推力终止

用MonteCarlo法分析固体火箭发动机推力终止过程内弹道散布

The analysis of interior ballistic dispersion of SRM during thrust termination with Monte Carlo method

用辨识方法确定了带反喷固体火箭发动机推力终止过程中的瞬变参数，视这些参数是服从正态分布的随机变量，用MonteCarlo方法分析了推力终止过程内弹道的散布。

As the transient parameters during thrust termination of SRM with four reverse nozzles are determined by identification techniques and considered as random variables which obey normal distribution , the interior ballistic dispersion during thrust termination can be analyzed by Monte Carlo method .

固体火箭发动机反向喷管推力终止技术

Technique of thrust termination with reversal nozzle for solid rocket motors

固体火箭发动机推力终止试验技术探讨滚珠式推力终止装置可靠性研究

An Exploratory Research of Test Technique for Solid Rocket Motor Thrust Termination

按经济性考虑设计推力终止反喷管

Design of the Reversal Nozzle for Thrust Termination in Consideration of Economization

定性分析了固体战术地地导弹推力终止时反向喷流的气动干扰。

Aerodynamic interference of reverse jet for solid tactical ground to ground missile is analysed qualitatively .

本文介绍一个反向喷管推力终止的冷模拟实验。

A cold air experiment on thrust termination of a solid rocket motor with reversal nozzles is described in this paper .

研究了固体火箭发动机推力终止试验时，反向喷管堵盖打开时间及同步性测量方法。

Measuring method of opening time and operating synchronism of the reverse nozzle closures of solid rocket motor during thrust termination test was studied .

为解决无推力终止装置的末速不准问题，可在末级发动机采用姿态调整装置，对射角进行调整，配合末速以满足射程要求。

In order to solve the problem of lack of thrust termination devices , a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range .

某固体发动机推力终止装置结构空间十分有限，为保证推力终止时发动机负推力大于等于零的要求，必须尽可能地提高反推力效率。

The structural space of thrust termination mechanism in the solid motor is very limited . In order to meet the demand that negative thrust of the motor is not less than zero , efficiency of reverse thrust must be improved as far as possible .