高速旋转固体火箭发动机压力测量方法研究

Pressure measuring method on solid propellant rocket motor with High-speed rotation

针对某固体火箭发动机高速旋转模拟试验系统,介绍了一种固体火箭发动机燃烧室压强测量方法,并研制了一套存储测试装置,该装置以STM32为控制核心,由信号调理模块、存储模块和无线传输模块等组成。当前经测量获取的推力-时间数据计算而间接得到的压强数据误差较大,通过对发动机燃烧室压强的直接测量能有效地规避因摩擦对推力的影响而导致的压强测试不准确的弊端。该装置通过螺纹与高速主轴的末端相连,能够检测并记录发动机工作过程中的压强数据,试验后可以取下测试装置或通过无线传输将检测的数据发送给上位机进行显示,为之后固体火箭发动机结构的设计和改进提供重要的实验依据。

It introduces a kind of measuring method and develops a set of storage measuring instrument used to measure chamber pressure on the basis of a simulation test system for high-speed rotation solid rocket motor.Taking microcontroller STM32 as control center,this instrument is consist of signal adjusting module,storage module,wireless transmitting module,etc.At present,the error of pressure results from calculation of thrust-time data measured is large.The direct measurement of pressure is able to effectively avoid the deficiency that the influence of friction on the thrust results in measurement error.This instrument is connected to the end of spindle by thread and it is able to record the pressure signal during the working process of rocket motor.In addition,the test results can be transmitted to the host computer by taking instrument down or wireless transmission after the test,which will provide important reference for later design and improvement of solid propellant rocket motor.