Research On Design Method Of Rotating Engine Parameter Test System

Recently, to raise the firing accuracy of weapon, high speed rotation are generally adopted as the conventional field rockets. To need demand of the control system, low speed rotation are adopted in some missiles. So, it is important to test and study the different kinds of working characteristics of the rotated rocket motor. Now, passive rotated experimental devices and active rotated experimental devices are generally used as the experimental devices. In view of the high speed rotation of passive rotated experimental devices, this paper designs a test system which is used to test the thrust, pressure, temperature and rotational speed of the high speed rocket motor.Firstly, this paper introduces the test technology of high speed rotation solid propellant rocket motor and the current status of memorized test technology at home and abroad. This paper also describes the development trend of memorized test technology.Secondly, the test system of rocket motor is been overall designed. The design includes structure, technique index and key technology of the memorized tester, it also include the design scheme of testing software.Thirdly, software and hardware of the test system are designed.There are three parts in the designation of the hardware, including a memorized tester, which uses STC12C5A60AD as its control chip and FM24C256 as its external memory, can collect, store and transfer the pressure and temperature of the rocket motor; A rotational speed testing module, constituted by YTHN60 and USB-6251, which can test the rotational speed of the motor; A thrust testing module, constituted by BHR-4, DH3840 and USB-6251, which can test the thrust of the motor. This paper uses Labview as the software development platform to finish the data processing software for host computer.Finally, with some experiments, the memorized tester, the rotational speed testing module and the thrust testing module have been verified. The result of experiment proves that the parameter test system of rocket motor desgined in this paper is viable in the practical project.