Research On The Test Technology Of Parameters Of Rotation Speed/Velocity Of High-speed Rotating Missile

Rotating can keep high-speed rotating missile to stabilize and also can maintain the accuracy of its fired. The dynamic parameters when it is in the process are extremely important for analysis its performance. The dynamic parameters can be used to assisted analysis the airframe performance and the reason of mechanism failure,and it provide an important theoretical basis for optimization design. The fuze of low-cost and high-speed rotating missile is often encountered early burst, blind fire and other issues in the experiments. if we want to get the reasons which cause these problems, we should test the dynamic parameters of high-speed rotating missile when it in the processing. The background of this paper is that we need to test the rotation speed and velocity of a model missile and Shrapnel. After comprehensive analyzing the methods of testing angular velocity and speed of missile in domestic and foreign research, the characteristics of measured signal and the requirements of the test, we put forward the overall design program of test system and designed missile test systems of low range and high-range magnetic-type which based on the coil geomagnetic sensor and micro silicon accelerometer sensor. They were used to test the rotation speed of full-speed missile and the speed of active segment ,and test the rotation speed of the entire trajectory and the speed of shrapnel firing .First of all, the basic theory of the geomagnetic field is introduced. In this test system the coil geomagnetic sensor was selected to measure speed of high-speed rotating missile, by analysis and comparison of several common magnetic sensors used in different technologies and their application and combining the characteristics of this test object.Secondly, as the test environment of missile and Shrapnel is different, choose a capacitive silicon micro-accelerometer sensor as sensitive components of a low-range magnetic-type missile and piezoresistive silicon micro-accelerometer sensor as sensitive components of a high-range magnetic-type missile test system. At the same time in the whole system design process, taking the system's micro-size, micro-power requirements into account. On the design of hardware circuit, the power management module, signal conditioning circuits, A / D conversion components, data storage part and the digital logic control of part are in-depth analysis; On the design of software, made a brief introduction of each functional module of software which be used for analysis data in magnetic-type missile test system.Thirdly, assessment the precision of the magnetic-type missile test system by the experiment which we use Machete hammer and turntable calibrate sensor. We verified the test system reliability and stability by analyzed the data of the experiment.At Last , we process the rotation speed and overload data which measured a model missile in the live test by the low-range magnetic-type missile test system. In order to improve the accuracy, of parameters data, we de-noise data by the wavelet. The rotation speed and velocity data which we get by analyzing the measured data are totally in line with the actual situation and gained satisfactory results.