削面/配平翼飞行器的气动计算及分析  

Aerodynamic Prediction and Analysis for a Reentry Vehicle with Slice-Ailerons

作　　者：唐伟[1] 李为吉[1] 高晓成[2] 张勇[2] 马强[2] 

机构地区：[1]西北工业大学,陕西西安710072 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《西北工业大学学报》2004年第5期541-544,共4页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金 (10 0 72 0 74 )资助

摘　　要：带削面 /配平翼的钝双锥外形是高超声速飞行器实现机动飞行的有效途径。该外形具有配平升力大、升阻比大、空间大等特点 ,可以利用迎风翼面及背风翼面进行配平控制 ,而且侧向控制翼不仅可以控制侧向配平及稳定 ,还可以利用不同的扩张角改变飞行器的配平阻力和配平升阻比。研究了此类飞行器的迎风 /背风配平控制效率问题 ,以及飞行器的侧向稳定性问题 。The maneuvering requirements of hypersonic reentry vehicle with a biconic vehicle with slice-ailerons were presented, which is a promising concept because of its high trimming lift, high trimming lift-to-drag ratio and big inner volume. An engineering model developed from embedded Newtonian flow theory has been established to estimate the aerodynamic characteristics of the biconic vehicle with slice-ailerons. The vehicle can achieve its required trimming by windward control and/or leeward aileron deflection. Windward control has a higher control efficiency; decreasing the windward aileron deflection angle may increase the corresponding trimming angle of attack, which is of much benefit to structural design, joint hinge design and local thermal protection design. Side ailerons can be used to stabilize the vehicle in transverse direction, while bigger deflection angle of side aileron may cause neutral stability, and even instability. Regardless of the selection of windward control or leeward control, side ailerons may make scarcely any difference to the center of pressure, consequently the vehicle may obtain its trimming lift-to-drag ratio and trimming lift to realize different maneuvering abilities through different aileron expansion angles, while the corresponding trimming angle of attack will not be influenced. In order to improve the rolling control ability, a proposal of controlling rolling movement is given.

关 键 词：削面/配平翼 配平效率 稳定性 再入飞行器 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]