Studies on aeroservoelasticity semi-physical simulation test for missiles

• Published in: Science China. Technological sciences 2012-09, Vol.55 (9), p.2482-2488
• Main Authors: Wu, ZhiGang, Chu, LongFei, Yuan, RuiZhi, Yang, Chao, Tang, ChangHong
• Format: Article
• Language: English
• Subjects: Aeroservoelasticity; Computer simulation; Control systems; Engineering; Flight control systems; Mathematical models; Missiles; Unsteady aerodynamics; Vibration; 仿真测试系统; 半实物仿真试验; 导弹控制系统; 开环传递函数; 气动伺服弹性; 非定常空气动力学; 非线性因素; 飞行控制系统
• ISSN: 1674-7321; 1869-1900
• DOI: 10.1007/s11431-012-4940-4

Missiles may be damaged when aeroservoelastic problem occurs, which is caused by the interaction of structure flexibility and flight control system. Because of the limit of wind tunnel test condition, numerical methods are mostly used in previous aeroservoelastic studies. However, series of assumptions and simplification on structures, aerodynamics and flight control systems are unavoidably introduced, and various nonlinear factors are also ignored, therefore, they result in considerable errors. A nov- el method called aeroservoelasticity semi-physical simulation test is proposed in this paper, which takes the flexible missile with control system as the test object. Vibration signals at several locations of the missile are measured by accelerometers, then corresponding unsteady aerodynamics is computed based on the fact that airflow at high Mach is nearly quasi-steady, and finally unsteady aerodynamics is exerted simultaneously by shakers at certain locations of the missile. The aeroservoelasticity semi-physical simulation test system can be constructed after the control system is closed. Open loop transfer function test and closed loop stability test are carried out in sequence. The test principle and method proposed in this paper are verified by the concordance between the results of numerical simulation and experiment.