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近年来对高速直升机的研究日益兴盛起来,而高速直升机设计的关键问题就是升力的转移和过渡。本文利用自转状态在相同临界迎角下可以承担更多升力的特点,提出将自转引入升力转移的过程中,从而达到减小机翼面积、降低机体重量、减小阻力的目的。针对某一高速直升机方案的自转状态,本文设计和建设了试验模型和试验设备,进行了相应的实验研究。通过与直升机正常工作状态下旋翼的实验结果对比,得出了自转旋翼具有更高的效率的结论;并且根据实验结果分析了自转旋翼的稳定转速与前飞速度以及桨盘迎角的关系。通过与前期理论研究的计算结果相比较,对已有的气动模型进行了检验,理论与实验结果得到了相互印证。
In recent years, research on high-speed helicopters is increasingly flourishing, and the key issue in the design of high-speed helicopters is the transfer and transition of lift. In this paper, by utilizing the characteristic that the rotating state can bear more lift under the same critical angle of attack, the author put forward that the rotation is introduced into the process of lift transfer so as to reduce the wing area, reduce the body weight and reduce the resistance. Aiming at the rotation state of a high-speed helicopter program, this paper designs and constructs a test model and test equipment, and conducts a corresponding experimental study. By comparing with experimental results of rotor under normal working condition of helicopter, the conclusion is drawn that autorotation rotor has higher efficiency. According to the experimental results, the relationship between steady rotor speed and forward flight speed and angle of attack is analyzed. Compared with the previous theoretical results, the existing aerodynamic model has been tested, and the theoretical and experimental results have been confirmed.