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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2016, Vol. 37 ›› Issue (8): 2517-2524.doi: 10.7527/S1000-6893.2016.0101

• Numerical Simulation Investigations of Coupled Aerodynamics/Vehicle Motions • Previous Articles     Next Articles

Roll instability and control during pitching maneuver for a missile with strake wings

WANG Xiaobing, ZHAO Zhongliang, LI Hao, DA Xingya, TAO Yang   

  1. High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-02-16 Revised:2016-03-28 Online:2016-08-15 Published:2016-04-12
  • Supported by:

    National Natural Science Foundation of China (91216203, 11372336, 11532016)

Abstract:

The aerodynamic characteristics in roll of the missile with strake wings are always complicated, which can easily cause the non-directive deviation and oscillation and may lead to losing control of flight and impairing target accuracy. Investigations using the virtual flight testing system in 2.4 m transonic wind tunnel are conducted to study the interplay of roll instability and the longitudinal closed-loop control, and numerical simulation is also performed using the integrative method by aerodynamic/motion/control coupling. The results show that both wind tunnel test and numerical simulation predict the non-directive rolling motion and the pitch/roll coupled motion and prove that the decoupled control method can effectively inhibit the rolling motion and maintain a steady flight.

Key words: missile with strake wings, roll instability, virtual flight, wind tunnel test, numerical simulation, closed-loop control

CLC Number: