ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Roll instability and control during pitching maneuver for a missile with strake wings
Received date: 2016-02-16
Revised date: 2016-03-28
Online published: 2016-04-12
Supported by
National Natural Science Foundation of China (91216203, 11372336, 11532016)
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.
WANG Xiaobing , ZHAO Zhongliang , LI Hao , DA Xingya , TAO Yang . Roll instability and control during pitching maneuver for a missile with strake wings[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(8) : 2517 -2524 . DOI: 10.7527/S1000-6893.2016.0101
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