宽升阻比高速滑翔变体飞行器高效建模方法  

Efficient Modeling Method for High⁃Speed Gliding Variant Aircraft with Wide Lift⁃to⁃Drag Ratio

作　　者：孙佳鑫 靳梓康 崔景芝 闫文辉 俞宗汉 SUN Jiaxin;JIN Zikang;CUI Jingzhi;YAN Wenhui;YU Zonghan(College of Machinery and Engineering,North China University of Technology,Beijing 100144,China;School of Mechanical Engineering,Guizhou University,Guiyang 550025,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北方工业大学机械与材料工程学院,北京100144 [2]贵州大学机械工程学院,贵阳550025 [3]北京宇航系统工程研究所,北京100076

出　　处：《南京航空航天大学学报(自然科学版)》2025年第1期147-159,共13页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(12002162);北方工业大学毓秀创新项目(2024NCUTYXCX106)。

摘　　要：为实现高速变体飞行器的宽升阻比飞行性能,提出并发展了一种宽升阻比高速滑翔变体飞行器新型气动布局及其高效建模方法。该方法基于UG二次开发平台、采用二维B样条构建了高速滑翔变体飞行器的参数化体系,仅需27个参数完成整机气动构型设计。针对宽速域(Ma=2.5~8.5)、宽空域(H=6~25 km)、宽飞行迎角范围(AOA=0~10°)进行数值模拟。结果显示:新型变体飞行器能兼顾高速巡航(翼展开状态Ma=4.0~8.5升阻比均高于4.7)、低阻滑翔(翼收起状态5°迎角内阻力系数低于0.02,相比翼展开时降低20%~30%)及升阻比大幅调节的机动能力(升阻比能在0.3~4.7大幅变动),其性能可调节裕度大;乘波效应随机体上下表面间的溢流程度对应变化,即溢流越高、乘波效应越弱。因此,可通过调节变后掠翼开度来调整乘波效应在机体流向的强弱,从而达到适应各类飞行任务需求的目的。In order to achieve the flight performance of high-speed variant vehicles with wide lift-to-drag ratio,a new aerodynamic layout of high-speed gliding variant aircraft with wide lift-to-drag ratio is proposed and its efficient modeling method is developed.The method is based on the UG secondary development platform and adopts two-dimensional B-splines to construct the parametric system of the high-speed glider-variant aircraft,and only 27 parameters are needed to complete the aerodynamic configuration design of the whole aircraft.Numerical simulations are carried out under conditions of a wide speed range(Ma=2.5—8.5),a wide airspace(H=6—25 km),and a wide flight angle of attack(AOA=0—10°).The results show that the new variant vehicle can exhibit good performances in multi-situations,including the high-speed cruising with the lift-to-drag ratios higher than 4.7 when the wings are spread and Ma=4.0─8.5,the low-drag gliding with the drag coefficients lower than 0.02 when the wings are retracted and the angle of attack is within 5°(reduced by 20%─30%from those with spread wings),and different swept-back wing openings with a large adjustable range of lift-to-drag ratio from 0.3─4.7.The results also indicate that the wave-riding effect varies depending on the degree of the spillage between the upper and the lower surfaces of the fuselage,i.e.,the higher the spillage,the weaker the wave-riding effect.Thus,the strength of the wave-riding effect in the airframe flow direction can be decided by adjusting the opening of the swept-back wing,and the variant vehicle can fulfill various flight missions.

关 键 词：变体飞行器 气动布局 类乘波体 参数化建模 乘波效应 

分 类 号：V221[航空宇航科学与技术—飞行器设计]