| 非对称变弹翼高速导弹气动特性计算与分析 |
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| 引用本文： | 李通,闫鹏,蒋瑞民,周军.非对称变弹翼高速导弹气动特性计算与分析[J].四川兵工学报,2017(6):51-56. |
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| 作者姓名： | 李通 闫鹏 蒋瑞民 周军 |
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| 作者单位： | 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 |
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| 基金项目： | 航天支撑技术基金项目(2015-HT-XGD) |
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| 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.
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| 关 键 词： | 非对称变弹翼 Missile Datcom 气动特性 滚转运动 |
Calculation and Analysis of High-speed Missile' s Aerodynamic Characteristic with Asymmetric Morphing Wings |
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| Authors: | LI Tong YAN Peng JIANG Rui-min ZHOU Jun |
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| Abstract: | This paper investigates rapid calculation and analysis of aerodynamic characteristics of high-speed 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. |
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| Keywords: | asymmetrical morphing wings Missile Datcom aerodynamic characteristic rolling motion |
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