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Journal of Projectiles, Rockets, Missiles and Guidance >

2021 , Vol. 41 >Issue 2: 101 - 110

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2021.02.022

Research on Dynamic Characteristics of Canard Missiles with a Free-spinning Tail Using Numerical Virtual Flight Technology

  • PANG Chuanbo 1 ,
  • JIANG Shengju 1 ,
  • ZHAO Chao 2
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  • 1 Xi’an Modern Control Technology Research Institute,Xi’an 710065,China
  • 2 Xi’an Flight Automatic Control Research Institute,Aviation Industry Corporation of China,Xi’an 710065,China

Received date: 2020-04-26

  Online published: 2025-02-25

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Abstract

The influence of attitude change of free-spinning tail on aerodynamic characteristics and controllability is studied based on numerical virtual flight technology. By coupling solving N-S equations, rigid body dynamic equations and rudder control law, pitching maneuver and close-loop rolling control process of a free-spinning tail canard missile is simulated. The results show that in longitudinal maneuver process, when the tail is in the “cross” attitude, the downwash effect is the most significant, and the pitching control ability of the missile is partly weakened by the rotating tail, however, it has little effect on pitching oscillation convergence time and balance attitude angle. During close-loop roll control, the roll moment when using free-spinning tail is three times more than that of the fixed tail, and the pitching aerodynamic characteristics of the missile are not influenced.

Key words： canard configuration; free-spinning tail; virtual flight; numerical simulation

Cite this article

PANG Chuanbo , JIANG Shengju , ZHAO Chao . Research on Dynamic Characteristics of Canard Missiles with a Free-spinning Tail Using Numerical Virtual Flight Technology[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2021 , 41(2) : 101 -110 . DOI: 10.15892/j.cnki.djzdxb.2021.02.022

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