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A short-range take-off and landing UAV using distributed ducted power

A short-distance take-off and landing, unmanned aerial vehicle technology, applied in the field of unmanned aerial vehicles, to achieve the effect of improving take-off and landing performance, increasing endurance time, and improving aerodynamic efficiency

Active Publication Date: 2022-07-26
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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  • A short-range take-off and landing UAV using distributed ducted power
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  • A short-range take-off and landing UAV using distributed ducted power

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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-range take-off and landing drone using distributed ducted power, comprising a fuselage, a front wing, a rear wing, a trailing edge flap, an elevator, an aileron, a front landing gear, a main landing gear, a vertical tail, Rudder, ducted power pack and generator room, of which there are two fuselages, and the distance between the fuselage is less than the length of the wingspan of the front wings. , the rear wing is connected to and traverses the two fuselage tails, the two vertical tails are installed just 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 fuselage respectively;

[0017] The elevator is installed on the trailing edge of the left and right outer sides of the front wing, ...

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Abstract

The invention provides a short-range take-off and landing drone using distributed ducted power, and relates to the technical field of drones. The present invention has two fuselage, and the front wings are connected and traverse the front parts of the two fuselage. , the rear wing is connected to and traverses the tails of the two fuselages, and the vertical tails are respectively installed directly above the tails of the two fuselages. Weight, vibration, and fuel consumption; improved aerodynamic efficiency of the wing by pumping the boundary layer on the upper surface of the wing by means of ducted power packs distributed on the upper surface of the wing trailing edge flaps; the distribution of the power system avoids The failure of a single engine leads to the loss of control of the UAV, which improves the safety of the UAV; the trailing edge flap drives the ducted power group to deflect and change the thrust direction, which shortens the rolling distance of the UAV during the take-off and landing phase, and improves the safety of the UAV. The take-off and landing performance of UAVs expands the application scope of UAVs.

Description

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

Claims

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Application Information

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Patent Type & Authority Patents(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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