共轴刚性直升机前飞状态气动配平与性能分析  

Trimming Method and Aerodynamic Performance Analysis of Coaxial Rigid Helicopters in Forward Flight

作　　者：张永华[1] 赵旭[1] 周平[1] 徐跃宇 林永峰[2] Zhang Yonghua;Zhao Xu;Zhou Ping;Xu Yueyu;Lin Yongfeng(Northwestern Polytechnical University,Xi’an 710072,China;China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]西北工业大学,陕西西安710072 [2]中国直升机设计研究所,江西景德镇333001

出　　处：《航空科学技术》2020年第2期37-45,共9页Aeronautical Science & Technology

基　　金：航空科学基金(20175753030);直升机旋翼动力学国家级重点实验室基金(614222003060617)。

摘　　要：本文综合考虑了旋翼、机身、平尾气动特性,建立了共轴刚性直升机XH-59A前飞气动力模型。旋翼性能计算建立在叶素动量理论和Pitt/Peters入流模型的基础上,考虑了上下旋翼的相互干扰和周期变距,获得旋翼和直升机的力和力矩随旋翼总距的变化,验证了风洞试验结果,预测的旋翼的推力系数为试验值的88%~101%。针对直升机前飞时保持力和力矩平衡,构建了基于梯度优化方法的快速通用配平策略,控制参数包括上下旋翼总距、横向和纵向周期变距,以及桨盘倾角。预测了控制参数随前进比的变化,与飞行试验数据进行了对比,在前进比0~0.4范围内,控制参数的变化趋势相同,桨盘倾角、总距、纵向周期变距最大相差6°,差动总距最大相差1°,横向差动距最大相差2.4°,验证了气动配平和性能分析的可靠性。The aerodynamic characteristics of rotor,fuselage and horizontal tail were incorporated into the aerodynamic model of coaxial rigid helicopters in forward flight.Aerodynamic model of the rotor is based on blade element momentum theory and the Pitt/Peters inflow model in consideration of flow interactions between upper and lower rotors,collective and cyclic pitch variations.Forces and moments on the helicopter were predicted and valiated by wind tunnel experimental data.The rotor thrust coefficient calculated is 88%~101%of the result tested.To balance forces and moments on XH-59A helicopter in forward flight,a rapid trimming strategy based on gradient optimization method is constructed for general application.The control parameters include collective pitch,lateral and longitudinal cyclic pitch of both rotors,as well as the inclination of the rotor disk.Those control parameters variation with advancing ratio are predicted and compared with flight test data.The variation tendency of those parameters is consistent with the test data in the advance ratio range between 0~0.4.The maximum discrepancy between the data predicted and tested is 6°for shaft angle,collective pitch and longitudinal cyclic pitch,1°for differential collective pitch and 2.4°for differential lateral cyclic pitch,which prove the reliability of the trimming method and performance analysis.

关 键 词：共轴刚性旋翼 前飞 叶素动量理论 气动性能 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]