跷跷板旋翼舰面瞬态气弹响应分析及抑制方法
Analysis and control of transient aero-elastic response of teetering rotor on the shipboard
-
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。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.
-
Key words:
- aerospace propulsion system /
- teetering rotor /
- shipboard /
- aero-elastic response /
- control method
-
[1] Keller J A.Experiment and theoretical correlation of helicopter rotor blade-droop stop impacts[J].Journal of Aircraft,1999,36(2):443-450. [2] 韩东,高正.舰载无人直升机的应用和发展预测[A].第二十届全国直升机年会论文集[C].四川宜宾,2004:27-33. [3] Newman S J.The verification of a theoretical helicopter rotor blade sailing method by means of windtunnel testing[J].Aeronautical Journal,1995,99(982):41-51. [4] Geyer W P,Smith E C,Keller J A.Aeroelastic analysis of transient blade dynamics during shipboard engage/disengage operations[J].Journal of Aircraft,1998,35(3):445-453. [5] Keller J A.Analysis and control of the transient aeroelastic response of rotors during shipboard engagement and disengagement operations[D].Pennsylvania State University:2001. [6] Hao Kang,Chengjian He.Modeling and simulation of rotor engagement and disengagement during shipboard operations[C].Proceedings of the American Helicopter Society 60th Annual Forum,Maryland:Baltimore,2004. [7] 高正.直升机空气动力学的新成果[M].北京:航空工业出版社,1999,205-210.Gao Zheng.Recent achievements in the Field of helicopter aerodynamics[M].Beijing:Aviation Industry Press,1999,233-243. [8] Straub F K,Sangha K B,Panda B.Advanced finite element modeling of rotor blade aeroelasticity[J].Journal of the American Helicopter Society,1994,39(2):56-68. [9] 顾蕴松,明晓.舰船飞行甲板真实流场特性试验研究[J].航空学报,2001,22(6):500-504.Gu Yunsong,Ming Xiao.Experimental investigation on flow field properties around aft-deck of destroyer[J].Acta Aeronautica et Astronautica Sinica,2001,22(6):500-504. [10] 王浩文,高正,郑兆昌.前飞状态下直升机旋翼系统气弹响应及稳定性分析[J].振动工程学报,1999,12(4):521-528.Wang Haowen,Gao Zheng,Zheng Zhaochang.Aeroelastic response and stability of helicopter rotor blades in forward flight[J].Journal of Vibration Engineering,1999,12(4):521-528. [11] Colin R H.Helicopter flight dynamics simulation with refined aerodynamics modeling[D].Univerisity of Maryland,2000. [12] Wang Haowen,Gao Zheng.Rotor vibratory load prediction based on generalized forces[J].Chinese Journal of Aeronautics,2004,17(1):28-33.
点击查看大图
计量
- 文章访问数: 1437
- HTML浏览量: 2
- PDF量: 455
- 被引次数: 0