可变弯尾飞行器布局气动特性分析  

Aerodynamic analysis of a Variable-bend-tail vehicle

作　　者：唐伟[1] 张勇[1] 马强[1] 张鲁民[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2002年第2期222-226,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目 (项目批准号 1 0 0 72 0 74)

摘　　要：本文研究了可变弯尾飞行器的气动布局设计问题 ,并计算分析了此类飞行器的气动特性 ,提出了气动设计的关键问题。可变弯尾飞行器具有结构简单、气动热环境良好、气动控制独特、机动范围可调等特点 ,是高超声速飞行器实现机动飞行的有效途径。弯尾部分产生的铰链力矩是此类飞行器的设计关键。通过研究分析飞行器的质心位置、弯尾部分的尾长和弯尾角的相互关系 ,获得了使铰链力矩在飞行器较大配平范围内保持可接受程度的可变弯尾飞行器气动布局。The problems of aerodynamic configuration design for a Variable bend tail vehicle are studied, its aerodynamic characteristics are predicted and discussed, and the key issues for a Variable bend vehicle design are presented and evaluated. Variable bend tail vehicle can be a very useful approach for supersonic and hypersonic maneuver, because of its structural simplicity, favorable thermodynamics performance, unique control mechanism and adjustable maneuverability. The aerodynamic joint hinge moment generated by its bend tail is one of the most challenging problem . The location of the center of gravity, the length of the tail, the bend angle and the relationship between each other are discussed and a Variable bend tail vehicle configuration has been presented which has an acceptable hinge moment for a wide range of trimming flight conditions.

关 键 词：可变弯尾飞行器 气动布局 气动特性 铰链力矩 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]