CN112532128A - Aviation high-power composite brushless starting power generation system and control method thereof - Google Patents
Aviation high-power composite brushless starting power generation system and control method thereof Download PDFInfo
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- 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
- H02P9/14—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field
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Abstract
The invention discloses an aviation high-power composite brushless starting power generation system and a control method thereof, belonging to the technical field of aviation starting and power supply systems.
Description
Technical Field
The invention discloses an aviation high-power composite brushless starting power generation system and a control method thereof, and belongs to the technical field of aviation starting and power supply systems.
Background
The aviation starting power generation technology is an integrated design which utilizes the reversible principle of a motor to convert electric energy into mechanical energy and convert the mechanical energy into electric energy. When the airplane is started, the electric energy is converted into mechanical energy, namely, a power supply works in an electric state through a power conversion driving motor to drive an engine to rotate to meet the requirement of rotating speed, and the engine ignites to work. After the engine finishes the starting process, the engine drives the motor, and the system converts mechanical energy into electric energy required by the airplane and supplies power to electric equipment of the airplane. The motor has two purposes, so that the size and the weight of airborne equipment are reduced, and the reliability of the whole electrical system is effectively improved. The realization of the dual functions of starting and generating electricity is an important development direction of the advanced airplane electrical system.
With the development of the multi-electric/full-electric airplane technology, a power supply system requires the starting and generating power of a motor to be greatly increased, and a system power supply system develops from a single direct current or alternating current to an alternating current-direct current composite system. The traditional brushed direct-current aviation starting power generation system cannot meet the requirement of working at high altitude for long voyage and seriously restricts the reliability and maintainability of the airplane. In brushless dc starter generator systems for aircraft, a switched reluctance starter generator system is successfully used, for example, US005489810A discloses a switched reluctance starter generator solution, however, a switched reluctance motor requires a position sensor and a power converter in a power generation mode, which reduces system reliability and increases complexity of the system in long-term operation.
The double salient pole starting generator is a novel motor developed on the basis of a switched reluctance motor, has simple structure, high reliability and low cost, and is suitable for high-speed long-endurance running. When the speed-regulating motor is used as a motor, the speed-regulating performance is good, and the four-quadrant operation is easy to realize. When the generator operates, a controllable power converter and a rotor position sensor are not needed, the exciting current can be externally controlled to bidirectionally regulate the output voltage, and therefore the generator has more advantages in power generation compared with a switched reluctance motor. Patent CN103684127B discloses a combined brushless dc start generator system and control method, in which a permanent magnet motor and an electro-magnetic doubly salient motor operate coaxially, the permanent magnet motor operates electrically in the starting stage, the permanent magnet motor serves as an exciter in the generating stage, an excitation source is provided for an excitation winding of the electro-magnetic doubly salient motor, and the electro-magnetic doubly salient motor supplies power to a dc load by adjusting the excitation current. In the scheme, in order to meet the requirement of starting torque, the power of the permanent magnet motor is required to be larger, the system works in a power generation state for a long time, and the system efficiency is low. The patent CN106357164A discloses a double salient pole high voltage dc starting power generation system and a control method, wherein two-stage electro-magnetic doubly salient pole motor armature windings are connected in parallel with a bridge type uncontrolled rectifier circuit respectively and then used as a power generation output end of the starting power generation system, wherein a first electro-magnetic doubly salient pole motor three-phase armature winding is connected with a three-phase full bridge inverter and a push-pull forward converter in sequence respectively, and an input end of the push-pull forward converter is used for starting the starting power generation system, so as to solve the problems of unbalance between a starting power supply voltage and a power generation output voltage and the reduction of the reliability of the system caused by high frequency chopping during starting and running of a high. However, the starting of a single set of winding restricts the starting load capacity, and the requirement of alternating current and direct current power utilization cannot be met.
Disclosure of Invention
The purpose of the invention is:
the invention provides an aviation high-power composite brushless starting power generation system and a control method thereof, and can provide a doubly salient brushless motor aviation starting power generation system based on redundancy, multi-winding, alternating current and direct current dual-output and starting control multiplexing, in particular to an aviation starting power generation system with power of more than 12 kW.
The technical scheme of the invention is as follows:
in one aspect, the present invention provides an aviation high-power composite brushless starting power generation system, comprising: the system comprises a starting generator, a power generation controller, a multiplex starting controller, an AC/DC rectifier, an AC/AC converter, a current detection unit, a first conversion contactor, a second conversion contactor, a direct current contactor, an alternating current contactor, a starting contactor, a first multiplex contactor and a second multiplex contactor;
the starting generator is an electro-magnetic doubly salient reluctance motor, and the motor is coaxially and upwards provided with two main motor stators, two sections of main rotors, a set of exciter and a set of Hall position sensor;
the AC/DC rectifier includes: the device comprises a first bridge type uncontrolled rectifying circuit, a second bridge type uncontrolled rectifying circuit, a first capacitor and a second capacitor;
the AC/AC converter includes: the third bridge type uncontrolled rectifying circuit, the fourth bridge type uncontrolled rectifying circuit, the third capacitor, the fourth capacitor and the DC/AC conversion unit;
the power generation controller includes: the excitation circuit comprises a power generation control unit, an excitation contactor, a fifth bridge type uncontrolled rectifying circuit, an excitation chopper circuit and a diode, wherein the excitation contactor is controlled by the power generation control unit;
the multiplex start controller includes: the control circuit comprises a starting control unit, a first full-bridge inverter circuit and a second full-bridge inverter circuit;
the current detection unit includes: the current transformer comprises a first current transformer, a second current transformer, a third current transformer, a fourth current transformer, a fifth current transformer and a sixth current transformer;
the first conversion contactor, the second conversion contactor, the first multiplexing contactor and the second multiplexing contactor are controlled by a multiplexing starting controller;
the direct current contactor and the starting contactor are controlled by a power generation controller;
the alternating current contactor is controlled by an AC/AC converter;
the power generation controller, the multiplex starting controller and the AC/AC converter can transmit information among each other and with an airplane management system through a data bus;
specifically, a first armature winding, a third armature winding and a partial excitation winding are mounted on the first main motor stator;
a second armature winding, a fourth armature winding and a partial excitation winding are arranged on the second main motor stator;
the first main motor stator part excitation winding and the second main motor stator part excitation winding are connected in series to form a set of excitation winding, and the first armature winding, the second armature winding, the third armature winding and the fourth armature winding share the set of excitation winding;
the exciter comprises permanent magnet steel and an exciter winding;
the Hall position sensor comprises an induction magnetic ring and a Hall sensor;
specifically, the output end of the first armature winding and the output end of the second armature winding are respectively connected with the input end of the current detection unit, the output end of the current detection unit is respectively connected with the first contact of the first switching contactor and the first contact of the second switching contactor, the second contact of the first switching contactor is connected with the input end of the first bridge type uncontrolled rectifying circuit, and the second contact of the second switching contactor is connected with the input end of the second bridge type uncontrolled rectifying circuit;
the output positive end of the first bridge type uncontrolled rectifying circuit is connected with the output positive end of the second bridge type uncontrolled rectifying circuit, the positive end of the first capacitor, the positive end of the second capacitor and the first contact of the direct current contactor;
a second contact of the direct current contactor is used as a positive end of a direct current voltage output end of the starting power generation system;
the output negative end of the first bridge type uncontrolled rectifying circuit is connected with the output negative end of the second bridge type uncontrolled rectifying circuit, the negative end of the first capacitor and the negative end of the second capacitor to serve as the negative end of the direct-current voltage output end of the starting power generation system;
a third contact of the first conversion contactor is respectively connected with the output end of the first full-bridge inverter circuit and a first contact of the first multiplexing contactor, and a second contact of the first multiplexing contactor is connected with the input end of an external first brushless motor and is used as one of multiplexing control output ends of the starting and generating system;
a third contact of the second conversion contactor is respectively connected with the output end of the second full-bridge inverter circuit and a first contact of the second multiplexing contactor, and a second contact of the second multiplexing contactor is connected with the input end of an external second brushless motor and serves as a second multiplexing control output end of the starting power generation system;
specifically, the three-phase output end of the third armature winding and the three-phase output end of the fourth armature winding are respectively connected with the input end of the third bridge type uncontrolled rectifying circuit and the input end of the fourth bridge type uncontrolled rectifying circuit, the positive output terminal of the third bridge type uncontrolled rectifying circuit is connected with the positive terminal of the third capacitor, the positive terminal of the fourth capacitor and the positive input terminal of the DC/AC conversion unit, the negative output end of the third bridge type uncontrolled rectifying circuit is connected with the positive end of the fourth bridge type uncontrolled rectifying circuit, the negative end of the fourth bridge type uncontrolled rectifying circuit is connected with the negative end of the third capacitor, the negative end of the fourth capacitor and the negative input end of the DC/AC conversion unit, the alternating current output end of the DC/AC conversion unit is connected with the first contact of the alternating current contactor, and the second contact of the alternating current contactor is used as the alternating current voltage output end of the starting power generation system;
specifically, the output end of the exciter winding is connected with the first contact of the excitation contactor, the second contact of the excitation contactor is connected with the input end of the fifth bridge type uncontrolled rectifying circuit, the positive output end of the fifth bridge type uncontrolled rectifying circuit is respectively connected with the positive direct-current input end of the excitation chopper circuit and the cathode of the diode, and the negative output end of the fifth bridge type uncontrolled rectifying circuit is connected with the negative direct-current input end of the excitation chopper circuit; the output end of the excitation winding is connected with the output end of the excitation chopper circuit;
specifically, the second contact of the starting contactor is connected with the anode of the diode, and the first contact of the starting contactor, the bus input end of the first full-bridge inverter circuit and the bus input end of the second full-bridge inverter circuit are all connected with an external direct-current power supply and serve as one of the input ends of the starting power generation system;
the output ends of the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer and the sixth current transformer are connected with the input end of the power generation control unit and the input end of the starting control unit, so that the phase currents of the first armature winding and the second armature winding are detected;
the input end of the first bridge type uncontrolled rectifying circuit and the input end of the second bridge type uncontrolled rectifying circuit are connected with the input end of the power generation control unit, so that the voltage of the input ends of the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit is detected;
the output end of the Hall sensor is connected with the input end of the starting control unit, so that the rotor position of the starting generator is detected;
a first contact of the direct current contactor is connected with the input end of the power generation control unit, so that the direct current voltage of the starting power generation system is detected;
the output end of the power generation control unit is connected with the control input end of the excitation chopper circuit, so that the direct-current output voltage of the starting power generation system is adjusted;
specifically, the output end of the starting control unit is connected with the control input ends of the first full-bridge inverter circuit and the second full-bridge inverter circuit, so that the inversion control of the first full-bridge inverter circuit and the second full-bridge inverter circuit is realized;
the first armature winding and the second armature winding have the same number of turns and length;
the third armature winding and the fourth armature winding have the same number of turns and length;
the lengths of the first section of main rotor and the second section of main rotor are the same, and the rotor teeth are staggered by a mechanical angle of 7.5 degrees;
the first capacitor and the third capacitor are electrolytic capacitors; the second capacitor and the fourth capacitor are high-frequency ceramic dielectric capacitors;
the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer and the sixth current transformer are magnetic field balanced current transformers;
preferably, the hall sensor is a locking hall sensor, or a method for detecting the position of the rotor by using a rotary transformer, or a control method without position feedback;
preferably, the first, second, third, fourth and fourth bridge type uncontrolled rectifying circuits are three-phase full-bridge rectifying circuits formed by schottky diodes connected in parallel;
preferably, the first full-bridge inverter circuit and the second full-bridge inverter circuit are three-phase full-bridge inverter circuits formed by connecting multiple MOS transistors in parallel.
In another aspect, the invention provides a control strategy for an aviation high-power composite brushless starting power generation system, which comprises a starting mode control program and a power generation mode control program;
specifically, the starting mode control program receives a starting instruction, the power generation controller closes the starting contactor, and an external direct-current power supply is connected to the bus input ends of the first full-bridge inverter circuit and the second full-bridge inverter circuit and the direct-current input end of the excitation chopper circuit; the excitation chopper circuit regulates the excitation current to be a constant value; the multiplex starting controller closes the first conversion contactor and the second conversion contactor, and the direct-current power supply is inverted into three-phase alternating current through the first full-bridge inverter circuit and the second full-bridge inverter circuit and is connected with the first armature winding and the second armature winding of the starting generator, so that the starting generator is controlled to be in an electric state, and the starting of the aircraft engine is completed; when the rotating speed reaches the upper limit requirement or the starting command is cancelled, the power generation controller disconnects the starting contactor, and disconnects the exciting current output by the exciting chopper circuit, and the multiplex starting controller disconnects the first full-bridge inverter circuit and the second full-bridge inverter circuit, and disconnects the first conversion contactor and the second conversion contactor;
after the aircraft engine is started, the system enters a power generation mode, the starting generator is dragged by the aircraft engine to rotate, the power generation mode control program receives a power generation instruction, the power generation controller closes the excitation contactor, the three-phase alternating current output by the permanent magnet machine winding is rectified into direct current through the excitation contactor and a fifth bridge type uncontrolled rectifying circuit and is connected to an excitation chopper circuit, and the excitation chopper circuit outputs excitation current; the first armature winding, the second armature winding, the third armature winding and the fourth armature winding respectively output three-phase alternating current, the first armature winding and the second armature winding respectively pass through the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit for rectification and conversion, are connected in parallel and then pass through the first capacitor and the second capacitor for filtering, the power generation control unit detects the voltage value, adjusts exciting current output by the exciting chopper circuit, keeps the voltage as a required value, and closes the direct current contactor, so that power is supplied to a direct current bus bar on an airplane. The third armature winding and the fourth armature winding are respectively rectified and transformed by a third bridge type uncontrolled rectifying circuit and a fourth bridge type uncontrolled rectifying circuit, are filtered by a third capacitor and a fourth capacitor after being connected in series, and output required three-phase alternating current through a DC/AC (direct current/alternating current) transforming unit, and the DC/AC transforming unit closes an alternating current contactor so as to supply power for an alternating current bus bar on the airplane; the multiplex starting controller closes the first multiplex contactor and the second multiplex contactor to respectively drive the brushless motor on the machine to work;
specifically, the starting power generation system detects the six-phase current of the first armature winding and the second armature winding and the rotor position of the starting generator through the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer, the sixth current transformer and the hall sensor in the execution process of the starting control program, and inputs the detected six-phase current signal and the detected rotor position signal into the starting control unit, and the starting control unit realizes phase change and current control of the first full-bridge inverter circuit and the second full-bridge inverter circuit;
in the execution process of the power generation control program, the starting power generation system detects six-phase currents of the first armature winding and the second armature winding through the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer and the sixth current transformer, and inputs the detected six-phase current signals into the power generation control unit; the power generation control unit has the functions of outputting direct current by the computing system and judging whether the direct current is over-current or not according to the acquired six-phase current signals; the second function is to calculate the unbalance degree between the phases and judge whether the diodes of the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit have open circuit or short circuit faults;
in the execution process of the power generation control program, the voltage of the input end and the voltage of the output end of the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit are fed back to the power generation control unit by the starting power generation system, and the power generation control unit collects the line voltage and the direct current voltage and has the effects of regulating the exciting current according to the fed back voltage of the output end to keep the direct current output voltage of the system stable; action two judges whether the DC output voltage of the system has overvoltage or undervoltage;
the power generation control unit acquires the line voltage as an auxiliary condition of the undervoltage of the direct current output voltage, and does not judge the line voltage when the direct current output voltage is in a normal range; when the voltage of the direct current output voltage is lower than the direct current under-voltage threshold, the power generation control unit carries out under-voltage protection after time delay confirmation; when the direct current output voltage is lower than the normal regulating value but higher than the direct current under-voltage threshold, the power generation control unit additionally judges whether the average value of the six-line voltage is lower than the alternating current under-voltage threshold or not, and if the average value of the six-line voltage is lower than the alternating current under-voltage threshold, under-voltage protection is carried out after delay confirmation; the AC undervoltage threshold is 0.74 times the DC undervoltage threshold.
The invention has the beneficial effects that:
compared with the prior art, the invention has the following beneficial effects:
1. the brushless starting power generation system of the invention has the advantages that the motor simultaneously outputs direct current and alternating current system power supplies, the number of airborne components such as engine accessories, casings, heat dissipation and installation is reduced, and the weight of the whole airplane system is reduced.
2. The brushless starting power generation system of the invention separates the starting power circuit from the generating power circuit by arranging the switching contactor, and does not cause voltage impact on a non-working power circuit under the condition of unbalanced starting and generating voltage amplitudes, thereby improving the reliability of the system.
3. The starting controller of the brushless starting power generation system has a multiplexing function, and after the starting of the engine is finished, the multiplexing starting controller can be switched to control the brushless motors on the two machines to work, so that the working efficiency of the system is improved.
4. The current transformer of the brushless starting power generation system has a multiplexing function, and the number of transformers is reduced. When starting, phase current is provided for the starting control unit, and current control is realized; when generating electricity, phase current is provided for the electricity generation control unit, and protection of overcurrent of the motor and open circuit and short circuit of a power tube of the rectifying circuit is realized.
5. The power generation control unit of the brushless starting power generation system simultaneously acquires alternating current and direct current voltages in front of and behind the rectifying circuit, and can accurately judge direct current output overvoltage and undervoltage faults of the system. The method solves the problems that in the prior brushless direct current power generation system, because the diode of the bridge type uncontrolled rectifying circuit has reverse isolation characteristics and the direct current bus bar is connected with the storage battery in parallel, when the generator has no output, the direct current feedback voltage acquired by the system is the voltage of the storage battery, and is still higher than the undervoltage threshold, so that the undervoltage fault output by the generator can not be accurately judged.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a block diagram of an aviation high-power composite brushless starting power generation system of the present invention;
FIG. 2 is a sectional view of the main stator and main rotor structure of the starter-generator of the present invention;
FIG. 3 is a flow chart of a system startup control strategy according to the present invention;
FIG. 4 is a flow chart of a system power generation control strategy according to the present invention;
FIG. 5 is a flow chart of the multiplexing control strategy of the system multiplexing start controller according to the present invention;
FIG. 6 is a flow chart of the diode fault determination for the first and second bridge type uncontrolled rectifying circuits of the present invention;
FIG. 7 is a flow chart of the system DC output voltage under-voltage fault determination of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention. The specific embodiment of the invention is described in the following with reference to the drawings, and provides an aviation high-power composite brushless starting power generation system, which comprises: the system comprises a starting generator, a power generation controller, a multiplex starting controller, an AC/DC rectifier, an AC/AC converter, a current detection unit, a first conversion contactor, a second conversion contactor, a direct current contactor, an alternating current contactor, a starting contactor, a first multiplex contactor and a second multiplex contactor.
As shown in fig. 1, a block diagram of an aviation high-power composite brushless starting power generation system and a control strategy in one possible implementation of this embodiment includes: starter generator, power generation controller, multiplex starter controller, DC/AC conversion unit, AC/AC converter, current detection unit, first conversion contactor K1The second switching contactor K2D.C. contactor K3AC contactor K4Starting contactor K5First multiplexing contactor K6A second multiplexing contactor K7. The starter generator is an electrically excited doubly salient reluctance motor with 18kW total power, and a first main stator comprises a first armature winding W1And a third armature winding W3The first main stator comprises a second armature winding W2And a fourth armature winding W4Excitation winding WfAxially connected in series to two main stators, exciter windings WPMGAnd the Hall sensor is arranged at the end part of the stator. The AC/DC rectifier comprises a first bridge type uncontrolled rectifying circuit, a second bridge type uncontrolled rectifying circuit, a first capacitor and a second capacitor. The AC/AC converter comprises a third bridge type uncontrolled rectifying circuit, a fourth bridge type uncontrolled rectifying circuit, a third capacitor, a fourth capacitor and a DC/AC conversion unit. The power generation controller comprises a power generation control unit and an excitation contactor K8A fifth bridge type uncontrolled rectifying circuit, an excitation chopper circuit and a diode D1. The multiplexing starting controller comprises a starting control unit, a first full-bridge inverter circuit and a second full-bridge inverter circuit. The current detection unit comprises a first current transformer T1A second current transformer T2And a third current transformer T3And a fourth current transformer T4The fifth current transformer T5And a sixth current transformer T6。
First armature winding W1A second armature winding W2Respectively pass through six current transformers in the current detection unit and then are in contact with the first conversion contactor K1And a second transfer contactor K2Is connected to the first contact of the first contact,first conversion contactor K1And a second transfer contactor K2The second contact of the AC/DC rectifier is respectively connected with the input ends of a first bridge type uncontrolled rectifying circuit and a second bridge type uncontrolled rectifying circuit in the AC/DC rectifier, the output ends of the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit are connected in parallel and are filtered through a first capacitor C1 and a second capacitor C2, and the positive output end DC + of the AC/DC rectifier is connected with a direct current contactor K3First contact connection of, dc contactor K3The second contact of the second switch is used as the positive end of the system direct-current voltage output end; the output negative terminal of the AC/DC rectifier DC-is connected to ground as the negative terminal of the system DC voltage output.
First conversion contactor K1And a second transfer contactor K2The third contact respectively multiplexes the output end of the starting controller and the first multiplexing contactor K6First contact and second multiplexing contactor K7Is connected to the first contact of (1).
Third armature winding W3Fourth armature winding W4Respectively connected with the input ends of a third bridge type uncontrolled rectifying circuit and a fourth bridge type uncontrolled rectifying circuit in the AC/AC converter, the output ends of the third bridge type uncontrolled rectifying circuit and the fourth bridge type uncontrolled rectifying circuit are connected in series and pass through a third capacitor C3A fourth capacitor C4After filtering, the output end A, B, C, N of the AC/AC converter is connected with the input end of the DC/AC conversion unit and the AC current contactor K3Is connected to ground, ac contactor K3As a system ac voltage output.
Exciter winding WPMGAnd an excitation contactor K inside the power generation controller8The second contact is connected with a fifth bridge type uncontrolled rectifying circuit, and the positive output end of the fifth bridge type uncontrolled rectifying circuit is connected with a diode D1After the cathodes are connected in parallel, the cathode is used as an input excitation power supply of an excitation chopper circuit; and the output negative end of the fifth bridge type uncontrolled rectifying circuit is used as the input excitation power supply negative end of the excitation chopper circuit. Output end of excitation chopper circuit and excitation winding WfAnd (4) connecting.
The Hall sensor collects the rotor position theta of the starter generator and inputs the position theta to the internal starting control unit of the multiplex starting controller.
Current transformer T in current detection unit1、T2、T3、T4、T5、T6Outputs six-phase current detection signal ia1、ib1、ic1、ia2、ib2、ic2Respectively input to the internal starting control unit of the multiplex starting controller and the internal power generation control unit of the power generation controller.
Input end line voltage U of AC/DC rectifiera1b1、Ub1c1、Uc1a1、Ua2b2、Ub2c2、Uc2a2And the output end voltage DC + is respectively input to the power generation control unit in the power generation controller.
The external DC power supply is respectively connected with the power input end of the multiplex starting controller and the starting contactor K5First contact, starting contactor K5Second contact diode D1And the positive end of the output of the fifth bridge type uncontrolled rectifying circuit is connected in parallel.
The internal start control unit of the multiplex start controller outputs a first full-bridge inverter circuit driving signal PWM11-16And a second full-bridge inverter circuit driving signal PWM21-26First switching contactor K1The second switching contactor K2First multiplexing contactor K6A second multiplexing contactor K7A control signal. The power generation control unit in the power generation controller outputs the drive signal PWM of the excitation chopper circuitDExcitation contactor K8D.C. contactor K3Starting contactor K5A control signal. AC/AC converter output AC contactor K4A control signal. The power generation controller, the multiplex start controller and the AC/AC converter are communicated with each other and the airplane management system through data buses.
Fig. 2 is a sectional view of the main stator and rotor structure of the starting generator of the present invention, wherein the main stator 1 and the main stator 2 are both salient pole structures, the stator teeth are uniformly distributed, the stator 1 is provided with three sets of windings, namely a first armature winding 3, a third armature winding 5 and an excitation winding 7, and the stator 2 is provided with three sets of windings, namely a second armature winding 4, a fourth armature winding 6 and an excitation winding 7. The excitation winding is shared by the stators 1 and 2 and is arranged 5 in 4 basic slots, three phases of armature windings A, B and C are sequentially sleeved on three teeth on the inner side of the excitation winding, and the first armature winding 3 and the second armature winding 5 are close to the teeth of the stators. The main rotor 8 and the main rotor 9 are both salient pole structures, the teeth of the rotors are uniformly distributed, and the corresponding rotor teeth of the two rotors are staggered by 7.5 degrees of mechanical angle (equivalent to 60 degrees of electrical angle).
FIG. 3 is a flow chart of a system start control strategy of the invention, wherein a start command is received and a start contactor K is closed5Adjusting PWMDThe excitation chopper circuit keeps the excitation current at a constant value; closing the first switching contact K1The second switching contactor K2Based on the motor rotor position theta and phase current detection signal i outputted from the Hall sensora1、ib1、ic1、ia2、ib2、ic，PWM11-16And PWM21-26Driving the first full-bridge inverter circuit and the second full-bridge inverter circuit to invert the direct-current power supply into three-phase alternating current which is input to a first armature winding and a second armature winding of the starter generator, so that the starter generator is controlled to be in an electric state, and the starting of an aircraft engine is completed; when the rotating speed reaches the upper limit or the starting command is cancelled, the PWM is closedD、PWM11-16And PWM21-26Opening the starting contactor K5First switching contactor K1The second switching contactor K2。
FIG. 4 is a flow chart of a system power generation control strategy in the invention, after the aircraft engine is started, the starting generator is dragged to rotate by the aircraft engine, the system enters a power generation mode, the power generation control unit receives a power generation instruction, and the excitation contactor K is closed8Detecting DC output voltage value DC +, regulating PWMDThe duty ratio controls the exciting current output by the exciting chopper circuit, keeps the voltage DC + as a required value, and closes the direct current contactor K3Thereby supplying power to the dc bus bars on the aircraft. At the same time, the DC/AC conversion unit outputs the required three-phase alternating current and closes the alternating current contactor K4Thereby handing over to the aircraftThe current bus bar supplies power.
FIG. 5 is a flow chart of the multiplexing control strategy of the system multiplexing start controller of the present invention, after the start is completed, the multiplexing start controller closes the first multiplexing contactor K after receiving the command for controlling the brushless motor6A second multiplexing contactor K7And respectively driving the two external brushless motors to work.
FIG. 6 is a flow chart of the fault determination for the rectifier diodes of the first and second uncontrolled bridge rectifier circuits according to the present invention, wherein the phase current detection signal i detected by the power generation control unit is used in the power generation statea1、ib1、ic1、ia2、ib2、ic2Respectively calculate ia1、ib1、ic1Maximum difference between, ia2、ib2、ic2If the difference value exceeds the imbalance threshold, and after time delay confirmation, the open circuit fault of the corresponding bridge type uncontrolled rectifying circuit is judged; and calculating the difference value between the average value of the three-phase current corresponding to the bridge type uncontrolled rectifying circuit and the average value of the three-phase current of the other bridge type uncontrolled rectifying circuit, if the difference value exceeds a short-circuit threshold and is subjected to time delay confirmation, judging that the short-circuit fault of the bridge type uncontrolled rectifying circuit occurs, and otherwise, judging that the open-circuit fault occurs.
FIG. 7 is a flow chart of the system DC output voltage under-voltage fault determination of the present invention, wherein in the power generation state, the power generation control unit detects the line voltage Ua1b1、Ub1c1、Uc1a1、Ua2b2、Ub2c2、Uc2a2And the voltage DC + of the output end, if the DC + meets the normal voltage regulation range, the system output is considered to be normal; if DC + is lower than the DC undervoltage protection threshold UrefDCAnd determining the direct current output voltage undervoltage fault of the system after time delay confirmation; if the DC + is lower than the normal voltage regulation range but higher than the DC undervoltage protection threshold, increasing the judgment line voltage Ua1b1、Ub1c1、Uc1a1、Ua2b2、Ub2c2、Uc2a2Whether or not the average value of (1) is lower than UrefACIf the voltage is lower than the threshold and is confirmed by time delay, judging the direct current output voltage undervoltage fault of the system, wherein UrefAC＝UrefDC/1.35。
The technology of the invention applies a brushless direct current starting power generation system with the power of 18kW and is assembled on a multi-type unmanned aerial vehicle.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. An aviation high-power composite brushless starting power generation system is characterized by comprising: the system comprises a starting generator, a power generation controller, a multiplex starting controller, an AC/DC rectifier, an AC/AC converter, a current detection unit, a first conversion contactor, a second conversion contactor, a direct current contactor, an alternating current contactor, a starting contactor, a first multiplex contactor and a second multiplex contactor;
the starting generator is an electro-magnetic doubly salient reluctance motor and comprises two main motor stators, two sections of main rotors, a set of exciter and a set of Hall position sensors; a first armature winding, a third armature winding and a partial excitation winding are mounted on the first main motor stator; a second armature winding, a fourth armature winding and a partial excitation winding are arranged on the second main motor stator; the first main motor stator part excitation winding and the second main motor stator part excitation winding are connected in series to form a set of excitation winding, and the first armature winding, the second armature winding, the third armature winding and the fourth armature winding share the set of excitation winding; the exciter comprises permanent magnet steel and an exciter winding; the Hall position sensor comprises an induction magnetic ring and a Hall sensor;
the AC/DC rectifier includes: the device comprises a first bridge type uncontrolled rectifying circuit, a second bridge type uncontrolled rectifying circuit, a first capacitor and a second capacitor;
the AC/AC converter includes: the third bridge type uncontrolled rectifying circuit, the fourth bridge type uncontrolled rectifying circuit, the third capacitor, the fourth capacitor and the DC/AC conversion unit;
the power generation controller includes: the excitation circuit comprises a power generation control unit, an excitation contactor, a fifth bridge type uncontrolled rectifying circuit, an excitation chopper circuit and a diode, wherein the excitation contactor is controlled by the power generation control unit;
the multiplex start controller includes: the control circuit comprises a starting control unit, a first full-bridge inverter circuit and a second full-bridge inverter circuit;
the current detection unit includes: the current transformer comprises a first current transformer, a second current transformer, a third current transformer, a fourth current transformer, a fifth current transformer and a sixth current transformer;
the output end of the first armature winding and the output end of the second armature winding are respectively connected with the input end of the current detection unit, the output end of the current detection unit is respectively connected with the first contact of the first switching contactor and the first contact of the second switching contactor, the second contact of the first switching contactor is connected with the input end of the first bridge type uncontrolled rectifying circuit, and the second contact of the second switching contactor is connected with the input end of the second bridge type uncontrolled rectifying circuit;
the output positive end of the first bridge type uncontrolled rectifying circuit is connected with the output positive end of the second bridge type uncontrolled rectifying circuit, the positive end of the first capacitor, the positive end of the second capacitor and the first contact of the direct current contactor;
a second contact of the direct current contactor is used as a positive end of a direct current voltage output end of the starting power generation system;
the output negative end of the first bridge type uncontrolled rectifying circuit is connected with the output negative end of the second bridge type uncontrolled rectifying circuit, the negative end of the first capacitor and the negative end of the second capacitor to serve as the negative end of the direct-current voltage output end of the starting power generation system;
a third contact of the first conversion contactor is respectively connected with the output end of the first full-bridge inverter circuit and a first contact of the first multiplexing contactor, and a second contact of the first multiplexing contactor is connected with the input end of an external first brushless motor and is used as one of multiplexing control output ends of the starting and generating system;
a third contact of the second conversion contactor is respectively connected with the output end of the second full-bridge inverter circuit and a first contact of the second multiplexing contactor, and a second contact of the second multiplexing contactor is connected with the input end of an external second brushless motor and serves as a second multiplexing control output end of the starting power generation system;
the three-phase output end of the third armature winding and the three-phase output end of the fourth armature winding are respectively connected with the input end of the third bridge type uncontrolled rectifying circuit and the input end of the fourth bridge type uncontrolled rectifying circuit, the positive output terminal of the third bridge type uncontrolled rectifying circuit is connected with the positive terminal of the third capacitor, the positive terminal of the fourth capacitor and the positive input terminal of the DC/AC conversion unit, the negative output end of the third bridge type uncontrolled rectifying circuit is connected with the positive end of the fourth bridge type uncontrolled rectifying circuit, the negative end of the fourth bridge type uncontrolled rectifying circuit is connected with the negative end of the third capacitor, the negative end of the fourth capacitor and the negative input end of the DC/AC conversion unit, the alternating current output end of the DC/AC conversion unit is connected with the first contact of the alternating current contactor, and the second contact of the alternating current contactor is used as the alternating current voltage output end of the starting power generation system;
the output end of the exciter winding is connected with the first contact of the exciting contactor, the second contact of the exciting contactor is connected with the input end of the fifth bridge type uncontrolled rectifying circuit, the output positive end of the fifth bridge type uncontrolled rectifying circuit is respectively connected with the direct current positive input end of the exciting chopper circuit and the diode cathode, and the output negative end of the fifth bridge type uncontrolled rectifying circuit is connected with the direct current negative input end of the exciting chopper circuit; the output end of the excitation winding is connected with the output end of the excitation chopper circuit;
the second contact of the starting contactor is connected with the anode of the diode, the first contact of the starting contactor, the bus input end of the first full-bridge inverter circuit and the bus input end of the second full-bridge inverter circuit are connected with an external direct-current power supply to serve as one of the input ends of the starting power generation system.
2. The system of claim 1,
the output ends of the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer and the sixth current transformer are connected with the input end of the power generation control unit and the input end of the starting control unit, so that the phase currents of the first armature winding and the second armature winding are detected;
the input end of the first bridge type uncontrolled rectifying circuit and the input end of the second bridge type uncontrolled rectifying circuit are connected with the input end of the power generation control unit, so that the voltage of the input ends of the first bridge type uncontrolled rectifying circuit and the second bridge type uncontrolled rectifying circuit is detected;
the output end of the Hall sensor is connected with the input end of the starting control unit, so that the rotor position of the starting generator is detected;
a first contact of the direct current contactor is connected with the input end of the power generation control unit, so that the direct current voltage of the starting power generation system is detected;
the output end of the power generation control unit is connected with the control input end of the excitation chopper circuit, so that the direct-current output voltage of the starting power generation system is adjusted;
the output end of the starting control unit is connected with the control input ends of the first full-bridge inverter circuit and the second full-bridge inverter circuit, so that inversion control of the first full-bridge inverter circuit and the second full-bridge inverter circuit is realized.
3. The system of claim 1,
the first conversion contactor, the second conversion contactor, the first multiplexing contactor and the second multiplexing contactor are controlled by a multiplexing starting controller;
the direct current contactor and the starting contactor are controlled by a power generation controller;
the alternating current contactor is controlled by an AC/AC converter;
the power generation controller, the multiplex start controller and the AC/AC converter can carry out information transmission among each other and with an airplane management system through a data bus.
4. The system of claim 1,
the first armature winding and the second armature winding have the same number of turns and length;
the third armature winding and the fourth armature winding have the same number of turns and length;
the lengths of the first section of main rotor and the second section of main rotor are the same, and the rotor teeth are staggered by a mechanical angle of 7.5 degrees;
the first capacitor and the third capacitor are electrolytic capacitors; the second capacitor and the fourth capacitor are high-frequency ceramic dielectric capacitors;
the first current transformer, the second current transformer, the third current transformer, the fourth current transformer, the fifth current transformer and the sixth current transformer are magnetic field balanced current transformers.
5. The system of claim 1, wherein the hall sensor is a locking type hall sensor, or a method of detecting a rotor position using a resolver, or a control method without position feedback.
6. The system of claim 1, wherein the first, second, third, fourth and fourth uncontrolled bridge rectifier circuits are three-phase full-bridge rectifier circuits with schottky diodes connected in parallel.
7. The system according to claim 1, wherein the first full-bridge inverter circuit and the second full-bridge inverter circuit are three-phase full-bridge inverter circuits formed by connecting multiple MOS (metal oxide semiconductor) tubes in parallel.
8. A method of controlling the aviation high power composite brushless starting power generation system of claim 1, wherein the method comprises a starting mode control procedure, a power generation mode control procedure;
the starting mode control program receives a starting instruction, the power generation controller closes the starting contactor, and an external direct-current power supply is connected to the bus input ends of the first full-bridge inverter circuit and the second full-bridge inverter circuit and the direct-current input end of the excitation chopper circuit; the excitation chopper circuit regulates the excitation current to be a constant value; the multiplex starting controller closes the first conversion contactor and the second conversion contactor, and the direct-current power supply is inverted into three-phase alternating current through the first full-bridge inverter circuit and the second full-bridge inverter circuit and is connected with the first armature winding and the second armature winding of the starting generator, so that the starting generator is controlled to be in an electric state, and the starting of the aircraft engine is completed; when the rotating speed reaches the upper limit requirement or the starting command is cancelled, the power generation controller disconnects the starting contactor, and disconnects the exciting current output by the exciting chopper circuit, and the multiplex starting controller disconnects the first full-bridge inverter circuit and the second full-bridge inverter circuit, and disconnects the first conversion contactor and the second conversion contactor;
after the aircraft engine is started, the system enters a power generation mode, the starting generator is dragged by the aircraft engine to rotate, the power generation mode control program receives a power generation instruction, the power generation controller closes the excitation contactor, the three-phase alternating current output by the permanent magnet machine winding is rectified into direct current through the excitation contactor and a fifth bridge type uncontrolled rectifying circuit and is connected to an excitation chopper circuit, and the excitation chopper circuit outputs excitation current; the first armature winding, the second armature winding, the third armature winding and the fourth armature winding respectively output three-phase alternating current, the first armature winding and the second armature winding respectively carry out rectification transformation through a first bridge type uncontrolled rectifying circuit and a second bridge type uncontrolled rectifying circuit, and then carry out filtering through a first capacitor and a second capacitor after being connected in parallel, the power generation control unit detects the voltage value, adjusts the exciting current output by the exciting chopper circuit, keeps the voltage as a required value, and closes the direct current contactor, so that power is supplied to a direct current bus bar on the airplane; the third armature winding and the fourth armature winding are respectively rectified and transformed by a third bridge type uncontrolled rectifying circuit and a fourth bridge type uncontrolled rectifying circuit, are filtered by a third capacitor and a fourth capacitor after being connected in series, and output required three-phase alternating current through a DC/AC (direct current/alternating current) transforming unit, and the DC/AC transforming unit closes an alternating current contactor so as to supply power for an alternating current bus bar on the airplane; the multiplex starting controller closes the first multiplex contactor and the second multiplex contactor to respectively drive the brushless motor on the machine to work.
9. The control method according to claim 8,
the power generation control unit acquires line voltage as an auxiliary condition of undervoltage of the direct current output voltage, and when the direct current output voltage is lower than a normal regulating value but higher than a direct current undervoltage threshold, judgment on the line voltage is added.
10. The control method according to claim 9, wherein the determination method of the line voltage is as follows:
when the direct current output voltage is in a normal range, the power generation control unit does not judge the line voltage;
when the voltage of the direct current output voltage is lower than the direct current under-voltage threshold, the power generation control unit carries out under-voltage protection after time delay confirmation;
when the direct current output voltage is lower than the normal regulating value but higher than the direct current under-voltage threshold, the power generation control unit additionally judges whether the average value of the six-line voltage is lower than the alternating current under-voltage threshold or not, and if the average value of the six-line voltage is lower than the alternating current under-voltage threshold, under-voltage protection is carried out after delay confirmation; the AC undervoltage threshold is 0.74 times the DC undervoltage threshold.
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