CN111409836B - Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle - Google Patents
Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN111409836B CN111409836B CN202010237848.1A CN202010237848A CN111409836B CN 111409836 B CN111409836 B CN 111409836B CN 202010237848 A CN202010237848 A CN 202010237848A CN 111409836 B CN111409836 B CN 111409836B
- Authority
- CN
- China
- Prior art keywords
- power
- aerial vehicle
- unmanned aerial
- engine
- controller
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000010248 power generation Methods 0.000 title claims abstract description 14
- 230000007246 mechanism Effects 0.000 claims abstract description 14
- 230000001939 inductive effect Effects 0.000 claims abstract description 7
- 229910044991 metal oxide Inorganic materials 0.000 claims abstract description 4
- 150000004706 metal oxides Chemical class 0.000 claims abstract description 4
- 239000004065 semiconductor Substances 0.000 claims abstract description 4
- 230000001965 increasing effect Effects 0.000 claims description 7
- 238000002474 experimental method Methods 0.000 claims description 4
- 238000013528 artificial neural network Methods 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 3
- 210000001258 synovial membrane Anatomy 0.000 claims description 3
- 239000000446 fuel Substances 0.000 abstract description 2
- 230000001276 controlling effect Effects 0.000 description 7
- 239000000295 fuel oil Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D29/00—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto
- F02D29/02—Controlling engines, such controlling being peculiar to the devices driven thereby, the devices being other than parts or accessories essential to engine operation, e.g. controlling of engines by signals external thereto peculiar to engines driving vehicles; peculiar to engines driving variable pitch propellers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D31/00—Use of speed-sensing governors to control combustion engines, not otherwise provided for
- F02D31/001—Electric control of rotation speed
- F02D31/002—Electric control of rotation speed controlling air supply
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Control Of Eletrric Generators (AREA)
- Rectifiers (AREA)
Abstract
The invention discloses a power generation rectification control method of an aviation hybrid power system for a multi-rotor unmanned aerial vehicle, which comprises a hybrid power system, a hybrid rectifier, a controller, a standby battery and the multi-rotor unmanned aerial vehicle, wherein the hybrid rectifier comprises a rectifying diode and a power MOS (metal oxide semiconductor) tube which are connected in parallel, the rectifying diode comprises a common cathode and a common anode, each rectifying diode is distributed with a permanent magnet generator to form three-phase connection, the controller controls the power MOS tube to be disconnected to form an active rectifying circuit and a passive rectifying circuit, an engine is arranged on the multi-rotor unmanned aerial vehicle, a steering engine connecting rod mechanism and a steering engine are arranged on the engine and comprise a throttle valve and a rocker arm, and the constant-pressure output of the rotating speed of the engine is controlled by adopting the passive rectifying method under a low-power working condition; and under the high-power working condition, the invention integrates battery driving and fuel driving by adopting a non-inductive active rectification algorithm to realize boosting constant voltage control, has simple control and realizes the aims of boosting constant voltage control, unmanned aerial vehicle duration and heavy load.
Description
Technical Field
The invention relates to the technical field of generators and hybrid power, in particular to a power generation rectification control method of an aviation hybrid power system for a multi-rotor unmanned aerial vehicle.
Background
The multi-rotor unmanned aerial vehicle can realize vertical take-off and landing, hover and the like, has good maneuverability and flexibility, simple structure, simple control and high market acceptance, is widely applied to military and agricultural fields such as agriculture and forestry plant protection, electric power inspection, military reconnaissance and the like, has huge development potential and has very bright market prospect.
At present, a multi-rotor unmanned aerial vehicle generally adopts a power battery power supply mode, so that the endurance is short, the load is small, the battery capacity is reduced in winter or in a plateau low-temperature environment, and the endurance is obviously shortened; the fuel oil driving unmanned aerial vehicle has strong power, long aviation time and heavy load, but the fuel oil engine has obvious nonlinear characteristic, complex speed regulation, slow response speed and difficult control, and the fuel oil driving needs a transmission speed change mechanism with complex structure and huge volume, so that the power ratio is reduced; the rotating speed of the engine is controlled by adjusting the throttle valve through the steering engine connecting rod, when the throttle valve reaches the maximum opening degree, the load on the direct current side is continuously increased, the rotating speed is reduced, the output voltage is reduced, constant-voltage output cannot be realized, and the power consumption requirement of the unmanned aerial vehicle is not met.
Disclosure of Invention
In order to solve the problems, the invention provides a power generation and rectification control method for an aviation hybrid power system of a multi-rotor unmanned aerial vehicle, which integrates the characteristics of power battery driving and fuel driving, adopts a mode of combining active rectification and passive rectification, and realizes constant voltage output during variable load by the power generation and rectification control method combining engine speed control and the active and passive rectification control method.
The technical scheme adopted by the invention is as follows:
an aviation hybrid power system for a multi-rotor unmanned aerial vehicle comprises a hybrid power system, a hybrid rectifier, a controller, a standby battery and the multi-rotor unmanned aerial vehicle;
the hybrid power system comprises a two-stroke gasoline engine and a permanent magnet generator which are coaxially and mechanically connected, wherein: the permanent magnet generator, the controller, the standby battery and the multi-rotor unmanned aerial vehicle are all electrically connected with the hybrid rectifier, and the standby battery supplies power for the multi-rotor unmanned aerial vehicle;
the hybrid rectifier comprises three-phase half-bridge rectifiers formed by equal and parallel rectifying diodes and power MOS (metal oxide semiconductor) tubes, wherein the three-phase half-bridge rectifiers are divided into two groups of common cathodes and common anodes and are all in three-phase connection with the permanent magnet generator, so that only two rectifying diodes are conducted at any moment, and current flows from the phase with the highest potential to the phase with the lowest potential through a load;
the controller control power MOS pipe is formed with initiative rectifier circuit and passive rectifier circuit on-off, be equipped with the engine on the many rotor unmanned aerial vehicle, be equipped with steering engine link mechanism and steering engine on the engine, steering engine link mechanism includes throttle valve and rocking arm control throttle valve aperture, the rocking arm is located on the steering engine, the throttle valve is located on the engine, steering engine link mechanism connects the controller, be equipped with the switch on the controller.
Preferentially, the number of the rectifying diodes and the number of the power MOS tubes are six, and each phase of the permanent magnet generator is respectively connected with two rectifying diodes and the power MOS tubes.
Preferentially, the rectifier diode adopts a larger power rectifier diode to replace a freewheeling diode, and integrates the functions of passive rectification and active rectification.
Preferably, the power generation rectification control method for the aviation hybrid power system of the multi-rotor unmanned aerial vehicle comprises the following steps:
step one, initializing a system, enabling a steering engine to return, and adjusting a throttle valve on the engine to an idle position;
step two, judging the switching state of the controller, ending the flow when the controller is in an off state, reading the voltage and the current value of the direct current side of the hybrid rectifier when the controller is in an on state, calculating the power of the direct current side, and continuing the step three;
setting a power threshold value through multiple experiments, outputting three control signals by the controller when the power value is smaller than the power threshold value, and adjusting the high-side three-phase power MOS tubes to be in an off state to form a passive rectifying circuit, and controlling the rotation speed of the engine through the opening degree of a throttle valve to realize constant-voltage output;
when the rocker arm reaches the maximum position, namely the throttle valve reaches the maximum opening, according to the external characteristics of the engine, the rotating speed is reduced along with the increase of the load, so that the voltage after passive rectification is reduced, the power requirement of the multi-rotor unmanned aerial vehicle cannot be met, when the load power at the direct current side is larger than a power threshold value and the bus voltage is lower than a lower limit voltage, the controller switches a non-inductive active rectification algorithm, the non-inductive active rectification algorithm adopts a space vector algorithm, a counter potential observer is established through phase voltage and current, a rotating magnetic field is formed by observing the position and the rotating speed of a rotor on a permanent magnet generator, and the boosting and constant voltage control is realized;
and fifthly, when the load at the direct current side is reduced below a power threshold, switching the three-phase rectifier bridge high-side three-way power MOS tube to be in an off state, switching to a passive rectification method in the step three, controlling the rotation speed of the engine through a throttle valve to realize constant-voltage output, judging the power value, and circulating the step three and the step four.
Preferentially, in the third step, the method for adjusting the opening degree of the throttle valve by the passive rectifying circuit is as follows: calculating a common working voltage range of the multi-rotor unmanned aerial vehicle, reading bus voltage, and when the bus voltage is lower than a lower limit voltage, controlling a rocker arm by a steering engine connecting rod mechanism through a controller, increasing the opening of a throttle valve, and improving the rotating speed of an engine; when the bus voltage is higher than the upper limit voltage, the controller controls the rocker arm, reduces the opening of the throttle valve and reduces the rotating speed of the engine; when the bus voltage is in the normal voltage range, the controller controls the throttle position through the rocker arm to maintain the engine speed.
Preferentially, the non-inductive active rectification algorithm comprises a fuzzy control algorithm, an artificial neural network, a synovial membrane observer, a Kalman filtering observer and the like, precisely observes the rotor position and the rotating speed, and improves the switching critical point of active rectification and passive rectification.
The beneficial effects of the invention are as follows:
1. the active rectification and the passive rectification are combined, the engine control and the noninductive active rectification control are integrated, the constant-voltage output is realized by controlling the rotating speed of the engine during the passive rectification, the boosting and the constant-voltage control are realized by adopting a noninductive rectification algorithm during the active rectification, the practical experience is combined, the multiple experiments are carried out, the control is simple, and the reliability is high;
2. the light and efficient aviation hybrid power system solution is adopted, the advantages of power battery driving and fuel oil driving are integrated, the unmanned aerial vehicle endurance and load are improved, the control is simple, and the replaceability is strong.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of a hybrid rectifier of the present invention;
fig. 3 is a flow chart of a control method of the present invention.
Marked in the figure as: 1. the system comprises a hybrid power system, a two-stroke gasoline engine, a permanent magnet generator, a hybrid rectifier, a common cathode, a common anode, a standby battery, a controller and a multi-rotor unmanned aerial vehicle.
Detailed Description
As shown in fig. 1, an aviation hybrid power system for a multi-rotor unmanned aerial vehicle comprises a hybrid power system 1, a hybrid rectifier 2, a controller 4, a standby battery 3 and a multi-rotor unmanned aerial vehicle 5;
the hybrid system 1 comprises a two-stroke gasoline engine 11 and a permanent magnet generator 12 mechanically connected coaxially, wherein: the permanent magnet generator 12 is provided with a rotor, the permanent magnet generator 12, the controller 4, the standby battery 3 and the multi-rotor unmanned aerial vehicle 5 are electrically connected with the hybrid rectifier 2, and the standby battery 3 supplies power for the multi-rotor unmanned aerial vehicle 5;
the hybrid rectifier 2 comprises six rectifier diodes and power MOS (metal oxide semiconductor) transistors which are connected in parallel to form a three-phase half-bridge rectifier, the three-phase half-bridge rectifier is divided into two groups of a common cathode 21 and a common anode 22 and is in three-phase connection with the permanent magnet generator 12, as shown in fig. 2, V1 to V6 are rectifier diodes, S1 to S6 are power MOS transistors, V1, V3 and V5 are common cathode 21 and V2, V4 and V6 are common anode 22, V1, V2, V3, V4, V5 and V6 are respectively and electrically connected to form three-phase connection with the permanent magnet generator 12, S1 to S6 are respectively matched and are connected in parallel to two ends of V1 to V6 with the same serial number, only two rectifier diodes are guaranteed to be conducted at any moment, so that current flows from the phase with the highest potential to the phase with the lowest load current, the rectifier diodes adopt larger power rectifier diodes to replace the diodes, passive rectifier and active rectifier function is integrated, and the controller 4 controls the power MOS transistors to be disconnected to form an active rectifier circuit and a passive rectifier circuit;
be equipped with the engine on many rotor unmanned aerial vehicle 5, be equipped with steering wheel link mechanism and steering wheel on the engine, steering wheel link mechanism includes throttle valve and rocking arm control throttle opening, and on the steering wheel was located to the rocking arm, the throttle valve was located on the engine, steering wheel link mechanism connected with controller 4, is equipped with the switch on the controller 4.
Specifically, as shown in fig. 1-3, a power generation rectification control method for an aviation hybrid power system of a multi-rotor unmanned aerial vehicle comprises the following steps:
step one, initializing a system, enabling a steering engine to return, and adjusting a throttle valve on the engine to an idle position;
step two, judging the switching state of the controller 4, ending the flow when the controller is in the off state, reading the voltage and the current value of the direct current side of the hybrid rectifier 2 when the controller is in the on state, calculating the power of the direct current side, and continuing the step three;
step three, the working power supply of the multi-rotor unmanned aerial vehicle 5 which is matched with the hybrid power system 1 is a 12s lithium battery, and the voltage is controlled within a certain range without causing system oscillation due to the correspondingly slower engine, so that the most frequently working voltage range of the multi-rotor unmanned aerial vehicle 5 is selected to be 48V to 49V; when the bus voltage is higher, the rotating speed is increased, namely the output power is increased, the rotating speed and the power of the two-stroke gasoline engine 11 and the permanent magnet generator 12 are matched through multiple experiments, the maximum power 1.6kW can be output when the bus voltage threshold value is 48V, and the maximum power is taken as the power threshold value;
when the power value is smaller than 1.6kW, the controller 4 outputs three control signals and adjusts the high-side three-phase power MOS tube to be in an off state, so as to form a passive rectifying circuit, and the engine speed is controlled by the opening of the throttle valve to realize constant-voltage output, and the specific method is as follows: the method for regulating the opening degree of the throttle valve by the passive rectifying circuit comprises the following steps: calculating a common working voltage range of the multi-rotor unmanned aerial vehicle 5, reading bus voltage, and when the bus voltage is lower than 48V, controlling a rocker arm by a steering engine connecting rod mechanism through a controller 4, increasing the opening of a throttle valve, and improving the rotating speed of an engine; when the bus voltage is higher than 49V, the controller 4 controls the rocker arm, reduces the opening of the throttle valve and reduces the rotating speed of the engine; when the bus voltage is in the range of 48V to 49V, the controller 4 controls the throttle position through the rocker arm to maintain the engine speed;
when the rocker arm is at the maximum position, namely the throttle valve is at the maximum opening, according to the external characteristics of the engine, the rotating speed is reduced along with the increase of the load, so that the voltage after passive rectification is reduced, the power requirement of the multi-rotor unmanned aerial vehicle 5 cannot be met, when the load power at the direct current side is greater than 1.6kW and the bus voltage is lower than 48V, the controller 4 switches a non-inductive active rectification algorithm, the rectifier diode is used as a follow current diode, a release loop is provided, reactive power generated during active rectification control is buffered, high voltage is restrained, the safety of the circuit is ensured, the non-inductive active rectification algorithm adopts a space vector algorithm, a counter potential observer is established through phase voltage and current, a rotating magnetic field is formed at the rotor position and the rotating speed on the permanent magnet generator 12, and the boost and constant voltage control is realized; the noninductive active rectification algorithm also comprises a fuzzy control algorithm, an artificial neural network, a synovial membrane observer, a Kalman filtering observer and the like, precisely observes the rotor position and the rotating speed, and improves the switching critical point of active rectification and passive rectification;
and fifthly, when the load on the direct current side is reduced to below 1.6kW, switching the high-side three-way power MOS tube of the three-phase rectifier bridge to be in an off state, switching the three-way power MOS tube to be in a passive rectification method in the step three, controlling the rotating speed of an engine through a throttle valve to realize constant-voltage output, judging the power value, and circulating the step three and the step four.
The invention has the advantages that: the structure is simple, the power battery drive and the fuel oil drive are integrated, the unmanned aerial vehicle endurance and the load are increased, the active rectification and the passive rectification are combined, and the constant-voltage output is realized by controlling the rotating speed.
The foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present invention has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a power generation rectification control method for many rotor unmanned aerial vehicle's aviation hybrid power system which characterized in that: the aviation hybrid power system for the multi-rotor unmanned aerial vehicle comprises a hybrid power system, a hybrid rectifier, a controller, a standby battery and the multi-rotor unmanned aerial vehicle;
the hybrid power system comprises a two-stroke gasoline engine and a permanent magnet generator which are coaxially and mechanically connected, wherein: the permanent magnet generator, the controller, the standby battery and the multi-rotor unmanned aerial vehicle are all electrically connected with the hybrid rectifier;
the hybrid rectifier comprises three-phase half-bridge rectifiers which are formed by equal and parallel rectifying diodes and power MOS (metal oxide semiconductor) tubes, are divided into two groups of common cathodes and common anodes and are connected with the permanent magnet generator in a three-phase mode;
the controller controls the power MOS tube to be formed with an active rectifying circuit and a passive rectifying circuit, an engine is arranged on the multi-rotor unmanned aerial vehicle, a steering engine connecting rod mechanism and a steering engine are arranged on the engine, the steering engine connecting rod mechanism comprises a throttle valve and a rocker arm, the rocker arm controls the opening of the throttle valve, the rocker arm is arranged on the steering engine, the throttle valve is arranged on the engine, the steering engine connecting rod mechanism is connected with the controller, and a switch is arranged on the controller;
the power generation rectification control method comprises the following steps:
step one, initializing a system, enabling a steering engine to return, and adjusting a throttle valve on the engine to an idle position;
step two, judging the switching state of the controller, ending the flow when the controller is in an off state, reading the voltage and the current value of the direct current side of the hybrid rectifier when the controller is in an on state, calculating the power of the direct current side, and continuing the step three;
step three, through multiple experiments, matching the rotating speeds and the power of the two-stroke gasoline engine and the permanent magnet generator to obtain the maximum power of 1.6kW when the bus voltage threshold is 48V, taking the maximum power as the power threshold, outputting three control signals by the controller when the power value is smaller than the power threshold, and adjusting the high-side three-phase power MOS tube to be in an off state to form a passive rectifying circuit, and controlling the rotating speed of the engine to realize constant voltage output through the opening degree of a throttle valve;
step four, when the power is larger than a power threshold value and the rocker arm reaches the maximum position, namely the throttle valve reaches the maximum opening, the controller switches a non-inductive active rectification algorithm, a counter potential observer is established through phase voltage and current, a rotating magnetic field is formed by observing the position and the rotating speed of a rotor on the permanent magnet generator, and the control of boosting and constant pressure is realized;
and fifthly, entering the next cycle, judging the power value, and continuing the third step and the fourth step.
2. The power generation rectification control method for an aviation hybrid system of a multi-rotor unmanned aerial vehicle according to claim 1, wherein: the number of the rectifying diodes and the number of the power MOS tubes are six, and each phase of the permanent magnet generator is respectively connected with two rectifying diodes and the power MOS tubes.
3. The power generation rectification control method for an aviation hybrid system of a multi-rotor unmanned aerial vehicle according to claim 2, characterized by: the rectifier diode adopts a larger power rectifier diode.
4. The power generation rectification control method for an aviation hybrid system of a multi-rotor unmanned aerial vehicle according to claim 1, wherein: in the third step, the method for adjusting the opening degree of the throttle valve by the passive rectifying circuit comprises the following steps: calculating a common working voltage range of the multi-rotor unmanned aerial vehicle, reading bus voltage, and when the bus voltage is lower than a lower limit voltage, controlling a rocker arm by a steering engine connecting rod mechanism through a controller, increasing the opening of a throttle valve, and improving the rotating speed of an engine; when the bus voltage is higher than the upper limit voltage, the controller controls the rocker arm, reduces the opening of the throttle valve and reduces the rotating speed of the engine; when the bus voltage is in the normal voltage range, the controller controls the throttle position through the rocker arm to maintain the engine speed.
5. The power generation rectification control method for an aviation hybrid system of a multi-rotor unmanned aerial vehicle according to claim 1, wherein: the non-sensing active rectification algorithm comprises a fuzzy control algorithm, an artificial neural network, a synovial membrane observer and a Kalman filtering observer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010237848.1A CN111409836B (en) | 2020-03-30 | 2020-03-30 | Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010237848.1A CN111409836B (en) | 2020-03-30 | 2020-03-30 | Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111409836A CN111409836A (en) | 2020-07-14 |
| CN111409836B true CN111409836B (en) | 2023-05-30 |
Family
ID=71489759
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010237848.1A Active CN111409836B (en) | 2020-03-30 | 2020-03-30 | Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111409836B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112018954A (en) * | 2020-09-09 | 2020-12-01 | 中国石油天然气集团有限公司 | Low-speed power generation device for power faucet |
| CN114074763B (en) * | 2021-11-09 | 2023-02-10 | 南京航空航天大学 | Series hybrid power propulsion system based on turboshaft engine and design method |
| CN115549535A (en) * | 2022-09-16 | 2022-12-30 | 苏州达思灵新能源科技有限公司 | Starting and power generation controller of doubly salient direct-current excitation generator and control method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102739144A (en) * | 2012-06-29 | 2012-10-17 | 深圳市航盛电子股份有限公司 | Belt-starter generator (BSG) motor control system for micro hybrid vehicle |
| CN105322636A (en) * | 2015-08-10 | 2016-02-10 | 南京多零无人机技术有限公司 | Parallel hybrid power module for multi-rotor aircraft |
| CN106356970A (en) * | 2016-09-26 | 2017-01-25 | 北京瑞深航空科技有限公司 | Power supply device and power supply method and equipment thereof |
| CN106892124A (en) * | 2017-01-23 | 2017-06-27 | 北京瑞深航空科技有限公司 | Hybrid power unmanned plane |
| CN108190032A (en) * | 2018-02-05 | 2018-06-22 | 南京婆娑航空科技有限公司 | A kind of electronic control system and its control method of oil electricity mixing unmanned plane energy resource system |
| CN110395395A (en) * | 2019-08-05 | 2019-11-01 | 江苏心源航空科技有限公司 | Parallel operation formula multi-rotor unmanned aerial vehicle mixed power plant based on heavy oil internal combustion engine |
-
2020
- 2020-03-30 CN CN202010237848.1A patent/CN111409836B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102739144A (en) * | 2012-06-29 | 2012-10-17 | 深圳市航盛电子股份有限公司 | Belt-starter generator (BSG) motor control system for micro hybrid vehicle |
| CN105322636A (en) * | 2015-08-10 | 2016-02-10 | 南京多零无人机技术有限公司 | Parallel hybrid power module for multi-rotor aircraft |
| CN106356970A (en) * | 2016-09-26 | 2017-01-25 | 北京瑞深航空科技有限公司 | Power supply device and power supply method and equipment thereof |
| CN106892124A (en) * | 2017-01-23 | 2017-06-27 | 北京瑞深航空科技有限公司 | Hybrid power unmanned plane |
| CN108190032A (en) * | 2018-02-05 | 2018-06-22 | 南京婆娑航空科技有限公司 | A kind of electronic control system and its control method of oil electricity mixing unmanned plane energy resource system |
| CN110395395A (en) * | 2019-08-05 | 2019-11-01 | 江苏心源航空科技有限公司 | Parallel operation formula multi-rotor unmanned aerial vehicle mixed power plant based on heavy oil internal combustion engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111409836A (en) | 2020-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111409836B (en) | Power generation and rectification control method for aviation hybrid power system of multi-rotor unmanned aerial vehicle | |
| US11318847B2 (en) | Energy management control system suitable for solar-powered unmanned aerial vehicle and control method thereof | |
| CN106494328B (en) | It is a kind of based on electrical power line computation fuel-engined vehicle electric energy control system and method | |
| CN108767294A (en) | A kind of the power output control method and system of fuel cell power generation array system | |
| CN209088562U (en) | A kind of charge and discharge current limliting battery pack parallel control device of minimal switches | |
| CN107021191A (en) | One kind balance ship | |
| CN110127063B (en) | Unmanned aerial vehicle power system and control method thereof | |
| CN111605713B (en) | Hybrid rectifying device and control method of hybrid power system of unmanned aerial vehicle | |
| CN112829950A (en) | Long-endurance unmanned aerial vehicle oil-electricity hybrid automatic control system | |
| CN205811542U (en) | A kind of unmanned plane electric power system | |
| CN107749634B (en) | Unified direct current power flow controller for direct current power system | |
| CN112803767B (en) | DC/DC converter control system for charging/discharging power battery | |
| CN109204005B (en) | Photovoltaic extended-range vehicle-mounted composite power supply control system and method | |
| CN109638807B (en) | Fuel cell hybrid system with multiple voltage outputs | |
| CN209298969U (en) | A kind of charging unit | |
| CN109532517B (en) | Management control method for vehicle-mounted composite power supply energy | |
| CN108551258B (en) | RBF network supervision system and method of bidirectional DC-DC converter for storage battery | |
| CN207631000U (en) | A kind of charging pile of new energy | |
| CN113733984B (en) | Auxiliary equalizing charge device based on SOC estimation | |
| CN207638386U (en) | A kind of new energy charging pile | |
| CN218877622U (en) | Novel power management module for fuel cell aircraft | |
| CN109831006A (en) | A kind of self-regulation charging control circuit | |
| CN205622302U (en) | High -efficient miniwatt proton exchange membrane fuel cell and lithium cell hybrid power system | |
| CN114337411B (en) | Driving circuit of charging generator and control method thereof | |
| CN216531130U (en) | Wind-solar complementary power generation system |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |