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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.
In order to verify the characteristics of ultra-short-range take-off and large-load characteristics of a sector-propeller aircraft, a 6 kg-class sector was used as a research object. Based on the analysis of its structural features and flight principles, The longitudinal model of the wing-type aircraft is established to make the interface between the runway of the ground and the mid-air section effectively. The deflection of the elevator, the position of the center of gravity, the rotational speed of the wing and the load are analyzed by numerical simulation. The simulation results show that the take-off and landing distance is the shortest when no-load takes off, the maximum angle of the elevator should be maintained during the take-off, the closer the center of gravity is to the point of the wing force, the shorter the take-off and landing distance, , With the proper fan speed, the shortest take-off distance of the prototype is less than 9 m.Through comparative analysis, the good take-off performance requires the cooperation of several factors.