Microwave phase shifter in phased-array radar, communications, instrumentation, heavy ion accelerator and the missile attitude control system has a broad application prospects.
微波移相器在雷达、通信、仪器仪表、重离子加速器及导弹姿态控制系统中有着广泛的应用前景。
As a synthesis method in control system, the sliding mode of variable structure control is invariable, and which is its most excellent advantage in the missile attitude control system.
变结构控制作为控制系统的一种综合方法，它的滑动模态具有不变性，这是变结构控制在导弹姿态控制中最突出的优点。
This paper investigates the large Angle attitude post stall maneuver control for the agile turn phase of an air-to-air missile that has high off-boresight capability and head reverse maneuverability.
为研究具有大离轴角及越肩发射能力的先进空空导弹初始段敏捷转弯方法，研究了装有反作用喷气控制系统的空空导弹的大角度姿态过失速机动控制律。
A mini digital Attitude and Heading Reference System (AHRS) based on DSP is designed, which can be used on air-to-air missile with Strapdown Inertial Navigation System (SINS) as mid-course guidance.
论文针对使用捷联惯导系统为中制导的近距空空导弹，设计了一种基于数字信号处理器(dsp)的小型数字式捷联航姿应用系统。
This paper deals with the near-minimum-time attitude maneuver control of vertical launching tactical missile, in order to solve fast attitude maneuver of this kind of missile.
针对战术导弹垂直发射姿态调转时的快速性要求，研究了垂直发射快速姿态调转的次最小时间控制问题。
The north-seeking instrument can be well integrated with the bearing and attitude to serve all army chariot and missile launch system with its high practical value.
利用该方案，可将寻北仪和方位水平仪较好地结合在一起，可适用于各种陆用战车和导弹发射车，具有较高的实用价值。
These conclusions can be used for system design of rotating missile in the attitude control system and selection of structure and pneumatic parameters for supersonic fluidic elements.
所得结论可为旋转弹姿态控制系统的总体设计以及超音速射流元件的结构及气动参数选择提供依据。
The results show that the missile rotation has hardly effect on inner flow field structure of SFE, but some effects on the control thrust of attitude control motors both in magnitude and in direction.
结果表明，弹体旋转对超音速射流元件内部流场结构几乎没有影响，而对姿态控制发动机的控制推力大小和方向的影响不容忽视。
The effectiveness of aero control decreases as dynamic pressure decreases. Therefore impulse attitude control motor(ACM) is to be used to maintain fast response of missile in low dynamic pressure.
气动控制在低动压时其效率会有相当下降，为了使导弹在低动压时仍然具有一定的快速响应性，在导弹上安装脉冲姿控发动机参与姿态控制是一条可行的途径。
Based on infinite interpolation theory and multi-block grid technique, construction grid of interceptor missile with multiple attitude control motors was generated.
基于无限插值理论和多块网格技术，生成了带多姿控发动机的拦截弹结构体网格。
In order to effectively adjust attitude motion of interceptor missile by combine control, an attitude control method was presented.
为了有效地调整复合控制拦截弹的姿态运动，提出了一个姿态控制方法。
In order to effectively adjust attitude motion of interceptor missile by combine control, an attitude control method was presented.
为了有效地调整复合控制拦截弹的姿态运动，提出了一个姿态控制方法。
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