solar drone

A solar-powered unmanned aerial vehicle and fuselage technology, which is applied to unmanned aerial vehicles, motor vehicles, wing shapes, etc., to achieve the effects of light weight, reduced structural weight, and high lift.

Active Publication Date: 2018-01-19
山东雪莱粮仓智能科技有限公司
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

However, there are still various problems in the development process of solar-powered drones. The main problems that need to be overcome are: try to make the solar cell area of ​​the drone as large as possible, the overall structure is the simplest, the aerodynamic efficiency is the best, and the proportion of the whole machine is the lowest. In addition, high-efficiency, high-power density, and high-reliability motor system technology also needs to be further researched

Method used

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Embodiment Construction

[0014] Exemplary embodiments will be described here in detail.

[0015] exist figure 1 , figure 2 , image 3 , Figure 4 , Figure 5Among them, the front wing 1 is used as the main lifting surface of the solar unmanned aerial vehicle. It adopts the form of a straight wing with a large aspect ratio. Its plane shape is long and its cross section is streamlined. Wing slots, left and right ailerons are installed in the left and right aileron slots, and the left and right ailerons slide in the left and right aileron slots, and can be stretched back and forth. The top view of the right and left ailerons is rectangular, The cross-section is arc-shaped, and the cross-section of the left and right aileron slots is also arc-shaped. The left and right ends of the left aileron 2 and the left and right ends of the right aileron 3 are provided with spring grooves, and the spring grooves are all provided with Spring 4, the left and right aileron motors 5 are arranged at the front end o...

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Abstract

A solar unmanned aerial vehicle adopts a single fuselage layout, and the front wing is set as a large-area elongated main lifting surface. The high-efficiency motor and battery are evenly distributed on the left and right ends of the front wing through the power pod, so that the front wing It becomes the main load surface, so that the load-bearing force in the air or on the ground is uniform. The rear wing is the auxiliary lift surface of the full-motion control surface. Both the front and rear lift surfaces provide positive lift, which improves the aerodynamic efficiency of the aerodynamic layout itself. All lift surfaces can The area of ​​paving the solar cells is maximized, the control surfaces of the left and right ailerons adopt telescopic control, and the control of it and the landing gear all adopt a pull-wire drive mechanism, and the control of the rear wing is controlled by a reduction motor. The crankshaft and the connecting rod drive the vertical control wing to realize the overall deflection control of the vertical control wing and the rear wing. The control structure of the front and rear wings is simple and effective; Provide high-efficiency, high-power-density, high-reliability light-duty motor power systems to effectively reduce the specific gravity of the machine.

Description

technical field [0001] The invention relates to the field of UAV design, in particular to a solar-powered UAV. Background technique [0002] Solar aircraft appeared in the 1970s with the reduction of the cost of solar cells. Using solar energy as the auxiliary energy source or even the main energy source for future aircraft is an important research goal with directional and cutting-edge human development. Since solar aircraft flight does not require Self-contained fuel creates conditions for long-endurance flight. As an unmanned aerial vehicle that can operate in the stratosphere and above, high-altitude long-endurance UAV can be used in many fields such as intelligence, surveillance and reconnaissance, communication relay, target indication, damage assessment, telecommunications and television services. However, there are still various problems in the development process of solar-powered drones. The main problems that need to be overcome are: try to make the solar cell are...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/10B64D27/24
CPCB64C3/10B64D27/24B64U10/25B64U50/19Y02T50/40
Inventor 朱幕松
Owner 山东雪莱粮仓智能科技有限公司
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