1) optimal sliding-mode guidance law
最优滑模制导律
1.
An optimal sliding-mode guidance law which is robust to parameter perturbations and external disturbance is proposed for the space interception problem of maneuvering target,and an intelligent method of the guidance law is studied.
针对机动目标的空间拦截问题,文中介绍了一种对参数摄动和外干扰具有鲁棒性的最优滑模制导律,并对其智能化实现方法进行了研究。
2) Optimal guidance law
最优制导律
1.
Based on analyzing the missile and target motion dynamics, the fuzzy rules are established according to design expert experience of optimal guidance law and characteristics of measurement noise disturbances.
进行模糊末制导律设计时,在分析导弹和来袭目标运动特性的基础上,根据最优制导律设计专家经验和测量噪声的干扰特性建立模糊规则。
2.
By using the steepest ascent method,the optimal guidance law is gained to solve this kind of problem: the final time is undefined and there are constrains.
对三种不同的拦截情况 ,进行了仿真 ,结果证明梯度投影法数值求解导弹最优制导律是可行
3) sliding mode guidance
滑模制导律
1.
This method is introduced by taking example of the sliding mode guidance law.
以滑模制导律为例介绍了这种应用方法,仿真表明,应用该方法能够把视线转率限制在较小的范围之内,从而实现对目标的拦截。
4) Optimum Intermediate Guidance Law
最优中制导律
1.
The Optimum Intermediate Guidance Law of Long Distance Air-to-Air Missile;
远距空空导弹最优中制导律研究
5) suboptimal guidance law
次最优制导律
1.
A suboptimal guidance law for satellite guided bombs using a genetic algorithm;
基于遗传算法的卫星制导炸弹次最优制导律设计
2.
A suboptimal guidance law is designed based on single neuron to command satellite guided bombs to move with a small fall angle.
为了满足卫星制导炸弹大着地角的弹道要求,基于单神经元进行了次最优制导律设计。
6) optimal terminal guidance law
最优末制导律
1.
An optimal terminal guidance law with both interception and impact angle constraint is derived according to simplified missile movement equation and Lagrange method.
为了研究带有落角约束的最优末制导律,利用拉格朗日法,构造带有落点和落角约束的导弹运动方程,研究了制导系统中的动力学滞后对脱靶量和落角误差的影响。
补充资料：波束制导(见遥控制导)
波束制导(见遥控制导)
beam-rider guidance
boshu zhidao波束制导(beam一rider guidanee)见遥控制导。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条