Solar aircraft

An aircraft and solar energy technology, applied in the field of solar aircraft, can solve problems such as the limitation of the aspect ratio of aircraft, achieve the effects of low structural surface density, long-term high-altitude reconnaissance and monitoring, and convenient installation

Inactive Publication Date: 2016-03-16
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, solar-powered aircraft generally have a single fuselage layout, and the load distribution of avionics, energy storage batteries, etc. is

Method used

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Embodiment 1

[0044] A solar powered aircraft such as figure 1 with figure 2 As shown, it includes wing 2, fuselage 3, horizontal tail 4, vertical tail 5, power system 1, pod 6, energy storage battery 7, first connection joint 8 and second connection joint 9, and described pod 6 is fixed At the symmetrical position of the entire machine on the lower surface of the wing 2, the installation of the pod 6 not only takes into account the symmetry of the aircraft, but also reduces the rolling moment that the aircraft bears.

[0045] The energy storage battery 7 is distributed and fixed inside the wing 2, and the upper surface of the wing 2 is covered with solar cells 10;

[0046] Such as image 3 As shown, the first connection joint 8 is composed of a joint semicircle 82 and two first lugs 81, as Figure 4 As shown, the second connection joint 9 is composed of a joint ring 92 and at least 6 second lugs 91;

[0047] The fuselage 3 is a rod-shaped fuselage, and the two fuselages 3 are fixed on...

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Abstract

The invention belongs to the field of overall design of aviation aircrafts and particularly relates to a solar aircraft. The solar aircraft comprises a wing which is a rectangular wing. An energy storage battery is fixedly distributed in the wing. Solar cells are laid on the upper surface of the wing. Two aircraft bodies are fixed to the positions 1/4 and 3/4 of the wing in the tangential direction. Flat tails are parallel to the wing, perpendicular tails are perpendicular to the flat tails, and the flat tails and the perpendicular tails are fixed to the rear ends of the aircraft bodies. Two power systems are fixed to the front ends of the two aircraft bodies respectively. By the adoption of the solar aircraft, the arrangement of the two aircraft bodies is adopted and the energy storage battery is distributed in the wing, so that loads are evenly distributed, lifting weight balance and thrust and resistance balance are considered, energy balance needs to be further considered, it is guaranteed that the energy consumed for maintaining lifting force of the aircraft is equivalent to the energy obtained by the solar cells, and long-time high-altitude surveillance and monitoring can be achieved; and meanwhile, the solar aircraft of the structure has the good aerodynamic performance and is convenient to install.

Description

technical field [0001] The invention belongs to the field of overall design of aviation aircraft, and in particular relates to a solar-powered aircraft. Background technique [0002] The long-duration flight technology in near space (that is, the flight area that is higher than the flight area of ​​traditional aviation vehicles and lower than the flight area of ​​aerospace vehicles, approximately from 20 kilometers to 100 kilometers) has attracted much attention in recent years. Its unique flying height is especially suitable for ground persistent monitoring, communication relay and other tasks. [0003] Solar-powered aircraft can be designed to fly in near space, and can fly uninterruptedly in near space for several months or even years. Solar aircraft can complete a variety of tasks, and has broad application prospects in military and civilian fields, such as: it can be used as an uninterrupted relay communication platform, intelligence / surveillance / reconnaissance platfor...

Claims

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Application Information

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IPC IPC(8): B64C1/00B64D27/24B64C3/18
CPCB64C1/00B64C3/18B64C2001/0045B64D27/24Y02T50/60
Inventor 郭正侯中喜杨希祥王胤駸陈立立包月强闫秋飞张俊韬单上求
Owner NAT UNIV OF DEFENSE TECH
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