变转速刚性旋翼载荷分析与试验研究
发布时间：2018-12-23 10:52
【摘要】：直升机旋翼转速的变化将对直升机的飞行性能和动力学特性产生重要的影响。为了提高直升机的性能,旋翼转速优化的应用是当前国内外的一个研究热点。通过理论分析表明,合理地改变直升机旋翼的转速,可以有效地降低直升机工作过程中的需用功率。而旋翼转速的改变,会极大地增加旋翼结构动力学的复杂程度,这将对旋翼桨叶和桨毂的设计提出更高的要求。本文探索了变转速刚性旋翼系统的结构设计,设计了具有高刚度、轻质量的模型桨叶,以及刚性无铰式模型桨毂。模型桨叶采用变翼型、变弦长、带负扭,带尖削的几何外形,内部结构设计采用了碳纤维加玻璃纤维蒙皮、碳纤维“C型”大梁、碳纤维后缘条等构型。无铰式刚性旋翼桨毂以桨毂中央件承受离心力载荷和弯矩载荷,并设计了桨毂柔性片来增加桨毂挥舞方向的弯曲刚度,并对模型旋翼系统进行了强度、刚度的校核,进行优化设计。最后将模型旋翼加工出来以进行变转速刚性旋翼性能及振动载荷试验研究。本文开展了多风速、多转速、多拉力载荷的风洞试验。通过六分量天平和应变片测量了模型旋翼的桨毂载荷以及小拉杆、柔性片上的载荷,并结合理论知识对试验中测量载荷的变化规律进行了分析。此外,本文通过旋翼气弹综合模型,分析了旋翼模型桨叶的剖面载荷,分析其规律,为变转速刚性旋翼振动载荷的进一步研究打下基础。
[Abstract]:The change of helicopter rotor speed will have an important impact on the helicopter flight performance and dynamic characteristics. In order to improve the performance of helicopter, rotor speed optimization is a research hotspot at home and abroad. The theoretical analysis shows that changing the rotor speed reasonably can effectively reduce the required power in the helicopter working process. The change of rotor speed will greatly increase the complexity of rotor structure dynamics, which will put forward higher requirements for the design of rotor blade and hub. In this paper, the structural design of the rigid rotor system with variable rotational speed is explored. The model blades with high stiffness and light mass are designed, and the rigid non-hinged model propeller hub is designed. The model blade adopts the geometric shape of variable airfoil, variable chord length, negative torsion and sharp cutting. The internal structure is designed with carbon fiber with glass fiber skin, carbon fiber "C" beam, carbon fiber rear edge strip and so on. Non-hinged rigid rotor hub is subjected to centrifugal load and bending moment load with the center of the hub. The flexible blade of the hub is designed to increase the bending stiffness in the swing direction of the hub, and the strength and stiffness of the model rotor system are checked. Optimize the design. Finally, the model rotor is machined to study the performance and vibration load of the rigid rotor with variable rotational speed. In this paper, wind tunnel tests with multi wind speed, multi-speed and multi-tension load are carried out. The load on the propeller hub of the model rotor and the load on the small rod and flexible sheet were measured by the six-component balance and strain gauge. The variation of the measured load in the experiment was analyzed by combining the theoretical knowledge. In addition, based on the aero-elastic model of rotor, the profile load of rotor blade is analyzed and its law is analyzed, which lays a foundation for further research on vibration load of rigid rotor with variable rotational speed.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V275.1
本文编号：2389884
[Abstract]:The change of helicopter rotor speed will have an important impact on the helicopter flight performance and dynamic characteristics. In order to improve the performance of helicopter, rotor speed optimization is a research hotspot at home and abroad. The theoretical analysis shows that changing the rotor speed reasonably can effectively reduce the required power in the helicopter working process. The change of rotor speed will greatly increase the complexity of rotor structure dynamics, which will put forward higher requirements for the design of rotor blade and hub. In this paper, the structural design of the rigid rotor system with variable rotational speed is explored. The model blades with high stiffness and light mass are designed, and the rigid non-hinged model propeller hub is designed. The model blade adopts the geometric shape of variable airfoil, variable chord length, negative torsion and sharp cutting. The internal structure is designed with carbon fiber with glass fiber skin, carbon fiber "C" beam, carbon fiber rear edge strip and so on. Non-hinged rigid rotor hub is subjected to centrifugal load and bending moment load with the center of the hub. The flexible blade of the hub is designed to increase the bending stiffness in the swing direction of the hub, and the strength and stiffness of the model rotor system are checked. Optimize the design. Finally, the model rotor is machined to study the performance and vibration load of the rigid rotor with variable rotational speed. In this paper, wind tunnel tests with multi wind speed, multi-speed and multi-tension load are carried out. The load on the propeller hub of the model rotor and the load on the small rod and flexible sheet were measured by the six-component balance and strain gauge. The variation of the measured load in the experiment was analyzed by combining the theoretical knowledge. In addition, based on the aero-elastic model of rotor, the profile load of rotor blade is analyzed and its law is analyzed, which lays a foundation for further research on vibration load of rigid rotor with variable rotational speed.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V275.1
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