电控旋翼气弹动力学建模研究

陆洋; 王浩文; 高正

电控旋翼气弹动力学建模研究

南京航空航天大学直升机旋翼动力学国家级重点实验室, 江苏南京 10016

基金项目: 国防重点实验室基金资助(51463020101ZS52)

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出版历程
- 收稿日期: 2006-02-09
- 修回日期: 2006-09-26
- 刊出日期: 2006-12-28

Aeroelastic dynamic modeling of the Electrically Controlled Rotor

National Key Laboratory of Rotorcraft Aeromechnaics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 研究了电控旋翼的气弹动力学建模方法。以有限元旋翼气弹分析程序LORA01为基础,首先给出了一种能计及襟翼移轴补偿影响的时域综合非定常气动力模型,并将伺服襟翼作为额外引入的质量体计入结构动力学模型;之后结合有限元法,根据Hamilton原理导出由广义力表示的带襟翼桨叶非线性运动方程,采用基于Newmark方法的隐式数值积分法对桨叶运动方程进行求解。最后,利用主动控制襟翼旋翼的试验数据对模型进行了比较验证,证明了所建模型的正确性。
- 航空、航天推进系统 /
- 电控旋翼 /
- 襟翼 /
- 气弹动力学 /
- 建模 /
- 空气动力学 /
- 结构动力学
Abstract: For the purpose of aeroelastic analysis of the Electrically Controlled Rotor(ECR),an aeroelastic dynamic model is built in this paper.Firstly,a synthetic unsteady aerodynamic model in time domain is presented,which can take account of the unsteady effect of the flap nose overhang.The inertia effect of the flap is introduced into the structural dynamic model as an independent mass.According to the Hamilton principle,the nonlinear motion equation of the blade with flap is deduced with the form of generalized forces.Then,based on the finite element aeroelastic analysis code LORA01,the implicit equation of ECR blade motion is solved by an improved Newmark numerical integration method.At last,the ECR aeroelastic dynamic model is validated through comparison with the test results of the Active Control Flap(ACF) rotor.
- aerospace propulsion system /
- electrically controlled rotor /
- flap /
- aeroelastic dynamics /
- modeling /
- aerodynamics /
- structural dynamics

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参考文献(13)

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