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Hybrid power aircraft

A technology of hybrid power and aircraft, applied in the direction of power plant type, etc., to achieve the effect of reducing cruise resistance, reducing demand, and improving aerodynamic efficiency

Active Publication Date: 2021-03-09
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved by the present invention is to overcome the above-mentioned defects in the prior art, and to propose a hybrid aircraft with a new design idea, which uses the electric motor to assist the mode, reduces the demand for engine thrust when the aircraft takes off and goes around, and passes Improve the aerodynamic efficiency of the aircraft and reduce the demand for engine thrust during cruising, thereby reducing the aircraft's requirements for fuel engine indicators and paying too much weight for the fuel engine and its supporting systems and structures

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Embodiment Construction

[0050] The preferred embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings. The following descriptions are exemplary and not limiting to the present invention. Any other similar situations also fall within the protection scope of the present invention. In addition, in the following description, the same or similar reference numerals are attached to the same or similar components, and repeated descriptions are omitted.

[0051] First, the power system of the hybrid aircraft will be described.

[0052] Such as figure 1 As shown, the power system of the hybrid aircraft includes: two fuel engines 1a, 1b using fuel oil as the power source; two electric motors 4a, 4b using electric power as the power source; A battery 5 for power supply; a motor controller 6 for controlling the motors 4a, 4b, specifically controlling their start and stop, output power, etc.; a flight control system 3 for controlling the flight o...

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Abstract

The invention discloses a hybrid power aircraft which comprises an aircraft fuselage; high aerodynamic efficiency wings; a high lift device; a fuel engine; a motor; a battery; a motor controller; anda flight control system which is adopted to control the motor controller, so that when the high lift device is unfolded, the motor is in a preset state; when the aircraft takes off or flies back, thefuel engine is started, and the motor is started to output auxiliary power required by the aircraft taking off or flies back. And after the high-lift device is folded, the motor is shut down and the aircraft is only driven by the fuel engine. According to the hybrid power aircraft, a brand-new design thought is provided, the requirement for engine thrust when the aircraft takes off and flies backis lowered in a motor assisting mode, meanwhile, the hybrid power aircraft can be matched with a small-thrust fuel engine during cruising, and therefore the index requirement of the aircraft for the fuel engine can be lowered.

Description

technical field [0001] The invention relates to a hybrid aircraft using a fuel engine and an electric motor. Background technique [0002] The mainstream aircraft in service are all driven by fuel engines, such as turbofan engines with high bypass ratio, and their comprehensive efficiency has gradually reached the peak. Moreover, traditional fuel-powered aircraft have a greater demand for engine power during take-off and go-around stages, but much less power demand during cruising. If the traditional fuel-fuel power is used, the requirements for the fuel-fueled engine are relatively high, not only requiring the fuel-fueled engine to provide sufficient thrust during the take-off and go-around phase, but also requiring lower fuel consumption during the cruising phase. [0003] In this regard, with the optimization of the energy structure, a conceptual scheme using electric motors as power has appeared in recent years, and has been applied to small aircraft. The propulsion po...

Claims

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Application Information

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IPC IPC(8): B64D27/02
CPCB64D27/02B64D27/026Y02T50/60
Inventor 吴大卫陈名乾钟园王帮亭陈震宇金晶
Owner COMAC
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