扇翼飞行器短距起飞性能

Take-off performance of the fan-wing aircraft

摘要:

为验证扇翼飞行器超短距起飞特性及大载荷特性.以某型6 kg级扇翼飞行器为研究对象，在分析其结构特点和飞行原理的基础上，根据该飞行器在地面与空中的受力情况，建立了扇翼飞行器的纵向模型，使地面滑跑段与空中段有效衔接，并通过数值仿真，对比分析了升降舵偏转量、重心位置、扇翼转速以及载荷量对扇翼飞行器起飞滑跑距离的影响.仿真结果表明：空载时起飞滑跑距离最短；在起飞过程中需要保持升降舵上偏最大角度；重心位置越靠近扇翼力作用点，起飞滑跑距离越短；在这些因素固定的情况下配合适当扇翼转速，最终获得该样机不到9 m的最短起飞滑跑距离.通过对比分析，良好的起飞性能需要几个因素的配合设置.

Abstract:

To verify the short take-off and large-load characteristics of the fan-wing aircraft, a 6 kg fan-wing aircraft is studied. Based on the analysis of its structure characteristics and flight principle, the longitudinal model is built according to the force analysis on the ground and in the air, which effectively connects the ground running and the aerial flying. Meanwhile, four factors (elevator deflection, position of center of gravity, fan wing rotation speed, and airplane load) influenced the take-off running distance are analyzed and compared through numerical simulations. The simulation results show that: the no-load flight leads to the shortest take-off distance; the elevator deflection is located as large as it can be during the take-off process; as the center of gravity closer to the force application position of the cross-flow fan, the take-off distance remains shorter; when the factors are fixed, the shortest take-off distance, less than 9 m, is obtained with an optimal rotation speed. The allocation of the four factors is needed to gain a better take-off performance through the comparative analyses.