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直升机急拉杆机动飞行仿真建模与验证
引用本文:李攀,陈仁良.直升机急拉杆机动飞行仿真建模与验证[J].航空学报,2010,31(12):2315-2323.
作者姓名:李攀  陈仁良
作者单位:南京航空航天大学 直升机旋翼动力学重点实验室
摘    要: 针对直升机大机动飞行仿真,建立了一个非线性的飞行动力学模型,考虑了翼型非定常/动态失速、机动飞行引起的动态尾迹畸变、桨叶弹性变形效应和发动机动态特性。采用基于有限元分析的挥舞-摆振-扭转耦合的弹性桨叶模型,并利用一种新的数值方法将旋翼/机体耦合运动方程表示为显式形式,整个飞行动力学模型表示为状态空间格式。以UH-60A直升机在高速飞行条件下的急拉杆机动飞行为例进行仿真计算,并与飞行试验数据进行对比验证。分析表明,仿真结果与试验结果吻合,高速飞行条件下机体抬头过程中前行桨叶非定常气动载荷的计算误差是引起旋翼和机体运动仿真误差的主要原因。

关 键 词:直升机  飞行动力学  机动飞行  非定常空气动力学  飞行仿真  
收稿时间:2010-04-01;

Formulation and Validation of a Helicopter Model for Pull-up Maneuver Simulation
Li Pan,Chen Renliang.Formulation and Validation of a Helicopter Model for Pull-up Maneuver Simulation[J].Acta Aeronautica et Astronautica Sinica,2010,31(12):2315-2323.
Authors:Li Pan  Chen Renliang
Institution:Science and Technology on Rotorcraft Aerodynamics Laboratory, Nanjing University ofAeronautics and Astronautics
Abstract:A nonlinear flight dynamics model is established for helicopter large amplitude maneuvering flight simulation which takes into consideration the effects of unsteady aerodynamics and dynamic stall, dynamic wake distortion induced by maneuvers, elastic deformations of blades and engine dynamics. A coupled flap-lag-torsion elastic blade model is formulated based on the finite element method and the coupled rotor/fuselage equations of motion are presented in explicit form using a novel numerical method. Thus, the entire model is presented in finite-state form. As an example, a pull-up maneuver of helicopter UH-60A under high speed flight condition is simulated. The correlation of the results with the flight test data is provided. It is shown that the results agree well with flight test data and the primary contribution to the discrepancy of the simulation of the motions of the rotor and fuselage comes from inaccurate prediction of the unsteady airloads on the blades of the advancing side in the nose-up process.
Keywords:helicopter  flight dynamics  maneuver  unsteady aerodynamics  flight simulation
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