Based on the rotor free-wake model and the rotor trim model, an analytical method is developed for the prediction of helicopter rotor induced velocities on missile trajectory.
应用自由尾迹方法和旋翼配平模型，建立了一个悬停和前飞状态旋翼在导弹发射线上的诱导速度计算模型。
Some real-time computation problems for the optimization of air defence missile trajectory are presented, and the quasi-Newton methods are used to compute the initial optimization trajectory.
提出防空导弹轨道优化的一些实时计算问题，并且应用拟牛顿法计算初始优化轨道。
According to a predetermined trajectory, ballistic missile with rocket engine propulsion takes a flight to intended targets under the action of the control system.
弹道导弹是用火箭发动机推进，在控制系统作用下按预定的弹道飞行至预定攻击的目标。
By using the line of sight (LOS) measurements from space based infrared sensors, free flight phase trajectory estimation problem of ballistic missile is studied.
主要研究空间预警系统利用星载红外传感器的视线测量估计弹道导弹自由飞行段弹道的问题。
Due to mission profile , launched conditions and trajectory , maneuver chains for stand off missile are designed . instruction control model and maneuver model is setup for ucav flight simulation.
结合作战任务剖面、导弹发射条件和弹道，设计出无人机防区外攻击导弹发射前、后的机动动作链。
According to force analyzing of missile, the complicated force calculation has been replaced by the fitting formula, and a simplified trajectory model has been developed.
根据导弹受力特性分析，用拟合公式替代了复杂的外力计算，并建立了简化的外弹道模型。
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。
The calculation result of example shows that glide standard trajectory designed can meet the trajectory tactical requirements when missile is launched in different velocity and altitude.
实例计算结果表明，设计的下滑基准弹道可以满足载机不同发射速度、不同发射高度条件下弹道的技术要求。
The longitudinal glide trajectory design for general air-to-ship missile is studied. Using spline function as glide standard trajectory of missile is presented.
对一般空舰导弹的纵向下滑弹道进行了设计研究，提出用样条函数作为导弹的纵向下滑基准弹道。
In this study we have attempted to investigate the trajectory stability problems of head-on anti-tactical ballistic missile guidance by way of the Lawes Criterion.
针对一种拦截战术弹道导弹制导规律的特点，以经典的劳斯稳定判据为依据，对其制导控制回路的稳定性进行了分析。
As an example, maximum trajectory optimization was applied on a two-stage ballistic missile, and a comparison of original and optimal trajectories was presented with figures and tables.
对某型二级弹道式导弹进行了最大射程弹道优化，并将得到的最大射程弹道与原弹道进行了比较分析。
In order to enter into the ideal trajectory with minimal energy, the nonlinear thrust vector control and the prediction guidance are adopted in the missile guidance control system.
为使飞行器能在主动段很快地进入到理想弹道上，系统采用了非线性的推力向量控制及预测制导方法。
In order to reappear the fuze movement rule through testing the parameter of movement under simulation trajectory environment, the missile-borne memory test system is designed in the thesis.
为了通过测试引信在模拟弹道环境下的运动参数，再现其运动规律，本文研制了新型弹载存储测试系统。
In order to realize large airspace transfer orbital trajectory of an anti-ship missile, a 3-dimensional virtual target's proportional navigation guidance (PNG) law is proposed.
为了实现反舰导弹的大空域变轨，提出了一种三维虚拟目标比例导引律。该导引律利用简单的控制指令就能控制导弹完成复杂的大空域变轨。
In order to realize large airspace transfer orbital trajectory of an anti-ship missile, a 3-dimensional virtual target's proportional navigation guidance (PNG) law is proposed.
为了实现反舰导弹的大空域变轨，提出了一种三维虚拟目标比例导引律。该导引律利用简单的控制指令就能控制导弹完成复杂的大空域变轨。
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