主动段的英文

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英文翻译
造句

active leg
powered phase
propulsion branch

主动 initiative
段 section; segment; part; para ...
弹道主动段 powered phase of trajectory
主动段弹道 powered trajectory
主动段截击 boost phase intercept; boost-phase interception; thrust phase intercept
主动段速度 speed under power
主动段以后 postboost
主动段制导 powered phase guidance
主动段转弯 boost turn
主动段马赫数 sustained mach number
弹道主动段制导 delivery guidance
轨道主动段制导 ascent guidance
主动段飞行距离 all-burnt range
主动段稳定系统 powered stabilization system
主动段制导装置 primary-guidance equipment
主动段终点高度 all-burnt altitude; burnout altitude
主动段终点偏差 deviation at burnout
地面控制的主动段制导 ground controlled boost guidance
主动段末端运动参数 burnout conditions
在弹道主动段上短时间机动 short powered-flight maneuver
被动段 inactive leg
滑动段 glissile segment
活动段 active segment
被动段上升 power-out ascent
手动段同步 manual segment synchronization

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例句与用法

The precision of hitting will be improved obviously if we can offer a set of simple guidance control systems in powered phase of the rocket projectile
如果能在火箭主动段加一套简易的控制系统来控制火箭的姿态，则将大大提高火箭的命中精度。
Spinning flight of ballistic missile in boost phase is a new idea in order to penetrate laser ’ s interception . spinning missiles may be unstable due to dynamic and control interactions
弹道导弹主动段自旋飞行是一种新的构想,旨在对抗激光武器拦截,实现主动段突防。
Aiming at this problem , particle filter is studied . combination filter algorithm is constituted using ukf and improved particle filter ( upf ) , and missile ’ s states with noise increase are estimated
针对这个问题,研究了粒子滤波算法,利用ukf和改进的粒子滤波( upf )组成联合滤波估计算法,可以有效估计具有噪声增大时导弹主动段运动状态。
According to the character of ballistic missile in boost phase , the gravity turn model is established , and according to the position relationship between early warning satellite and the target , the measure model is established
根据弹道导弹主动段运动的特点,建立了主动段运动重力转弯模型。根据预警卫星与目标的位置关系,建立了观测模型。
In this dissertation , missile ’ s states in the boost phase and trajectory parameters estimate algorithms are studied by using angles of arrival measurement from space - based infrared sensor , and the availability and precision is validated through simulation
本文主要利用地球同步轨道的预警卫星敏感器探测的目标视线角测量,对导弹主动段运动状态和弹道参数估计算法进行了研究,并通过仿真验证了方法的有效性和可行性。
The controlling force developed by the jets is working at the beginning of the initiative trajectory ( 0 . 385 - 3 . 385s ) to control the attitude of the projectile to keep its axis on the direction of launch - direction , so as to reduce the effect of initial disturbance
控制力由喷流作用力产生，在主动段的初始段( 0 . 385 3 . 385秒)控制弹体的姿态，使弹轴维持在初始方向上，从而减少初始干扰，减小落点散布(飞行时间约170秒) ，提高精度。
The missile ’ s lunch point parameters and burnout point parameters are estimated using boost phase state estimation , and the impact point is predicted according to ellipse trajectory theory . and the effect of the estimation error of the burnout point on the impact estimate precision is analyzed
应用主动段的状态估计值估计了导弹发射点参数和关机点参数,根据椭圆弹道理论进行了落点预报,并分析了关机点参数估计误差对落点估计精度的影响。
Based on the aerodynamic characteristics of space shuttle booster - like missile bodies at angle of attack from 0 to 180 , the flying characteristics of high maneuver at 90 angle of attack and velocity consuming at 180 angle of attack are analyzed
摘要以新一代无翼式气动布局导弹为背景，在大攻角气动特性理论基础上，分析了在导弹主动段、攻角在180范围内变化的导弹飞行特性，得出了90内大攻角最大转弯能力和180攻角附近最大降速效果的结论。
Aiming at the nonlinearity of state and measure equation and measurement being only angle information , which results in poor observability and classical estimate methods such as extended kalman filter not converging , the boost phase states and covariance are estimated using unscented kalman filter ( ukf )
针对状态方程和观测方程都是非线性方程,观测量只有角度信息,造成可观测性弱、经典的滤波算法如扩展卡尔曼滤波方法不易收敛的问题,利用unscented卡尔曼滤波ukf算法对主动段进行状态和协方差估计。