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Hybrid twin-engine coaxial twin-propeller helicopter

A hybrid and twin-engine technology, applied in the direction of the transmission device driven by multiple power devices, the type of power plant, etc., can solve the problems of poor stability, low transmission efficiency, low energy recovery rate and reuse rate, etc. Achieve the effects of good stability, high transmission efficiency and energy saving effect

Inactive Publication Date: 2015-10-21
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 hybrid power twin-engine coaxial twin-screw helicopter, which solves the problems of poor stability, low transmission efficiency, and generally low energy recovery rate and reutilization rate of the coaxial twin-screw helicopter in the prior art

Method used

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  • Hybrid twin-engine coaxial twin-propeller helicopter

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Embodiment Construction

[0013] Embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0014] See attached figure 1 , the hybrid twin-engine coaxial twin-screw helicopter of the present invention includes a deceleration system, a power system, a control system and an auxiliary system;

[0015] The power system includes clutch I10, engine II11, torque coupler II12, clutch II13, motor or generator II14, rectifier or inverter II15, supercapacitor pack 20, rectifier or inverter I29, clutch III30, electric motor or generator Engine I31, clutch IV32, engine I33 and torque coupler I35; torque coupler I35 is connected with electric motor or generator I31 and engine I33 respectively through clutch III30 and clutch IV32, and torque coupler II12 is respectively connected with engine II11 through clutch I10 and clutch II13 , motor or generator II14 connected, motor or generator II14, motor or generator I31 are respectively connected to the supercapac...

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Abstract

The invention belongs to the technical field of hybrid power, relates to a hybrid-power twin-engine type coaxial-double-propeller helicopter and aims to solve the problems that an existing coaxial-double-propeller helicopter in the prior art is poor in transmission system stability, low transmission efficiency, low energy recovery rate and low universal recycling rate. A torque coupler I is connected with an electric motor / engine I and an engine I via a clutch III and a clutch IV, a torque coupler II is connected with an engine II and an electric motor / engine II, the electric motor / engine II and the electric motor / engine I are connected with a super capacitor set, the torque coupler I and the torque coupler II in parallel are linked to a differential box via a transmission shaft IV and a transmission shaft III, the differential box is connected with a reduction gearbox I and a reduction gearbox II via a transmission shaft V and a transmission shaft II, the reduction gearbox I and the reduction gearbox II in parallel are linked onto a bevel gearbox, and the bevel gearbox drives an upper propeller and a lower propeller to rotate via a spindle I and a spindle II.

Description

technical field [0001] The invention belongs to the technical field of hybrid power, and in particular relates to a hybrid power twin-engine coaxial twin-blade helicopter. Background technique [0002] The traditional coaxial twin-propeller helicopter transmission mode is that a single engine is directly connected to the blades through a reduction box and a bevel box, and the controller controls various actuators to work. The power source of the system is only one engine. When flying in one rotation cycle, it will be affected by the flight environment and operating conditions, and its load will often change, which will affect the stability of the engine output speed, especially in the state of take-off and landing. The load changes more, the transmission efficiency is low, and the stability is poor. Under normal circumstances, the operator will adjust the engine throttle and adjust the pitch of the blades to change the power output by the engine, which is not in the best fu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/02B64D35/08
Inventor 陈延礼孟凡华黄大年刘顺安于显利姚永明刘佳琳刘通
Owner JILIN UNIV
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