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Ducted single-propeller saucer-shaped unmanned aerial vehicle

An unmanned aerial vehicle and ducted technology, applied in the field of unmanned aerial vehicles, can solve problems such as flying accidents that are easy to encounter objects, and achieve the effects of compact structure, strong maneuverability and good concealment.

Inactive Publication Date: 2010-05-12
哈尔滨盛世特种飞行器有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The high-speed rotating blades are also easy to hit objects and cause flight accidents

Method used

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  • Ducted single-propeller saucer-shaped unmanned aerial vehicle
  • Ducted single-propeller saucer-shaped unmanned aerial vehicle
  • Ducted single-propeller saucer-shaped unmanned aerial vehicle

Examples

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Embodiment Construction

[0016] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0017] Depend on Figure 1-Figure 4 It can be seen that the upper end of the landing gear 10 of the present invention is fixed with a duct 1, the upper end of the duct 1 is equipped with a frame 2, and the center of the frame 2 is equipped with a power unit 5 on the central axis of the duct 1, and the upper power unit of the duct 1 5 Fuel tanks 8 are installed symmetrically on both sides, and the power unit 5 is placed in the upper part of the duct 1 through the paddle shaft 3 and the connecting paddle 4, and the anti-rotation fixing parts uniformly arranged in a circle are installed between the inner wall of the lower part of the duct 1 and the outer wall of the middle cabin 12. The rudder surface 6, the longitudinal and front ends of the bottom of the duct 1 are symmetrically equipped with a set of airflow nozzle rudders 7 respectively, the b...

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Abstract

The invention relates to a ducted single-propeller saucer-shaped unmanned aerial vehicle which is characterized in that the upper end part of a landing gear is fixed with a duct, the upper end part of the duct is provided with a frame, the middle part of the frame is provided with a power plant arranged along the central axis of the duct, fuel tanks are symmetrically arranged at two sides of the power plant above the frame, the power plant is connected with a propeller arranged at the upper part in the duct by a propeller shaft, swirl-reducing fixed control surfaces which are uniformly and circumferentially arranged are installed between the inner wall at the lower part of the duct and the outer wall of a main hold, the vertical front and back ends at the bottom of the duct are symmetrically provided with a group of air flow nozzle rudders respectively, the lateral left and right ends at the bottom of the duct are symmetrically provided with a group of air flow nozzle rudders respectively, avionics are arranged in the duct, and an autopilot is installed in the main hold. The invention is economical and practical and has the advantages of compact structure, reasonable design, very good concealment, high flight efficiency, fuel saving, convenient maintenance and strong adaptability. In addition, the invention can take off and land vertically, hover, whirl and fly with low noise at any place.

Description

technical field [0001] The invention belongs to an unmanned aerial vehicle, in particular to a ducted single-blade dish. Background technique [0002] At present, it is known that modern common unmanned fixed-wing aircraft need a higher speed for takeoff and landing to enable the wings to generate sufficient lift, causing about 50% of flight accidents to occur during takeoff and landing, and parking on the ground takes up a lot of space. Most of the modern common rotor unmanned aerial vehicles adopt the structure of single rotor with tail rotor and coaxial double rotor of helicopter. The high-speed rotating blade is a fatal threat to the operator. The high-speed rotating blades are also easy to bump into objects and cause flight accidents. Contents of the invention [0003] The object of the present invention is to overcome the weak point that exists in the above-mentioned technology, provide a kind of compact structure, reasonable design, low-altitude low-speed, vertica...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/06B64C27/20
Inventor 王忠信孙树生吴世海
Owner 哈尔滨盛世特种飞行器有限公司
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