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A kind of power control system and aircraft

A power control system and controller technology, applied in the field of aircraft, can solve the problems of slow response speed, poor stability, high fuel consumption, etc., and achieve the effects of fast response speed, easy start-up, and reduced fuel consumption

Active Publication Date: 2020-07-24
深圳凌悦航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the embodiment of the present invention provides a power control system and an aircraft, aiming at solving the common problems of low fuel injection control accuracy, high fuel consumption, difficult start-up, and poor Adapt to plateau operating environment, poor stability, slow response speed and many other shortcomings

Method used

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  • A kind of power control system and aircraft
  • A kind of power control system and aircraft
  • A kind of power control system and aircraft

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Embodiment 1

[0039] like figure 1 As shown, this embodiment provides a power control system 100, which is applied to an aircraft.

[0040] In a specific application, the aircraft may specifically be aircraft, drones, airships, and other types of aircraft using EFI engines. For example, plant protection drones for unmanned plant protection operations.

[0041] like figure 1 As shown, in this embodiment, the aircraft 1000 includes a power control system 100, an air intake system 200, a fuel supply system 300, an ignition system 400, a battery, at least one propeller and at least one engine, and the power control system 100 includes a controller 110 and The engine temperature sensor 120, the intake air temperature sensor 130, the intake air pressure sensor 140, the throttle position sensor 150 and the Hall sensor 160 connected with the controller 110, the intake system 200 includes a throttle valve plate and at least one steering gear, the controller 110 is also connected with battery, ste...

Embodiment 2

[0056] like figure 2 As shown, in this embodiment, the power control system 100 further includes a fault alarm 170 connected to the controller 110 .

[0057] In a specific application, the failure alarm may specifically be a light alarm, an audio alarm or an audible and visual alarm. Wherein, the light alarm can specifically use LED lights, and the sound alarm can specifically use a buzzer or a combination of a voice chip and a horn.

[0058] In this embodiment, the controller is used to issue an alarm control signal when the temperature data, intake air temperature data, intake air pressure data, rotation data or position data of the engine are not received; The control signal is controlled by the controller to issue a corresponding fault alarm prompt.

[0059] In a specific application, if the engine temperature data, intake air temperature data, intake pressure data, rotation data or position data are not received, it means that the engine temperature sensor, intake air ...

Embodiment 3

[0064] like image 3 As shown, in this embodiment, the fuel supply system 300 includes a fuel tank 310, a weight 320, an oil filter 330, a booster oil pump 340, an oil pressure regulator 350, a fuel pressure gauge 360, an oil distributor 370 and at least one electric injection Nozzle 380.

[0065] In a specific application, the number of injectors is determined by the number of engines. image 3 exemplarily shows six oil injectors, and correspondingly, the oil distributor is also a six-point oil distributor, that is, the oil distributor includes one oil passage inlet and six oil passage outlets, which are used to input One way of fuel is divided into six outputs.

[0066] like image 3 As shown, the weight 320 is set in the oil tank 310, the oil tank 310, the oil filter 330 and the booster oil pump 340 are connected in sequence through oil pipes, the booster oil pump 340, the oil pressure regulator 350 and the oil separator 370 are connected through a three-way oil pipe, an...

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PUM

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Abstract

A power control system (100) and an aircraft, the power control system (100) comprising: a controller (110), an engine temperature sensor (120), an intake temperature sensor (130), an intake pressure sensor (140), a throttle position sensor (150), and a Hall sensor (160). Engine temperature data, intake temperature data, intake pressure data, engine rotation data, and position data of a throttle valve disc are detected to obtain the rotational speed of the engine and the rotational angle of a propeller. Each time the propeller is rotated to a specific angle, an ignition system (400) is controlled to start ignition. A fuel injection quantity of a fuel supply system (300) is controlled according to the rotational speed of the engine and the position data of the throttle valve disc, and is adjusted according to the engine temperature data, the intake temperature data, and the intake pressure data.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to a power control system and an aircraft. Background technique [0002] With the continuous development of science and technology, various types of aircraft, such as airplanes, unmanned aerial vehicles, and airships, are becoming more and more popular, which bring great convenience to people's daily transportation. Among them, small aircraft are particularly widely used in plant protection operations, aerial photography, rescue, and small cargo transportation. [0003] However, the existing small aircraft using fuel piston engines generally have many shortcomings such as low fuel injection control accuracy, high fuel consumption, difficult start-up, unsuitability to plateau operating environments, poor stability, and slow response speed. Contents of the invention [0004] In view of this, the embodiment of the present invention provides a power control system and an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/055F02C7/22F02C9/28F02C9/48H01T13/08H01T13/38
CPCF02C7/055F02C7/22F02C9/28F02C9/48H01T13/08H01T13/38
Inventor 赵自超闫小乐张锡环万耿栋骆艺特
Owner 深圳凌悦航空科技有限公司