跷跷板旋翼舰面瞬态气弹响应分析及抑制方法

韩东; 高正; 王浩文; 李昕柏

跷跷板旋翼舰面瞬态气弹响应分析及抑制方法

1.
南京航空航天大学直升机旋翼动力学重点实验室, 江苏南京 210016
2.
哈尔滨地区军代室, 黑龙江哈尔滨 150066

计量
- 文章访问数: 1587
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- 被引次数: 0
出版历程
- 收稿日期: 2005-09-28
- 修回日期: 2006-03-20
- 刊出日期: 2006-08-28

Analysis and control of transient aero-elastic response of teetering rotor on the shipboard

1.
National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Army Office in Harbin, Harbin 150066, China

摘要

摘要: 为了研究跷跷板旋翼在舰面起动和停转过程中的瞬态气弹响应问题,本文在中等变形梁的基础上,引入跷跷板旋翼整体挥舞有限转角广义坐标,采用非线性准定常气动模型,根据Hamilton原理建立了基于广义力的跷跷板旋翼动力学方程,舰面流场采用试验测试数据。通过与国外试验数据及计算值的对比验证了本文计算模型的正确性。计算表明,舰面跷跷板旋翼存在桨叶过大挥舞与机体相碰的问题。对于可能防止相碰的机械措施和操纵方式进行了分析。
- 航空、航天推进系统 /
- 跷跷板旋翼 /
- 舰 /
- 气弹响应 /
- 抑制方法
Abstract: To investigate the problem of transient dynamic aero-elastic response of teetering rotor engagement and disengagement during shipboard operations,finite rotation of teeter angle was introduced as generalized coordinate based on the moderate deflection beam model.Nonlinear quasi-steady aerodynamic model was adopted and the flow field was determined by the test data.According to the Hamilton principle,dynamic equations were derived based on the generalized force formation.Calculation results are in good agreement with the test data and the data from other literatures.Result shows that teetering rotor blade tip has the danger of touching fuselage because of the excess flapping motion during shipboard operations.Some methods of controlling blade excess flapping are discussed.Installation of the blade flap restraint device can restrict the blade excess flapping.Increasing collective pitch has contrary effect.Cyclic pitch control has some effect on the blade flapping motion.The blade excess flapping motion can be evidently reduced by the control of the rotor speed.
- aerospace propulsion system /
- teetering rotor /
- shipboard /
- aero-elastic response /
- control method

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参考文献(12)

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