摘要
提出一种小型无人复合式升力飞艇的设计方案,艇身为采用设计对称翼型的升力体,横截面呈椭圆形,艇翼面可倾转至垂直状态或水平状态,能够满足起飞或平飞需要。通过数值分析确定整体气动布局、升力体艇囊的设计及机翼与浮升体气动设计优化。同时提出艇囊分割分块设计制作方法,解决吊舱、机翼与艇身的连接。通过FLUENT软件计算复合飞艇的气动特性,并与相同体积的传统飞艇的气动特性进行了比较。仿真结果表明:设计的复合飞艇飞行阻力小,升力性能优越,最大升阻比迎角为8°,失速迎角可达16°,制作的缩比模型验证了设计方案的可行性。
A design plan for a small unmanned hybrid lift airship is proposed in this paper. It is a lift body with a symmetrical airfoil,the cross-section is oval,and its wing can tilt to verticality or horizontality to meet requirements of takeoff or level flight. The overall aerodynamic configuration,lift body gasbag design and wings-buoyant body aerodynamic design optimization are determined through numerical analysis. A design and manufacture method of dividing block gasbag to solve the connection problem of pod,wings and body. The FLUENT software is used to analyze the aerodynamic characteristics of the hybrid airship,which are compared with traditional airship of the same volume. Analysis showed that the hybrid airship has low flight drag,excellent lift performance,8° angle of attack at maximum lift-drag ratio,and up to 16 ° stall angle. Furthermore,a scale model has verified the feasibility of the design.
出处
《飞行力学》
CSCD
北大核心
2016年第3期21-25,共5页
Flight Dynamics
基金
航空科学基金资助(2014ZA55001)
河南省高等学校重点科研项目(15A590002)
国家级大学生创新创业训练计划项目(201410485002)
关键词
复合式升力飞艇
布局设计
气动性能
数值仿真
缩比模型
hybrid lift airship
layout design
aerodynamic performance
numerical simulation
scale model
