CN112810822B - Aviation aircraft with function of initiating and controlling method thereof - Google Patents

Aviation aircraft with function of initiating and controlling method thereof Download PDF

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Publication number
CN112810822B
CN112810822B CN202011642148.7A CN202011642148A CN112810822B CN 112810822 B CN112810822 B CN 112810822B CN 202011642148 A CN202011642148 A CN 202011642148A CN 112810822 B CN112810822 B CN 112810822B
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China
Prior art keywords
motor
starting
current
power
starting motor
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CN112810822A (en
Inventor
苏红飞
王庆伟
陈登科
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Sun Hawk(henan) Aviation Industry Co ltd
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Sun Hawk(henan) Aviation Industry Co ltd
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B63/00—Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices
    • F02B63/04—Adaptations of engines for driving pumps, hand-held tools or electric generators; Portable combinations of engines with engine-driven devices for electric generators
    • F02B63/042—Rotating electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
    • F02N11/00—Starting of engines by means of electric motors
    • F02N11/04—Starting of engines by means of electric motors the motors being associated with current generators
    • 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
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
    • 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
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/14—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
    • 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
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/14—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
    • H02J7/1415—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle with a generator driven by a prime mover other than the motor of a vehicle
    • 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
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/14—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
    • H02J7/1438—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle in combination with power supplies for loads other than batteries
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K1/00—Details of the magnetic circuit
    • H02K1/02—Details of the magnetic circuit characterised by the magnetic material
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K1/00—Details of the magnetic circuit
    • H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
    • H02K1/22—Rotating parts of the magnetic circuit
    • H02K1/27—Rotor cores with permanent magnets
    • 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
    • H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
    • 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
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H02K7/1807—Rotary generators
    • 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
    • H02P6/00—Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor position; Electronic commutators therefor
    • 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
    • H02P6/00—Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor position; Electronic commutators therefor
    • H02P6/08—Arrangements for controlling the speed or torque of a single motor
    • 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
    • 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
    • H02P2101/00—Special adaptation of control arrangements for generators
    • H02P2101/30—Special adaptation of control arrangements for generators for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Eletrric Generators (AREA)
  • Control Of Motors That Do Not Use Commutators (AREA)

Abstract

The invention discloses an aviation aircraft with an integral starting function, which comprises a starting motor, an engine and a storage battery, wherein the starting motor is connected with the integral starting controller, the storage battery supplies power to the integral starting controller, the starting motor adopts a permanent magnet three-phase alternating-current lossless motor, the engine is provided with a power output shaft, the power output shaft is connected with a motor rotor arranged in the starting motor and can drive the power output shaft to rotate through the starting motor, the motor rotor comprises a rotor magnetic cylinder, the rotor magnetic cylinder adopts neodymium iron boron permanent magnet steel, the integral starting controller adopts an MCU module for control, an algorithm controlled by the MCU module adopts a DTC, and a DC-DC conversion circuit is arranged in the integral starting controller.

Description

Aviation aircraft with function of initiating and controlling method thereof
Technical Field
The invention belongs to the technical field of aircraft engines, and particularly relates to an aircraft with an initiating integrated function and a control method thereof.
Background
The aeroengine is a highly complex and precise thermodynamic machine, is used as the heart of an airplane, is not only the power of the airplane in flight, but also is an important driving force for promoting the development of aviation industry, and after the development for hundreds of years, the aeroengine has been developed into a mature product with extremely high reliability, the variety of the engine is more and the function is also more and more perfect, the engine used as a power system is very important equipment in the field of aircrafts, especially in the field of small aircrafts, the original aeroengine adopts a starting motor only with a starting function, and the original starting motor drives a power output shaft of a generator to rotate through a speed reducing mechanism, so that the starting is completed; the original engines have a plurality of problems, namely, the original engines have the problems of weak power, the torque required by the operation of the whole engine is increased when the temperature is low, the problem that the engine is not moved by the starting motor easily occurs, so that the take-off failure of the engine is caused, the existing starting motor has a plurality of related mechanical parts, the structure is complex, the weight is large, the weight of the whole aircraft can be increased in the use process, the energy consumption of the aero-generator is increased, the existing starting motor does not correspond to a storage battery and an externally-added load power supply device, the function of the whole starting motor is single, other operations such as power storage cannot be performed, the general applicability of the aero-engine is reduced, and the use of the aero-engine is not utilized.
Disclosure of Invention
The invention aims at: the aviation aircraft with the function of starting and the control method thereof solve the technical problems that the existing aviation aircraft is single in function, heavy in mechanical part load, easy to break down in starting and incapable of carrying out electricity storage operation on a storage battery.
The technical scheme adopted by the invention is as follows: the utility model provides an aircraft with play integrative function, including starter motor, engine and battery, the starter motor connection is provided with plays and starts integrative controller, the battery is supplied power to play and is launched integrative controller, the battery passes through the electric wire and is connected with the aerial survey equipment and the lighting apparatus of setting inside aircraft, the starter motor adopts permanent magnet three-phase to exchange lossless motor, the inside power output shaft that is provided with of engine, the power output shaft is connected with the motor rotor who sets up inside the starter motor, can drive power output shaft through the starter motor and rotate, also can drive the starter motor through power output shaft's rotation simultaneously and carry out the electric power storage operation, motor rotor includes the rotor magnetic jar, rotor magnetic jar adopts neodymium iron boron permanent magnet steel, it adopts MCU module to control to play integrative controller, MCU module control's algorithm adopts DTC, it is provided with DC-DC conversion circuit to start the inside of integrative controller.
Further, the starting torque of the starter motor is 34.2Nm, the starter motor is in a power generation state at more than 4500RPM, and the voltage-reducing output current of the DC-DC conversion circuit is 80A and 28V direct current.
Further, the motor structure of the motor rotor is 18P16N, the design power is 2.5KW, and the output torque is 34.2Nm.
Further, a rectifying and voltage stabilizing circuit is arranged in the DC-DC conversion circuit.
Furthermore, the aerial survey equipment adopts a photoelectric hanging cabin, and the lighting equipment adopts a lighting lamp, so that power is supplied to the photoelectric hanging cabin and the lighting lamp through a storage battery.
A control method of an aviation aircraft with an initiating integrated function comprises the following steps:
s1, outputting a commutation signal by collecting the position of a motor rotor, and commutating the current of a stator winding arranged inside the motor rotor along a certain sequence according to the change of the position of the motor rotor;
s2, driving a starting motor to operate, controlling the current of the starting motor through current feedback detection, enabling the starting motor to work under rated current, driving the starting motor to rotate through a power output shaft when an engine works normally, enabling the starting motor to work in a power generation state, and converting alternating current generated by the starting motor into direct current through a three-phase full-wave rectifying circuit;
s3, monitoring voltage and current output by a power generation state of a starting motor by adopting an MCU, adjusting the PWM frequency and the output duty ratio, adjusting the on-off time and frequency of a MOS tube Q7, controlling the power generation output voltage to be constant 28V output, controlling the current to be 80A rated current, when a grid G of the Q7 is in a high level, conducting D, S of the Q7, charging a capacitor C1 through a Q7 inductor and an L1 inductor in the current direction VCC, and simultaneously supplying power to a rear-stage load, wherein the inductor can generate self-induced electromotive force to block the current from passing, and meanwhile, the inductor can store magnetic energy; when the grid G of the Q7 is at a low level, the Q7 is cut off, the current flowing through the inductor L1 is reduced, the inductor can generate self-induced electromotive force to prevent the current from being reduced due to the characteristics of the inductor, the electromotive force is filtered by the filter capacitor C1, passes through the load to the ground and then passes through the flywheel diode D8 to form a loop, and when the electromotive force on the inductor is reduced or disappears, the circuit supplies power to a later-stage load through the filter capacitor C1.
Further, the current circulation on the electronic winding in the step 1 is to detect the position of the magnetic pole of the rotor magnetic cylinder relative to the stator winding, and generate a position sensing signal at the determined position for switching, and the position sensing signal is connected with the control power switch circuit after being processed by the signal conversion circuit, so that the switching of the winding current is performed according to a certain logic relationship by the control power switch circuit.
Further, the rated current output by the starter motor in step 3 in the starting state is 200A, and the peak current is 300A.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
according to the invention, by integrating the starting function and the power generation function into a whole, the mechanical mechanism is simplified, the whole load is lightened, the arrangement of the machine body is more flexible, the AC brushless permanent magnet motor is adopted, the output power of the power generation state is improved through DC-DC conversion, the storage battery can be charged simultaneously without trouble of lack of electricity, the permanent magnet AC motor is adopted, the starting torque is larger, the starting is not affected by temperature, the aerocraft can take off smoothly in low-temperature weather, the whole system is controlled by the MCU module, the DTC algorithm is adopted, the output voltage of the starter generator is constant 28V, the current is controlled to 80A rated current, the power supply and charging operation of the aerocraft can be ensured to be carried out by the starter generator in time, the universal applicability is further ensured, and the normal operation of the aerocraft is ensured.
Drawings
FIG. 1 is a schematic diagram of a connection module of the present invention;
FIG. 2 is a schematic structural view of a motor rotor;
FIG. 3 is a schematic of a regulated current circuit schematic of a start-up integrated controller;
FIG. 4 is a schematic diagram of a voltage regulator circuit of the initiating integrated controller;
fig. 5 is a schematic diagram of the operation flow of the starter-integrated motor.
Detailed Description
The present invention will be described in further detail with reference to the following examples in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Example 1
The utility model provides an aviation aircraft with play integrative function, including starter motor, engine and battery, the starter motor connection is provided with plays and starts integrative controller, and the battery is supplied power to play and is launched integrative controller, and the battery passes through the conductor wire and is connected with the navigation survey equipment and the lighting apparatus that set up in aviation aircraft inside, and the starter motor adopts permanent magnet three-phase alternating current to be harmless motor, and the starting torque of starter motor is 34.2Nm, and the starter motor is greater than 4500RPM in the power generation state, and DC-DC conversion circuit's step-down output current is 80A,28V direct current. The inside power output shaft that is provided with of engine, power output shaft and the motor rotor who sets up in the starter motor inside are connected and synchronous rotation, can drive power output shaft through the starter motor and rotate, also can drive the starter motor through power output shaft's rotation simultaneously and carry out the electric power storage operation, and motor rotor includes rotor magnetic cylinder, and rotor magnetic cylinder adopts neodymium iron boron permanent magnet steel, and motor rotor's motor structure is 18P16N, design power 2.5KW, output torque 34.2Nm. The starting integrated controller is controlled by adopting an MCU module, an algorithm controlled by the MCU module adopts a DTC, a DC-DC conversion circuit is arranged in the starting integrated controller, and a rectifying and voltage stabilizing circuit is arranged in the DC-DC conversion circuit, so that the stability of the current delivered by the starting motor is ensured. The battery can continuously receive the electric quantity transmitted by the starting motor in the using process of the engine, then the battery is charged, in the using process, the photoelectric hanging cabin in the aerial survey equipment and the illuminating lamp in the illuminating equipment can be powered through the battery, and the power can be directly supplied to the photoelectric hanging cabin and the illuminating lamp through the starting motor in the running process of the engine, so that the aerial vehicle does not need external power supply, and the corresponding equipment on the aerial vehicle can be charged and powered through the engine.
A control method of an aviation aircraft with an initiating integrated function comprises the following steps:
s1, a commutation signal is output by collecting the position of a motor rotor, current of a stator winding arranged inside the motor rotor is commutated according to the change of the position of the motor rotor and along a certain sequence, current circulation on an electronic winding is switched by detecting the position of a magnetic pole of a rotor magnetic cylinder relative to the stator winding and generating a position sensing signal at a certain position, and the position sensing signal is connected with a control power switch circuit after being processed by a signal conversion circuit, so that the switching of winding current is carried out according to a certain logic relation by controlling the power switch circuit;
s2, driving a starting motor to operate, controlling the current of the starting motor through current feedback detection, enabling the starting motor to work under rated current, driving the starting motor to rotate through a power output shaft when an engine works normally, enabling the starting motor to work in a power generation state, and converting alternating current generated by the starting motor into direct current through a three-phase full-wave rectifying circuit;
s3, monitoring voltage and current output by the starting motor in a power generation state by adopting an MCU, adjusting the PWM frequency and the output duty ratio, adjusting the on-off time and frequency of the MOS transistor Q7, controlling the power generation output voltage to be constant 28V output, controlling the current to be 80A rated current, and controlling the rated current output by the starting motor in a starting state to be 200A and the peak current to be 300A. When the grid G of the Q7 is at a high level, D, S of the Q7 is conducted, the current direction is VCC, the VCC passes through the Q7, passes through the L1 inductor, charges the capacitor C1 and simultaneously supplies power to a load at a later stage, and due to the characteristics of the inductor, the inductor can generate self-induced electromotive force to prevent current from passing through, and meanwhile the inductor can store magnetic energy; when the grid G of the Q7 is at a low level, the Q7 is cut off, the current flowing through the inductor L1 is reduced, the inductor can generate self-induced electromotive force to prevent the current from being reduced due to the characteristics of the inductor, the electromotive force is filtered by the filter capacitor C1, passes through the load to the ground and then passes through the flywheel diode D8 to form a loop, and when the electromotive force on the inductor is reduced or disappears, the circuit supplies power to a later-stage load through the filter capacitor C1.
In the use process, the starting function and the power generation function are combined into a whole through the structural arrangement of the starting motor and the connection of the starting motor and the engine, so that a mechanical mechanism is simplified, the whole load is lightened, the machine body is arranged more flexibly, the output power of a power generation state is improved through an alternating current brushless permanent magnet motor and DC-DC conversion, the current and the voltage transmitted by the starting motor can be ensured to be in a stable state through an MCU module and a DTC algorithm, the storage battery can be charged simultaneously through the combination with the storage battery, the condition of power shortage of the storage battery is avoided, meanwhile, the starting torque is larger due to the adoption of the permanent magnet alternating current motor, the starting is not influenced by temperature, and the power generation device can take off smoothly in low-temperature weather.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.

Claims (3)

1. An aircraft with play integrative function, its characterized in that: the power generation system comprises a starting motor, an engine and a storage battery, wherein the starting motor is connected with a starting integrated controller, the storage battery supplies power to the starting integrated controller, the storage battery is connected with aerial measurement equipment and illumination equipment arranged in an aviation aircraft through a conductive wire, the starting motor adopts a permanent magnet three-phase alternating current lossless motor, a power output shaft is arranged in the engine, the power output shaft is connected with a motor rotor arranged in the starting motor, the power output shaft can be driven to rotate through the starting motor, meanwhile, the starting motor can be driven to generate power through the rotation of the power output shaft, the motor rotor comprises a rotor magnetic cylinder, the rotor magnetic cylinder adopts neodymium iron boron permanent magnet steel, the starting integrated controller is controlled by an MCU module, an algorithm controlled by the MCU module adopts a DTC, and a DC-DC conversion circuit is arranged in the starting integrated controller;
the starting torque of the starting motor is 34.2Nm, the starting motor is in a power generation state and is larger than 4500RPM, and the voltage-reducing output current of the DC-DC conversion circuit is 80A and 28V direct current;
the motor structure of the motor rotor is 18P16N, the design power is 2.5KW, and the output torque is 34.2Nm;
the control method of the aviation aircraft with the function of initiating the whole comprises the following steps:
s1, outputting a commutation signal by collecting the position of a motor rotor, and commutating the current of a stator winding arranged inside the motor rotor along a certain sequence according to the change of the position of the motor rotor;
s2, driving a starting motor to operate, controlling the current of the starting motor through current feedback detection, enabling the starting motor to work under rated current, driving the starting motor to rotate through a power output shaft when an engine works normally, enabling the starting motor to work in a power generation state, and converting alternating current generated by the starting motor into direct current through a three-phase full-wave rectifying circuit;
s3, monitoring voltage and current output by a power generation state of a starting motor by adopting an MCU, adjusting the on-off time and frequency of a MOS tube Q7 by adjusting PWM frequency and output duty ratio, controlling the power generation output voltage to be constant 28V output, controlling the current to be 80A rated current, and when a grid G of the Q7 is in a high level, conducting D, S of the Q7, wherein the current direction is VCC, passing through the Q7, passing through an L1 inductor, charging a capacitor C1 and supplying power to a rear-stage load; when the grid G of the Q7 is at a low level, the Q7 is cut off, the current flowing through the inductor L1 is reduced, and the circuit supplies power to a later-stage load through the filter capacitor C1;
the current circulation on the electronic winding in the step 1 is realized by detecting the position of the magnetic pole of the rotor magnetic cylinder relative to the stator winding and generating a position sensing signal at the determined position for switching, and the position sensing signal is connected with the control power switch circuit after being processed by the signal conversion circuit, so that the switching of the winding current is realized by the control power switch circuit.
2. An aircraft with integrated initiation function as claimed in claim 1, wherein: and a rectifying and voltage stabilizing circuit is arranged in the DC-DC conversion circuit.
3. An aircraft with integrated initiation function as claimed in claim 1, wherein: the aerial survey equipment adopts a photoelectric hanging cabin, and the lighting equipment adopts a lighting lamp, so that power is supplied to the photoelectric hanging cabin and the lighting lamp through a storage battery.
CN202011642148.7A 2020-12-31 2020-12-31 Aviation aircraft with function of initiating and controlling method thereof Active CN112810822B (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114718792A (en) * 2022-04-27 2022-07-08 西安德赛控制***有限责任公司 Starting integrated controller for realizing energy bidirectional flow and control method thereof
CN114759675B (en) * 2022-04-27 2023-06-16 西安德赛控制***有限责任公司 Modularized large-current parallel-connection starting integrated controller and control method
CN114977646B (en) * 2022-04-27 2024-04-16 西安德赛控制***有限责任公司 Integrated control system with controllable output heavy current in big moment of torsion position

Citations (2)

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Publication number Priority date Publication date Assignee Title
CN206274631U (en) * 2016-12-30 2017-06-23 台州市汉达动力科技有限责任公司 A kind of starting-generating two-in-one system of motorcycle
CN108512469A (en) * 2018-04-02 2018-09-07 南京航空航天大学 A kind of permanent magnetism starting-generating system and its control method with fault-tolerant ability

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206274631U (en) * 2016-12-30 2017-06-23 台州市汉达动力科技有限责任公司 A kind of starting-generating two-in-one system of motorcycle
CN108512469A (en) * 2018-04-02 2018-09-07 南京航空航天大学 A kind of permanent magnetism starting-generating system and its control method with fault-tolerant ability

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