复合推力构型直升机飞行性能及参数敏感性研究  

Research on Flight Performance and Sensitivity to Parameter for Rotor- wing Compound Helicopter

作　　者：林李李 李建波[1] 刘晓昕 王倩楠 LIN Li-li;LI Jian-bo;LIU Xiao-xin;WANG Qian-nan(National Laboratory of Science and Technology on Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室

出　　处：《航空计算技术》2019年第5期90-95,共6页Aeronautical Computing Technique

基　　金：江苏省高校优势学科建设工程项目资助(PAPD)

摘　　要：为建立旋翼/机翼复合推力构型直升机全机需用功率计算模型,提出了一种旋翼和机翼的升力分配和操纵策略,并以此找到了一种该构型直升机飞行性能的计算方法,并就航程、航时及飞行包线等飞行性能进行计算分析。为了对设计方案进行论证,在引入重量模型的基础上,通过调整旋翼直径、螺旋桨直径等7项设计参数,开展了针对航程、航时及最大平飞速度的参数敏感性分析,得到了不同总体参数对于性能指标的敏感性结果,依据结果进行总体参数的优化工作,得到了满足目标性能的总体参数。This paper firstly establishes the calculation model of the total power required for the rotor/wing compound thrust configuration helicopter,and proposes a lift distribution and steering strategy for the rotor and wing,and finds a calculation method for the flight performance of the configuration.And calculate and analysis of flight performance such as voyage,time and flight envelope.In order to demonstrate the design scheme,based on the introduction of the weight model,the parameter sensitivity analysis for the voyage,time and maximum leveling speed was carried out by adjusting the seven design parameters such as the diameter of rotor and propeller,and the different overall parameters are obtained for the performance indicators.Based on the sensitivity results of the optimization of the overall parameters,obtained the overall parameters to meet the target performance.

关 键 词：飞行器设计 复合式直升机 飞行性能 参数敏感性 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]