制导律,guidance law英语短句,例句大全

制导律,guidance law
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

英文短句/例句

1.Study of a Guidance Law for SAR Image Guided Missiles一种SAR成像制导导弹制导律研究
2.Design of Robust Guidance Law for SINS/GPS Guided Bomb惯性/卫星制导炸弹鲁棒制导律设计
3.The Design of Guidance Law of Aerodynamic Missile Based on Intelligent Sliding-mode Variable Structure飞航导弹智能自适应滑模制导律设计
4.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
5.Design of H_∞ Control Based Nonlinear Terminal Guidance Law基于H_∞控制的非线性末制导律设计
6.Design and Simulation of Guidance Law Based on Non-singular Terminal Sliding Mode for Guided Bomb with INS/GPSINS/GPS制导炸弹非奇异Terminal滑模制导律设计与仿真
7.Deep space impact exploration guidance based on advanced predictive guidance基于改进预测制导的深空撞击探测末制导律
8.Optimal Terminal Missile Guidance Law Based on Fuzzy Neural Networks基于模糊神经网络的导弹最优寻的末制导律
9.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
10.Air-to-Air Missile Robust Adaptive Guidance Law and Scene Simulation Research;空空导弹鲁棒自适应制导律及其视景仿真研究
11.Air-to-Air Missile Intellectualized Guiding Law and Three Dimensional Animation Simulation Research;空空导弹智能化制导律和三维动画仿真研究
12.The Research of Missile Precision Terminal Guidance Law Based on Fuzzy Logic;基于模糊逻辑的导弹精确末制导律研究
13.Nonlinear H_2/H_∞ Robust Guidance Law of Missile Based on State Feedback基于状态反馈的导弹非线性H_2/H_∞鲁棒制导律
14.Investigation into Variable Structure Midcourse Guidance Law of Intercept Missile Based on Data Link基于数据链的拦射导弹变结构中制导律研究
15.Forecast Variable Structure Midcourse Guidance Law Design for Supersonic Intercept Missile超声速拦射导弹的一种预测变结构中制导律
16.Adaptive Terminal Sliding Mode Guidance Law for Air-to-Air Missile Based on Neural Network空空导弹的神经网络自适应终端滑模末制导律
17.Dynamic Inversion Based 3D Terminal Guidance Law Designed for Anti-Ship Cruise Missiles基于动态逆的反舰巡航导弹三维末制导律设计
18.Research on Terminal guidance law of missiles based on nonsingular terminal sliding mode基于非奇异Terminal滑模的导弹末制导律研究

相关短句/例句

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 lawH∞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。