1) guidance law
制导律
1.
Three-dimensional guidance model and guidance law design for head pursuit interception;
前向拦截的三维制导模型及制导律设计
2.
Variable structure guidance law with terminal attack angle constraint;
带终端攻击角度约束的变结构制导律
2) Midcourse Guidance Law
中制导律
1.
Variable Structure Midcourse Guidance Law with Angle Constraint for Anti-Ship Missile;
带落角约束的反舰导弹变结构中制导律研究
2.
A Optimal Midcourse Guidance Law Using Neural Network;
基于RBF神经网络的一种最优中制导律
3.
Derivation and simulation of a suboptimal midcourse guidance law for air-launched cruise missile;
一种次优空射巡航导弹中制导律的推导与仿真
3) terminal guidance law
末制导律
1.
Robust terminal guidance law for maneuvering targets;
拦截机动目标的一种鲁棒末制导律设计
2.
Considering the attack process of the television guidance UCAV,taking a terminal guidance law of UCAV as a problem of tracking the target at meeting the impact attitude angle restriction,the law based on autopilot was designed,which eliminates the influences of dynamic factor of autopilot and gravity factor on hitting the target.
综合考虑电视指令制导无人攻击机的作战过程,将其末制导律设定为满足落角约束的目标跟踪问题,设计了一种基于自动驾驶仪末制导律,该方法消除了自动驾驶仪动态因素和重力等因素的影响;并通过以平行接近法作为辅助导引法来克服追踪法的缺陷;新的末制导律加自适应卡尔曼滤波,使得无人攻击机不仅可以对固定目标实施攻击也可以对低速移动目标实施攻击,且能保持无人攻击机垂直命中目标,提高作战效能。
3.
Selecting appropriate terminal guidance law is an important factor for the precise guidance of anti-ship missile.
选择合适的末制导律是实现反舰导弹精确制导的重要因素。
4) initial guidance law
初制导律
1.
A closed-form initial guidance law based on feed forward and feedback neural network control for finite propulsive reentry spacecraft was presented.
提出了一种前馈反馈神经网络闭路初制导律。
2.
Based on analysis of characteristics of initial guidance, a new initial guidance law and a new method of calculating time to go are brought forward.
在分析组合制导中初制导阶段特点的基础上 ,给出了一种新的初制导律形式 ,并且提出了一种适合初制导律的剩余时间拟合方法。
5) H∞ guidance law
H∞制导律
1.
Certainly, the guidance law is simple and avoids solving Hamilton-Jacobi partial differential inequation in H∞ guidance law.
此导引律设计简单,避免了H∞制导律中求Hamilton-Jacobi偏微分不等式的解析解。
6) guidance law
制导规律
1.
The guidance law of photos pot in mirror is presented.
提出了镜面像点制导规律的基本原理,针对存在的缺陷给出了它的改进形式,进行了理论分析,并与三点法制导规律做了比较。
2.
The relation between guidance law and target position forecast from development of classic guidance law is summarized.
在分析经典制导规律的改进过程中,总结出制导规律的性能与对目标位置预测的关系,从而得出改进制导规律的一种思路。
3.
By combining the differential equation with the according guidance law, a relative trajectory equation is set up which will help to study the characteristic of trajectory.
文中的推理过程表明 ,这种导引规律对导弹、目标的运动速度几乎没有限制 ,理论上说明运用该制导规律的导弹将能对付高机动大速度目标 ,其弹道方程的建立 ,使得研究该制导规律下的弹道特性成为可能。
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