Rotorcraft simulation modelling and validation for control law design
Rotorcraft simulation modelling and validation for control law design
复制标题
旋翼机仿真建模和控制律设计验证
DOI：
10.1017/s0001924000001780
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发表时间：
2007
期刊：
影响因子：
--
通讯作者：
A. Gubbels
中科院分区：
文献类型：
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作者：
B. Manimala;D. Walker;G. Padfield;M. Voskuijl;A. Gubbels
本文描述了用于操纵品质和飞行控制调查的贝尔412直升机高保真仿真模型的开发和验证。基线模型的特点是主旋翼具有刚性的铰接式叶片单元，具有襟翼和滞后自由度。贝尔412惠普发动机/调速器的动态特性由一个二阶系统表示。基线模型的其他关键特征包括有限状态动态流入模型和滞后阻尼器动力学。对于轴上响应，基线模型与15-120kt速度范围内的飞行测试数据具有很好的一致性。对离轴响应的预测就不那么准确了。引入了几种模型增强选项以获得改进的离轴响应。结果表明，在Peters-He有限状态动态入流模型中考虑尾迹几何扭曲效应，可以显著改善瞬变操纵时的俯仰/横滚离轴响应。
Abstract This paper describes the development and validation of a high fidelity simulation model of the Bell 412 helicopter for handling qualities and flight control investigations. The base-line model features a rigid, articulated blade-element formulation of the main rotor, with flap and lag degrees of freedom. The Bell 412 HP engine/governor dynamics are represented by a second-order system. Other key features of the base-line model include a finite-state dynamic inflow model and lag damper dynamics. The base-line model gives excellent agreement with flight-test data over the speed range 15-120kt for on-axis responses. Prediction of off-axis responses is less accurate. Several model enhancement options were introduced to obtain an improved off-axis response. It is shown that the pitch/roll off-axis responses in transient manoeuvres can be improved significantly by including wake geometry distortion effects in the Peters-He finite-state dynamic inflow model.