小型巡飞弹螺旋桨气动优化设计  

Aerodynamic Optimization Design of Small Loitering Munition Propeller

作　　者：吴超[1] 李海城 许建华[2,3] 王欢 尚云斌[1] 金阳 WU Chao;LI Haicheng;XU Jianhua;WANG Huan;SHANG Yunbin;JIN Yang(Xi’an Modern Control Technology Research Institute,Xi’an 710065,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China)

机构地区：[1]西安现代控制技术研究所,西安710065 [2]西北工业大学航空学院,西安710072 [3]飞行器基础布局全国重点实验室,西安710072

出　　处：《南京航空航天大学学报》2024年第4期698-704,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：小型巡飞弹螺旋桨桨叶尺寸较小,桨毂占比较大,螺旋桨性能易受桨毂影响。小型巡飞弹实际飞行螺旋桨转速偏高,航时不够,且螺旋桨风洞试验测试结果、设计计算结果以及实际飞行数据差异较大。针对计算结果不吻合的问题,开展了试验构型的数值模拟,结果表明桨毂产生较大的负拉力和扭矩,是造成螺旋桨效率下降、转速上升的主要原因。根据计算结果,本文给出了巡航工况下桨毂拉力及扭矩的修正公式及螺旋桨优化设计思路。针对试验数据不吻合的问题,设计了巡飞弹推进系统风洞试验,成功解决了来流干扰,获得了准确的测试结果。为了提升螺旋桨效率,根据螺旋桨涡流理论推导了螺旋桨计算模型,以巡航工况效率为优化目标,爬升工况推力及反扭矩为约束条件,利用遗传算法工具箱开展了螺旋桨气动外形优化设计,并通过推进系统风洞试验进行了验证。试验结果表明优化设计有效,巡飞工况下螺旋桨效率提升了17.2%。The propeller performance of small loitering munition is easily affected by the smaller blade size and lager hub ratio.A loitering munition encountered the problems of propeller speed is too high,and the endurance is not enough,the propeller wind tunnel test,the calculation results and flight performance are different.Aiming at the problem of inconsistent calculation results,the numerical simulation of the experimental subject was carried out.The result shows that the propeller hub produces a large negative thrust and torque,which is the most important factor leading to a significant decrease in propeller efficiency and increase in propeller speed.According to the calculation results,the formula of the hub thrust and torque correction and the propeller optimization design are given.In view of the large difference between the wind tunnel test efficiency value and flight performance,the propulsion system wind tunnel test was carried out,the problem of incoming flow interference is solved and accurate experimental results are obtained.In order to improve propeller efficiency,a propeller calculation model is derived based on propeller vortex theory,the optimization design of propeller aerodynamic profile is carried out by using genetic algorithm toolbox,with the efficiency of propeller at cruise as objective,the thrust and maximum counter torque in climb as constraints.The design results are verified by the wind tunnel test of the propulsion system.Experimental results show that the optimized design is effective,and the propeller efficiency is increased by 17.2%at cruise.

关 键 词：巡飞弹 螺旋桨 优化设计 风洞试验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]