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- Based on linear quadratic Gaussian (LQG) theory, this paper shows a study of a LQG optimal guidance law that minimizes the terminal miss distance and control energy consumption within the intercepting period. 以线性二次型高斯 (LQG)理论为基础 ,研究一种最小化末端脱靶量和拦截周期内控制能量消耗的具有可变有效导航比的LQG最优制导规律。
- LQG optimal guidance law LQG最优制导规律
- Abstract Optimal guidance law for a torpedo impacting vertically on a maneuvering evader in three dimensions is studied. 摘要 本文研究了三维空间中鱼雷垂直命中机动目标的最优导引律设计问题。
- Applying the optimal guidance law in this paper to a reentry warhead, this optimal control law was proved effective through computer simulation. 将此最优制导算法应用到某型再入弹头，通过计算机仿真验证了算法的正确性。
- First, the Maximum principle is used to generate an optimal guidance law for lunar landing, and the TPBVP is to be solved as a result of the numerical solution for optimal trajectory. 文中首先应用极大值原理设计了最优着陆制导控制律，此时求解最优轨迹变成一个两点边值问题(TPBVP)。
- The simulation results indicate that PN is one of the optimal guidance laws for non-maneuvering targets, and the OGL discussed in this thesis outperforms PN while intercepting maneuvering targets. 仿真结果表明，在不考虑目标机动加速度的情形下，传统比例导引律就是一种最优制导律，而本文所述的最优制导律较之传统比例导引律对于拦截机动目标精度更高，且算法简单，因此具有一定的适用性及工程应用参考价值。
- Impact Angle and Final Position Constrained Optimal Guidance Law 限制导弹落角和落点的最优制导律
- The Use of Steepest Ascent Method in Optimal Guidance Law Simulation of Missile 梯度法在导弹最优制导律仿真中的应用
- Approximate optimal guidance law for aeroassisted plane change problem 气动辅助异面变轨问题中近最优导引律解
- A RANDOM OPTIMAL GUIDANCE LAW OF AIR-TO-AIR MISSILE IN ALL DIRECTIONS 空-空导弹全向攻击随机最优制导律
- Trajectory Simulations on Active-Radar-Guided AAM Based on Optimal Guidance Law 基于最优末制导律的主动雷达空空导弹的弹道研究
- the optimal guidance law 最优制导律
- optimal guidance law 最优制导律
- Based on the game theory and LQG optimal control theory, the mini-max robust filtering is presented, which can minimize the filtering errors under the disturbance of uncertain noises. 根据博弈理论与最优控制理论,提出一种能够在具有不确定噪声干扰中最小化滤波误差的极小极大值鲁棒滤波器。
- The optimal high altitude guidance law with reentry constraint conditions is derived by using the optimal control theory,and the algorithm of time to go is also given. 采用最优控制理论推导出具有再入约束条件的高空最优制导律,给出了剩余时间的计算方法。
- Based on optimal control theory and singularly perturbed theory, a singularly perturbed midcourse guidance law that guarantees air-to-ground missiles to ascent quickly is proposed. 摘要为满足实际作战的要求，基于最优控制理论和奇异摄动方法，提出了一种可保证中远程空地导弹快速爬升到最优高度的中制导律。
- Simulation results show that the performance of the designed guidance law is superior to that of TPN and APN, and close to that of OPG. 仿真研究表明，该导引律性能优于TPN，APN，接近OPG。
- linear-quadratic-Gaussian optimal eontrol(LQG optimal controi) 线性二次型高斯最优控制
- In this paper, the precise initial guidance law based on velocity gain guidance and the state transition matrix for orbit interception were proposed. 摘要对于轨道拦截问题，给出了一种基于速度增益制导和状态转移矩阵的精确初制导方法。
- The miss distance caused by guidance method error and the effects of perturbation are compensated in this initial guidance law. 该初制导方法能补偿制导方法误差和轨道摄动对拦截脱靶量的影响。
