Missile and carrier rocket modal test method

Abstract

The invention discloses a missile and carrier rocket modal test method comprising the method of vibration mode decoupling measurement sensor arrangement and multi-exciter excitation combination. Vibration mode decoupling measurement sensors are arranged in three quadrant lines of the external side of a missile or carrier rocket structure, wherein one quadrant line adheres two-way sensitive sensors and the other two quadrant lines adhere one-way sensitive sensors; the vibration mode data of the modal at excitation points are extracted; a data table of correspondence of the numbers of the excitation points and the vibration mode data is established; the absolute values of the vibration mode data of the data table are ordered in a decreasing way and bound with the number order of the excitation points; the numbers of the first and second excitation points and the symbols of the corresponding vibration mode data are extracted; and the situation that the optimization scheme aims at the same excitation position is merged so that the optimized excitation combination is obtained. The number of sensor measurement channels is reduced, the effectiveness of data acquisition is enhanced, the data volume of data acquisition is reduced and the difficulty of data analysis and processing is reduced.

Description

technical field [0001] The invention belongs to the field of dynamic characteristic measurement of missiles and launch vehicles, and specifically refers to a modal test method. Background technique [0002] The existing missile and launch vehicle modal test methods have been quite mature after years of development, and are at the leading level at home and abroad. The missile and launch vehicle modal test system consists of a data acquisition and processing system, an excitation system and a measurement system. The excitation system includes a power amplifier, an exciter and a force sensor. [0003] The data acquisition and processing system collects, processes and analyzes the signals of the acceleration sensor and the force sensor. The data acquisition system generates an excitation electric signal, and drives the vibration exciter through the power amplifier to excite the test piece. At the same time, the signal of the force sensor installed in front of the vibrator is fe...

AI Technical Summary

Problems solved by technology

For missiles and launch vehicles, the sensors are basically installed on the quadrants, generally installed on one of the quadrants or adjacent quadrants, but the amount of measurement data is large, the measurement information is complex, and the coupling mode decoupling measurement capability is insufficient;

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