This paper studies a new guidance law for wide quick pursuit.
研究了一种用于全向快速追踪的导引规律。
The system consists of a guidance law and a basic attitude controller.
系统分为基本姿态控制器设计和制导系统设计两个部分进行研究。
While fuzzy guidance law with robust, intelligent, is great concerned.
其中模糊制导律鲁棒性强，智能性高，受到很大关注。
Three different formulations of the guidance law requirement are presented.
提出了三种不同组合的制导规律要求。
When targets flight with zero load-factor, it is a changeable proportional factor guidance law.
当目标作非机动飞行时，最优制导律是变比例系数的比例制导。
Based on Fuzzy Neural Network (FNN), an intelligent adaptive sliding-mode guidance law is presented.
在自适应滑模导引律的基础上，提出了一种基于模糊神经网络(FNN)的自适应滑模导引律。
Besides, the analog guidance law can not also apply digital signals come from the data link directly.
传统的模拟信号导引律已不能满足将数据链的数字接收信号直接应用的要求。
New guidance law based on latest control theory has become a hot spot in precision guidance technology.
基于最新控制理论的新型导引律成为各国精确制导技术的研究热点。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
A nonlinear guidance law and control strategy is proposed for aircraft applying to attack the ground fixed targets.
对于攻击地面固定目标的飞行器，提出一种非线性制导律和控制方法。
Based on fuzzy logic, a fuzzy intercept wire-guided guidance law of the underwater vehicle is proposed in this paper.
基于模糊逻辑理论，本文提出了一种水下航行器模糊前置点线导导引律。
This design method guaranteed better homing performance compared with the proportional guidance law and traditional DGL.
所提出的设计方法较比例导引律和传统微分对策导引律具有更好的寻的性能。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
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。
The guidance law right to intercept moving targets is of a highly adaptive and a kind precision guided law with practical value.
并且对拦截机动目标有很强的自适应性，是一种具有工程实用价值的高精度末制导律。
For the case of a three-dimensional interception, a new continuous extended sliding mode guidance law with robustness is proposed.
对于三维目标拦截问题，提出了一种新的具有鲁棒性的扩展连续滑动模态末制导律。
Based on the variable structure control theory, a guidance law that can perpendicularly impact on the target was proposed in this paper.
基于变结构控制理论，提出了一种垂直命中目标的导引律。
From differential game point of view, a optimum intercept guidance law with uncertain factors is discussed on minimum-maximum principle.
本文从微分对策观点出发，利用极小极大原理讨论了带有不确定因素的最优拦截制导律。
Traditional homing guidance law can not meet the increasingly strict interception requirements, especially for target with great maneuver.
传统末制导律不能满足日趋严格的拦截要求，尤其是目标大机动规避。
A midcourse guidance law based on zero effort miss forecasting is presented for intercepting a high-speed target in three-dimensional space.
针对三维空间内的高速飞行目标，提出了一种基于预测零控脱靶量的中制导段导引方法。
Finally, to the difficulty of the design parameters in adaptive fuzzy guidance law, two adaptive fuzzy guidance laws based on RBF are designed.
最后，针对自适应模糊导引律参数设计的困难，设计了两种基于RBF神经网络的自适应模糊导引律。
For a new time-to-go algorithm, the optimal guidance law can be realized without a trajectory control engine along the lengthwise axis of the missile.
由于采用了一种新的剩余时间算法，在空间拦截弹的弹体纵轴方向无轨道控制发动机的情况下，也可以实现这种最优导引规律。
Firstly, based on simplified dynamics of lunar soft landing, an explicit guidance law was induced by solving the special two-point boundary value problem.
首先，基于简化的软着陆动力学模型，通过求解特殊两点边值问题，给出了一种实时显式制导方法。
The estimated results of the slopes are introduced into the EKF to get state estimations without radome interference which generates the guidance law command.
将斜率估计结果代入EKF，得到滤除天线罩误差影响的系统状态量估计结果并形成制导指令。
Finding rapid and analytical solution to the calculation of zero effort miss (ZEM) has helped to improve the calculation speed of the predictive guidance law.
寻找快速的甚至是解析的零控脱靶量(ZEM)计算方法有助于提高预测制导方法的计算速度。
Secondly, error modules of main braking were established and errors of the guidance law designed above were analyzed by error sensitivity coefficient matrixes.
其次，建立了月球软着陆主制动段的误差模型，并运用误差敏感系数矩阵对所提出制导律的制导误差进行分析。
To meet the cruise missiles air-to-surface attack requirement, specified impact angle guidance law is presented based on line of sight (LOS) information framework.
根据飞航导弹对面攻击的需要，针对可以获取的信息，设计了视线角信息框架下的双平面导引规律，以实现指定入射角的攻击，并从理论上进行了分析。
The key for fighter aircraft to implement target pursuit and interception in an air dogfight is to design high performance guidance law for its fire control system.
战机追踪导引性能的关键是其火控系统应具有高性能的导引律。
Neglecting the time canstants, axial accelerations and the control overflow, the optimal strategy is reduced to the conventional proportional navigation guidance law.
当不计飞行器的响应时间、纵向加速度和控制溢出时，蜕化为常规比例导引。
Neglecting the time canstants, axial accelerations and the control overflow, the optimal strategy is reduced to the conventional proportional navigation guidance law.
当不计飞行器的响应时间、纵向加速度和控制溢出时，蜕化为常规比例导引。
应用推荐