Multipurpose dual-module combined hybrid power unmanned aerial vehicle

A hybrid and combined technology, applied in the field of drones, can solve problems such as poor maneuverability, short battery life, and few functions of drones, and achieve the effect of improving battery life

Pending Publication Date: 2018-02-27
成都军融项目管理有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, and the purpose is to provide a multi-purpose dual-module combined hybrid unmanned aerial vehicle, which solves the problems of the existing unmanned aerial vehicles with few functions, short battery life, and poor mobility.

Method used

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  • Multipurpose dual-module combined hybrid power unmanned aerial vehicle
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  • Multipurpose dual-module combined hybrid power unmanned aerial vehicle

Examples

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Effect test

Embodiment 1

[0043] Such as Figure 1-6As shown, a multi-purpose dual-module combined hybrid unmanned aerial vehicle of the present invention includes a combined flying wing module 1 and a power task cabin module 2, and the combined flying wing module 1 includes a screw assembly 33, a combined flying wing The cabin 3, the flying wing power part 4 and the flying wing connector 5 are connected with the combined flying wing cabin 3 to be provided with four sets of screw assemblies 33, and the ducted propeller part of the screw assembly 33, in order to meet the requirements of lifting heavy loads , The diameter of the rotor and the volume of the duct are large, and the diameter of the propeller is 1.4 meters to 1.6 meters, which provides a large lift for the UAV. Arranged in a square, the unmanned aerial vehicle is provided with lifting power through the screw assembly 33. The flying wing power part 4 is arranged in the combined flying wing cabin 3 to provide kinetic energy for the screw wing ...

Embodiment 2

[0061] Such as Figure 7-8 As shown, the present invention is a multi-purpose dual-module combined hybrid unmanned aerial vehicle. On the basis of Embodiment 1, the flying wing connector 5 is a slider body 10, and the mission cabin matched with the slider body 10 The connecting piece 8 is a chute body 11, and the slider body 10 is slidably inserted into the chute body 11 to combine the combined flying wing module 1 and the power task cabin module 2 into one.

[0062] The flying wing connector 5 is a chute structure 12, and the task cabin connector 8 matched with the chute structure 12 is a slider structure 13, and the slider structure 13 is inserted into the chute structure 12 by sliding to make the combined flying wing The wing module 1 and the power mission cabin module 2 are combined into one.

[0063] In this embodiment, what is mainly disclosed is the connecting structure of the chute and the slide block (slide rail). When the male groove is inserted into the female groo...

Embodiment 3

[0065] Such as Figure 9 As shown, the present invention is a multi-purpose dual-module combined hybrid unmanned aerial vehicle. On the basis of Embodiment 1, the flying wing connector 5 is an electromagnet structure 14, and the mission cabin connector 8 is a docking iron Block 15, the combined flying wing module 1 is adsorbed on the docking iron block 15 of the power mission cabin module 2 through the electromagnet structure 14; the combined flying wing module 1 and the power mission cabin module 2 are combined into one.

[0066] An electromagnet is a device that generates electromagnetism when energized. A conductive winding matching its power is wound on the outside of the iron core. This current-carrying coil is magnetic like a magnet, and it is also called an electromagnet (electromagnet). We usually make it into a bar or shoe shape to make the core easier to magnetize. In addition, in order to demagnetize the electromagnet immediately when it is powered off, we often u...

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Abstract

The invention discloses a multi-purpose dual-module combined hybrid unmanned aerial vehicle, which comprises a combined flying wing module and a power task cabin module. Parts and flying wing connecting parts, at least one set of screw assembly is connected with the combined flying wing cabin, and the lifting power is provided for the UAV through the screw wing assembly, and the flying wing power part is arranged in the combined flying wing cabin as a spiral Wing assembly provides kinetic energy, and described flying wing connecting piece is arranged at the bottom of combined flying wing cabin; Combined flying wing cabin both sides are respectively provided with wing; Described power task cabin module comprises task loading compartment, turboprop engine and task cabin connecting piece, The front end or the rear end of the task loading compartment is provided with a turboprop engine, which provides cruise flight power for the UAV through the turboprop engine, and a task compartment connector is provided on the top of the task loading compartment; the combined flying wing module passes through the The wing connecting piece is flexibly connected with the mission cabin connecting piece of the power mission cabin module.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-purpose dual-module combined hybrid unmanned aerial vehicle. Background technique [0002] At present, the common multi-rotor vertical take-off and landing drones are almost all concentrated in the consumer field, and they are professionally classified as consumer-grade drones. Its payload is only a few hundred grams to a few kilograms. Due to the limitation of the industrial chain and its own technical conditions, a large number of UAV R&D companies in China have not yet developed a multi-rotor UAV with a large payload. Their products are more used. It is used for aerial photography, entertainment or to complete a very small amount of industrial flight missions. [0003] The advantages of traditional fixed-wing aircraft are fast flight speed, long range and cruising time, but the disadvantages are long take-off and landing distances and require high-qua...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22
CPCB64C27/22
Inventor 蔡学军蒲子敏
Owner 成都军融项目管理有限公司
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