Study On Control System Of Calibration Of Rocket Engine Thrust Measurement At The Testing Tocation

Before the measurement test of rocket engine thrust, the calibration and checking of measuring system which related to the accuracy of the measured data and the reliability of the measurement process is indispensable and important. The method, simulating actual working conditions to finish the static calibration of measurement system on spot-local calibration, has been widely adopted in the research department and productive unit of the rocket engine.This paper describes the loading control technology of the device of rocket engine thrust measurement at the testing location. Firstly, discussing and analyzing the research situation at home and abroad, mastering the latest trend and direction of the current development in this field. Secondly, designing the device of rocket engine thrust measurement at the testing location and discussing the component parts of the device. Again, according to classical control theory, detail of the control option and a control model of such kind of control device are given. Then, finishing hardware design of control system. The main content is the control circuit of each part; Finishing the software design through programming; After completing the previous sections, the reliability of this equipment are proved through the relevant experiment procedures. The device of rocket engine thrust measurement at the testing location is a blend of the servo control technology and piezoelectric ceramic micro-displacement technology which improves the perfor mance of equipment and the efficiency of the experiment greatly, also eliminate the strength and disadvantages of the manual operation.At the request of Xi ’an aerospace automation co., LTD, finishing the design of overall effort and mechanical structure. The mechanical structure design mainly includes the driving parts, transmission parts, ball screw and moving beam, etc. Through the above- mentioned structural design, it will lay the foundation of the following control design;Secondly, with the aid of the classical control theory, introducing the latest control technology to the design of control system in this article and constructing control models for which is fit the automatic calibration of rocket engine thrust measurement at the testing location. From the principle of servo control system, automatic control unit is demonstrated, and the control model of the Ac servo moto is established;Again, according to solving the above-described control scheme, form hardware aspect, this paper puts in place practical, effective solutions leading to control system. This article mainly relies on normative study and analyses from several following aspects: servo control unit, microcomputer network control unit, manual control unit, etc. Each unit of electrical control circuit is established and the design of the electrical diagrams is completed.Then, the design of software: in this part, according to the principle of modular design, finishing the design of software. Specifically, the main achievement of this research is as follows: Manual control module, auto- loads module, actuating drive control module, data processing module. This design programmer which reduce the complexity of the arithmetic enables program-design, debugging and maintenance simple.Finally, it describes the using process of software. According to the related experimental procedures, the uncertainty of standard dynamometer is evaluated by experimentation. the second step, load characteristic test and creep test are carried out. O n the basis of experimental result above- mentioned, so figure out general performance of the device.Finally, the experiment suggests that the device of automatic calibration of rocket engine thrust measurement at the testing location meets the design requirements in performance. Meanwhile it shows reliability of micro displacement of piezoelectric ceramic technology.