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underwater terminal guidance 水下终点制导
High-speed reentry aerocraft is usually with terminal guidance system. 高速再入飞行器通常具有末制导系统。
The matching problem of terminal maneuver and terminal guidance trajectory of anti-ship missile is analyzed. 对反舰导弹的末端机动与末制导段弹道之间的配合问题进行了分析。
A terminal guidance model is designed for air-to-air missile (AAM)to intercept maneuvering targets in this paper. 构造了拦截加速机动目标的空空导弹末制导状态模型。
The simulation of the terminal guidance procedure is carried out, and some factors which affect the miss distance quantity are analyzed. 提出了修正比例导引律的实现方案 ,进行了末制导过程的仿真 ,并分析了影响脱靶量的一些因素。
To improve the capture probability,the hand-over point of anti-ship missiles between midcourse guidance and terminal guidance was analyzed. 为了提高对目标的捕捉概率,研究了反舰导弹中末制导交班点的选择问题。
Based on the six-freedom-degree ballistic equations, the model of air to ground submunition in the terminal guidance stage was established. 利用六自由度动力学模型对末段弹道进行了仿真。
From the characteristics of terminal guidance projectile at moving targets,the impact conditions of moving targets in simulation system were analyzed. 从末制导炮弹对运动目标射击的特点出发,探索了模拟系统设计中运动目标的命中条件。
From the characteristics of terminal guidance projectile at moving targets, the impact conditions of moving targets in simulation system were analyzed. 摘要从末制导炮弹对运动目标射击的特点出发，探索了模拟系统设计中运动目标的命中条件。
The final phase is terminal guidance when the missile uses a highly accurate tracking system to make rapid maneuvers for intercepting the target. 最后的阶段是末端制导，此阶段导弹利用高精度的追踪系统，快速机动，截击目标。
In the terminal guidance stage of longrange airtoground missile, its parameters vary widely and abruptly, causing the missile to miss the target. 制导精度分析是空地导弹制导控制系统设计过程中必须考虑的关键因素之一。
A simplified linearized feedback control method of terminal guidance was put forward for a nonlinearized model including unknown parameters of missile in this paper. 针对包含未知参数的导弹运动非线性模型,提出了一种用于末制导的线性化反馈简化控制方法。
One simulation system for anti-missile ECM is developed. This system is aimed at anti-ship missiles with terminal guidance radar and may work on a high performance PC. 研制了一个可以在高性能个人计算机上运行的、针对采用末制导雷达的反舰导弹的电子对抗问题的仿真系统。
For observing, evaluating and researching the effect of ECM to terminal guidance radar of antiship missile, a simulation system for ECM to antiship missile is developed. 为观察、评估和研究针对反舰导弹末制导雷达的电子干扰的效果,研制了一个反舰导弹电子对抗仿真系统。
When the space interceptor transits intermediate guidance into terminal guidance, its attitude may deviate far from the expected state for some uncertain terms. 当空间拦截器由中制导阶段转入末制导阶段时，受不确定因素的影响，其姿态可能与预定姿态相差较远。
The computational results show that the transform condition with higher precision to the terminal guidance by using proportional guidance in the midcourse is guaranteed. 计算结果表明，在中段运用比例导引可保证向末制导转换时有较高精度的转换条件。
The Synthetic Discriminant Function (SDF) algorithm and the optical method to realize SDF are reviewed.A new missile terminal guidance system based on SDF correlator is presented. 论述了综合判别函数（SDF）的基本理论和光学实现途径，提出了一种基于综合判别相关器的导弹末制导系统。
In basic framework of total system,signal stage,isomorphic simulation for centroid chaff countering anti-ship missile terminal guidance radar,models of warship were researched. 在全系统的、信号级的、同构的仿真研究基本框架下,从研究针对反舰导弹末制导雷达的质心式箔条干扰的目的出发,对目标舰的有关模型进行了研究。
This approach makes correction to radar-seeker signal efficiently by making the best use of SINS information, and meets real time and precision demanded by system by adjusting nodal point number of filter,and increases the precision of terminal guidance. 该方法可充分利用捷联惯导信息,对雷达导引头的测量信号进行有效的校正补偿,同时又可根据系统对校正算法实时性与精度的要求,通过合理地调整滤波算法节点数来满足系统的设计要求,从而大大地提高反舰导弹末制导的导引精度。
Simulation result showed that response time of missile was reduced and guidance accuracy was accordingly increased by side jet and aerodynamic compound control manner in terminal guidance. 通过仿真研究表明：在末制导阶段，采用燃气动力/气动力复合控制方式可提高导弹的快速性，进而提高导弹的制导控制精度。