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。
The products have been used for military vehicle power supply, rocket launcher ground control devices and analogue aerospace station system.
已应用于军用车载电源、火箭发射地面控制装置及模拟空间仓等系统中。
The paper presents the composition, functions, technical performance and research of the solid rocket ramjet engine ground test equipment and measurement control system in detail.
介绍了固体火箭冲压发动机地面实验装置及测控系统组成、功能、技术指标和可以开展的研究工作。
The practical applications of this control system to the hypergolic bipropellant attitude control rocket engines at 30kg and 100kg thrust levels respectively are stated.
说明了该控制系统在30公斤级与100公斤级的双组元燃料变推力姿控火箭发动机中的具体应用情况。
The developing experience of launch rocket integration and control system is rather abundant in Ukraine.
乌克兰在运载火箭总体和控制系统方面的研制经验是比较丰富的。
The design and realization of a variable thrust liquid rocket engine control system is present in this paper.
本文讨论了某型变推力液体火箭发动机数字控制系统的设计和实现。
A variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper.
针对分级燃烧循环液体火箭发动机启动过程的特点，提出了一种变结构控制系统。
A pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
本文对变推力液体火箭发动机的脉宽采样数字控制系统进行了理论分析和实验研究。
It is very important to simulate the precision of fire of simple control Long Range Multiple Launch rocket System (LRMLRS) for improving the dispersion and reducing the number of rocket used in test.
简易控制远程多管火箭密集度仿真是提高射击密集度和减少简易制导多管火箭试验用弹量的重要手段。
This paper presents the critical design, researching method and procedure of acquisition system for valve current signal of liquid attitude control rocket engine.
介绍了液体火箭姿控发动机阀门电流信号采集系统的设计要点、研制方法与主要开发过程。
In the instantaneous thrust measurement of an attitude control solid rocket motor, dynamic characteristic of thrust measurement system affects the accuracy of thrust measurement.
在姿控发动机的瞬态推力测量中，推力测量系统的动态特性是影响推力准确测量的一个至关重要的因素。
Using microcontroller, the design and implementation of the common test instrument for aerial rocket launch control system solved the problems mentioned before.
但现有的航箭发控系统检测仪既不具有通用性，又不能测试航箭发射脉冲参数。
Using microcontroller, the design and implementation of the common test instrument for aerial rocket launch control system solved the problems mentioned before.
但现有的航箭发控系统检测仪既不具有通用性，又不能测试航箭发射脉冲参数。
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