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针对常规坐地起降飞机动力系统无法兼顾悬停效率和平飞效率、大的方向舵和副翼导致阻力和结构重量增加、近地面悬停时反弹气流导致飞机无法精准操纵等问题,设计了一种小型电动力四旋翼坐地起降无人机,采用四旋翼实现悬停飞行。飞机平飞时只需一个针对平飞状态优化的螺旋桨提供推力,并利用动力配平改善平飞飞行性能。建立了气动力计算模型、推进系统计算模型和全机重量计算模型;并对螺旋桨、电机以及动力系统匹配进行了优化设计;针对提出的四旋翼坐地起降布局和常规布局坐地起降无人机开展了对比计算。结果表明,四旋翼坐地起降无人机比常规坐地起降无人机具有更好的飞行性能。
Aiming at the problem that the power system of the conventional take-off and landing aircraft can not balance the efficiency of hovering and the flying efficiency, the large rudder and ailerons lead to the increase of the resistance and the weight of the structure, and the rebound of the air when the near-ground hovering causes the precision control of the aircraft, Electric four-rotor takeoff and landing UAV, using four rotors to achieve hover flight. When the aircraft is flying, only one propeller optimized for level flight is provided, and power leveling is used to improve flight performance. The aerodynamic calculation model was established to promote the system calculation model and the whole machine weight calculation model. The propeller, the motor and the power system matching were optimally designed. According to the proposed four-rotor take-off and landing structure and the conventional layout, Carried out comparative calculation. The results show that the four-rotor landing takeoff and landing UAV than conventional landing takeoff and landing UAV has better flight performance.