Aerodynamic Characteristics of Aircraft Model with Cable Suspension System under Rotary Motion

A wind-tunnel test of rotary motion around a velocity vector is a crucial method for investigating the intricate maneuvering characteristics of fighter aircraft, including spin and high-angle-of-attack maneuvers. In this paper, a method for constant rotary angular velocity motion is proposed, using a novel six-degree-of-freedom cable-driven parallel suspension mechanism (CDPSM). The correlation between the aircraft model's attitude angles and rotary motion parameters is established, and a closed-loop control algorithm is developed, employing cable length as a variable to achieve precise motion control. Taking the standard dynamic model as an example, an integrated design of the model-balance-support system is performed, and measurements of static and dynamic aerodynamic characteristics are conducted in a low-speed wind tunnel, encompassing steady and oscillatory spin at high angles of attack. The results demonstrate that the CDPSM facilitates rotary motion around velocity vector, and the proposed design approach proves to be effective and feasible. Through the acquisition and analysis of aerodynamic data, it is observed that parameters such as the half-cone angle, angular velocity, and oscillatory spin modes significantly influence the aerodynamic characteristics. This research provides technical support for modeling unsteady aerodynamics at high angles of attack and analyzing spin characteristics.