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Aircraft

A technology of aircraft and fuselage, applied in the field of aircraft, can solve the problems of unmanned aerial vehicle design, frequent calibration of aircraft center of gravity, and large influence of aircraft center of gravity, etc., to achieve fast and effective loading, unloading and replacement, avoid interference, and reduce cruising noise Effect

Pending Publication Date: 2021-11-09
彭振根
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, compound-wing UAVs on the market are mostly used in the field of aerial survey and inspection, but rarely in the field of logistics; most of them use a single wing, in order to improve the wingspan of the loader, the length is mostly more than 2.5 meters, and the overall design flexibility of the fuselage It is not high. It is cumbersome and complicated to replace batteries, goods or equipment inside the fuselage, which is not conducive to loading, unloading and replacement. The weight of goods or equipment has a great impact on the center of gravity of the aircraft, and the center of gravity of the aircraft is frequently calibrated
[0006] In summary, it can be seen that the existing unmanned aerial vehicle design is not excellent in the field of logistics, and there are many defects. For this reason, the present invention is provided

Method used

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Effect test

Embodiment 1

[0045] This embodiment provides an aircraft. An aircraft includes a fuselage, a first component and a second component arranged on both sides of the fuselage; Disassemble the reorganized warehouse section; the first assembly includes the slave wing 2 arranged on both sides of the fuselage and the front arm 3 arranged on the slave wing 2, and the front arm 3 also includes the front arm 3 arranged on the front arm 3 The power unit; the second assembly includes the main wing 4 arranged on both sides of the fuselage and the rear arm 5 arranged on the main wing 4, and the rear arm 5 also includes a power unit arranged on the rear arm 5; this The wingspan of the aircraft's slave wing is 1900 (unit: mm, the same below), the wingspan of the main wing is 1800, and the length of the fuselage is 1630. Rectangular wing with tapered wingtips at the tip of the secondary wing and end plates at the tip of the main wing. From the leading edge of the wing to the nose 350, the leading edge of t...

Embodiment 2

[0047] This embodiment is further optimized on the basis of embodiment 1. Specifically, the lower part of the main body of the fuselage is connected to the warehouse section through a chain slot snap-fit ​​self-locking structure. The chain slot snap-fit ​​self-locking structure includes a chain slot and a slot buckle. The chain slot is arranged at the horizontal matching edge of the main body of the fuselage and the bin section, and the slot buckle fastens the chain slot set on the main body of the fuselage with the chain slot of the bin section, so that the main body of the fuselage is connected with the bin section; the matching surface of the chain slot is provided with Sealing strips, springs are arranged in the slot buckle, the number of slot buckles is multiple, the material is metal with sufficient strength and a certain weight, and the surface is not smooth to increase friction, the slot buckle can slide on the chain slot under a certain external force; The chain groove...

Embodiment 3

[0049] This embodiment is further optimized on the basis of Embodiment 2. Specifically, the battery compartment 1, the cargo compartment, the battery compartment 2 and the vertical mating surface of the main body of the fuselage are connected through a dovetail structure. The dovetail structure includes T-shaped slots and The convex body and the T-shaped slot are set on the main body of the fuselage and the cargo compartment, the convex body is set on the battery compartment 1 and the battery compartment 2, and the dovetail groove structure connects the battery compartment 1, cargo compartment, battery compartment 2 and the main body of the fuselage into one As a whole, the displacement of the compartment section in the direction of fuselage width and fuselage length is limited. The cross-section of the two battery compartments is 260*140 thick and the outer surface is coplanar with the outer surface of the main body of the fuselage. The compartment section is open mold casting....

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Abstract

The invention discloses an aircraft, and belongs to a heavy-load logistics composite wing unmanned aerial vehicle in the technical field of unmanned aerial vehicles, and the technical scheme is that the unmanned aerial vehicle comprises a fuselage, and a first assembly and a second assembly which are arranged on the two sides of the fuselage; the fuselage comprises a fuselage main body and bin sections which are arranged on the fuselage main body and can be detached and recombined in sequence; the first assembly comprises driven wings arranged on the two sides of the fuselage and front vehicle arms arranged on the driven wings, and the front vehicle arms further comprise power devices arranged on the front vehicle arms. The second assembly comprises main wings arranged on the two sides of the vehicle body and rear vehicle arms arranged on the main wings. Each rear vehicle arm further comprises a power device arranged on the corresponding rear vehicle arm. According to the large-load logistics composite wing unmanned aerial vehicle, the internal loading space of the aircraft is large, but the wingspan is relatively small, and the application and application range is wider.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to an aircraft. Background technique [0002] With the advancement of UAV technology, the market has begun to explore the application of UAVs in the field of logistics. The existing UAVs in the field of logistics are mainly divided into three categories: multi-rotor UAVs, fixed-wing UAVs and compound-wing UAVs. man-machine. [0003] For the convenience and flexibility of multi-rotor UAVs, it is used in many fields. The multi-rotors on the market are mainly divided into four-rotors, six-rotors, octa-rotors and other types of coaxial dual propellers. Common application fields such as aerial photography, surveying and mapping, plant protection, Monitoring, inspection, etc. Most of the multi-rotors used for load on the market are six-axis or above, resulting in a huge body size of the multi-rotor. Since the multi-rotor is not suitable for flying at high altitudes, it ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/00B64C3/20B64D27/24B64C1/00B64D27/26B64C27/22B64D27/40
CPCB64C3/00B64C3/20B64D27/24B64C1/00B64C27/22B64D27/40
Inventor 彭振根
Owner 彭振根
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