Gasoline-electric hybrid power multi-rotor aircraft and flight control method thereof

A multi-rotor aircraft and oil-electric hybrid technology, applied in the aviation field, can solve the problems of increasing the difficulty of fuselage load arrangement, reducing the efficiency of the main lift propeller, and increasing the structural complexity of the aircraft, so as to achieve the improvement of endurance time and load capacity, and reliability Guaranteed performance and improved practicability

Active Publication Date: 2017-07-07
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the schemes published in the above four patents, the propellers driven by the piston engine are arranged in the center of the fuselage. On the one hand, it increases the difficulty of the load arrangement of the fuselage; Thereby reducing the effi

Method used

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  • Gasoline-electric hybrid power multi-rotor aircraft and flight control method thereof
  • Gasoline-electric hybrid power multi-rotor aircraft and flight control method thereof
  • Gasoline-electric hybrid power multi-rotor aircraft and flight control method thereof

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Embodiment Construction

[0031] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0032] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Orientation indicated by rear, left, right, vertical, horizontal, top, bottom, inside, outside, clockwise, counterclockwise, etc. The positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than ...

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Abstract

The invention provides a gasoline-electric hybrid power multi-rotor aircraft and a flight control method thereof. The aircraft comprises a fuselage, a main power system and an auxiliary control system. The main power system comprises a fuel engine, a transmission system and main elevating propellers. The two main elevating propellers are symmetrically arranged on the two sides of the fuselage. The fuel engine drives the main elevating propellers to rotate through the transmission system. The two main elevating propellers are consistent in rotation speed and opposite in rotation direction. The auxiliary control system comprises a plurality of auxiliary propellers driven by a motor. The multiple auxiliary propellers are connected with the fuselage through supporting rods and symmetrically distributed on the two sides of the fuselage. The auxiliary propellers and the driving motor obliquely rotate by set angles in the fuselage direction around the axes of the installed supporting rods. According to the gasoline-electric hybrid power multi-rotor aircraft provided by the invention, only a set of simple transmission mechanism is added, a steering engine control mechanism is omitted, the structure complexity is increased less, the reliability is still ensured to a certain extent, the endurance time is greatly prolonged, the loading capacity is greatly improved, and the practicability of the multi-rotor aircraft is greatly improved.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to an oil-electric hybrid multi-rotor aircraft and a flight control method thereof. Background technique [0002] The traditional multi-rotor aircraft uses multiple motor-driven propellers to provide the pulling force required for flight, and with the support of the flight control system, it can fly forward, backward, left, and right by tilting the attitude of the aircraft. Because there is no transmission and mechanical control mechanism of a traditional helicopter, it has a simple structure and easy handling. Simple, high reliability and other advantages. But at the same time, because the motor is used as the power source and the energy density of the current battery is low, the cruising time of the electric multi-rotor aircraft is very short, generally no more than half an hour, which greatly limits the application of the electric multi-rotor aircraft. [0003] Fuel-powered mu...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64C27/14B64C27/59B64D27/08B64D27/24
CPCB64C27/08B64C27/14B64C27/59B64D27/08B64D27/24Y02T50/60
Inventor 邓阳平田力高正红
Owner NORTHWESTERN POLYTECHNICAL UNIV
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