高速直升机方案中升力转移过程的设计和试验研究

在众多高速直升机方案中，最有发展前途的就是旋翼／机翼转换式高速直升机。目前大多数转换式高速方案都采用升力转移来解决导致直升机不能飞得更快的根本原因——旋翼相对气流分布的不对称性所造成的气流分离及激波问题，即从直升机模式由旋翼承担升力过渡列固定翼飞机模式由机翼承担升力。而升力转移过程中，升力、功率和操纵的平滑过渡则是此方案的关键。本文根据某高速直升机方案设计了其升力转移过程，并用试验对升力转移过程进行了验证。

Design and Experiment of Lift Transfer in Scheme of High-Speed Helicopter

With the development of helicopter in military and civil aviation,it is necessary to increase its flight speed. The research in this filed has been done for long time. So many projects in scheme of high speed helicopter are presented in recent years. However, every project must solve a problem related to main rotor stall and shock wave-the reasons that restrict the forward speed of the helicopter.Most of the projects solve this problem by lift transfer,that is, to shift the lift from the main rotor in the helicopter model to the wing in the air plane model.In the schemes, the project of rotor/wing interchanging model is most hopeful. The key technique of the project of the high speed rotorcraft is the smoothness of lift shift,power and control. In this paper, the process of the lift shift is designed. To verify the feasibility of the scheme, the wind tunnel experiment is needed. The especial model of the diskwing/co axial rotors, or DCAR and a test rig are designed and built. The lift and the power are measured in different wind speeds, rotate speeds, attack angles for the diskwing and the DCAR. Based on these test data, the calculation method is revised for aerodynamic characteristics of the DCAR.Then,the feasibility of the lift shift for the DCAR is proved.