方程解析求解.通过离散计算方法来解决该问题,首先将运动状态方程组离散化,然后推导了各离散时间点最优制导律的递推公式,并通过取均值得到各时间段上常系数的制导律,以减少计算量.该方法降低了带多约束条件最优制导律的设计难度,同时具有较广泛的适用范围.利用设计所得制导律,进行了制导炮弹六自由度全弹道仿真,并同使用比例导引律的计算进行了比较.结果显示,着地角增加了108%,制导精度提高了246%.更多还原

【Abstract】 To solve the guidance problem of satellite-guided projectiles,an optimal guidance law was designed with restrictions of the landing angle,miss distance and control energy.During guidance,the projectile kinematics model was time-varying.As a result,the optimal guidance law design need analytically solve differential equations with varying parameter,which was very difficult.This problem was solved using a discrete computation method.The motion state equations were initially discretized,then the recursion formulas of optimal guidance laws were derived at all the discrete time points.Using mean values,the constant coefficient guidance laws at each time segment were obtained to reduce the computation load.This method decreased the design difficulty and could be widely applied.Whole ballistic simulation of six degree-of-freedom was made using the optimal guidance law and general proportional navigation guidance law respectively.Comparing with results from the proportional navigation law,the optimal guidance law produced landing angle increase of more than 108% and accuracy improved more than 246%.更多还原