直升机旋翼气弹动力学优化策略(Ⅰ)——灵敏度分析技术研究  

The helicopter rotor aeroelastic sensitivity analysis technology

作　　者：王红州 李有祥 石阳 陈明军 

机构地区：[1]航天神舟飞行器有限公司,北京100074 [2]总装驻618厂军代室,北京100074

出　　处：《应用力学学报》2012年第5期541-547,628,共7页Chinese Journal of Applied Mechanics

摘　　要：基于旋翼气弹动力学模型以及摄动法的灵敏度分析和直接解析的链式规则灵敏度分析相结合技术,推导了直升机旋翼气弹动力学的气弹稳定性、模态频率、自转惯量、桨叶质量、桨叶动应力等参数的灵敏度计算过程。通过算例计算结果表明:使用灵敏度分析方法与直接优化相比,实现动应力减少1.2%,质量减少0.84%,优化时间缩短2.73倍;该灵敏度分析技术对于直升机旋翼气弹动力学优化设计收敛的速度和优化结果效果明显。The helicopter rotor sensitivity of aeroelastic stability,modal frequency,auto-rotary inertia,blade quality and blade dynamic stresses is derived,which is based on the helicopter rotor aeroelastic dynamics,by combining the perturbation method of sensitivity analysis and the direct analytical chain rules sensitivity analysis techniques.Calculation results obtained indicate that by using sensitivity analysis of model optimization and the direct optimization,dynamic stress is reduced 1.2%,total quality of rotor blade reduction of 0.84%,optimization time is shortened by 2.73 times value.The effectiveness of the sensitivity analysis technique for helicopter rotor aeroelastic dynamics optimization design convergence speed and the optimum results is demonstrated.

关 键 词：直升机旋翼气弹动力学 摄动法 链式规则 灵敏度分析 气弹稳定性 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]