适合于柔性结构扑翼飞行器的空间非定常涡格法  

Three-Dimensional Unsteady Vortex Lattice Method for Flexible Structure Flapping-Wing Aerial Vehicle

作　　者：余春锦[1] 昂海松[1] 陈青[2] 张敏[2] 张莉[2] 

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京210016 [2]南昌航空大学航空与机械学院,南昌330063

出　　处：《南京航空航天大学学报》2008年第4期451-455,共5页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：推导了新的基于空间非定常涡格法的扑翼飞行器升力和推力的计算公式,然后分析了瞬时形状速度对它们的影响。与实验结果的对照表明,基于向量分析、考虑了飞行中的诱导阻力因素的新公式可以有效地估算升力和推力。由于结构的柔性使扑翼在扑动过程中存在变形,本文考虑了空间涡格法中扑翼的/ηt对气动力的影响,提出了/ηt的表达式,使之更接近真实扑动情况,并计算了其对扑翼飞行器升力和推力的影响。通过计算发现,升力系数和推力系数的正峰值和负峰值随/ηt增大而增大,平均升力和平均推力也随/ηt增大而增大,表明可以通过改变结构参数达到改善气动性能的目的,对扑翼飞行器的研制有一定的指导作用。Formulations of the lift and the thrust are derived based on the three-dimensional unsteady vortex lattice method, and the effect on instantaneous shape velocity is analyzed. Based on the vector analysis and the considered factor of the induced drag the new formulations can adequately estimate the lift and the thrust of flapping-wing compared with the experimental data. Because the deformations are existed in the flexible structural flapping-wing during flapping process, in the vortex lattice method the instantaneous shape velocity aη/at is considered for aerodynamics effect of flapping-wing aerial vehicle. In order to approach the real flapping situation, an expression of aη/at is proposed and its effect on the lift and the thrust of the flapping-wing is calculated. It is found by the calculation that, as aη/at increases, the positive peak value and negative peak value of Ct and C, increase, and the average lift and the thrust increase. The study has a guide acting for the design of flapping-wing aerial vehicle.

关 键 词：扑翼 非定常涡格法 柔性结构 扑翼飞行器升力和推力 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程] V211.3