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作 者:WU ZhiGang CHU LongFei YUAN RuiZhi YANG Chao TANG ChangHong
机构地区:[1]School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China [2]The First Aircraft Institute,Aviation Industry Corporation of China,Xi'an 710089,China
出 处:《Science China(Technological Sciences)》2012年第9期2482-2488,共7页中国科学(技术科学英文版)
基 金:supported by the National Natural Science Foundation of China (Grant Nos. 90716006,10902006)
摘 要: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 novel 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.
关 键 词:aeroservoelasticity semi-physical simulation unsteady aerodynamic aerodynamic derivative method SHAKER MISSILE
分 类 号:V215.3[航空宇航科学与技术—航空宇航推进理论与工程] TJ765.2[兵器科学与技术—武器系统与运用工程]
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