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An unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing

A short-range take-off and landing, unmanned aerial vehicle technology, applied in the field of unmanned aerial vehicles, to achieve the effect of improving aerodynamic efficiency, reducing weight, and improving take-off and landing performance

Active Publication Date: 2018-09-25
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this patent does not advantageously couple the distributed power system with the aerodynamic components such as the wings of the UAV to improve the aerodynamic efficiency and propulsion efficiency of the UAV.

Method used

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  • An unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing
  • An unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing
  • An unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing

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Embodiment Construction

[0015] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0016] A short take-off and landing unmanned aerial vehicle using distributed ducted power, including fuselage, front wing, rear wing, trailing edge flap, elevator, aileron, front landing gear, main landing gear, vertical tail, The rudder, the ducted power group and the generator compartment, wherein, there are two fuselages, and the distance between the fuselages is smaller than the length of the wingspan of the front wings. , the rear wing is connected and traverses the tails of the two fuselages, the two vertical tails are respectively installed directly above the tails of the two fuselages, the two front landing gears are respectively installed under the fronts of the two fuselages, and the two main The landing gear is installed under the rear of the two fuselages respectively;

[0017] The elevator is installed on the rear edge of the left and rig...

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Abstract

The invention provides an unmanned aerial vehicle using distributed ducted power and capable of short-distance take-off and landing and relates to the technical field of unmanned aerial vehicles. Theunmanned aerial vehicle has two fuselages. A front wing connects and traverses the fronts of the two fuselages, and a rear wing connects and traverses the tail portions of the two fuselages. Verticaltail wings are respectively installed directly above the tail portions of the two fuselages. An oil-electricity hybrid power scheme is adopted to prolong endurance of the unmanned aerial vehicle, andreduce weight, vibration and the oil consumption rate of a power system. Ducted power assemblies distributed on the upper surfaces of trailing edge flaps of the wings suction boundary layer airflow onthe upper surfaces of the wings so as to increase the aerodynamic efficiency of the wings. Distributed arrangement of the power system avoids a problem that malfunction of one engine causes a runawayunmanned aerial vehicle, thus improving safety of the unmanned aerial vehicle. The trailing edge flaps drive the ducted power assemblies to deflect so as to change a thrust direction, thus shorteningsliding distances in take-off and landing stages of the unmanned aerial vehicle, improving take-off and landing performance of the unmanned aerial vehicle, and expanding the application range of theunmanned aerial vehicle.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a short-distance take-off and landing unmanned aerial vehicle. Background technique [0002] At present, the power forms of drones are mainly divided into two types: oil-powered and electric. Oil-powered drones have a long battery life, but the weight, vibration and noise of the engine are very large, and the exhaust gas will pollute the environment. Electric drones are green, clean, light in weight and low in noise, but limited by the current level of battery technology, the power of the power system is small and the battery life is short. In addition, most drones currently use a single engine. The engine is installed at the nose or tail of the fuselage. The redundancy of the power system is low. Once a failure occurs, it is easy to cause the drone to lose control and crash. In order to solve the above problems, the existing patent technology such as the Chines...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/02B64C39/08
CPCB64C39/02B64C39/08B64U70/60B64U10/25B64U50/19B64U50/14
Inventor 张炜马一元白志亮
Owner NORTHWESTERN POLYTECHNICAL UNIV
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