大型翼伞的三维气动性能分析  

A Three-dimensional Analysis on Aerodynamic Performance of a Large Parafoil

作　　者：陆伟伟[1] 张红英[1] 连亮[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《航天返回与遥感》2015年第3期1-10,共10页Spacecraft Recovery & Remote Sensing

基　　金：国家自然科学基金(11002070);航空科学基金(2012ZC52035)

摘　　要：随着回收物质量的增加和回收物可控定点回收要求的提出,大型翼伞的设计研究迫在眉睫。文章采用有限体积法求解K-epsilon二方程湍流模型下的Navier-Stokes(N-S)方程,对某大型翼伞进行三维定常数值模拟,研究考虑伞衣鼓包下翼伞的气动性能,同时对翼伞单侧后缘下拉情况下(翼伞转弯过程)的气动性能进行初步分析。结果表明,翼伞的升力系数随迎角的增大而增加,达到失速迎角后缓慢降低。翼伞阻力系数在负迎角时随迎角增大而缓慢降低,而在正迎角时随迎角增大而增加。翼伞升阻比开始时随迎角增大而增加,在迎角等于8°时达到最大值后随迎角增大而逐渐降低。同时,单侧后缘下拉翼伞相比普通翼伞升力与阻力系数均有所增加,但其最大升阻比却有所减小。With the increase of the weight of recovery item and the recovery requirements controlled for landing at fixed-point being proposed, the design study of a large parafoil is imminent. The finite volume method is used to solve the Navier-Stokes（N-S）equation with K-epsilon two-equation turbulence model. A 3D steady numerical simulation for the large parafoil is conducted for the aerodynamic performance in view of the canopy deformation, while a preliminary analysis of the aerodynamic performance is made for parafoil unilateral flap deflection（parafoil turning process）. The results show that the parafoil lift coefficient increases with increasing angle of attack and slowly decrease after reaching the stalling angle. The drag coefficient slowly decreases with the increasing angle of attack when the angle of attack is negative, and increases with increasing angle of attack when positive angle of attack is arrived. And the lift-drag ratio increases with increasing angle of attack at the beginning and gradually decreased with increasing angle of attack after reaching the maximum value 8 degrees. Meanwhile, the lift and drag coefficients of the unilateral flap deflection parafoil increase compared to those ordinary parafoil, but its maximum lift-drag ratio somewhat decreases.

关 键 词：大型翼伞 数值模拟 气动性能 鼓包 回收着陆 

分 类 号：V244[航空宇航科学与技术—飞行器设计]