Tiltable hybrid rotor-wing aircraft

A hybrid power and rotary wing technology, applied in the field of aircraft, can solve the problems of limited take-off, unstable flight of multi-rotor aircraft, low safety factor, etc., and achieve the effects of energy saving, stable and reliable cruising, and low site requirements

Active Publication Date: 2015-12-23
南京多零无人机技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Existing aircraft mainly include two types of fixed-wing and multi-rotor, wherein the fixed-rotor aircraft mainly includes two large fixed-wings, which can take off vertically, land vertically and fly forward, and the flight is safe and

Method used

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Embodiment Construction

[0015] Such as figure 1 As shown, the present invention discloses a hybrid power tiltable wing aircraft, comprising a main body 1, an electric multi-rotor module, an aeroengine fixed-wing module, a flight control computer 4 and an empennage 5, wherein the flight control computer 4 is installed on the main engine On the body 1, the empennage 5 is installed at the tail of the main body 1. The electric multi-rotor module includes four hydraulic actuators 21 and four rotors. The four hydraulic actuators 21 are installed in groups of two at the front end of the main body 1 respectively. And the rear end, the rotor includes brushless motor 22, two-blade folding paddle 23, carbon fiber support 24 and support joint bearing 25, two-blade folding paddle 23 is installed on the brushless motor 22, and brushless motor 22 is installed on the end of carbon fiber support 24 The carbon fiber bracket 24 is symmetrically fixed on the left and right sides of the main body 1 through the bracket jo...

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Abstract

The invention relates to the field of aircrafts, in particular to a tiltable hybrid rotor-wing aircraft. According to the tiltable hybrid rotor-wing aircraft disclosed by the invention, an electric multi-rotor-wing module and an aero-engine fixed-wing module are combined. At the take-off stage, two movable tilting wings are in a vertical state, and the maximum lift force can be provided for the tiltable hybrid rotor-wing aircraft when the tiltable hybrid rotor-wing aircraft takes off; four rotor wings keeps the aircraft body stable, so that the tiltable hybrid rotor-wing aircraft stably rises; when the tiltable hybrid rotor-wing aircraft rises to needed cruising height, two movable tilting wings which are in the vertical state are changed to be in a horizontal state, the four rotor wings are folded, and the air resistance is reduced, so that the tiltable hybrid rotor-wing aircraft flies safely and stably, the tiltable hybrid rotor-wing aircraft has the advantages of a fixed-wing aircraft and the advantages of a multi-rotor-wing aircraft, namely the requirements for take-off and landing sites are low, and the tiltable hybrid rotor-wing aircraft is stable and reliable during cruising; the tiltable hybrid rotor-wing aircraft is powered by both oil and electricity, and a needed power mode is selected according to actual situations when the tiltable hybrid rotor-wing aircraft is used, so that the effect of saving energy sources is reached.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to a hybrid power tiltable-wing aircraft. Background technique [0002] Existing aircraft mainly include two types of fixed-wing and multi-rotor, wherein the fixed-rotor aircraft mainly includes two large fixed-wings, which can take off vertically, land vertically and fly forward, and the flight is safe and stable. Long runway to provide power for takeoff, takeoff is limited. Multi-rotor aircraft do not need a runway to provide power for take-off, and can stagnate in the air, but multi-rotor aircraft are unstable in flight and have a low safety factor. Contents of the invention [0003] The purpose of the present invention is to overcome the defects in the prior art, and provide a hybrid power tiltable-wing aircraft that is not limited by the field when taking off and landing, and is safe and stable when cruising. [0004] The technical solution for realizing the purpose of the present i...

Claims

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Application Information

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IPC IPC(8): B64C27/52B64C27/28B64D27/24B64D27/06
CPCY02T50/60
Inventor 姚龙江
Owner 南京多零无人机技术有限公司
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