非对称变弹翼高速导弹气动特性计算与分析  

Calculation and Analysis of High-speed Missile's Aerodynamic Characteristic with Asymmetric Morphing Wings

作　　者：李通[1] 闫鹏[2] 蒋瑞民[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072 [2]中国航天科技集团公司,北京100048

出　　处：《兵器装备工程学报》2017年第6期51-56,共6页Journal of Ordnance Equipment Engineering

基　　金：航天支撑技术基金项目(2015-HT-XGD)

摘　　要：通过不对称旋转左右弹翼的后掠角实现弹翼的不对称变化,利用飞行器快速计算软件Missile Datcom计算不同条件下导弹的气动参数。基于气动数据分析了后掠角非对称变化对升力、阻力、俯仰力矩及滚转力矩等气动特性的影响。通过分析可知,弹翼的不对称变形可显著的改变滚转力矩系数,将不对称变形的弹翼作为辅助控制机构,控制导弹的滚转运动,提高滚转运动的准确性和快速性。This paper investigates rapid calculation and analysis of aerodynamic characteristics of highspeed missle that can morph wings asymmetrically. Asymmetrical variable sweep is realized by rotate wings and aerodynamic parameters under different flight conditions are computed using Missile Datcom. Based on results of calaulation,it is indispensable to analyze the effects of asymmetric variable sweep on aerodynamic characteristics,such as drag,lift,pitching moment,rolling moment and so on. According to analysis,the changes are particularly significant in rolling-moment coefficient due to asymmetrical deformation. Thus,auxiliary controller based on asymmetrical morphing wings is proposed to improve the veracity and rapidity of rolling motion.

关 键 词：非对称变弹翼 MISSILE Datcom 气动特性 滚转运动 

分 类 号：TJ761.6[兵器科学与技术—武器系统与运用工程]