Design And Realization Of Launching Test System For Rockets

In the development and production process of rocket air burst fuze, fuze test system plays an important role in improving production efficiency and product quality. On the one hand, test system can simulate the external trajectory environment parameters of fuze and automatically detect the corresponding output, which reduce test time significantly. On the other hand, it can select the the high quality products according to the parameters measured, which ensures the product reliability and improves the product quality.In this dissertation, the implementation of test system of air burst fuze is introduced. Based on the test needs in circuit module functional test, after-assembly test and after-embedment test, specific functional and index requirements are epurated. According to the principle of fuze and modular design concept, a test system is designed. The test system consists of a power supply circuit, a signal conditioning circuit, a turbine alternator output simulation circuit, a speed signal generating circuit, a current detection circuit and a communication interface circuit. The test system software includes peripheral devices module, setting detection module, speed signal simulation module, AD sampling module, interface communication module and process control module.Aiming at solving the problem of projectile speed simulation during the test of dynamic flight equivalent simulation, a new method by controlling the distance between airflow vent and fuze is introduced. Based on the flow characteristics, the speed formula of axial flow outside the vent, namely the theoretical formula of projectile simulation speed, is given. Combined with the specific situation, the flow field numerical simulation under the condition of a given diameter circular orifice is carried out, and the speed data of axial flow are obtained, the comparison between the simulation results and theoretical formulas is also carried out. In order to reduce the calculation error of the formula, a modified formula is derived with the tool of MATLAB according to the aforementioned theory of axial flow speed and simulation data samples, providing a theoretical support to the dynamic flight equivalent simulation test.Test system prototype is produced based on the theory and methods introduced. The experimental results show the test system is reliable, all parameters meet the test requirements, and the system test time is reduced by 75% compared with the manual test time.