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Parallel dual-engine coaxial unmanned helicopter

An unmanned helicopter and dual-engine technology, applied in the field of aircraft, can solve the problems of low reliability and weak carrying capacity, and achieve the effects of sufficient power, low vibration and high lift

Inactive Publication Date: 2014-07-09
JILIN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to propose a parallel twin-engine coaxial unmanned helicopter, which solves the problems of weak carrying capacity and low reliability in the prior art

Method used

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  • Parallel dual-engine coaxial unmanned helicopter
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  • Parallel dual-engine coaxial unmanned helicopter

Examples

Experimental program
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Embodiment Construction

[0036] Embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0037] See attached figure 1 The parallel twin-engine coaxial unmanned helicopter of the present invention comprises a rotor device I1, a rotor device II96, a pitch variable mechanism I3, a pitch variable mechanism II6, a speed reducer 34, a power coupling device 12, an engine I20, an engine II22, and a connecting frame 95 and landing gear 21;

[0038] The lower end of the connecting frame 95 is fixed with the landing gear 21, and the speed reducer 34 and the power coupling device 12 are fixed on the connecting frame 95 from top to bottom; the engine I20 and the engine II22 are located below the power coupling device 12 , fixed in parallel on the connecting frame 95, the output torques of the engine I20 and the engine II22 are respectively connected to the two input ends of the power coupling device 12 through the belt transmission mechanism, and the en...

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Abstract

The invention relates to a parallel dual-engine coaxial unmanned helicopter, belongs to the technical field of aircraft and aims to solve the problems that the prior aircraft is poor in carrying capacity and low in reliability. Two engines are symmetrically arranged and fixedly connected to the lower portion of a connection frame; a power coupler is fixedly connected to the middle of the connection frame; a reducer is fixedly connected to the upper portion of the connection frame; four belt drive sets are symmetrically arranged; each belt drive set is connected with an engine output shaft, a power coupler input shaft, a power coupler output shaft and a reducer input shaft on one side of the belt drive set; power of the two engines is decelerated by the belt drive sets, is collected and outputted by the power coupler, is transmitted to the reducer through the belt drive sets, and is transmitted to upper and lower rotors through two coaxial hollow spindles. Variable pitches of the upper and lower rotors are controlled through two independent pitch varying sets respectively. Power is centrally output after the power of the two engines is coupled; the parallel dual-engine coaxial unmanned helicopter is high in reliability, simple to control and reloadable.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to a parallel twin-engine coaxial unmanned helicopter. Background technique [0002] At present, due to its high hovering efficiency, compact structure, and symmetrical aerodynamic layout, the twin-blade coaxial unmanned helicopter has been widely used in civilian and military fields. Due to the coaxial rotation of the two rotors, the transmission structure is complex, the transmission structure is asymmetrical, and the vibration is relatively large. In the prior art, usually one engine drives two main rotors at the same time, or two engines drive two rotor shafts respectively. When one engine drives two main rotors at the same time, the power is insufficient, which limits the ability to carry heavy loads. It is difficult to offset the severe vibration generated by one engine at high altitude and long-term flight; when using two engines to drive the two rotor shafts re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/26B64C27/12
Inventor 陈延礼王春雪黄大年刘顺安于显利姚永明刘佳琳刘通
Owner JILIN UNIV
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