火星旋翼气动建模与分析  

Aerodynamic modeling and analysis of Mars rotor

作　　者：宣金婷 丁志伟 李建波[1] XUAN Jinting;DING Zhiwei;LI Jianbo(National Key Laboratory of Helicopter Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机动力学全国重点实验室,江苏南京210016

出　　处：《飞行力学》2024年第3期82-88,共7页Flight Dynamics

摘　　要：针对火星大气环境下旋翼的气动建模问题开展了研究。首先,从火星大气环境研究入手,采用黏性涡粒子方法建立了火星大气环境下置信度较高的六旋翼无人机旋翼气动模型。然后,对火星不同大气密度、不同飞行状态下的旋翼气动性能与流场特征进行了分析。研究结果表明:在悬停和前飞状态下,火星多旋翼无人机旋翼的消耗功率均随火星大气密度的降低而增加,且在低密度区域增幅更加明显;在火星较低的大气密度下,为了满足拉力需求,旋翼桨尖涡增强,使得诱导速度增加,从而导致了旋翼消耗功率的增加。The problem of rotor aerodynamic modeling in Mars atmospheric environment was studied. Firstly, starting from the study of Mars atmospheric environment, the viscous vortex particle method was used to establish the aerodynamic model of the Mars hexacopter rotor with high confidence in the Mars atmospheric environment. Then, the aerodynamic performance and flow field characteristics of the Mars rotor under different atmospheric densities and different flight conditions were analyzed. The research results show that the power consumption of the Mars hexacopter rotor increases with the decrease of the Martian atmospheric density in both hover and forward flight, and the increase is more significant in the lower density area. Under the lower atmospheric density of Mars, in order to meet the demand of lift, the rotor tip vortex is enhanced, which makes the induced velocity increase, resulting in the increase of rotor power consumption.

关 键 词：火星六旋翼无人机 气动建模 黏性涡粒子方法 流场特征 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计] P185.3[天文地球—天文学]