The invention discloses a novel heavy-load aircraft with a stub-wing lift fuselage. Comprising an airfoil-shaped lift fuselage, front stub wings connected to the two sides of the nose of the lift fuselage in a smooth transition mode, rear stub wings connected to the two sides of the tail of the lift fuselage in a smooth transition mode, a propeller power mechanism arranged on the nose of the lift fuselage, a V-shaped empennage arranged on the tail of the lift fuselage and a ventral fin arranged on the belly of the lift fuselage. The wingspan of the novel heavy-load stub wing lift fuselage aircraft is less than or equal to 2m, the wingspan of the front stub wing is smaller than that of the rear stub wing, and the mounting angle of the front stub wing is larger than that of the rear stub wing; after the scheme is adopted, the lift fuselage can provide large lift force, the short wings can provide a part of lift force, meanwhile, longitudinal balancing of the aircraft can be completed by adjusting the mounting angle, the static stability requirement of the aircraft is met, the performance of high-speed cruise is reserved, the wingspan of the wings is reduced, and the stability of the aircraft is improved. Therefore, the unmanned aerial vehicle has flexible performance and can be applied to narrow and complex environments.
本发明公开了一种新型大载重短翼升力机身飞行器,包括翼型的升力机身、平滑过渡连接于升力机身机头处两侧的前短翼、平滑过渡连接于升力机身机尾处两侧的后短翼、设于升力机身机头处的螺旋桨动力机构、设于升力机身机尾处的V型尾翼、以及设于升力机身机腹的腹鳍;且该新型大载重短翼升力机身飞行器的翼展≤2m,前短翼的翼展小于后短翼的翼展,前短翼的安装角大于后短翼的安装角;在采用此方案后,升力机身可提供较大的升力,短翼在提供一部分升力外,同时可以通过调整安装角来完成飞行器纵向配平,满足飞行器的静稳定性需求,并且此方案保留了高速巡航的性能,以及减小了机翼翼展,从而使得无人机具备机动灵活的性能,可应用于狭小复杂的环境。
Novel heavy-load aircraft with stub-wing lift fuselage
一种新型大载重短翼升力机身飞行器
2024-12-17
Patent
Electronic Resource
Chinese