折叠式主弹翼气动特性研究  

Investigation into Aerodynamic Characteristics of Folding Wing Guided Bomb

作　　者：吴小胜[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《北京理工大学学报》2010年第9期1024-1027,共4页Transactions of Beijing Institute of Technology

基　　金：国家部委预研基金项目(9140A1301810BQ01)

摘　　要：针对制导航弹的气动设计要求,设计了一种前后折叠式弹翼.并使用数值计算和工程计算方法研究前后折叠式弹翼、钻石背弹翼以及后折前张式弹翼的气动特性.计算结果表明:前后折叠式弹翼与钻石背弹翼升力系数在攻角较小时接近,在攻角较大时,前后折叠式翼的升力系数大于钻石背弹翼;前后折叠式弹翼的升阻比最大;后折前张式弹翼的外形滚转阻尼力矩系数最小;钻石背弹翼的外形滚转阻尼力矩系数最大.To increase the ratio of lift to drag of guided bomb, a folding multi-surface wing was designed. Computational fluid dynamics （CFD） numerical simulation method and semi-empiric method was used to compare the aerodynamic characteristics of folding multi-surface wing to that of diamond back wing with the same airfoil, chord and surface area. The results indicate the following facts： the lift coefficient of folding multi-surface wing is close to the diamond back wing at small angle of attack, but, at large angle of attack, the lift coefficient of folding multi-surface wing is larger than that of diamond back wing. The folding multi-surface wing has largest ratio of lift to drag. In addition, the rolling damping of folding wing is smaller than that of diamond back wing.

关 键 词：制导航弹 气动特性 折叠式弹翼 数值计算 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]