通用大气飞行器的参数化气动布局研究  

Aerodynamic configuration design for a parameterized lifting body common aero vehicle

作　　者：唐伟[1] 桂业伟[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》2009年第3期325-328,共4页Acta Aerodynamica Sinica

摘　　要：提出了一种新的升力体类通用大气飞行器布局方案。应用基于二次曲线的模线设计方法,通过二次曲线的控制点和形状参数实现参数化外形建模,构造适用于通用大气飞行器的升力体布局方案,提高飞行器气动布局方案的设计效率,为进一步的气动特性计算和布局方案设计优化奠定基础。采用修正的内伏牛顿流理论,对通用大气飞行器进行高超声速气动特性计算,并进行了质心设计,获得的高超声速稳定配平升阻比达到3.5以上。进行了控制舵面设计和控制效率的计算分析。A lifting body configuration aiming at a potential common aero vehicle has been proposed and studied. Using spline lofting design process based on conic shape parameter and cross section control pointers, a parameterized lifting body configuration is introduced to increase the design effectiveness. One of the predicaments for the aerodynamic design of hypersonic vehicles with high lift-to-drag ratio is the compromise among lift-to-drag ratio, volume utility ratio, stability, controllability and heat environment. The designed lifting body has a flat triangle form, a 5 degree bent angle with 4 deflectable control surfaces, the volume utilizing ratio is 0.35 for a 5 meter long vehicle, and the stable trimming hypersonic lift to drag ratio is as high as 3.5 taking friction drag and base drag into account, which makes the extremely long distance gliding maneuvering possible. Because of the flat body, the distance between the longitudinal center of pressure and the transverse center of pressure is elongated, and the yaw moment dynamic derivative coefficient decreased evidently, more attention is needed to be paid for the static and dynamic stabilities and controllability in lateral direction. The trimming flight angle of attacks can be achieved by both leeward control method and windward control method, whereas the windward control has a higher efficiency. For the rolling control, the differential deflection angles control mode is useful for both pair of the leeward control surfaces and the windward control surfaces. The present work indicates that this parameterized aerodynamic configuration design method is a high efficiency way, and the proposed lifting body has the potential possibility to be further investigated and applied as a common aero vehicle.

关 键 词：通用大气飞行器 升力体 二次曲线模线 稳定性 操纵性 飞行器方案设计 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]