导弹大迎角下非线性诱导滚转力矩数值研究

doi:10.7527/S1000-6893.2013.0212

Abstract

Abstract:

The nonlinear effect of a tactical missile's rolling moment at high angles of attack is numerically studied in the present paper. The capability of the computational fluid dynamics (CFD) scheme in capturing leading edge vortex and its breakdown is verified by a standard delta wing model. A missile in normal configuration in "++" layout, consisting of wings, body, tail rudders and cable fairing, is numerically investigated by solving Reynolds averaged Navier-Stokes equations. The results show that the nonlinear rising of the rolling moment appears after the angle of attack becomes greater than 20°, leading to the inadequacy of the rudder's roll control ability. The mechanism of this phenomenon is obtained through the decomposition of the contributions of each component to the rolling moment as well as an analysis on the flow structure. With the increase in the angles of attack, the leading edge vortex of the tail rudder at the windward side breaks first, which weakens its function of restraining the rolling movement.

Key words: missile, high angle of attack, rolling moment, computational fluid dynamics, vortex breakdown

CLC Number:

V211.3

XU Kezhe, ZHANG Yufei, CHEN Haixin, LI Bin, LIU Xianming, FU Song. Numerical Study of Induced Nonlinear Rolling Moment of Finned Missile at High Angles of Attack[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 97-104.

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Numerical Study of Induced Nonlinear Rolling Moment of Finned Missile at High Angles of Attack

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