Two-body omnidirectional aircraft with ducted power devices hinged to dish-shaped body

Abstract

The invention discloses a two-body omnidirectional aircraft with ducted power devices hinged to a dish-shaped body. The two-body omnidirectional aircraft comprises a dish-shaped body fuselage, the ducted power devices and power hinge air channels. The dish-shaped body fuselage can generate aerodynamic lift force during high-speed flight; a vertical air inlet through hole is formed in the center of the dish-shaped body fuselage; the air inlet through hole is connected with a ducted power device through a power hinge air channel; a disc-shaped functional load bin is erected above the air inlet through hole, and a weather cock is arranged above the functional load bin; the vector included angle between the ducted power device and the dish-shaped body fuselage can be changed by adjusting the bending angle of the power hinge air channel so as to generate a momentum moment conservation moment; the ducted power device comprises an outer cylinder, a jet engine and a pneumatic control surface; the jet engine is located in the outer cylinder, and the air inlet end of the outer cylinder communicates with the air outlet end of the power hinge air channel. The pneumatic control surface is arranged in a cylinder opening of the outer cylinder on the air outlet side of the jet engine; the thrust vector of the jet engine can be changed by adjusting the deflection angle of the pneumatic control surface so as to generate pneumatic torque.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, in particular to a two-body omnidirectional aircraft in which a ducted power device and a disc-shaped body are hinged. Background technique [0002] In recent years, UAV technology has developed rapidly. By carrying various functional loads on UAVs, UAVs have been applied in many fields and replaced manned aircraft to complete various specific tasks. [0003] UAVs are mainly divided into fixed-wing UAVs and rotary-wing UAVs according to different structural types. For fixed-wing UAVs, although it has the advantages of fast speed, long range, and strong maneuverability, it also has the disadvantage of being limited by the take-off and landing site. When taking off, it either needs a runway or an ejection track. When landing, Either slide down or parachute down, resulting in poor take-off and landing safety and flexibility of fixed-wing UAVs. For rotor UAVs, although it has the a...

AI Technical Summary

Problems solved by technology

For fixed-wing UAVs, although it has the advantages of fast speed, long range, and strong maneuverability, it also has the disadvantage of being limited by the take-off and landing site. When taking off, it either needs a runway or an ejection track. When landing, Either slide down or parachute, resulting in poor take-off and landing safety and flexibility of fixed-wing UAVs

For rotor UAVs, although it has the advantages of vertical take-off and landing, hovering in the air, and low requirements for take-off and landing sites, it has the disadvantages of slow flight speed, short battery life, and poor maneuverability.

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