WO2019129084A1

WO2019129084A1 - Power control system and aircraft

Info

Publication number: WO2019129084A1
Application number: PCT/CN2018/123971
Authority: WO
Inventors: 赵自超; 闫小乐; 万耿栋; 张宏振; 张锡环
Original assignee: 深圳常锋信息技术有限公司
Priority date: 2017-12-27
Filing date: 2018-12-26
Publication date: 2019-07-04
Also published as: CN108252809A; CN108252809B

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

Power control system and aircraft

Technical field

The invention belongs to the technical field of aircrafts, and in particular relates to a power control system and an aircraft.

Background technique

With the continuous development of science and technology, various types of aircraft have become popular, such as airplanes, drones, and airships, which have greatly facilitated people's daily transportation. Among them, small aircraft are widely used in plant protection operations, aerial photography, rescue, small cargo transportation, etc.

technical problem

The existing small aircraft using a fuel piston engine generally has many shortcomings such as low fuel injection control precision, high fuel consumption, difficulty in starting, unsuitable for high altitude working environment, poor stability, and slow response speed.

Technical solution

In view of this, the embodiments of the present invention provide a power control system and an aircraft, which are intended to solve the problem that the existing small-sized aircrafts using the fuel piston engine generally have low fuel injection control precision, high fuel consumption, difficulty in starting, and no Adapt to the problems of high altitude working environment, poor stability, slow response and many other shortcomings.

A first aspect of an embodiment of the present invention provides a power control system applied to an aircraft, the aircraft including the power control system, an air intake system, a fuel supply system, an ignition system, a battery, at least one propeller, and at least one engine The power control system includes a controller and an engine temperature sensor, an intake air temperature sensor, an intake pressure sensor, a throttle position sensor, and at least one Hall sensor coupled to the controller, the air intake system including air filter a throttle assembly and a steering gear assembly; the throttle assembly includes a throttle body, a throttle valve plate, a throttle rotation shaft, two throttle rotary bearings, and a throttle limiter, the steering gear assembly Including the steering gear, the steering gear mount, the steering gear rotating pair and the steering ball ball tie rod;

The controller is further coupled to the battery, the steering gear, the fuel supply system, and the ignition system;

The engine temperature sensor is disposed in the engine for detecting temperature data of the engine and transmitting to the controller; the intake air temperature sensor is disposed in the air intake system for detecting intake air temperature data and Sending to the controller; the intake pressure sensor is disposed in the intake system for detecting intake pressure data and transmitting to the controller; the Hall sensor is disposed in the ignition system, Detecting rotation data of the engine and transmitting to the controller; the throttle position sensor is disposed in the air intake system, configured to detect position data of the throttle shaft and send the position data to the controller;

The controller processes the rotation data to obtain a rotation speed of the engine and a rotation angle of the propeller, and each time the propeller rotates to a specific angle, the ignition system is controlled to be ignited to make the engine work normally. The controller further controls the fuel injection amount of the fuel supply system according to the rotation speed and the position data, and according to the temperature data, the intake air temperature data, and the The intake pressure data adjusts the amount of fuel injection.

In one embodiment, the power control system further includes a fault alarm coupled to the controller;

When the controller does not receive the temperature data, the intake air temperature data, the intake air pressure data, the rotation data or the position data, issue an alarm control signal; the fault controller according to the The alarm control signal issues a corresponding fault alarm prompt.

In one embodiment, the intake system includes an air filter, a throttle assembly, and a steering assembly, the air filter including an air filter seat, a first filter layer, and a second filter layer, the throttle assembly The utility model comprises a throttle body, a throttle valve plate, the throttle rotating shaft, two throttle rotating bearings and a throttle limiter, wherein the steering gear assembly comprises the steering gear, the steering gear fixing seat and the steering gear rotating pair And the steering ball ball lever;

The first filter layer and the second filter layer are both disposed in the air filter seat in a detachable manner, the first filter layer is disposed outside the second filter layer, and the first filter layer is used for Filtering large particulate impurities in the air, the second filter layer is used to filter small particulate impurities in the air;

The intake passage of the throttle body is streamlined, and the two throttle rotary bearings constitute a rolling double bearing structure, and the throttle limiter radially limits the throttle shaft of the throttle;

The rotation plane of the steering gear is a parallelogram, and the rotation angle of the steering gear is the same as the rotation angle of the throttle rotation axis.

In one embodiment, the fuel supply system includes a fuel tank, a weight, an oil filter, a booster oil pump, a hydraulic pressure regulator, a fuel pressure gauge, an oil separator, and at least one electric fuel injector, and the weight is disposed at the In the fuel tank, the oil tank, the oil filter and the booster oil pump are sequentially connected by an oil pipe, and the booster oil pump, the oil pressure regulator and the oil separator are connected by a three-way oil pipe, and the electric oil is connected The fuel injector is connected to the oil separator through a nozzle holder of the oil outlet of the oil separator, and the oil pressure regulator is connected to the oil inlet of the oil tank through a fuel pipe, and the fuel pressure gauge is disposed at the oil pressure gauge a fuel pipe connected between the oil pressure regulator and the oil tank, the booster oil pump, the oil pressure regulator, the fuel pressure gauge and the electric fuel injector are all connected to the controller;

The weight sinks into the bottom of the oil tank, so that the oil in the oil tank is filtered by the oil filter and pressurized by the fuel boosting pump; the pressurized oil flows into the oil through the three-way oil pipe a pressure regulator and the oil separator; the oil pressure gauge outputs the oil to the oil tank when the fuel pressure gauge detects that the pressure value of the oil is greater than a preset pressure threshold; the fuel pressure When the table detects that the pressure value of the oil is less than or equal to a preset pressure threshold, the oil pressure regulator is closed; the controller adjusts the fuel injection amount by controlling the electric fuel injection nozzle to be energized or de-energized. When the electric fuel injector is energized, it is turned on and injected, and it is closed when it is not energized.

In one embodiment, the aircraft further includes an electric start management system including a power supply circuit board coupled to the engine and the battery;

The power supply circuit board acquires electrical energy of the battery to power the engine to control the engine to start.

In one embodiment, the aircraft further includes a power management system including a voltage regulator chip coupled to the controller, the ignition system, the battery, and the steering gear;

The voltage stabilizing chip acquires electric energy of the battery and adjusts a voltage of the electric energy to an operating voltage of the controller, the steering gear, and the ignition system, for the controller, the steering gear, and the The ignition system is powered.

In one embodiment, the ignition system includes an igniter and a spark plug;

The spark plug is composed of an insulator, a casing and an electrode, the insulator is an alumina ceramic having an alumina content of 95%; the casing is a steel piece, and the spark plug is fixed to the engine through the casing a cylinder head; the electrode includes a center electrode and a side electrode, a spark gap is disposed between the center electrode and the side electrode, the center electrode is connected to the igniter, and the igniter is connected to the controller The side electrode is grounded through the housing, and the controller controls the igniter to output a high voltage signal to the center electrode whenever the propeller rotates to a specific angle, and breaks the spark gap to generate an electric spark, igniting An oil-gas mixture in the engine cylinder.

In one embodiment, the controller processes the temperature data and the intake air temperature data to obtain a temperature of the engine and a temperature of air entering the intake system, and also to the intake pressure data Processing to obtain the pressure of the air entering the intake system;

The controller controls the fuel injection amount according to a temperature of the engine or a temperature of the air, the fuel injection amount being negatively correlated with a temperature of the engine or a temperature of the air; The pressure of the air controls the amount of fuel injected, which is positively correlated with the pressure of the air.

In one embodiment, the aircraft further includes a flight control system, a remote controller, and a ground station, the flight control system being coupled to the controller, the steering gear, the electric start management system, and the power management system ;

The flight control system and the remote controller or the ground station generate a corresponding control signal according to a control command sent by the remote controller or the ground station by wireless communication, to the controller, the steering gear And the electric start management system and the power management system perform control;

The control signal includes a pulse width modulation signal sent to the steering gear, and the steering gear rotates according to the pulse width modulation signal to adjust an opening degree of the throttle valve piece;

The controller further obtains opening degree data and intake air amount data of the throttle valve piece according to the pulse width modulation signal to adjust the injection quantity.

A second aspect of an embodiment of the present invention provides an aircraft comprising the power control system of any of the above.

Beneficial effect

The embodiment of the invention detects the engine speed and the propeller rotation angle according to the rotation data by detecting the engine temperature data, the intake air temperature data, the intake pressure data, the engine rotation data, the throttle valve position data, and the pulse width modulation signal. Whenever the propeller rotates to a certain angle, the ignition system is controlled to ignite to make the engine work normally; the fuel injection system is controlled according to the engine speed, the throttle valve position data or the pulse width modulation signal, and the engine is normal. During the working process, the fuel injection system is adjusted according to the engine temperature data, the intake air temperature data and the intake pressure data, so that the fuel injection system can be accurately controlled, thereby effectively reducing fuel consumption and making the engine easy to start. It can adapt to the high altitude working environment, good stability and fast response.

DRAWINGS

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the embodiments or the description of the prior art will be briefly described below. It is obvious that the drawings in the following description are only the present invention. For some embodiments, other drawings may be obtained from those of ordinary skill in the art in light of the inventive workability.

1 is a schematic structural diagram of a power control system according to Embodiment 1 of the present invention;

2 is a schematic structural diagram of a power control system according to Embodiment 2 of the present invention;

3 is a schematic structural view of a fuel supply system according to Embodiment 3 of the present invention;

4 is a schematic structural view of an aircraft provided in Embodiment 4 of the present invention.

Embodiments of the invention

In the following, the technical solutions in the embodiments of the present invention will be clearly described in conjunction with the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are the present invention. Some embodiments, not all of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts shall fall within the scope of the present invention.

The term "comprising" and variations of the invention in the specification and claims of the invention and the above description are intended to cover a non-exclusive inclusion. For example, a series of systems, products, or devices are not limited to the listed modules or units, but may alternatively include modules or units not listed, or, optionally, other modules inherent to those products or devices. Or unit. Moreover, the terms "first," "second," and "third," etc. are used to distinguish different objects and are not intended to describe a particular order.

Embodiment 1

As shown in Figure 1, this embodiment provides a power control system 100 that is applied to an aircraft.

In specific applications, the aircraft may specifically be various types of aircraft using an electric spray engine such as an airplane, a drone, an airship, and the like. For example, plant protection drones for unmanned plant protection operations.

As shown in FIG. 1, in the present 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 control. And an engine temperature sensor 120 coupled to the controller 110, an intake air temperature sensor 130, an intake pressure sensor 140, a throttle position sensor 150, and a Hall sensor 160, the intake system 200 including a throttle valve plate and at least one steering gear The controller 110 is also coupled to a battery, a steering gear, a fuel supply system 300, and an ignition system 400.

In a specific application, the power control system is specifically configured to control the power level of the aircraft by controlling the fuel injection amount of the fuel supply system.

In this embodiment, an engine temperature sensor is disposed in the engine for detecting temperature data of the engine and sent to the controller; the intake air temperature sensor is disposed in the intake system for detecting the intake air temperature data and transmitting the data to the controller; The air pressure sensor is disposed in the air intake system for detecting the intake pressure data and sent to the controller; the Hall sensor is disposed in the ignition system for detecting the rotation data of the engine and transmitting to the controller; the throttle position sensor is set in the A gas system for detecting position data of the throttle valve and transmitting it to the controller.

In specific applications, both the engine temperature sensor and the intake air temperature sensor can be selected according to actual needs, such as a thermocouple or a thermistor temperature sensor. Contact or non-contact temperature sensors are available depending on the type of contact. Among them, the temperature detection range of the engine temperature sensor is -50 ° C ~ 100 ° C, the temperature detection range of the intake air temperature sensor is -50 ° C ~ 60 ° C, can achieve the engine cold start by the controller in extremely cold environment.

In a specific application, the intake pressure sensor detects the absolute pressure of the air in the intake manifold behind the throttle valve of the intake system; the throttle position sensor is also referred to as a throttle opening sensor or a throttle switch for The opening of the throttle valve of the intake system is detected.

In this embodiment, the controller is configured to process the rotation data detected by the Hall sensor to obtain the rotation speed of the engine and the rotation angle of the propeller, and control the ignition system to ignite each time the propeller rotates to a specific angle to make the engine work normally; The controller is further configured to control the fuel injection amount of the fuel supply system based on the rotational speed and position data, and adjust the fuel injection amount according to the temperature data, the intake air temperature data, and the intake pressure data during normal engine operation.

In specific applications, the controller can be selected as ECU (Electronic) Control Unit, electronic control unit), you can also choose any processing device with data processing and control functions, for example, central processing unit (Central Processing Unit, CPU), can also be other general-purpose processors, digital signal processors (DSP), application specific integrated circuits (Application Specific Integrated Circuit (ASIC), Field-Programmable Gate Array (FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components, etc.

In a specific application, the specific angle to which the propeller is rotated is the angle at which the throttle valve opening is achieved to achieve the optimum air-fuel ratio (ie, the ratio of the mass of air to the fuel in the mixture). It can fully burn the oil and gas mixture in the engine cylinder, improve fuel efficiency and reduce fuel consumption.

In one embodiment, the controller is specifically configured to process the temperature data and the intake air temperature data to obtain the temperature of the engine and the temperature of the air entering the intake system, and also process the intake pressure data to obtain air entering the intake system. pressure;

The controller controls the fuel injection amount according to the temperature of the engine or the temperature of the air. The fuel injection amount is negatively correlated with the temperature of the engine or the temperature of the air. The controller also controls the fuel injection amount according to the pressure of the air. The fuel injection amount is positively correlated with the pressure of the air. .

In specific applications, in the case of low engine temperature or low air temperature, in order to make the engine work normally, it is necessary to appropriately increase the fuel injection amount so that the engine can adapt to the high cold environment; in the case of high engine temperature or high air temperature The fuel injection amount can be appropriately reduced to increase the air-fuel ratio, so that the oil-gas mixture can be fully burned to reduce fuel consumption, and at the same time, the engine can use a high-temperature environment; the magnitude of the air pressure is directly related to the oxygen content in the air, in the plateau, the mountain, etc. At high altitudes, the air pressure is low and the oxygen content is low. At this time, the fuel injection amount is reduced, the air-fuel ratio can be increased, and the oil-gas mixture can be burned more fully, so that the engine can adapt to the high altitude environment.

In the present embodiment, the number of the propeller, the engine, and the steering gear are the same, and the specific number is determined according to actual needs. In one embodiment, the number of propellers, engines, and steering gears is six, and the six propellers include three positive propellers of the same size and size and three counter propellers of the same size and size.

It should be understood that, in practical applications, the aircraft necessarily includes a main mechanical structure, a flight control system, and a conventional structure such as a connection interface and a signal transmission line for realizing signal transmission between the components, and only an exemplary introduction in this embodiment. The part related to this embodiment.

In the embodiment, by detecting the temperature data of the engine, the intake air temperature data, the intake pressure data, the rotation data of the engine, and the position data of the throttle valve piece, the rotation speed of the engine and the rotation angle of the propeller are obtained according to the rotation data, and whenever the propeller rotates to At a certain angle, the ignition system is controlled to start to make the engine work normally; the fuel injection system is controlled according to the engine speed and the position data of the throttle valve, and during the normal operation of the engine, according to the engine temperature data, the intake air The temperature data and the intake pressure data adjust the fuel injection amount of the fuel supply system, which can accurately control the fuel injection amount of the fuel supply system, thereby effectively reducing fuel consumption, making the engine easy to start, adapting to the altitude working environment, and having good stability. quick response.

Embodiment 2

As shown in FIG. 2, in the present embodiment, the power control system 100 further includes a fault alarm 170 connected to the controller 110.

In a specific application, the fault alarm may specifically be a light alarm, an audible alarm or an audible and visual alarm. Among them, the LED alarm light can be selected specifically for the light alarm, and the sound alarm can be selected by a buzzer or a combination of a voice chip and a speaker.

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

In the specific application, if the engine temperature data, the intake air temperature data, the intake pressure data, the rotation data or the position data are not received, the engine temperature sensor, the intake air temperature sensor, and the intake pressure for collecting the corresponding data are described. The sensor, the Hall sensor or the throttle position sensor has a fault. At this time, by issuing a corresponding alarm prompt by the control fault alarm, the relevant staff can be found and eliminated in time.

In a specific application, the fault alarm can issue different alarm prompts for different faults, so that the relevant staff can identify different fault types according to different alarm prompts. Correspondingly, when the fault alarm is a light alarm, it can include a plurality of LED lights of different colors, and the LED lights of each color are used to prompt a fault. It is also possible to realize different lighting states by controlling the LED lights to prompt different faults, which can effectively reduce the number of LED lights, for example, by controlling the LED lights to achieve flashing, slow flashing, constant lighting, etc. Prompt for different faults.

It should be understood that, in practical applications, when the fault alarm adopts a light alarm or an audible and visual alarm based on an LED lamp, it also includes a conventional structure such as a dimmer and an LED driver for controlling the LED lamp. The parts related to the present embodiment are only exemplarily described in the examples.

In this embodiment, when the temperature data, the intake air temperature data, the intake pressure data, the rotation data or the position data collected by each sensor are not received, the fault controller is controlled to issue a corresponding fault alarm prompt, which may cause a fault to the flight control system. The status is effectively prompted to facilitate troubleshooting in a timely manner.

Embodiment 3

As shown in FIG. 3, in the present embodiment, the fuel supply system 300 includes a fuel tank 310, a weight 320, an oil filter 330, a booster oil pump 340, a hydraulic regulator 350, a fuel pressure gauge 360, an oil separator 370, and at least An electric fuel injection nozzle 380.

In a particular application, the number of injectors is determined by the number of engines. In Fig. 3, six injectors are exemplarily shown. Correspondingly, the oil separator is also a one-six oil separator, that is, the oil separator includes one oil passage inlet and six oil passage outlets for The input fuel is divided into six outputs.

As shown in FIG. 3, the weight 320 is disposed in the oil tank 310. The oil tank 310, the oil filter 330 and the booster oil pump 340 are sequentially connected through the oil pipe, and the booster oil pump 340, the oil pressure regulator 350 and the oil separator 370 pass through the three-way oil pipe. The fuel injection nozzle 380 is connected to the oil separator 370 through a nozzle holder (not shown) located at the oil outlet of the oil separator 370. The oil pressure regulator 350 is connected to the oil tank 310 through the oil pipe, and the fuel pressure gauge 360 The oil pipe connected between the oil pressure regulator 350 and the oil tank 310 is connected to the controller 110 (not shown).

In this embodiment, the weight sinks into the bottom of the oil tank, so that the oil in the oil tank is filtered by the oil filter and pressurized by the fuel boosting pump; the pressurized oil flows into the oil pressure regulator and the oil separator through the three-way oil pipe; When the fuel pressure gauge detects that the pressure value of the oil is greater than the preset pressure threshold, the oil pressure regulator outputs oil to the fuel tank; when the fuel pressure gauge detects that the oil pressure value is less than or equal to the preset pressure threshold, the oil pressure regulator is closed; The controller adjusts the fuel injection amount by controlling the electric fuel injection nozzle to be energized or de-energized. When the electric fuel injection nozzle is energized, it is turned on and injected, and is closed when not energized.

In specific applications, the oil filter is used to filter impurities in the fuel to improve the purity of the fuel; the fuel booster pump is used to pressurize the oil filtered by the oil filter, and the specific boost amount can be set according to actual needs, for example It can increase the fuel pressure to 3 kg per square centimeter.

In a specific application, the three-way oil pipe is used to divert the supercharged fuel, a part flows into the oil pressure regulator to perform oil pressure regulation, and a part flows into the oil separator, and is output to the engine cylinder through the fuel injector for combustion.

In a specific application, the preset pressure threshold is equal to or greater than the fuel pressure value after the fuel booster is pressurized. For example, the preset pressure threshold may be set to 3 kg per square centimeter or 4 kg per square centimeter. The fuel pressure gauge detects the pressure value of the fuel. When the fuel pressure value is greater than the preset pressure threshold, the oil pressure regulator opens the pressure relief valve at one end connected to the fuel tank, and outputs the oil to the oil tank to release the oil pressure, so that the pressure of the fuel is lowered. When the fuel pressure value is less than or equal to the preset pressure threshold, the pressure relief valve is closed, and the fuel is output to the engine through the oil separator and the electric fuel injector.

In the specific application, the working state of the electric fuel injector is controlled by the controller, and the amount of fuel injection is adjusted by controlling the opening and closing frequency and duration of the electric fuel injector.

In a specific application, the electrospray nozzle can be realized by a normally closed electromagnetic valve, and the normally closed electromagnetic valve is opened when energized, and closed when not energized.

It should be understood that, in practical applications, the fuel supply system necessarily includes a conventional structure such as a fuel tank cap, and only the portions related to the present embodiment are exemplarily described in the present embodiment.

In this embodiment, by performing fuel pressurization, oil separation, pressure value detection, overpressure draining and fuel injection quantity control, accurate fuel injection can be realized, and the stable operation of the fuel supply system of the aircraft is ensured.

Embodiment 4

As shown in FIG. 4, in the present embodiment, the aircraft 1000 includes the power control system 100, the intake system 200, the fuel supply system 300, the ignition system 400, the battery 500, at least one steering gear 600, at least one of the above embodiments. A propeller, at least one engine 700, an electric start management system 800, a power management system 900, and a flight control system 000.

For the sake of convenience of illustration, only one engine and one steering gear are shown by way of example in FIG.

In this embodiment, the air intake system includes an air filter, a throttle assembly, and a steering gear assembly, the air filter includes an air filter seat, a first filter layer, and a second filter layer, and the throttle assembly includes a throttle body and a throttle. Door valve piece, throttle rotating shaft, two throttle rotating bearings and throttle limiter, the steering gear assembly includes a steering gear, a steering gear fixed seat, a steering gear rotating pair and a steering ball ball pull rod;

The first filter layer and the second filter layer are both detachably disposed on the empty filter holder, the first filter layer is disposed outside the second filter layer, and the first filter layer is used for filtering large particle impurities in the air, and the second filter layer Used to filter small particles of impurities in the air;

The turning plane of the steering gear is a parallelogram, and the turning angle of the steering gear is the same as the turning angle of the throttle valve.

In this embodiment, the air filter through the outer layer is the first filter layer and the inner layer is the second filter layer, which can effectively filter various large particles or small particle impurities in the air, thereby improving the purity of the air, thereby improving the oil and gas mixture. The first filter layer and the second filter layer can be fixed on the air filter seat by a cable tie, a elastic rope or the like to achieve detachable fixing, and the aging or filtering of the first filter layer or the second filter layer is facilitated. Replace when the performance is degraded.

In this embodiment, by adopting the streamlined design of the intake passage, the intake air can be smoothly flowed without gas rebound; by adopting the rolling double bearing structure, the rolling friction during the throttle rotation can be achieved, the friction force can be reduced, and the response of the steering gear can be improved. Speed and servo life. The axial position of the throttle shaft is realized by adopting the throttle position sensor, and the radial limit of the throttle shaft is realized by using the throttle stopper, thereby avoiding the displacement of the throttle shaft in the radial direction, thereby ensuring the displacement of the throttle shaft. The stability of the entire air intake system, as well as the positioning and limit of the throttle shaft, can ensure that the throttle shaft does not appear stuck and stuck.

In the embodiment, by using the steering plane of the parallelogram structure, the rotation angle of the steering gear is consistent with the rotation angle of the throttle shaft, the nonlinearity of the intake system is reduced, and the throttle valve is easy to be used. The opening is controlled. In the actual installation process, the steering gear adopts the upper inclined mode, which is parallel with the rotation plane of the propeller, so that the wind generated when the propeller rotates can better cool the steering gear, realize the heat dissipation to the steering gear, and improve the service life of the steering gear.

In this embodiment, the ignition system includes an igniter and a spark plug; the spark plug is composed of an insulator, a casing and an electrode, the insulator is an alumina ceramic having an alumina content of 95%; the casing is a steel member, and the spark plug is fixed to the casing through the casing The cylinder head of the engine; the electrode includes a center electrode and a side electrode, a spark gap is disposed between the center electrode and the side electrode, the center electrode is connected to the igniter, the igniter is connected to the controller, and the side electrode is grounded through the casing, whenever the propeller is rotated to a specific angle The controller controls the igniter to output a high voltage signal to the center electrode, breaks the spark gap to generate an electric spark, and ignites the oil and gas mixture in the engine cylinder.

In the specific application, the igniter can be specifically selected as a capacitor discharge igniter. The controller comprehensively controls the specific ignition timing of the igniter according to various parameters such as the engine speed, the rotation angle of the propeller, the engine temperature, the intake air temperature, the intake pressure and the battery voltage, so that the ignition timing and the ignition angle of the igniter are met. The best ignition conditions ensure a successful ignition.

In this embodiment, the electric start management system includes a power supply circuit board connected to the engine and the battery; the power supply circuit board obtains power of the battery to supply power to the engine to control engine start.

In this embodiment, the engine is powered by directly taking power from the battery, ensuring that the engine has a sufficiently large starting current so that the engine can be started quickly.

In this embodiment, the power management system includes a voltage regulator chip connected to the controller, the ignition system, the battery, and the steering gear; the voltage regulator chip acquires the power of the battery and adjusts the voltage of the power to operate as a controller, a steering gear, and an ignition system. Voltage, powering the controller, steering gear and ignition system.

In this embodiment, the controller, the steering gear and the ignition system are powered by the voltage regulation of the battery, which can provide a stable supply voltage for the controller, the steering gear and the ignition system, avoid the loss of the battery power, and improve the power utilization.

In this embodiment, the flight control system is connected to the controller, the steering gear, the electric start management system, and the power management system;

The flight control system and the remote control or the ground station generate corresponding control signals according to the control commands sent by the remote controller or the ground station through wireless communication, and control the controller, the steering gear, the electric start management system and the power management system;

The control signal includes a pulse width modulation signal sent to the steering gear, and the steering gear rotates according to the pulse width modulation signal to adjust the opening degree of the throttle valve piece;

The controller also obtains opening degree data and intake air amount data of the throttle valve piece according to the pulse width modulation signal to adjust the fuel injection amount.

In a specific application, the flight control system may be a central processing unit (CPU), or may be other general purpose processors, digital signal processors. (Digital Signal Processor, DSP), Application Specific Integrated Circuit (ASIC), off-the-shelf programmable gate array (Field-Programmable Gate Array, FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components, etc. The general purpose processor may be a microprocessor or the processor or any conventional processor or the like. The flight control system can be built-in or external storage medium for storing data or algorithm programs. The storage medium can be hard disk, memory, plug-in hard disk, smart memory card (Smart Media Card, SMC), Secure Digital (Secure Digital, SD) card, flash card (Flash Card) and so on.

In a specific application, the remote controller refers to a remote controller that is held by a user and can control the flight state of a small aircraft such as a drone. The remote controller is provided with a rocker, a handle, a communication module, and the like.

In a specific application, the ground station may be any smart terminal having human-computer interaction and wireless communication function, such as a mobile phone, a tablet computer, a personal digital assistant, a PC client, and the like. The ground station can simultaneously realize the processing of the surveying and mapping data of the working plot and the control of the flight state of the drone. When the surveying and mapping data processing function is realized, the corresponding surveying and mapping application is run on the ground station; the flight state control function of the drone is realized. When the drone flight state control application is running on the ground station.

It will be apparent to those skilled in the art that, for convenience and brevity of description, only the division of each functional unit and module described above is exemplified. In practical applications, the above functions may be assigned to different functional units as needed. The module is completed by dividing the internal structure of the device into different functional units or modules to perform all or part of the functions described above. Each functional unit and module in the embodiment may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit, and the integrated unit may be hardware. Formal implementation can also be implemented in the form of software functional units. In addition, the specific names of the respective functional units and modules are only for convenience of distinguishing from each other, and are not intended to limit the scope of protection of the present invention. For the specific working process of the unit and the module in the foregoing system, reference may be made to the corresponding process in the foregoing method embodiment, and details are not described herein again.

In the above embodiments, the descriptions of the various embodiments are different, and the parts that are not detailed or described in a certain embodiment can be referred to the related descriptions of other embodiments.

The units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, may be located in one place, or may be distributed to multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of the embodiment.

In addition, each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above integrated unit can be implemented in the form of hardware or in the form of a software functional unit.

The embodiments described above are only for explaining the technical solutions of the present invention, and are not intended to be limiting; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art will understand that The technical solutions described in the examples are modified, or some of the technical features are equivalently replaced; and the modifications or substitutions do not deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in Within the scope of protection of the present invention.

Claims

A power control system is provided for use in an aircraft, the aircraft including the power control system, an intake system, a fuel supply system, an ignition system, a battery, at least one propeller, and at least one engine, the power control system A controller and an engine temperature sensor, an intake air temperature sensor, an intake pressure sensor, a throttle position sensor, and at least one Hall sensor coupled to the controller, the air intake system including an air filter, a throttle assembly, and a steering gear assembly; the throttle assembly includes a throttle body, a throttle valve plate, a throttle rotating shaft, two throttle rotating bearings, and a throttle limiter, the steering gear assembly including a steering gear and a steering gear Fixed seat, steering gear rotating pair and steering ball ball tie rod;

The controller is further coupled to the battery, the steering gear, the fuel supply system, and the ignition system;

The engine temperature sensor is disposed in the engine for detecting temperature data of the engine and transmitting to the controller; the intake air temperature sensor is disposed in the air intake system for detecting intake air temperature data and Sending to the controller; the intake pressure sensor is disposed in the intake system for detecting intake pressure data and transmitting to the controller; the Hall sensor is disposed in the ignition system, Detecting rotation data of the engine and transmitting to the controller; the throttle position sensor is disposed in the air intake system, configured to detect position data of the throttle shaft and send the position data to the controller;

The controller processes the rotation data to obtain a rotation speed of the engine and a rotation angle of the propeller, and each time the propeller rotates to a specific angle, the ignition system is controlled to be ignited to make the engine work normally. The controller further controls the fuel injection amount of the fuel supply system according to the rotation speed and the position data, and according to the temperature data, the intake air temperature data, and the The intake pressure data adjusts the amount of fuel injection.
The power control system of claim 1 wherein said power control system further comprises a fault alarm coupled to said controller;

When the controller does not receive the temperature data, the intake air temperature data, the intake air pressure data, the rotation data or the position data, issue an alarm control signal; the fault controller according to the The alarm control signal issues a corresponding fault alarm prompt.
The power control system of claim 1 wherein said intake system comprises an air filter, a throttle assembly and a steering assembly, said air filter comprising an air filter seat, a first filter layer and a second a filter assembly, the throttle assembly including a throttle body, a throttle valve plate, the throttle rotation shaft, two throttle rotation bearings, and a throttle limiter, the steering gear assembly including the steering gear, a steering gear mount, a steering gear turner and a steering ball ball tie rod;

The first filter layer and the second filter layer are both disposed in the air filter seat in a detachable manner, the first filter layer is disposed outside the second filter layer, and the first filter layer is used for Filtering large particulate impurities in the air, the second filter layer is used to filter small particulate impurities in the air;

The intake passage of the throttle body is streamlined, and the two throttle rotary bearings constitute a rolling double bearing structure, and the throttle limiter radially limits the throttle shaft of the throttle;

The rotation plane of the steering gear is a parallelogram, and the rotation angle of the steering gear is the same as the rotation angle of the throttle rotation axis.
The power control system according to claim 1, wherein said fuel supply system comprises a fuel tank, a weight, an oil filter, a booster oil pump, a hydraulic regulator, a fuel pressure gauge, an oil separator, and at least one electrospray a fuel nozzle, the weight is disposed in the oil tank, the oil tank, the oil filter and the booster oil pump are sequentially connected by an oil pipe, the booster oil pump, the oil pressure regulator and the oil separator Connected to the oil separator through a three-way oil pipe connection, the oil injection nozzle is connected to the oil separator of the oil outlet of the oil separator, and the oil pressure regulator is connected to the oil inlet of the oil tank through a oil pipe The fuel pressure gauge is disposed on a fuel pipe connected between the oil pressure regulator and the oil tank, and the booster oil pump, the oil pressure regulator, the fuel pressure gauge, and the electric fuel injector are both The controller is connected;

The weight sinks into the bottom of the oil tank, so that the oil in the oil tank is filtered by the oil filter and pressurized by the fuel boosting pump; the pressurized oil flows into the oil through the three-way oil pipe a pressure regulator and the oil separator; the oil pressure gauge outputs the oil to the oil tank when the fuel pressure gauge detects that the pressure value of the oil is greater than a preset pressure threshold; the fuel pressure When the table detects that the pressure value of the oil is less than or equal to a preset pressure threshold, the oil pressure regulator is closed; the controller adjusts the fuel injection amount by controlling the electric fuel injection nozzle to be energized or de-energized. When the electric fuel injector is energized, it is turned on and injected, and it is closed when it is not energized.
The power control system of claim 1 wherein said aircraft further comprises an electric start management system, said electric start management system comprising a power supply circuit board coupled to said engine and said battery;

The power supply circuit board acquires electrical energy of the battery to power the engine to control the engine to start.
The power control system of claim 1 wherein said aircraft further comprises a power management system, said power management system comprising a connection to said controller, said ignition system, said battery and said steering gear Voltage regulator chip

The voltage stabilizing chip acquires electric energy of the battery and adjusts a voltage of the electric energy to an operating voltage of the controller, the steering gear, and the ignition system, for the controller, the steering gear, and the The ignition system is powered.
The power control system of claim 1 wherein said ignition system comprises an igniter and a spark plug;

The spark plug is composed of an insulator, a casing and an electrode, the insulator is an alumina ceramic having an alumina content of 95%; the casing is a steel piece, and the spark plug is fixed to the engine through the casing a cylinder head; the electrode includes a center electrode and a side electrode, a spark gap is disposed between the center electrode and the side electrode, the center electrode is connected to the igniter, and the igniter is connected to the controller The side electrode is grounded through the housing, and the controller controls the igniter to output a high voltage signal to the center electrode whenever the propeller rotates to a specific angle, and breaks the spark gap to generate an electric spark, igniting An oil-gas mixture in the engine cylinder.
A power control system according to claim 1 wherein said controller processes said temperature data and said intake air temperature data to obtain a temperature of said engine and a temperature of air entering said intake system And processing the intake pressure data to obtain a pressure of air entering the intake system;

The controller controls the fuel injection amount according to a temperature of the engine or a temperature of the air, the fuel injection amount being negatively correlated with a temperature of the engine or a temperature of the air; The pressure of the air controls the amount of fuel injected, which is positively correlated with the pressure of the air.
A power control system according to claim 1 wherein said aircraft further comprises a flight control system, a remote control and a ground station, said flight control system and said controller, said steering gear, said electric start a management system and the power management system are connected;

The flight control system and the remote controller or the ground station generate a corresponding control signal according to a control command sent by the remote controller or the ground station by wireless communication, to the controller, the steering gear And the electric start management system and the power management system perform control;

The control signal includes a pulse width modulation signal sent to the steering gear, and the steering gear rotates according to the pulse width modulation signal to adjust an opening degree of the throttle valve piece;

The controller further obtains opening degree data and intake air amount data of the throttle valve piece according to the pulse width modulation signal to adjust the injection quantity.
An aircraft characterized by comprising the power control system of any one of claims 1 to 9.