Hybrid power long-endurance multi-shaft air vehicle

A technology of multi-axis aircraft and hybrid power, which is applied in the direction of aircraft, motor vehicles, rotorcraft, etc., can solve the problems of multi-axis aircraft that are difficult to fly and have a large loss of efficiency, and achieve the effect of improving endurance and increasing flight time

Active Publication Date: 2015-12-09
郝建新
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method can ensure the simplicity of the structure, but the energy is converted from chemical energy to electrical energy, and the efficiency loss is relatively large.
[0005] Known patent No. is CN204210733U " a kind of hybrid four-rotor aircraft ", adopts fuel engine to provide the main lift of

Method used

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  • Hybrid power long-endurance multi-shaft air vehicle
  • Hybrid power long-endurance multi-shaft air vehicle
  • Hybrid power long-endurance multi-shaft air vehicle

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Embodiment Construction

[0024] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0025] Depend on Figure 1-3 It can be seen from the illustrated embodiment that this embodiment includes a disc-shaped equipment installation platform 1, on which a fuel engine 2 is fixed, and the fuel engine 2 adopts a gasoline engine (model: ZENEP20 or OS38200GT-22), and the gasoline engine The rotating output shaft is provided with a flight rotor 3 for generating lift, and four attitude adjustment rotor installation arms 4 are arranged radially around the equipment installation platform 1. The four attitude adjustment rotor installation arms 4 have the same structure and are all curved upwards. The four attitude adjustment rotors 9 are slightly higher than the flight rotor 3; the anti-twist adjustment steering gear controlled by the aircraft attitude control system 5 (model: iFLY-F2A or CUAVARDUPILOTMEGA2.6) is fixed at the end of...

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Abstract

The invention discloses a hybrid power long-endurance multi-shaft air vehicle. The hybrid power long-endurance multi-shaft air vehicle comprises a device installing platform. A fuel engine is fixed to the device installing platform, and a flight rotor wing used for producing lift force is arranged on a rotating outputting shaft of the fuel engine. A plurality of posture adjusting rotor-wing installing arms are arranged on the periphery of the device installing platform in a radial mode, the tail ends of the posture adjusting rotor-wing installing arms are fixedly controlled by reverse torsion adjusting steering engines of an air vehicle posture control system, direct current motors are vertically fixed to angle adjusting motor fixing supports of the reverse torsion adjusting steering engines, and posture adjusting rotor wings are arranged on rotating outputting shafts of the direct current motors. Air vehicle supporting foot frames are arranged below the device installing platform. The hybrid power long-endurance multi-shaft air vehicle has the advantages that the structure is reasonable, the weight is small, and cruising capacity is high.

Description

technical field [0001] The invention relates to a hybrid long-endurance multi-axis aircraft. Background technique [0002] At present, most multi-axis aircraft use lithium polymer batteries as the power source. Because their energy density is much lower than that of biofuels, the battery life is basically within 30 minutes, and the batteries are heavy, which limits the load of the aircraft. And in actual use, the discharge current of the purely electric multi-axis aircraft is large, resulting in a limited number of charging cycles for the lithium polymer battery, resulting in dozens of lags that must be replaced, resulting in high usage costs. [0003] Purely fuel-powered multicopters are also theoretically possible, and some related researches are in progress, but this type of aircraft will lose the biggest advantage of existing multicopters, that is, simple structure. Its complex variable collective pitch structure will make the payload, reliability, size, and cost uncont...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64D27/02
Inventor 郝建新
Owner 郝建新
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