CN111446894A - Unmanned aerial vehicle starting and power generation integrated control system and control method thereof - Google Patents
Unmanned aerial vehicle starting and power generation integrated control system and control method thereof Download PDFInfo
- Publication number
- CN111446894A CN111446894A CN202010175898.1A CN202010175898A CN111446894A CN 111446894 A CN111446894 A CN 111446894A CN 202010175898 A CN202010175898 A CN 202010175898A CN 111446894 A CN111446894 A CN 111446894A
- Authority
- CN
- China
- Prior art keywords
- starting
- power
- power generation
- brushless motor
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/08—Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
- H02K11/30—Structural association with control circuits or drive circuits
- H02K11/33—Drive circuits, e.g. power electronics
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K29/00—Motors or generators having non-mechanical commutating devices, e.g. discharge tubes or semiconductor devices
- H02K29/06—Motors or generators having non-mechanical commutating devices, e.g. discharge tubes or semiconductor devices with position sensing devices
- H02K29/08—Motors or generators having non-mechanical commutating devices, e.g. discharge tubes or semiconductor devices with position sensing devices using magnetic effect devices, e.g. Hall-plates, magneto-resistors
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/20—Structural association with auxiliary dynamo-electric machines, e.g. with electric starter motors or exciters
Abstract
The invention belongs to a control system and a method of an unmanned aerial vehicle, and aims at the problems that the starting and the power generation of the engine of the existing unmanned aerial vehicle are composed of two independent devices and a control system thereof, the weight of the body of the unmanned aerial vehicle is increased, and the complexity and the instability of an avionic system in the starting and the power generation processes are also increased; the direct-current brushless motor is coaxially connected with the output end of the engine, when the direct-current brushless motor is started, the starting battery supplies power for the starting and power generation integrated circuit unit, the engine is driven to rotate to the starting rotating speed through the direct-current brushless motor, when the direct-current brushless motor generates power, the starting and power generation integrated circuit unit stops supplying power, the direct-current brushless motor outputs three-phase alternating current to the starting and power generation integrated circuit unit, and the three-phase alternating current is rectified and filtered to provide electric energy for airborne equipment and; the control method is based on the control system to complete starting and power generation.
Description
Technical Field
The invention belongs to an unmanned aerial vehicle control system and method, and particularly relates to an unmanned aerial vehicle starting and power generation integrated control system and a control method thereof.
Background
In traditional unmanned aerial vehicle field, the start-up of aeroengine for the unmanned aerial vehicle is accomplished with the help of starter motor and starting drive, and starting drive will no longer be used after the engine starts, carries out work jointly by generator motor and power generation facility to satisfy aircraft continuation of the journey requirement.
The engine is started by using a starting motor connected with the engine mechanically or in a transmission manner to drive the engine to ignite under high-speed motion. After the engine starts, can turn into mechanical energy with the chemical energy of fuel such as petrol, produce the power that unmanned aerial vehicle flies. The commonly used starting motors are various in types, and the starting devices matched with the commonly used starting motors are different.
The engine is driven by the engine to convert the mechanical energy of the motor into electric energy. Similarly, different power generation motors are adopted, and power generation devices of the power generation motors also have differences.
In the starting and power generation system of the engine of the unmanned aerial vehicle, starting and power generation are two sets of independent systems, and for the unmanned aerial vehicle which is sensitive to weight and has high requirements on the constituent structure of the avionic system, the starting and power generation scheme not only increases the weight of the unmanned aerial vehicle, but also increases the complexity of the avionic system structure and the instability of functions.
Disclosure of Invention
The invention provides an unmanned aerial vehicle starting and power generation integrated control system and a control method thereof. The main aim at solves the problem that the starting and the power generation of the engine of the unmanned aerial vehicle in the prior art rely on two sets of independent systems, thereby not only increasing the self weight of the unmanned aerial vehicle, but also increasing the structural complexity and the functional instability of the avionic system.
In order to achieve the purpose, the invention provides the following technical scheme:
the utility model provides an unmanned aerial vehicle starts electricity generation integral type control system which characterized in that: the system comprises an engine, a direct current brushless motor, a starting and power generation integrated circuit unit and a starting battery; the direct current brushless motor is coaxially connected with the output end of the engine;
the starting battery is used for supplying power to the starting and power generation integrated circuit unit;
the starting and power generation integrated circuit unit is used for receiving a starting instruction and supplying power to the direct current brushless motor; the starting and power generation integrated circuit unit stops supplying power to the direct current brushless motor after detecting that the engine reaches a starting rotating speed;
the direct-current brushless motor is used for driving the engine to work after the power generation integrated circuit unit is started to supply power;
the engine is used for driving the direct-current brushless motor to rotate when the engine works, so that the direct-current brushless motor winding generates three-phase alternating current, the three-phase alternating current is output to the starting and power generation integrated circuit unit, and electric energy is provided for the airborne equipment and the airborne battery after rectification and filtering of the starting and power generation integrated circuit unit.
Further, the starting and power generation integrated circuit unit comprises a control circuit, a driving circuit and a power circuit;
the starting battery is a direct-current 24V battery and respectively supplies power to the control circuit, the driving circuit and the power circuit;
the control circuit comprises a 24-12V voltage reduction module, a 12-5V voltage reduction module, a 5-3.3V voltage reduction module and a microcontroller minimum system; the 24-12V voltage reduction module, the 12-5V voltage reduction module and the 5-3.3V voltage reduction module reduce the 24V voltage of the starting battery to 3.3V working voltage for supplying power to the minimum system of the microcontroller; the 24-12V voltage reduction module reduces the 24V voltage of the starting battery to 12V working voltage for supplying power to the driving circuit module; the microcontroller minimum system is used for outputting six paths of PWM square waves to the driving circuit after receiving the starting signal;
the driving circuit is used for driving the power circuit to generate three-phase alternating current according to the six paths of PWM square waves output by the control circuit;
the power circuit is used for inverting the direct current into three-phase alternating current to enable the direct current brushless motor to work when the power generation integrated circuit unit is started to transmit power to the direct current brushless motor; when the brushless DC motor transmits power to the starting and power generation integrated circuit unit, the brushless DC motor is used for rectifying three-phase alternating current into direct current and providing electric energy for airborne equipment and an airborne battery.
Further, the power circuit includes six MOSFETs and six SBDs;
in the drive circuit, each drive chip is respectively connected with two MOSFETs, an SBD is connected between the drain electrode and the source electrode of each MOSFET in parallel, the source electrode of the lower bridge MOSFET connected with each drive chip is grounded, the source electrode of the upper bridge MOSFET connected with each drive chip is respectively connected with a three-phase winding of the DC brushless motor, and the drain electrode of the upper bridge MOSFET connected with each drive chip is connected with the anode of the starting battery.
Further, a voltage stabilizing module is arranged between the power circuit and the airborne equipment.
Further, the microcontroller minimum system receives a starting instruction through unmanned aerial vehicle remote control.
Further, the microcontroller receives a starting instruction through a serial port communication circuit.
Further, a Hall sensor is installed on the brushless DC motor and connected with a minimum system of the microcontroller.
Further, the microcontroller minimum system is also connected with a safety starting line switch, and the microcontroller minimum system is allowed to receive a starting instruction only when the safety starting line switch is closed.
A control method for starting a power generation integrated control system of an unmanned aerial vehicle is characterized by comprising the following steps:
s1, starting engine
The starting battery supplies power to the starting and power generation integrated circuit unit, the starting and power generation integrated circuit unit receives a starting instruction and supplies power to the direct current brushless motor, and the direct current brushless motor drives the engine to work until the rotating speed of the engine reaches a starting speed;
s2, generating power by the engine
Starting the power generation integrated circuit unit to stop outputting current to the direct current brushless motor; the engine drives the direct current brushless motor to rotate to generate three-phase alternating current;
s3, supplying power to the brushless DC motor
The direct current brushless motor outputs three-phase alternating current to the starting and power generation integrated circuit unit, and provides electric energy to the airborne equipment and the airborne battery after rectification and filtering of the starting and power generation integrated circuit unit.
Further, when the engine speed is greater than or equal to a preset speed value, S3 is executed continuously to S3; when the rotating speed of the engine is smaller than a preset rotating speed value, the power generation integrated circuit unit is started to stop providing electric energy for the airborne equipment and the airborne battery, and the airborne battery supplies power to the airborne equipment.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the integrated control system for starting and generating the power of the unmanned aerial vehicle, the unmanned aerial vehicle is started and generates power by virtue of the set of control system, the direct-current brushless motor is coaxially connected with the output end of the engine, the direct-current brushless motor can drive the engine to work during starting, and the engine can drive the direct-current brushless motor to synchronously rotate during generating the power, so that the self weight of the unmanned aerial vehicle is effectively reduced, the structural complexity of an avionic system is reduced, and the stability of an avionic function is enhanced.
2. The starting and power generation integrated circuit unit is powered by the starting battery and comprises a control circuit and a power circuit. When the brushless direct-current motor is started, 24V voltage of a starting battery is reduced and then supplies power to a minimum system of the microcontroller, the driving circuit converts six paths of PWM square waves transmitted by the minimum system of the microcontroller and transmits the converted PWM square waves to the power circuit, and three-phase alternating current is output to the brushless direct-current motor after inversion; during power generation, the power circuit rectifies the three-phase alternating current into direct current and then provides electric energy for the airborne equipment and the airborne battery. The start-up and power generation integrated circuit unit is used for finishing start-up and power generation integrated control.
3. The power circuit comprises six MOSFETs and six SBDs, wherein the six SBDs are respectively connected between the drain electrode and the source electrode of each MOSFET in parallel, so that the MOSFETs can be prevented from being broken down by counter electromotive force generated in the rotation process of the motor.
4. A voltage stabilizing module is arranged between the power circuit and the airborne equipment, so that the voltage output to the airborne equipment is ensured to be stable.
5. The engine of the invention can be started by a remote control command, which is convenient for the debugging operation of ground personnel.
6. The direct current brushless motor is provided with the Hall sensor which is used for detecting the position information of the current direct current brushless motor.
7. The minimum system of the microcontroller is connected with a safe starting line switch, and a starting instruction is sent out to be executed only when the safe starting line switch is in an opening state, so that the safety of a control system is further ensured.
8. According to the control method for starting the power generation integrated control system of the unmanned aerial vehicle, when the unmanned aerial vehicle is started, the power generation integrated circuit unit transmits power to the direct current brushless motor, and the direct current brushless motor drives the engine to work until the rotating speed of the engine reaches the starting speed; during power generation, the engine drives the direct-current brushless motor to rotate, and the power generation integrated circuit unit is started to provide electric energy for the airborne equipment and the airborne battery. The starting and the power generation of the engine can be completed by depending on one set of system, and the control method is simple and convenient.
9. The power supply required by the airborne equipment can be switched between the power generation power supply and the airborne battery so as to ensure that the unmanned aerial vehicle has good cruising ability.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle start-up and power generation integrated control system according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of an integrated circuit unit for starting power generation according to an embodiment of the present invention;
FIG. 3 is an electrical connection diagram of the integrated circuit unit for starting power generation according to the embodiment of the present invention;
FIG. 4 is a schematic diagram of a start-up control flow in an embodiment of the present invention;
fig. 5 is a schematic diagram of a power generation control flow in the embodiment of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the embodiments of the present invention and the accompanying drawings, and it is obvious that the described embodiments do not limit the present invention.
Like figure 1, an unmanned aerial vehicle starts electricity generation integral type control system, including engine, DC brushless motor, start electricity generation integral type circuit unit and start-up battery, DC brushless motor with the output coaxial coupling of engine satisfies the start-up and the electricity generation functional demand of unmanned aerial vehicle engine.
When the engine is started, the starting battery supplies power to the starting and power generation integrated circuit unit, the starting and power generation integrated circuit unit transmits power to the direct-current brushless motor after receiving a starting instruction, the high-speed rotation of the direct-current brushless motor is utilized, the engine reaches a certain rotating speed, namely the rotating speed is started, and the engine is ignited; and after the ignition is successful, the engine generates three-phase alternating current through the coaxially connected direct current brushless motor, and the three-phase alternating current is rectified by starting the power generation integrated circuit unit to convert the alternating current into direct current potential airborne equipment and an airborne battery for power supply.
As shown in fig. 2, the start-up and power generation integrated circuit unit includes a control circuit and a power circuit, wherein the control circuit includes a 24-12V buck module, a 12-5V buck module, a 5-3.3V buck module, a minimum microcontroller system and a driving circuit module. The 24-12V voltage reduction module, the 12-5V voltage reduction module and the 5-3.3V voltage reduction module reduce the 24V voltage of the starting battery to 3.3V working voltage for supplying power to the minimum system of the microcontroller; the 24-12V voltage reduction module reduces the 24V voltage of the starting battery to 12V working voltage for supplying power to the driving circuit module. After the minimum system of the microcontroller receives the starting signal, six paths of PWM square waves are controlled and output to the driving circuit, the driving circuit converts a 3.3V control signal input by the minimum system of the microcontroller into a 12V driving signal and outputs the driving signal to a power device in the power circuit, and the output of large current is realized through a switch of the power device, so that the direct-current brushless motor is dragged to move. When the rotating speed of the engine meets the power generation requirement, three-phase alternating current output by the direct current brushless motor coaxially connected with the engine is converted into direct current by starting a three-phase rectifier bridge circuit in the power generation integrated circuit unit, the rectified direct current is output to the airborne equipment and the airborne battery through the voltage stabilizing module, and the airborne equipment does not need to be provided with the voltage stabilizing module if the airborne equipment is provided with the voltage stabilizing module.
Referring to fig. 3, the minimum system of the microcontroller in the control circuit is connected with the serial communication circuit, the hall sensor detection circuit and the remote control receiving circuit. The serial port communication circuit is used as a communication bridge between the minimum system of the microcontroller and the aircraft controller; the detection circuit of the Hall sensor is used for feeding back the position information of the current DC brushless motor, so that the minimum system of the microcontroller keeps outputting correct PWM square waves; in addition, for making things convenient for the debugging of ground personnel, the accessible remote control circuit starts the unmanned aerial vehicle engine. The driving circuit consists of 3 identical driving chips and can convert six paths of PWM signals input by the control circuit into PWM signals of MOSFETs capable of being driven by 12V. The power circuit comprises six MOSFETs (field effect transistors) and six SBDs (schottky rectifier diodes); every driver chip in the drive circuit connects two MOSFET respectively, correspond upper bridge and the lower bridge of power circuit, connect an SBD in parallel between every MOSFET's drain electrode and the source electrode, every driver chip corresponds the source electrode ground connection of the MOSFET of lower bridge, every driver chip corresponds the source electrode of the MOSFET of upper bridge and is connected with the three-phase winding of DC brushless motor respectively, every driver chip corresponds the drain electrode of the MOSFET of upper bridge and links to each other with the positive pole of starting battery, PHA, PHB, PHC connect the three-phase winding of DC brushless motor respectively. The three-phase alternating current output by the direct current brushless motor winding is rectified into direct current voltage in a certain range through six SBDs in the power generation stage.
The control method based on the control system comprises the following steps:
s1, starting engine
The starting battery supplies power to the starting and power generation integrated circuit unit, the starting and power generation integrated circuit unit receives a starting instruction and transmits power to the direct current brushless motor, and the direct current brushless motor drives the engine to work after being powered on until the rotating speed of the engine reaches the starting speed;
s2, generating power by the engine
Starting the power generation integrated circuit unit to stop outputting current to the direct current brushless motor; the engine drives the direct current brushless motor to rotate;
s3, supplying power to the brushless DC motor
The brushless DC motor transmits three-phase alternating current to the starting and power generation integrated circuit unit, and the three-phase alternating current is rectified by the starting and power generation integrated circuit unit to provide electric energy for the airborne equipment and the airborne battery.
As shown in fig. 4, in the startup control, after the whole control system is powered on, the initial hardware configuration is first performed, and after the configuration is completed, the state detection is performed. In order to ensure the safety of ground workers in the starting stage of the engine, the minimum system of the microcontroller is also connected with a safety starting line switch, in the actual operation, the engine is allowed to be started only after the ground workers close the safety starting line switch, and the safety starting line switch can be an entity switch device and can also be realized through a control program.
In addition, the system also detects signals of a Hall sensor of the direct current brushless motor in real time, monitors the voltage of a power supply battery, and returns the state of the current starting power generation integrated device according to a certain frequency.
When the starting and power generation integrated circuit unit receives a starting signal from the outside, the minimum system of the microcontroller outputs a corresponding control signal of the direct current brushless motor to the driving circuit according to a preset starting mode. In addition, the minimum system of the microcontroller continues to report the current state of the device, and after the start is finished, the minimum system of the microcontroller outputs a signal.
When the system is started, the engine outputs three-phase alternating current through the brushless direct current motor, and the three-phase alternating current converts the generated alternating current into direct current through a three-phase rectifier bridge circuit in the device. The magnitude of the rectified voltage is determined by the current rotation speed, so that the rectified voltage is a direct-current voltage within a certain interval range. In order to be able to use this voltage, a regulation module is also required, which converts the fluctuating rectified voltage into a constant voltage.
As shown in fig. 5, in the power generation control process, after the engine is normally started, the start-up power generation integrated circuit unit returns the state information of the current start-up power generation integrated circuit unit, such as the battery voltage, the hall signal, the safety start line, the rotation speed, and the like, in real time. And judging the engine speed under the condition that the state information is normal, when the engine speed is higher than 4500rpm, the on-board equipment is powered by the power generation circuit, and before power generation is started, the on-board equipment is powered by the on-board battery. After the power generation starts, the power generation circuit can supply power to the airborne equipment and can also charge the airborne battery. After the power supply paths of the power generation and the onboard equipment are switched on, the rotating speed of the engine is reduced to a certain extent. In order to ensure that the engine provides enough flight power for the unmanned aerial vehicle, when the rotating speed of the engine is less than 3200rpm, the system closes a power supply path between the power generation and the airborne equipment, and the airborne equipment is powered by an airborne battery. The engine speed reaches 4500rpm to generate power, the onboard equipment with the engine speed lower than 3200rpm is powered by the onboard battery, the engine speed is the set value of the embodiment, and the specific setting can be carried out according to the engine parameters during specific operation.
The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle starts electricity generation integral type control system which characterized in that: the system comprises an engine, a direct current brushless motor, a starting and power generation integrated circuit unit and a starting battery; the direct current brushless motor is coaxially connected with the output end of the engine;
the starting battery is used for supplying power to the starting and power generation integrated circuit unit;
the starting and power generation integrated circuit unit is used for receiving a starting instruction and supplying power to the direct current brushless motor; the starting and power generation integrated circuit unit stops supplying power to the direct current brushless motor after detecting that the engine reaches a starting rotating speed;
the direct-current brushless motor is used for driving the engine to work after the power generation integrated circuit unit is started to supply power;
the engine is used for driving the direct-current brushless motor to rotate when the engine works, so that the direct-current brushless motor winding generates three-phase alternating current, the three-phase alternating current is output to the starting and power generation integrated circuit unit, and electric energy is provided for the airborne equipment and the airborne battery after rectification and filtering of the starting and power generation integrated circuit unit.
2. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 1, wherein: the starting and power generation integrated circuit unit comprises a control circuit, a driving circuit and a power circuit;
the starting battery is a direct-current 24V battery and respectively supplies power to the control circuit, the driving circuit and the power circuit;
the control circuit comprises a 24-12V voltage reduction module, a 12-5V voltage reduction module, a 5-3.3V voltage reduction module and a microcontroller minimum system; the 24-12V voltage reduction module, the 12-5V voltage reduction module and the 5-3.3V voltage reduction module reduce the 24V voltage of the starting battery to 3.3V working voltage for supplying power to the minimum system of the microcontroller; the 24-12V voltage reduction module reduces the 24V voltage of the starting battery to 12V working voltage for supplying power to the driving circuit module; the microcontroller minimum system is used for outputting six paths of PWM square waves to the driving circuit after receiving the starting signal;
the driving circuit is used for driving the power circuit to generate three-phase alternating current according to the six paths of PWM square waves output by the control circuit;
the power circuit is used for inverting the direct current into three-phase alternating current to enable the direct current brushless motor to work when the power generation integrated circuit unit is started to transmit power to the direct current brushless motor; when the brushless DC motor transmits power to the starting and power generation integrated circuit unit, the brushless DC motor is used for rectifying three-phase alternating current into direct current and providing electric energy for airborne equipment and an airborne battery.
3. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 2, wherein: the power circuit comprises six MOSFETs and six SBDs;
in the drive circuit, each drive chip is respectively connected with two MOSFETs, an SBD is connected between the drain electrode and the source electrode of each MOSFET in parallel, the source electrode of the lower bridge MOSFET connected with each drive chip is grounded, the source electrode of the upper bridge MOSFET connected with each drive chip is respectively connected with a three-phase winding of the DC brushless motor, and the drain electrode of the upper bridge MOSFET connected with each drive chip is connected with the anode of the starting battery.
4. An integrated control system for starting and generating power by unmanned aerial vehicle as claimed in claim 2 or 3, wherein: and a voltage stabilizing module is arranged between the power circuit and the airborne equipment.
5. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 4, wherein: and the microcontroller minimum system receives a starting instruction through the remote control of the unmanned aerial vehicle.
6. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 4, wherein: and the microcontroller receives a starting instruction through the serial port communication circuit.
7. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 6, wherein: and the direct current brushless motor is provided with a Hall sensor, and the Hall sensor is connected with a minimum system of the microcontroller.
8. The integrated control system for starting and generating power of unmanned aerial vehicle as claimed in claim 7, wherein: the minimum system of the microcontroller is also connected with a safe starting line switch, and the minimum system of the microcontroller is allowed to receive a starting instruction only when the safe starting line switch is closed.
9. A control method for starting a power generation integrated control system by an unmanned aerial vehicle is characterized by comprising the following steps:
s1, starting engine
The starting battery supplies power to the starting and power generation integrated circuit unit, the starting and power generation integrated circuit unit receives a starting instruction and supplies power to the direct current brushless motor, and the direct current brushless motor drives the engine to work until the rotating speed of the engine reaches a starting speed;
s2, generating power by the engine
Starting the power generation integrated circuit unit to stop outputting current to the direct current brushless motor; the engine drives the direct current brushless motor to rotate to generate three-phase alternating current;
s3, supplying power to the brushless DC motor
The direct current brushless motor outputs three-phase alternating current to the starting and power generation integrated circuit unit, and provides electric energy to the airborne equipment and the airborne battery after rectification and filtering of the starting and power generation integrated circuit unit.
10. The control method of the integrated control system for starting and generating power by the unmanned aerial vehicle as claimed in claim 9, wherein: s3 is that when the engine speed is greater than or equal to a preset speed value, S3 is continuously executed; when the rotating speed of the engine is smaller than a preset rotating speed value, the power generation integrated circuit unit is started to stop providing electric energy for the airborne equipment and the airborne battery, and the airborne battery supplies power to the airborne equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010175898.1A CN111446894A (en) | 2020-03-13 | 2020-03-13 | Unmanned aerial vehicle starting and power generation integrated control system and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010175898.1A CN111446894A (en) | 2020-03-13 | 2020-03-13 | Unmanned aerial vehicle starting and power generation integrated control system and control method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111446894A true CN111446894A (en) | 2020-07-24 |
Family
ID=71650508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010175898.1A Pending CN111446894A (en) | 2020-03-13 | 2020-03-13 | Unmanned aerial vehicle starting and power generation integrated control system and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111446894A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112443444A (en) * | 2020-12-24 | 2021-03-05 | 中国电建集团江西省电力建设有限公司 | Wireless remote control one-key starting device of gasoline engine and control method thereof |
| CN112564249A (en) * | 2020-11-05 | 2021-03-26 | 深圳拓邦股份有限公司 | Control method and device for realizing charge and discharge functions |
| CN115013211A (en) * | 2022-06-01 | 2022-09-06 | 嘉兴中创航空技术有限公司 | Unmanned aerial vehicle multifunctional engine starting system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104993749A (en) * | 2015-07-31 | 2015-10-21 | 重庆力华科技有限责任公司 | Inverter device for internal combustion engine inverter generator live start function and method thereof |
| US10260471B2 (en) * | 2015-02-18 | 2019-04-16 | Ge Aviation Systems Llc | Aircraft starting and generating system |
| CN110155345A (en) * | 2019-06-05 | 2019-08-23 | 重庆隆鑫通航发动机制造有限公司 | Unmanned plane hybrid power system |
| CN110242470B (en) * | 2019-05-30 | 2020-10-27 | 西安交通大学 | Starting and power generation integrated system for oil-electricity hybrid unmanned aerial vehicle and control method |
-
2020
- 2020-03-13 CN CN202010175898.1A patent/CN111446894A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10260471B2 (en) * | 2015-02-18 | 2019-04-16 | Ge Aviation Systems Llc | Aircraft starting and generating system |
| CN104993749A (en) * | 2015-07-31 | 2015-10-21 | 重庆力华科技有限责任公司 | Inverter device for internal combustion engine inverter generator live start function and method thereof |
| CN110242470B (en) * | 2019-05-30 | 2020-10-27 | 西安交通大学 | Starting and power generation integrated system for oil-electricity hybrid unmanned aerial vehicle and control method |
| CN110155345A (en) * | 2019-06-05 | 2019-08-23 | 重庆隆鑫通航发动机制造有限公司 | Unmanned plane hybrid power system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112564249A (en) * | 2020-11-05 | 2021-03-26 | 深圳拓邦股份有限公司 | Control method and device for realizing charge and discharge functions |
| CN112443444A (en) * | 2020-12-24 | 2021-03-05 | 中国电建集团江西省电力建设有限公司 | Wireless remote control one-key starting device of gasoline engine and control method thereof |
| CN115013211A (en) * | 2022-06-01 | 2022-09-06 | 嘉兴中创航空技术有限公司 | Unmanned aerial vehicle multifunctional engine starting system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111446894A (en) | Unmanned aerial vehicle starting and power generation integrated control system and control method thereof | |
| JP6684359B2 (en) | Hybrid power source drone | |
| US8618771B2 (en) | Electric powered vehicle, vehicle charge device and vehicle charge system | |
| US7157869B2 (en) | Control system and control method for motor powered four wheel drive vehicle | |
| CN102343877B (en) | Low voltage bus stability | |
| US10000137B2 (en) | Hybrid vehicle with means for disconnection of a depleted auxiliary battery in order to allow for more rapid main battery charging | |
| CN111786598B (en) | Motor control device and motor control method | |
| CN103780177A (en) | Automobile AC generator voltage regulator and voltage regulation method | |
| CN112810822B (en) | Aviation aircraft with function of initiating and controlling method thereof | |
| KR100611178B1 (en) | Control device for motor-driven 4wd vehicle and related control method | |
| CN107933935B (en) | Unmanned aerial vehicle control system | |
| CN109693796A (en) | Aircraft oil electricity mixing energy supplying system, aircraft and its control method | |
| CN104579063B (en) | The delay control circuit of generating set and control method | |
| CN111003189A (en) | Power control system and method of hybrid unmanned aerial vehicle | |
| CN214247559U (en) | Wireless remote control one-key starting device for gasoline engine | |
| CN111478415B (en) | Charging device, method and system | |
| KR20190025778A (en) | Hybrid gasoline-electric propulsion system | |
| CN110395396B (en) | Unmanned aerial vehicle self-starting system and control method thereof | |
| CN204498038U (en) | The delay control circuit of generating set | |
| CN109421467B (en) | Hybrid power vehicle and air conditioner control method thereof | |
| CN205945471U (en) | Unmanned aerial vehicle starts power generation system based on brushless motor drive | |
| Qian et al. | Design and Implementation of Hybrid UAV Starter/Generator Module | |
| CN203374367U (en) | Control device of range extender diesel generating set | |
| CN219821781U (en) | Hybrid unmanned aerial vehicle power system based on brushless motor | |
| CN213517942U (en) | Driving circuit of coreless motor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200724 |
|
| RJ01 | Rejection of invention patent application after publication |