姿态控制发动机

采用CFD方法对一类火箭弹姿态控制发动机扩散段流场进行了数值模拟，并对几种典型流场进行了分析。

CFD method is used to simulate the flow field in divergent section of an attitude contorl motor , then several typical flow fields are analyzed .

旋转状态下姿态控制发动机喷流流场的数值模拟

The Jet Flow Field Simulations of a Rotating Attitude Control Motor

一种姿态控制发动机扩散段流场的数值模拟

Numerical simulation of divergent section flow field of an attitude control motor

姿态控制发动机相邻控制力相互影响研究

Research of the Interaction Between Adjusting Control Forces of the Attitude Control Motors

将非定常空气动力学数值计算方法创造性地应用于姿态控制发动机瞬态流场计算。

( 2 ) Transient jet-interaction phenomena , challenge project , is analyzed by computational unsteady aerodynamic method .

姿态控制发动机真空环境下工作产生的羽流对航天器造成的影响非常明显。

The plume from the attitude controlling rocket motor nozzle has an obvious effect on the aircraft in vacuum .

通过对某型导弹的姿态控制发动机模型及其在数字仿真中的实现进行研究。

A major motivation for this article is to investigate attitude control motor models of some kind of missile and achievement in digital simulations .

这些子级上安装了瓦·彼·格鲁什科设计的四推力室主发动机和谢·帕·科罗廖夫设计的用来控制推力矢量的新型姿态控制发动机。

The main four-chamber engines designed by V.P.Glushko and new control engines from S.P.Korolev for controlling the thrust vector were installed in these units .

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 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 .

本文用稀薄气体流场直接模拟的方法对卫星姿态控制发动机喷管外考虑化学反应的真空羽流场进行了数值模拟，得到了与理论分析相一致的数值模拟结果。

Vacuum plume out of the satellite altitude controlling engine nozzle with chemical reaction has been numerically simulated by using Direct Simulation Monte Carlo methods ( DSMC ) in this paper . The numerical simulation result obtained in this paper agrees well with the theoretical analysis .

姿态控制推进电动机控制发动机推力的电路

Attitude control propulsion motor throttle circuit

自旋激光驾束导弹实时仿真系统旨在研究该导弹的转速、转角的近似计算和解决姿态控制时执行机构&姿态控制发动机在点火时刻的空间位置问题。

Approximate calculations on rotational speed and angle of spinning missile under laser beam ride guidance for real time simulation are investigated , and a problem of obtaining the space position of an actuator that is an attitude control motor and carrying out attitude control is resolved .