The invention relates to a double-fuselage vertical take-off and landing fixed-wing unmanned aerial vehicle structure. A fuselage of the aircraft is a double-fuselage bilaterally symmetrical about a longitudinal axis, connecting rods integrally formed with the fuselage and used for fixing rotors and empennages are arranged at the head and the tail of the fuselage, and a four-rotor system is fixedly arranged on a front connecting rod and a rear connecting rod of the fuselage; the wings stretch across the two airframes and are divided into a left wing, a middle wing and a right wing; an arched empennage is fixedly arranged on the fuselage tail connecting rod; the propulsion propeller system is fixedly arranged on the middle wing; and the wheel type undercarriage system comprises four undercarriage damping connecting rods and aircraft wheels and is arranged on the lower sides of the left aircraft body and the right aircraft body. According to the aircraft structure, a double-fuselage structure is adopted, so that the aircraft has a large enough task space and is suitable for placing a large-size load; and meanwhile, the rotor wings and the empennage connecting rods can be integrally designed with the fuselage, additional installation of rotor wing rods is avoided, the fuselage and the rotor wing rods are integrally formed, the structure of the aircraft is simplified, the structural strength is guaranteed, and the structural weight is reduced.

本发明涉及一种双机身垂直起降固定翼无人飞行器结构。飞行器的机身为纵轴左右对称的双机身、机身头部和尾部有与机身一体化成型的用于固定旋翼和尾翼的连杆，四旋翼系统固定设置于机身前连杆和后连杆上；机翼横跨两个机身，分为左机翼、中部机翼和右机翼；机身尾部连杆上固定设置有“拱形”尾翼；推进螺旋桨系统固定设置于中部机翼上；轮式起落架系统包括四个起落架减震连杆及机轮，安置于左右机身下侧。本发明的飞行器结构，因采用了双机身结构，使飞行器具有足够大的任务空间，适合放置大尺寸载荷；同时旋翼和尾翼连杆能够与机身设计为一体，避免额外安装旋翼杆，机身和旋翼杆一体成型，简化了飞行器结构，既保证了结构强度，又降低了结构重量。