A small unmanned aerial vehicle with winged aerodynamic layout

A small unmanned aerial vehicle, aerodynamic layout technology, applied to unmanned aircraft, wings, motor vehicles, etc., can solve the problems of limited distance and time, restricting the process of military information construction, and low survivability

Active Publication Date: 2022-06-28
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Military aspects: long-distance early warning, ground reconnaissance and surveillance are limited in distance and time, and their survivability is low, which seriously restricts the process of military informatization construction

Method used

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  • A small unmanned aerial vehicle with winged aerodynamic layout
  • A small unmanned aerial vehicle with winged aerodynamic layout
  • A small unmanned aerial vehicle with winged aerodynamic layout

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Embodiment Construction

[0042] In order to solve the problems of limited range, empty time and flight height of existing UAVs, and to expand the functions of small UAVs, so that they can rely on their own power to complete the high-altitude, long-distance and long-distance flight that could not be completed before. The invention provides a small unmanned aerial vehicle powered by solar energy, having a certain mission load, capable of completing tasks such as surveying, mapping and reconnaissance, and / or being used in various application fields such as meteorological surveying and mapping.

[0043] The power source of the solar drone according to the present invention is solar energy, and the capture of solar energy is realized by solar panels arranged on the aircraft. Due to the different intensity of sunlight in different climates and time conditions, the power that the solar panel can supply also changes accordingly. In order to ensure the normal and smooth operation of the solar drone, it is neces...

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PUM

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Abstract

A small solar unmanned aerial vehicle with wing layout of the present invention: front and rear two-part fuselage; front-end swept wing and rear-end forward-swept wing; twin motors and propellers arranged at the front end of the two-part fuselage; connecting the front and rear wings The bridge arm of the section; two motors and propellers arranged on the outside of the left and right bridge arms; an inverted vertical tail connected to the rear part of the fuselage. A solar panel group is respectively arranged on the upper surfaces of the left swept wing, right swept wing, left forward swept wing, and right forward swept wing to provide energy for the continuous flight of the drone. When taking off, the left and right propellers can be used for vertical take-off and landing, which improves the ease of use and take-off stability of the aircraft; multi-set propeller control improves the maneuverability and reliability of the aircraft; the inverted tail can replace the landing gear As a support, the structure is simplified to save weight; the invention does not have landing gear, and can realize short-distance throwing without runway requirements when taking off, and can realize gliding and landing when landing, and can also realize vertical take-off and landing and hovering in the air.

Description

technical field [0001] The invention relates to a small unmanned aerial vehicle adopting a wing-type aerodynamic layout. Background technique [0002] Low-altitude solar-powered aircraft has many advantages, such as: providing a communication platform for remote and mountainous areas; high-resolution ground pictures taken at close range, which can detect forest fires, search and rescue, etc., and have broad applications. Generally, small low-altitude UAVs that rely on their own fuel as their power source have the problems of short range, short stay time and severely limited air height. In addition, in some cases, small UAVs are required to perform high maneuvering tasks. Due to the small take-off weight of the UAVs, they cannot carry enough fuel and will not be able to meet the requirements of flight missions. [0003] Taking border reconnaissance as an example, the use of active reconnaissance aircraft will be affected by the range, flight time and local environment, and i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/36B64C3/32B64C29/00
CPCB64C3/36B64C3/32B64C29/00B64U10/10B64U50/19
Inventor 李可张可立彭卓清刘昊伯李竟语王少凡陈晓丹杨顺昆
Owner BEIHANG UNIV
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