上层大气层飞行器气动布局优化设计  

Aerodynamic layout optimization design of upper atmosphere aircraft

作　　者：李俊红[1,2] 黄飞 靳旭红[1,2] 苗文博 程晓丽 LI Junhong;HUANG Fei;JIN Xuhong;MIAO Wenbo;CHENG Xiaoli(China Academyof AerospaceAerodynamics,Beijing 100074,China;Laboratory of Aero-thermal Protection Technology for Aerospace Vehicles,China Aerospace Science and TechnologyCorporation,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]中国航天科技集团有限公司航天飞行器气动热防护实验室,北京100074

出　　处：《航空学报》2024年第22期67-76,共10页Acta Aeronautica et Astronautica Sinica

基　　金：省部级项目。

摘　　要：针对上层大气层飞行器,基于试验粒子MonteCarlo方法,开展了正方形、正六边形和圆形等不同横截面形状的飞行器本体在定容条件下的气动布局优化研究,获得了飞行器本体阻力最小时的长细比,并以阻力最优时的飞行器本体为基础,确定了包含太阳电池翼构型的飞行器自配平气动布局,最后对飞行器稳定性进行了分析。研究结果表明:在250km上层大气层,飞行器本体摩阻占比较大,该占比随着飞行器本体长细比的增大而增加;在长细比为12.98时,飞行器本体阻力最小;定容条件下,飞行器本体阻力系数与长细比呈线性变化,摩阻系数与压阻系数则保持不变;3种横截面形状中,正方形截面的飞行器本体阻力最大,六边形次之,圆形最小。对于太阳电池翼结构,第一折偏转(布局1)时和三折全部偏转(布局2)时,飞行器处于自配平状态的偏转角度分别为33.8°和18°考虑飞行器本体散热时,布局1要更优越一些。对于安装偏差,质心向飞行器底部偏移时,飞行器处于静不稳定状态,质心向飞行器头部偏移时,飞行器处于静稳定状态。Optimization of the aerodynamic layout of square,hexagonal and circular upper atmosphere aircraft with different cross sections under constant volume was studied by using the test particle Monte Carlo(TPMC)method.The aspect ratio of the aircraft body with the minimum drag force is obtained.Based on this body,the auto-trim aerodynamic layout of the aircraft including the solar cell wing configuration is determined.Finally,the stability of the aircraft is analyzed.The results show that at the upper atmosphere of 25o km,the fraction of friction force in drag of the aircraft body is relatively large,increasing with the increase of the aspect ratio of the aircraft body.When the aspect ratio is 12.98,the total drag of the aircraft body is the smallest.The total drag force coefficient of the aircraft body varies linearly with its aspect ratio under constant volume,while the friction force coefficient and the pressure force coefficient remain constant.In three kinds of cross section shapes mentioned above,the total drag force of the square section is the greatest,followed by that of the hexagon and the circle.For the solar cell wing structure,the wing deflection angles of the aircraft inauto-strim state are 33.8°and 18°for the first solar section deflection configuration(Configuration 1)and the total three solar section deflection configuration(Configuration 2),respectively.For the aircraft wing in auto-strim state,Configuration 1 is superior when considering the heat dissipation of the aircraft body.Regarding installation deviation,when the center of the aircraft is shifted to the bottom of the aircraft,it is in a statically unstable state,and when the center of mass is shifted to the head of the aircraft,it is in a statically stable state.

关 键 词：上层大气层 飞行器 自配平 气动 布局 静稳定 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]