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Novel control method for high aspect-ratio flying wing solar-powered airplane

A technology of solar-powered aircraft and large aspect ratio, which is applied in aircraft control, aircraft assembly, aircraft parts, etc., can solve the problems of slow development of flying-wing layout aircraft, low efficiency of flying-wing layout rudder surfaces, and difficult operation, and achieve simplified operation Effect of system and structure weight, reduction of composition and total weight, simplification of control system

Active Publication Date: 2015-04-29
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

However, due to the low efficiency of the rudder surface of the flying wing layout and the relative difficulty of maneuvering, the development of flying wing layout aircraft has been slow.
The American Helios aircraft controlled the aircraft through sophisticated sensing elements and a complex automatic control system, but eventually failed to disintegrate in the air due to poor stability

Method used

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  • Novel control method for high aspect-ratio flying wing solar-powered airplane
  • Novel control method for high aspect-ratio flying wing solar-powered airplane
  • Novel control method for high aspect-ratio flying wing solar-powered airplane

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Embodiment Construction

[0025] Combine below figure 1 , 2 , 3 further illustrate the implementation of the vector thrust technology in the present invention:

[0026] The invention provides a novel control mode of a solar-powered aircraft with a large-aspect-ratio flying wing layout, which can simplify the control system and structural weight, increase the working load of the aircraft, and increase the reliability of aircraft control. like figure 1 As shown, the scheme is to install the vector rudder frame structure at the front end of the solar aircraft pod 4 of the conventional large aspect ratio flying wing layout solar aircraft (solar aircraft wing tip plate 1, solar aircraft outer section 2, solar aircraft middle section 3) , and then install the motor at the front end of the vector steering frame structure. The steering gear 5 controls the vector motor frame 8 to rotate along the rotating shaft 7 on the vertical plane through the connecting rod 6, thereby controlling the vertical deflection ...

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Abstract

The invention provides a novel control method for a high aspect-ratio flying wing solar-powered airplane. Through a steering engine, the tension line direction of a vector motor is controlled, the rotating speed of the motor is controlled and the deflection of a control surface is adjusted, so that the flying state of the airplane is controlled; and complicated control system and sensing system are simplified, so as to achieve the function of controlling the airplane. According to the control method, stable control on the high aspect-ratio flying wing solar-powered airplane can be finished; the control system can be simplified; the structure weight can be reduced; the working load of the airplane is improved; and the control reliability of the airplane is increased.

Description

1. Technical field: [0001] The invention provides a new control method for a solar-powered aircraft with a large-aspect-ratio flying wing layout, and belongs to the intersecting field of solar photovoltaic technology and unmanned aerial vehicle technology. 2. Background technology: [0002] With the increasing demand for long-endurance drones in today's world, the development and utilization of solar-powered aircraft in various fields has gradually been promoted. As a new layout method with light weight, low resistance, high aerodynamic efficiency and low life cycle cost, the flying wing layout has been widely used in solar aircraft. However, due to the low efficiency of the rudder surface of the flying wing layout and the relative difficulty in maneuvering, the development of flying wing layout aircraft has been slow. The American Helios aircraft controlled the aircraft through sophisticated sensing elements and a complex automatic control system, but ultimately failed to ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/00B64F5/00B64F5/10B64F5/60
CPCY02T50/40
Inventor 孙康文王若钦孙明旭孙谋
Owner BEIHANG UNIV
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