摘要
为实现场域受限下空投物资精准、低速无损着陆,开展串列翼货运无人机末端低速着陆段大攻角气动与操稳特性研究。针对串列翼无人机大攻角气动非线性与前后机翼气动强耦合问题,采用分离涡模拟方法分析大攻角强耦合非线性气动特性,计算得到各部件升阻系数、俯仰力矩及焦点位置随攻角变化规律,进一步研究不同机身截面对飞行器纵向稳定性的影响,根据机翼表面压力分布规律及周围流场结构分析串列翼前后翼耦合机理,提出了串列翼大攻角全动后翼操纵方案。研究结果表明:所设计的串列翼货运无人机在大攻角下方形机身截面相比圆形截面静稳定度变化更加平稳;其在0°~50°较大攻角范围内存在前后翼耦合现象,前翼脱体涡和后翼翼端脱体涡共同作用影响后翼的压力分布,后翼升力损失最高达32%;全动后翼使可控攻角提高至50°,可为大攻角深失速着陆提供足够的控制力矩。
To achieve accurate cargo airdrop and low-speed undamaged landing in limited area,the high angle of attack aerodynamic and operational characteristics of tandem wing cargo UAV are researched.Considering the aerodynamic nonlinearity at high angle of attack and the strong coupling of front and rear wings of tandem wing UAV,the Detached Eddy Simulation(DES)method is used to analyze the nonlinear aerodynamic characteristics at high angle of attack.The lift coefficient,drag coefficient and pitch moment of each component and aerodynamic center are calculated with the variation of the angle of attack.The influence of different fuselage cross sections on the longitudinal stability of the UAV is further studied.The coupling mechanism of tandem wing is analyzed according to the distribution characteristics of wing surface pressure and the structure of surrounding flow field.A manipulation scheme for the fullmotion rear wing at high angle of attack in the tandem wing UAV is proposed.The results show that the static stability of the square fuselage cross section is more stable than the round cross section at high attack angle.In the wide range of attack angle from 0°to 50°,there is aerodynamic coupling between the front and rear wings.The pressure distribution of the rear wing is affected by the aerodynamic coupling between the front and rear wings,and the lift loss of the rear wing is up to 32%.The full-motion rear wing increases the controllable angle of attack to 50°,which can provide sufficient control torque for deep stall landing at high angle of attack.
作者
杨芃芊
陈禹彤
刘俊辉
杨杰豪
单家元
孙士珺
YANG Pengqian;CHEN Yutong;LIU Junhui;YANG Jiehao;SHAN Jiayuan;SUN Shijun(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Key Laboratory of Dynamics and Control of Flight Vehicle of Ministry of Education,Beijing Institute of Technology,Beijing 100081,China;National Key Laboratory of Land and Air Based Information Perception and Control,Beijing 100081,China)
出处
《航空学报》
北大核心
2025年第9期186-201,共16页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(62473043,62103049)
山东省重点研发计划(重大科技创新工程)项目(2020CXGC011502)。
关键词
串列翼布局
大攻角
气动特性
准平衡滑翔
全动后翼
无人机
tandem wing layout
high angle of attack
aerodynamics
quasi-balanced glide
full-motion rear wing
UAV
