本发明属于机械结构设计技术领域,涉及一种涡桨垂直起降固定翼飞机总体气动布局,包含桶状机身、曲面V型尾翼、分段机翼、水平固定布置涡桨发动机、涡桨机构、偏航配平机构;涡桨发动机位于分段机翼翼尖;机身桨盘桨叶可折叠收缩于尾部机身之中,垂直起降时机身桨盘倾转垂直于机身,张开桨叶并启动电机提供机身尾部升力,巡航时关闭电机折叠收缩桨叶,倾转机身桨盘整体收纳于尾部机身之中,机翼桨盘倾转至水平拉力位置;通过本发明可使涡桨航空器巡航阶段更接近固定翼飞机,具有工程可实现性并使此类型飞机的整体安全性和经济性能显著提升,达到低内损,且无翼下乱流,保障垂直起降及悬停阶段的稳定和安全性。
The invention belongs to the technical field of mechanical structure design, and relates to an overall aerodynamic layout of a turboprop vertical take-off and landing fixed wing aircraft, which comprises a barrel-shaped fuselage, a curved V-shaped empennage, segmented wings, a horizontally fixed turboprop engine, a turboprop mechanism and a yaw balancing mechanism, the turboprop engine is positioned at the tip of the segmented wing; the fuselage propeller disc blades can be folded and contracted in the tail fuselage, during vertical take-off and landing, the fuselage propeller disc tilts to be perpendicular to the fuselage, the propeller blades are opened, the motor is started to provide fuselage tail lifting force, during cruising, the motor is closed, the propeller blades are folded and contracted, the fuselage propeller disc tilts to be integrally stored in the tail fuselage, and the wing propeller disc tilts to the horizontal tension position; by means of the method, the cruising stage of the turboprop aircraft is closer to that of a fixed-wing aircraft, engineering realizability is achieved, the overall safety and economic performance of the aircraft of the type are remarkably improved, low internal loss is achieved, no turbulent flow under wings exists, and the stability and safety of the vertical take-off and landing stage and the hovering stage are guaranteed.
一种涡桨垂直起降固定翼飞机
2024-05-31
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |