摘要
临近空间飞行器的升阻比与最大飞行距离紧密相关,是飞行器设计的核心指标。飞行器气动外形设计是获取高升阻比的主要手段。通过分析影响升阻比的关键要素,明确高升阻比设计需考虑的主要工程约束,提炼了飞行器气动外形高升阻比设计应遵循的一般性设计原则,可对临近空间飞行器气动布局设计提供指导。根据高空飞行条件下飞行器所受阻力特性分析,提出以降低飞行器摩擦阻力为未来应重点关注的设计方向。
The lift-drag ratio of a near-space vehicle is closely related to maximum flight distance which is the core index of the aircraft design.The design of aircraft aerodynamic configuration is a primary approach to gain a high lift-drag ratio.The universal design principles which should be followed is extracted in the design of high lift-drag ratio by analyzing the key factors influencing the lift-drag ratio and clarifying the main engineering constraints need to be considered.These principles could provide guidance for the aerodynamic configuration design of near space vehicle.According to the drag analysis of flight vehicles in high altitude circumstance,the design direction of reducing skin friction ought to be concentrated in future is proposed.
作者
朱广生
杨攀
段毅
李思怡
苗萌
Zhu Guang-sheng;Yang Pan;Duan Yi;Li Si-yi;Miao Meng(China Academy of Launch Vehicle Technology,Beijing,100076;Science and Technology on Space Physics Laboratory,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2022年第4期7-10,共4页
Missiles and Space Vehicles
基金
国家自然科学基金项目(U21B6003)。
关键词
临近空间飞行器
高升阻比
气动外形
设计原则
工程约束
near space vehicle
high lift-drag ratio
aerodynamic configuration
design principles
engineering constraints
