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弹箭与制导学报 >

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

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

基于数值虚拟飞行的自旋尾翼鸭式布局弹箭动态气动特性研究

  • 庞川博 1 ,
  • 蒋胜矩 1 ,
  • 赵超 2
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  • 1 西安现代控制技术研究所,西安 710065
  • 2 中国航空工业集团公司西安飞行自动控制研究所,西安 710065

庞川博(1989—),男,四川南充人,工程师,硕士,研究方向:弹箭空气动力学及气动布局设计。

收稿日期: 2020-04-26

  网络出版日期: 2025-02-25

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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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摘要

基于数值虚拟飞行技术,研究自旋尾翼鸭式布局弹箭尾翼姿态变化对弹体气动特性及操控性的影响。通过耦合求解非定常流动控制方程、刚体动力学方程以及舵偏控制率,对自旋尾翼鸭式布局弹箭的俯仰机动过程以及闭环滚转控制过程进行了模拟。结果表明:弹体作纵向机动,自旋尾翼处于“十”型姿态时鸭舵洗流的作用最显著,尾翼旋转运动对弹体俯仰操控能力有一定程度减弱,但对俯仰振荡收敛时间以及平衡姿态角影响较小;在滚转姿态控制过程中,采用自旋尾翼时的滚转控制力矩是采用固定尾翼的3倍以上,且全弹的俯仰气动特性基本不受影响。

关键词： 鸭式布局; 自旋尾翼; 虚拟飞行; 数值模拟

本文引用格式

庞川博 , 蒋胜矩 , 赵超 . 基于数值虚拟飞行的自旋尾翼鸭式布局弹箭动态气动特性研究[J]. 弹箭与制导学报, 2021 , 41(2) : 101 -110 . DOI: 10.15892/j.cnki.djzdxb.2021.02.022

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

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