主动段的英文

• active leg
• powered phase
• propulsion branch

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

• 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。