CN114865965A - Aviation low-voltage direct-current three-stage generator power supply system and design method - Google Patents

Aviation low-voltage direct-current three-stage generator power supply system and design method Download PDF

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Publication number
CN114865965A
CN114865965A CN202210563283.5A CN202210563283A CN114865965A CN 114865965 A CN114865965 A CN 114865965A CN 202210563283 A CN202210563283 A CN 202210563283A CN 114865965 A CN114865965 A CN 114865965A
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voltage
current
output
terminal
power supply
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Inventor
薛开昶
甘忠文
袁光伟
龙江
顾兴阳
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Guizhou Aerospace Linquan Motor Co Ltd
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Guizhou Aerospace Linquan Motor Co Ltd
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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
    • H02P9/26—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices
    • H02P9/30—Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
    • 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
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/20—Structural association with auxiliary dynamo-electric machines, e.g. with electric starter motors or exciters
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M5/00—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases
    • H02M5/40—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc
    • H02M5/42—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters
    • H02M5/44—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac
    • H02M5/453—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal
    • H02M5/458—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
    • H02M5/4585—Conversion of ac power input into ac power output, e.g. for change of voltage, for change of frequency, for change of number of phases with intermediate conversion into dc by static converters using discharge tubes or semiconductor devices to convert the intermediate dc into ac using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only having a rectifier with controlled elements
    • 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
    • H02P9/04—Control effected upon non-electric prime mover and dependent upon electric output value of the generator
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
    • H02P9/08—Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Control Of Eletrric Generators (AREA)

Abstract

A power supply system of three-stage generator for aviation low-voltage direct current comprises a three-stage starting generator and a starting generator controller, wherein the three-stage starting generator comprises a permanent magnet auxiliary exciter, a main exciter, a rotary rectifier tube, a main motor and a rotary transformer, the starting generator controller comprises an MOS tube three-phase full bridge, an alternating current excitation power supply, a voltage regulator, an auxiliary power supply, a control circuit and a current sensor S F And S dc . At the time of starting, makeThe starting process works in a maximum torque current ratio mode, and drives the three-stage starter generator to rotate to the engine ignition speed from rest. During power generation, the voltage regulator outputs exciting current to regulate the three-phase AC voltage value output by the main motor to realize the DC voltage V dc Voltage stabilization control of (3); the three-phase alternating current voltage v output by the main motor is realized through the three-phase full bridge of the MOS tube M To a direct voltage V dc On the other hand to achieve a voltage V dc And boost control when the voltage is too low.

Description

Aviation low-voltage direct-current three-stage generator power supply system and design method
Technical Field
The invention belongs to the technical field of electronic circuits, and particularly relates to a three-stage generator power supply system for aviation low-voltage direct current and a design method.
Background
For an aerial man-machine, the requirement on reliability is high, and the fault diffusion can be prevented by de-excitation of the motor after the fault occurs; the overload capacity of 1.5 times of rated current, 5min, 2 times of rated current and 5s is required when normal power generation voltage stabilization output is carried out; the capability of outputting 3 times of short-circuit current is required; it is desirable to have less high band ripple. For aircrafts below 12kW, 28V low-voltage direct current is generally adopted to supply power to airborne equipment.
The three-stage starter generator power system comprises a three-stage starter generator and a starter generator controller, wherein the three-stage starter generator is used for converting mechanical energy and variable-voltage variable-frequency alternating current energy. In a starting state, the starter generator controller provides alternating current exciting current for the starter generator, converts direct current electric energy provided by the starting power supply into variable voltage variable frequency alternating current electric energy, supplies power for the three-stage generator, and drives the motor to reach the ignition rotating speed of the engine from a static state; in a power generation state, the starter generator controller stabilizes the variable frequency alternating current voltage output by the three-stage starter generator by adjusting the exciting current and converts the constant voltage alternating current voltage into 28V stabilized direct current to supply power to the aviation onboard equipment.
For the three-stage motor, the high-voltage power system and the generator power system are commonly used, but the three-stage motor power system has the following disadvantages:
1) the power supply is generally applied to a high-voltage power supply system, and is still less applied to the field of low-voltage direct-current power supply systems;
2) the method is generally applied to a generator power system, and the application of the starter generator power system is in a development stage.
For a starter generator system for a low-voltage direct-current power supply system, a direct-current brushed starter generator system is generally adopted by a person at present. The direct current brush starting generator system has the advantages of high power density and simple control optimization. However, the dc brush-start generator has the following disadvantages:
1) the fault rate of the direct current brush starting generator phase converter is high, especially in the high-altitude operation environment;
2) the carbon brush of the direct current brush starting generator has short service time and needs to be replaced periodically;
3) during operation, the carbon dust falling from the carbon brush can reduce the insulation performance of the motor.
The power supply system of the permanent magnet starting generator is commonly adopted in the field of aviation unmanned machines, the power supply system of the permanent magnet starting generator has the advantages of simple motor design and high efficiency, but the power supply system of the permanent magnet starting generator has the following defects:
1) the permanent magnet starting generator adopts permanent magnet excitation, and after a fault occurs, the safety of a starting generator power supply system cannot be ensured through demagnetization;
2) during power generation, the permanent magnet starter generator cannot perform power generation and voltage stabilization in a time-varying mode by adjusting exciting current, the power density of a starter generator controller is low, and the realization of power generation power of more than 4kW is difficult;
3) after 1.5 times rated current, 5min, 2 times rated current and 5s overload capacity are considered, the power density of the power supply system of the permanent magnet starter generator has no obvious advantages compared with a three-level starter generator;
4) 3 times of short-circuit current output capacity is difficult to realize by a permanent magnet starting generator power supply system;
5) when generating electricity, the starting generator controller needs to adopt a high-frequency switching power supply technology to generate electricity and stabilize voltage, although the output power supply has small ripples, the high-frequency ripple frequency spectrum hardly meets the requirements of relevant standards.
Disclosure of Invention
In order to solve the technical problem, the invention provides a three-stage generator power supply system for aviation low-voltage direct current and a design method.
The invention is realized by the following technical scheme.
The invention provides a three-stage generator power supply system for aviation low-voltage direct current, which comprises a three-stage starting generator and a starting generator controller, wherein the three-stage starting generator comprises a permanent magnet auxiliary exciter, a main exciter, a rotary rectifying tube, a main motor and a rotary transformer; the starter generator controller comprises an MOS tube three-phase full bridge, an AC excitation power supply, a voltage regulator, an auxiliary power supply, a control circuit and a current sensor S F And a current sensor S dc (ii) a The permanent magnet auxiliary excitation stator armature winding W PMG Outputting three-phase alternating current v PWM A, B and C terminals are connected to the auxiliary power supply and A, B and C input terminals of a voltage regulator, respectively, and the rotor armature winding W of the main exciter EM Outputting three-phase alternating current v EM Excitation winding W of main motor rotor through rotating rectifier ME Stator field winding W of connected main exciter EE The F + end and the F-end are connected with the output end of the AC excitation power supply and the output end of the voltage regulator, and the stator armature winding W of the main motor MM Three-phase alternating current v M A, B and C ends are respectively connected with A, B and C ends of MOS tube three-phase full bridge, the rotary transformer stator outputs speed position signal P and is connected with control circuit, DC bus Vdc The + end and the-end of the direct current bus are respectively connected with a three-phase full bridge of the MOS tube Adc Plus and minus terminals of AC excitation power supply input V Bi The positive end and the negative end of the voltage regulator, the positive end and the negative end of the output power supply input and the control circuit are connected, and the negative end of the voltage regulator is connected with the direct current bus V dc Is connected with the end of the MOS tube, and the three-phase alternating current signal i is output by the three-phase full bridge of the MOS tube ABC A driving signal G connected with the control circuit and output by the control circuit A A driving signal G connected with the three-phase full bridge of the MOS tube and output by the control circuit B And a switch control signal S B A driving signal G connected with the AC excitation power supply and output by the control circuit C And a switch control signal S C Is connected with a voltage regulator and an auxiliary power supplyTwo-way power output V c1 、V c2 A current signal I connected with the control circuit and output by the auxiliary power supply D A power supply enable signal E connected with the control circuit and output by the control circuit n Connected to an auxiliary power supply, current sensor S dc Power terminal, output signal I dc Respectively connected with the DC bus V dc Is connected with the control circuit, and the current sensor S F The power end and the output signal iF are respectively connected with the excitation winding W EE The F + end of the switch is connected with the control circuit.
Furthermore, the MOS three-phase full bridge comprises an A-phase bridge arm, a B-phase bridge arm, a C-phase bridge arm and a filter capacitor C dc Current sensor S A1 、S A2 And S A3 Driving signal G A Comprising G A1 、 G A2 、G A3 、G A4 、G A5 And G A6 Three-phase alternating current i ABC Includes i A 、i B And i C (ii) a A end of the MOS three-phase full bridge and an A-phase bridge arm upper tube Q A1 Source and lower tube Q A2 The drain electrode of the bridge arm A is connected with the upper tube Q A1 Drain electrode of and DC bus V Adc The + terminal of the A-phase bridge arm lower tube Q is connected A2 Source S and dc bus V Adc Is connected with the end B of the MOS three-phase full bridge and the upper tube Q of the B-phase bridge arm A3 Source S and lower tube Q of A4 Drain electrode D of the bridge arm B is connected with a tube Q on the bridge arm B A3 Drain electrode of and DC bus V Adc Is connected with the positive end of the B-phase bridge arm lower tube Q A4 Source electrode and DC bus V Adc Is connected with the end C of the MOS three-phase full bridge and the upper tube Q of the C-phase bridge arm A5 Source and lower tube Q A6 Drain electrode of (1) is connected, and the upper tube Q of C-phase bridge arm A5 Drain electrode of and DC bus V Adc Is connected with the positive end of the C-phase bridge arm lower tube Q A6 Source electrode and DC bus V Adc Is connected to the terminal of the filter capacitor C Adc Both ends of the direct current bus V are respectively connected with the direct current bus V Adc Is connected with the positive terminal and the negative terminal, and a current sensor S A1 、S A2 And S A3 Respectively connected to terminals A, B and C, a current sensor S A1 、S A2 And S A3 Respectively with the output signal i A 、i B And i C Corresponding connection, the drive signal G A1 、G A2 、G A3 、G A4 、G A5 And G A6 Are respectively connected with Q A1 、Q A2 、Q A3 、Q A4 、Q A5 And Q A6 The corresponding gate is connected.
Further, the AC excitation power supply comprises a diode D B1 A plurality of boost DC/DC modules and a filter capacitor C B Power tube Q B1 、Q B2 、Q B3 And Q B4 SCR of relay, drive signal G B Comprising G B1 、G B2 、G B3 And G B4 (ii) a Is formed by an input V Bi And a diode D B1 Is connected to the anode of diode D B1 Is respectively connected with the input + ends of a plurality of boosting DC/DC modules, and the input V Bi Is connected with the input ends of a plurality of boosting DC/DC modules, and the output ends of the boosting DC/DC modules are respectively connected with the positive end and the negative end of a direct current bus V s Are connected to the + terminal and the-terminal of, an input V Bi End of and DC bus V s Is connected to the terminal of the filter capacitor C B DC bus V with two ends respectively s Are connected to the + terminal and the-terminal of Q B1 Drain electrode of and DC bus V s The + end of the terminal is connected; the relay SCR is provided with two switches, wherein the input end of the first switch is connected with Q B1 Source and Q of B2 Drain electrode connection of, Q B2 Source electrode and DC bus V s Is connected to the minus terminal, Q B3 Drain electrode of and DC bus V s Is connected with the + terminal of the relay SCR, the input terminal of the second switch of the relay SCR is connected with Q B3 Source electrodes S and Q of B4 Drain electrode connection of, Q B4 Source electrode and DC bus V s Of the output of the switch in the relay SCR and the output v Bo Connecting, driving signal G B1 、G B2 、G B3 And G B4 Are respectively connected with Q B1 、Q B2 、Q B3 And Q B4 Is connected to the gate of, switches the control signal S B And is connected with the control end of the relay SCR.
Further, the voltage regulator comprises a diode D C1 、D C2 、D C3 、D C4 、D C5 、 D C6 And D C7 Power tube Q C1 、Q C2 And Q C3 Filter capacitor C C Relay GCR, drive signal G C Comprising G C1 ～G C3 (ii) a A terminal and D terminal of voltage regulator C1 And D C2 Is connected with the cathode of the voltage regulator, and the B end of the voltage regulator is connected with the D end C3 And D C4 Is connected with the cathode of the voltage regulator, the C end of the voltage regulator is connected with the D C5 And D C6 The cathode of (a) is connected; d C1 、D C3 And D C5 Cathode and DC bus V G Is connected to the + terminal, D C2 、D C4 And D C6 Anode and dc bus V G Is connected to the terminal of the filter capacitor C C DC bus V with two ends respectively G Are connected to the + terminal and the-terminal of Q C1 Drain electrode of and DC bus V G Is connected with the + terminal of the relay GCR, the input terminal of the first switch of the relay GCR and Q C1 Source and Q of C2 Drain electrode connection of, Q C2 Source electrode and DC bus V G Is connected at one end to D C7 Cathode and DC bus V G Is connected with the input end of a second switch in the relay GCR and D C7 And Q C3 Drain electrode connection of, Q C3 Source electrode and DC bus V G Of the relay GCR and the output v of the switch Co Is connected to the-terminal, a drive signal G C1 、G C2 And G C3 Are respectively connected with Q C1 、Q C2 And Q C3 Is connected to the gate of, switches the control signal S C And is connected with the control end of the relay SCR.
Further, the auxiliary power supply includes a diode D D1 、D D2 、D D3 And D D4 A non-isolated DC/DC module, a first isolated DC/DC module, a second isolated DC/DC module, a current sensor S D (ii) a + terminal and D of auxiliary power supply D1 Anodic bonding, D D1 Cathode connected to the + terminal of the non-isolated DC/DC module output, D D2 、D D3 And D D4 The anode is respectively connected with A, B and the C terminal, D D2 、D D3 And D D4 The cathode is connected with a + end of the input of the non-isolated DC/DC module, an-end of the auxiliary power supply is connected with a-end of the input of the non-isolated DC/DC module, an-end of the output of the first isolated DC/DC module and an-end of the output of the second isolated DC/DC module, and the + end and the-end of the output of the non-isolated DC/DC module are respectively connected with the + end and the-end of the input of the first isolated DC/DC module and the + end and the-end of the input of the second isolated DC/DC module; the DC/DC converter also comprises two power supplies, wherein the positive end and the negative end of the output of the first isolation DC/DC module are connected with the first power supply V c1 Is connected with the + terminal and the-terminal of the second isolated DC/DC module output and a second power supply V c2 Is connected with the positive terminal and the negative terminal, a current sensor S D Power terminal and second power source V c2 Is connected to the + terminal of the current sensor S D Output signal I D Power supply enable signal E n And is connected with the enabling terminal E of the input of the second isolation DC/DC module.
A design method of a three-stage generator power system for aviation low-voltage direct current comprises the following steps:
step 1: rated current is set as I N And the output of 1.5I can be ensured under the conditions of the lowest generating speed and the voltage stabilization of the three-stage starting generator N (ii) a Step 2: ensuring that the output voltage of the three-level starter generator does not exceed 45V when the highest power generation rotating speed and the load current are switched from 150% to 20%; and step 3: let the average inductance L ═ L (L) of the armature winding of the main motor d +L q ) /2, inductive reactance X at maximum generating speed max ＝ω max L, 1.5I N X max <35V; and 4, step 4: the inductive reactance of the armature winding of the main exciter at the lowest generating rotating speed is set as X emin The resistance of the excitation winding of the main motor at the highest working temperature is R emax To ensure X emin /R emax >0.5; and 5: let the inductance of the main motor excitation winding be L e The resistance at the lowest operating temperature is R emin Guaranteed time constant L e /R emin <50 ms; and 6: ensuring the voltage V after the permanent magnet auxiliary excitation output rectification in the three-stage starting generator within the range of the generating rotating speed and under the condition that the load of the voltage regulator is from no load to the maximum load G In the range of 12V to 45VInternal; and 7: setting the frequency of AC exciting power supply as f, the maximum AC exciting current effective value of main exciter as I Fmax Excitation inductance of the main exciter is L ee To make 130V<2πfL ee I Fmax <170V; and 8: the rotation speed position signal P output by the rotation transformer stator comprises a rotation speed signal n and a position signal theta, and the position signal theta is 0 degrees and corresponds to the zero crossing point of the phase voltage descending section A of the main motor under no load; and step 9: for the direct current bus V in the voltage regulator G Capacitor C of C Ensuring that the energy on the main excitation winding is totally fed back to the capacitor C C Upper time, capacitance C C The voltage on is still within the allowable range; step 10: the power supply to the control circuit is realized by an auxiliary power supply, a power supply V c2 For supplying power to power tube driving circuit in control circuit, power supply V c1 For supplying power to other circuits in the control circuit, if the power supply V c2 Output current I of D In case of abnormality, the power supply enables signal E n The isolation DC/DC module 2 in the isolation power supply is forbidden to work; step 11: in the starting process, the starting generator controller drives the three-stage starting generator to rotate to the ignition speed of the engine from rest; step 12: after the engine reaches the generating rotation speed, the engine enters the generating process, and when the generating rotation speed and the load change, the voltage regulator and the MOS tube three-phase full-bridge control stably output the direct-current voltage V dc 。
Further, the step 11 starting process comprises the following steps:
step 1101: outputting a switch control signal S through a control circuit B And S C Switching on a SCR switch of the relay and switching off a GCR switch of the relay; step 1102: the input voltage V of 28V is boosted by the DC/ DC modules 1 and 2 … … n in the AC excitation power supply Bi Converted into a voltage V of 270V s Increasing output power by connecting a plurality of boosting DC/DC modules in parallel; step 1103: by Q in AC excitation power supply B1 ～Q B4 The formed single-phase H bridge supplies alternating current exciting current to the main exciter; step 1104: the control circuit adopts a control strategy of a quasi-speed outer ring and a current inner ring, and generates an MOS transistor III through sinusoidal Space Vector Pulse Width Modulation (SVPWM) controlDrive signal G of phase full bridge A The starting process is operated in a maximum torque to current ratio mode.
Further, the power generation process of step 12 includes the following steps:
step 1201: outputting a switch control signal S through a control circuit B And S C Switching off the SCR switch of the relay and switching on the GCR switch of the relay; step 1202: the output of three-phase alternating current voltage value of the main motor is regulated by the exciting current output by the voltage regulator, and then direct current voltage V is regulated dc The voltage stabilization control of (3); step 1203: the three-phase alternating current voltage v output by the main motor is realized through the three-phase full bridge of the MOS tube M To a direct voltage V dc On the other hand to achieve a voltage V dc And boost control when the voltage is too low.
Further, the voltage stabilization control in step 1202 includes the following steps:
step 12021: generating a driving signal G of a voltage regulator in a control circuit C1 Generating the power tube Q by using dual-loop control C1 Drive signal G of C1 In the double-loop control, the voltage loop is an outer loop, the exciting current loop is an inner loop, and the voltage outer loop is used for outputting the voltage V dc Tracking parameter voltage V ref And generates a current inner loop reference signal I fref The current inner loop is used for leading the excitation current i of the main exciter F Tracking reference signal I fref The current inner ring output is used for controlling the power tube Q C1 Drive signal G C1 Duty cycle D of (2); step 12022: according to the output DC current I dc Determining the voltage outer loop reference voltage V ref Set the rated current as I N In I dc <2I N When making V ref 28V, in I dc From 2I N To 3I N When changed, make V ref Reducing the voltage from 28V to 0V; step 12023: determining the maximum exciting current I allowed by the output of the voltage loop according to the input rotating speed n fmax ，I fmax At a rotation speed n, 1.5I N Lower, output voltage V dc The excitation current corresponds to the expected voltage stabilization value; step 12024: at an input voltage V dc <At 40V, drive signal G C3 Power tube Q1 C3 Constant-conduction power tube Q C2 Drive signal G C2 And a power tube Q C1 Drive signal G C1 Complementary conduction to make the follow current flow through the power tube Q C2 Instead of Q C2 The anti-parallel diode of (1); step 12025: at an input voltage V dc >At 40V, make the driving signal G C1 ～G C3 Are all equal to 0, power tube Q C1 ～Q C3 Constant turn-off, exciting current of main exciter passing through power tube Q C2 And the reverse parallel diode and the diode DC7 feed energy back to the direct current bus V G In the above way, the rapid demagnetization is realized.
Further, the step 1203 includes the steps of:
step 12031: according to three-phase current i A 、i B And i C Determining a drive signal G for synchronous rectification control A1G ～G A6G Defining a three-phase current i A 、i B And i C The direction of the outflow starting generator controller is positive direction, I refH And I refL Respectively +1/5 and-1/5 of rated current when i A >I refH When making G A2G 1, otherwise G A2G When i is equal to 0 B >I refH When making G A4G 1, otherwise G A4G When i is equal to 0 C >I refH When making G A6G 1, otherwise G A6G When i is equal to 0 A <I refL When making G A1G 1, otherwise G A1G When i is equal to 0 B <I refL When making G A3G 1, otherwise G A3G When i is equal to 0 C <I refL When making G A5G 1, otherwise G A5G 0; step 12032: according to a DC voltage V dc D.c. current I dc Determining a driving signal G for boost voltage stabilization control A1O ～G A6O Defining a driving signal G A2O The falling edge lag theta is 180 DEG and the angle delta 1 Driving signal G A2O High level pulse width of delta 2 When the DC voltage V is dc <24V and I dc <2I N By increasing delta 2 To increase the active current i q The direct current voltage is stabilized at 24V by adjusting delta 1 To make a reactive current i d Decrease delta 0 1 Corresponding reduction of demagnetization reactive current i d ，δ 1 The adjustment range of (1) is 0-60 DEG, delta 2 The adjusting range of G is 0-90 DEG A1O ～G A6O Having the same positive pulse width, in accordance with G A2O 、G A5O 、 G A4O 、G A1O 、G A6O 、G A3O The boosting and voltage stabilizing control drive signal G is formed by sequentially 60 degrees of phase difference A1O ～G A6O (ii) a Step 12033: according to the driving signal G controlled by synchronous rectification A1G ～G A6G And a voltage-boosting and voltage-stabilizing control drive signal G A1O ～G A6O Determining three-phase full-bridge driving signal G of MOS transistor A ，
Figure BDA0003653101410000091
Figure BDA0003653101410000092
The invention has the beneficial effects that: 1. the design method of the three-stage starter generator power supply system for the aviation low-voltage direct current is suitable for aviation manned machines with high reliability requirements, and compared with a direct current brush starter generator power supply system, the three-stage starter generator power supply system is higher in reliability and more convenient to maintain, and compared with a permanent magnet starter generator power supply system, the three-stage starter generator power supply system can be de-magnetized in failure, so that the safety is higher;
2. the common main exciter exciting winding is adopted during starting and power generation, and compared with a mode of adopting an independent three-phase alternating-current exciting winding during starting, the power density of the motor is higher;
3. in the alternating current excitation power supply, the starting power supply voltage is increased from 28V to 270V through the boosting DC/DC module, so that the compatibility problem of a common main exciter excitation winding during starting and power generation is solved;
4. the inverter during starting and the rectifier during power generation are both realized by adopting an MOS tube three-phase full bridge, so that the hardware reuse of starting and power generation states is realized, and the defect that the traditional starter becomes a dead weight of an airplane after the starting task is finished is overcome;
5. by adopting SVPWM control of the maximum torque current ratio, the capacity requirement of a starting power supply is effectively reduced;
6. during power generation, digital double-loop control of the voltage outer ring and the current inner ring is adopted, and compared with a mode of combining an analog single voltage ring and current soft feedback control, the control precision is higher, and the control parameter setting is easier;
7. during power generation, along with the output current I dc The voltage ring is input with a parameter voltage V which is changed from 2 times of rated current to 3 times of rated current ref The maximum voltage during load shedding can be effectively inhibited by reducing the voltage from 28V to 0V;
8. when generating electricity, the voltage ring is output with the allowed maximum exciting current I fmax The excitation current value under the working rotating speed n and 1.5 times of rated current is limited, and the maximum voltage during load shedding can be effectively inhibited;
9. when the voltage regulator works normally, the follow current tube Q C2 The synchronous rectification circuit works in a synchronous rectification mode, and compared with a diode freewheeling mode, the efficiency is remarkably improved;
10. the voltage regulator adopts an asymmetric half-bridge structure to replace a traditional Buck circuit, and when overvoltage is output, the voltage regulator can disconnect the power tube Q C3 The mode realizes quick de-excitation, and the response speed is faster;
11. during power generation, the MOS tube three-phase full bridge works in a synchronous rectification mode, compared with diode three-phase full bridge rectification, the conduction voltage drop of the power tube is obviously reduced, and the efficiency is obviously improved;
12. by adopting the MOS tube voltage boosting and stabilizing control, the dynamic characteristic of the three-level starter generator system can be improved, and the maximum voltage during load shedding can be effectively inhibited.
Drawings
FIG. 1 is a block diagram of a three stage starter generator power system configuration according to the present invention;
FIG. 2 is a three-phase full bridge circuit diagram of the MOS transistor of the present invention;
FIG. 3 is a circuit diagram of an AC excitation power supply of the present invention;
fig. 4 is a circuit diagram of a voltage regulator of the present invention;
FIG. 5 is a circuit diagram of an auxiliary power supply according to the present invention;
FIG. 6 is a schematic diagram of the start control of the present invention;
FIG. 7 is a schematic diagram of the regulator operation of the present invention;
fig. 8 is a schematic diagram of the operation of the asymmetric half-bridge in the voltage regulator of the present invention;
FIG. 9 is a schematic diagram of the synchronous rectification driving signal generation of the MOS transistor three-phase full bridge according to the present invention;
FIG. 10 is a schematic diagram of the generation of the driving signal for the three-phase full bridge of the MOS transistor for voltage boosting and stabilizing control according to the present invention;
FIG. 11 is a vector diagram of the uncontrolled rectifier control and the controlled rectifier control of the present invention.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
The power system of the three-stage starter generator comprises two parts, namely a three-stage starter generator and a starter generator controller. When the three-stage starter generator system is started, the starting power supply is 28V DC, and the starting torque is 25 N.m (0-1000 r/min) and 10 N.m (1000-6000 r/min). In the case of a generator, the output is 28VDC, the output power is 6kW (7500 r/min-13000 r/min), and the generator has 150% rated load, 5min and 200% rated load: an overload capability of 5 s; and the short-circuit capability of outputting current not less than 300% of rated current within 5 s. The application background of the embodiment is an aviation unmanned aerial vehicle adopting a turboprop engine, and an airborne device adopts a 28V LVDC power supply system.
FIG. 1 shows a MOS tube three-phase full-bridge circuit diagram, a three-stage starter generator power system device for aviation low-voltage direct current, which comprises a three-stage starter generator and a starter generator controller, wherein the three-stage starter generator comprises a permanent magnet auxiliary exciter, a main exciter, a rotary rectifier tube, a main motor and a rotary transformer, and the starter generator controller comprises an MOS tube three-phase full-bridge, an alternating current excitation power supply, a voltage regulator, an auxiliary power supply, a control circuit and a current sensor S F And S dc (ii) a Is composed of permanent-magnet auxiliary exciting stator armature winding W PMG Outputting three-phase alternating current v PWM A, B and C terminals of the main exciter are connected to the auxiliary power supply and A, B and C input terminals of the voltage regulator, respectively, and the rotor armature winding W of the main exciter EM Outputting three-phase alternating current v EM Excitation winding W of main motor rotor through rotating rectifier ME Stator field winding W of connected main exciter EE F + end and F-end of the AC excitation power supply output v respectively Bo A star terminal and a-terminal of, a voltage regulator output V Co Are connected with the positive terminal and the negative terminal of the main motor MM Three-phase alternating current v M A, B and C ends are respectively connected with A, B and C ends of MOS tube three-phase full bridge, the rotary transformer stator outputs speed position signal P to be connected with control circuit, DC bus V dc The + end and the-end of the direct current bus are respectively connected with a three-phase full bridge of the MOS tube Adc Plus and minus terminals of AC excitation power supply input V Bi The positive end and the negative end of the voltage regulator, the positive end and the negative end of the output power supply input and the control circuit are connected, and the negative end of the voltage regulator is connected with the direct current bus V dc Is connected with the end of the MOS tube, and the three-phase alternating current signal i is output by the three-phase full bridge of the MOS tube ABC A driving signal G connected with the control circuit and output by the control circuit A A driving signal G connected with the three-phase full bridge of the MOS tube and output by the control circuit B And a switch control signal S B A driving signal G connected with the AC excitation power supply and output by the control circuit C And a switch control signal S C Two-way power supply output V connected with voltage regulator and used as auxiliary power supply c1 、V c2 A current signal I connected with the control circuit and output by the auxiliary power supply D A power supply enable signal E connected with the control circuit and output by the control circuit n Connected to an auxiliary power supply, current sensor S dc Power terminal, output signal I dc Respectively connected with the DC bus V dc Is connected with the control circuit, and the current sensor S F Power terminal of, output signal i F Are respectively connected with the excitation winding W EE The F + end of the switch is connected with the control circuit.
Current sensor S F The method is realized by ACS730KLCTR-40AB-T of Allegro company, and the range of the method is-40A to + 40A. Current sensor S dc The method is realized by HC5F800-S of LEM company, and the range is-800A- + 800A. The control circuit adopts a DSP + FPGA structure, the DSP adopts TMS320F28335PGFA of TI company, and the FPGA adopts EP3C25E114CN of Altera company.
The common main exciter exciting winding is adopted during starting and power generation, and compared with a mode of adopting an independent three-phase alternating-current exciting winding during starting, the power density of the motor is higher.
Fig. 2 shows an IGBT three-phase full-bridge circuit diagram. The MOS three-phase full bridge comprises an A-phase bridge arm, a B-phase bridge arm, a C-phase bridge arm and a filter capacitor C dc Current sensor S A1 、S A2 And S A3 Driving signal G A Comprising G A1 ～G A6 Three-phase alternating current i ABC Includes i A 、i B And i C (ii) a Is composed of an A end and an A-phase bridge arm upper tube Q A1 Source S and lower tube Q of A2 Drain electrode D of the bridge arm A is connected with a tube Q on the bridge arm A A1 Drain electrode D and DC bus V Adc The + end of the A-phase bridge arm is connected with the lower tube Q A2 Source electrode S and DC bus V Adc Is connected with the end B, and the end B is connected with the upper tube Q of the B-phase bridge arm A3 Source S and lower tube Q of A4 Drain electrode D of the bridge arm B is connected with a tube Q on the bridge arm B A3 Drain electrode D and DC bus V Adc Is connected with the positive end of the B-phase bridge arm lower tube Q A4 Source S and dc bus V Adc Is connected with the end C, and the end C is connected with the upper tube Q of the C-phase bridge arm A5 Source S and lower tube Q of A6 Drain electrode D of the bridge arm Q is connected with the drain electrode D of the bridge arm Q A5 Drain electrode D and DC bus V Adc Is connected with the positive end of the C-phase bridge arm lower tube Q A6 Source S and dc bus V Adc Is connected to the terminal of the filter capacitor C Adc Both ends of the direct current bus V are respectively connected with the direct current bus V Adc Is connected with the positive terminal and the negative terminal, and a current sensor S A1 、S A2 And S A3 Respectively connected to terminals A, B and C, a current sensor S A1 、S A2 And S A3 Respectively output signal i A 、i B And i C Driving signal G A1 ～G A6 Are respectively connected with Q A1 ～Q A6 Is connected to the gate G of (1).
Phase A, phase BAnd the C-phase bridge arm respectively adopts a MOS tube module MMN1000DB010B of MACMIC company. It can bear the maximum current of 1000A and has the on-resistance R on 1.7m Ω (150 ℃), withstand voltage of 100V. Filter capacitor C Adc Ceramic capacitors CT45-T-X5R-100V-107M of 100 Tanzhou macrostems are adopted to be connected in parallel, and a single capacitor is resistant to pressure of 100V and 100 muF. Current sensor S A1 、S A2 And S A3 The method is realized by HC5F800-S of LEM company, and the range is-800A- + 800A.
The inverter during starting and the rectifier during power generation are both realized by adopting an MOS tube three-phase full bridge, so that hardware reuse of starting and power generation states is realized, and the defect that the traditional starter becomes a dead weight of an airplane after a starting task is finished is overcome.
Fig. 3 shows a circuit diagram of an ac excitation power supply. The AC excitation power supply comprises a diode D B1 Boost DC/DC module 1, 2 … … n, filter capacitor C B Power tube Q B1 ～Q B4 Relay SCR, drive signal G B Comprising G B1 ～G B4 (ii) a Is formed by an input V Bi And a diode D B1 Is connected to the anode of diode D B1 Is connected to the + terminal of the boost DC/DC module 1, 2 … … n input, respectively, and the input V Bi Is connected with the input end of the boost DC/DC module 1, 2 … … n, and the output end of the boost DC/DC module 1, 2 … … n and the positive end and the negative end are respectively connected with the direct current bus V s Are connected to the + terminal and the-terminal of, an input V Bi End of and DC bus V s Is connected to the terminal of the filter capacitor C B DC bus V with two ends respectively s Are connected to the + terminal and the-terminal of Q B1 Drain electrode D and DC bus V s Is connected with the + end of the first switch in the relay SCR, and the input end 1A and the Q of the first switch in the relay SCR are connected with the positive end of the second switch B1 Source electrodes S and Q of B2 Drain electrode of D connection, Q B2 Source S and dc bus V s Is connected to the minus terminal, Q B3 Drain electrode D and DC bus V s Is connected with the + terminal of the second switch in the relay SCR, and the input end 2A and Q of the second switch in the relay SCR are connected with the positive terminal of the second switch B3 Source electrodes S and Q of B4 Drain electrode of D connection, Q B4 Source electrode S and DC bus V s Of the relay SCR, the output terminal 1Y of the first switch and the output terminal 2Y of the second switch in the relay SCR are respectively connectedAnd output v Bo Is connected to terminal, driving signal G B1 ～G B4 Are respectively connected with Q A1 ～Q A6 Is connected to the gate G of the switching control signal S B And the control end of the relay SCR is connected.
The boosting DC/DC module adopts SLBN28500H270SN of sublimation company, and the number of the boosting DC/DC modules in parallel connection is 3. The single SLBN28500H270SN module allows the regulated input voltage range to be 16-40 Vdc, can bear 100ms and 55V transient voltage, and has output voltage of 270V and 500W. SLBN28500H270SN size 60.6X 63.1X 13mm, weight 150 g. The relay SCR selects J400-J1N from 315 works of the Zhonghang industry. Power tube Q B1 ～Q B4 And two infineon MOS (Metal oxide semiconductor) tubes IPT60R050G7 are correspondingly selected and connected in parallel for each power tube code. The IPT60R050G7 has a single branch current of 57A and a withstand voltage of 650V.
The starting power supply voltage is increased from 28V to 270V by the boosting DC/DC module in the alternating current excitation power supply, and the problem of compatibility of a common main exciter excitation winding during starting and power generation is solved.
Fig. 4 is a circuit diagram of the voltage regulator. The voltage regulator comprises a diode D C1 ～D C7 Power tube Q C1 ～Q C3 Filter capacitor C C Relay GCR, drive signal G C Comprising G C1 ～G C3 (ii) a Is formed by an A terminal and a D terminal C1 And D C2 Cathode of (3) is connected with terminal B and terminal D C3 And D C4 Is connected to the cathode, C terminal and D C5 And D C6 Of the cathode electrode, D C1 、D C3 And D C5 Cathode and DC bus V G Is connected to the + terminal, D C2 、D C4 And D C6 Anode and dc bus V G Is connected to the terminal of the filter capacitor C C DC bus V with two ends respectively G Are connected to the + terminal and the-terminal of Q C1 Drain electrode D and DC bus V G Is connected with the + terminal of the relay GCR, the input terminal 1A of the first switch is connected with the Q terminal of the relay GCR C1 Source electrodes S and Q of C2 Drain electrode D of (2) is connected to, Q C2 Source S and dc bus V G Is connected at one end to D C7 Cathode and DC bus V G Is connected to the + terminalTo the input terminals 2A and D of a second switch in the relay GCR C7 And Q C3 Drain electrode of D connection, Q C3 Source S and dc bus V G Is connected to the output terminal 1Y of the first switch and the output terminal 2Y of the second switch in the relay GCR, respectively, with the output v Co Is connected with the + terminal and the-terminal of the driving signal G C1 ～G C3 Are respectively connected with Q C1 ～Q C3 Is connected to the gate G of the switching control signal S C And the control end of the relay SCR is connected.
Diode D C1 ～D C6 MBRB20200CT is selected, the voltage resistance is 200V, the current is 20A, and the conduction voltage drop is 0.7V. Capacitor C C The ceramic capacitor CT45-T-X5R-100V-107M is realized by connecting a plurality of ceramic capacitors in parallel, the voltage resistance of the ceramic capacitor CT is 100V, and the single-branch capacity of the ceramic capacitor CT is 100 mu F. Power MOS tube Q C1 ～Q C3 An automobile power tube IAUT300N10S5N015 of infineon company is selected, the withstand voltage of the automobile power tube IAUT is 100V, the current of the automobile power tube IAUT is 300A, and the on-resistance of the automobile power tube IAUT is 1.5m omega. Diode D C7 The power tube IAUT300N10S5N015 is realized by an antiparallel diode. The relay GCR is 315 factory J400-J1N.
FIG. 5 is a circuit diagram of an auxiliary power supply including a diode D D1 ～D D4 Non-isolated DC/DC module, isolated DC/DC module 1, isolated DC/DC module 2, current sensor S D (ii) a Is formed by a + terminal and a D terminal D1 Anodic bonding, D D1 Cathode connected to the + terminal of the non-isolated DC/DC module output, D D2 、D D3 And D D4 The anode is respectively connected with A, B and the C terminal, D D2 、 D D3 And D D4 The cathode is connected with the + end of the input of the non-isolated DC/DC module, the-end of the output of the isolated DC/DC module 1 and the-end of the output of the isolated DC/DC module 2 are connected, the + end and the-end of the output of the non-isolated DC/DC module are respectively connected with the + end and the-end of the input of the isolated DC/DC module 1 and the + end and the-end of the input of the isolated DC/DC module 2, and the + end and the-end of the output of the isolated DC/DC module 1 are connected with a first power supply V c1 Is connected with the + terminal and the-terminal of the output of the DC/DC module 2, and isolates the + terminal and the-terminal of the output of the DC/DC module from the second power supply V c2 Is connected with the positive terminal and the negative terminal, a current sensor S D Power terminal and power source V c2 Is connected to the + terminal of the current sensor S D Output signal I D Power supply enable signal E n And an enabling terminal E connected with the input of the isolated DC/DC module 2.
Diode D D1 ～D D4 MBRB20200CT is selected, the voltage resistance is 200V, the current is 20A, and the conduction voltage drop is 0.7V. The non-isolated DC/DC module adopts NSL28U2K4H60SN of Sichuan sublimation company, the effective input voltage stabilization range is 9-60V, and the output voltage stabilization value is set to be 30V. The isolated DC/DC module 1 and the isolated DC/DC module 2 respectively adopt power supply modules SAY2410H05S and SD24100H12S of Sichuan sublimation company to generate 5V power supply V c1 And a 12V power supply V c2 . Current sensor S D The method is realized by ACS724LLCTR-05AB-T of Allegro company, and the range of the method is-5A- + 5A.
A design method of a three-stage starter generator power system for aviation low-voltage direct current comprises the following steps:
step 1: rated current is set as I N And the output of 1.5I can be ensured under the conditions of the lowest generating speed and the voltage stabilization of the three-stage starting generator N ；
Step 2: ensuring that the output voltage of the three-level starter generator does not exceed 45V when the highest power generation rotating speed and the load current are switched from 150% to 20%;
and step 3: let the average inductance L ═ L (L) of the armature winding of the main motor d +L q ) /2, inductive reactance X at maximum generating speed max ＝ω max L, 1.5I N X max <35V；
And 4, step 4: the inductive reactance of the armature winding of the main exciter at the lowest generating rotating speed is set as X emin The resistance of the excitation winding of the main motor at the highest working temperature is R emax Ensure X emin /R emax >0.5；
And 5: let the inductance of the main motor excitation winding be L e The resistance at the lowest operating temperature is R emin Guaranteed time constant L e /R emin <50ms；
Step 6: the three-stage starting generator is ensured under the conditions that the load of the voltage regulator is from no load to the maximum load within the range of the generating rotating speedRectified voltage V of permanent magnet auxiliary excitation output in motor G In the range of 12V to 45V;
and 7: setting the frequency of AC exciting power supply as f, the maximum AC exciting current effective value of main exciter as I Fmax Excitation inductance of the main exciter is L ee To make 130V<2π fL ee I Fmax <170V；
And 8: the rotation speed position signal P output by the rotation transformer stator comprises a rotation speed signal n and a position signal theta, and the position signal theta is 0 degrees and corresponds to the zero crossing point of the phase voltage descending section A of the main motor under no load;
and step 9: for the direct current bus V in the voltage regulator G Capacitor C of C， Ensuring that the energy on the main excitation winding is totally fed back to the capacitor C C Upper time, capacitance C C The voltage on is still within the allowable range;
step 10: the power supply to the control circuit is realized by an auxiliary power supply, a power supply V c2 For supplying power to power tube driving circuit in control circuit, power supply V c1 For supplying power to other circuits in the control circuit, if the power supply V c2 Output current I of D In case of abnormality, the power supply enables signal E n The isolation DC/DC module 2 in the isolation power supply is forbidden to work;
step 11: in the starting process, the starter generator controller drives the three-stage starter generator to rotate to the ignition speed of the engine from rest;
step 12: after the engine reaches the generating rotation speed, the engine enters the generating process, and when the generating rotation speed and the load change, the voltage regulator and the MOS tube three-phase full-bridge control stably output the direct-current voltage V dc 。
Referring to the starting control schematic diagram shown in fig. 6, the starting process control described in step 11 includes the following steps:
step 1101: outputting a switch control signal S through a control circuit B And S C Switching on a SCR switch of the relay and switching off a GCR switch of the relay;
step 1102: the input voltage V of 28V is boosted by the DC/ DC modules 1 and 2 … … n in the AC excitation power supply Bi Transformation ofA voltage V of 270V s Increasing output power by connecting a plurality of boosting DC/DC modules in parallel;
step 1103: by Q in AC excitation power supply B1 ～Q B4 The formed single-phase H bridge supplies alternating current exciting current to the main exciter;
step 1104: the control circuit adopts a control strategy of a quasi-speed outer ring and a current inner ring, and generates a driving signal G of an MOS tube three-phase full bridge through sinusoidal Space Vector Pulse Width Modulation (SVPWM) control A The starting process is operated in a maximum torque to current ratio mode.
When maximum torque/current ratio control is employed, i d And I ref Is represented by the formula (1), i q The expression is shown in formula (2).
Figure RE-GDA0003728601560000181
In the formula (I), the compound is shown in the specification,
Figure BDA0003653101410000181
U 0 the voltage of the idle phase is effective.
Figure BDA0003653101410000182
By adopting the SVPWM control of the maximum torque current ratio, the capacity requirement of the starting power supply is effectively reduced.
Step 12, the power generation process control includes the following steps:
step 1201: the control circuit outputs switch control signals SB and SC, and the relay SCR switch is switched off and the relay GCR switch is switched on;
step 1202: the output of the three-phase alternating current voltage value of the main motor is regulated by the exciting current output by the voltage regulator, so that the voltage stabilization control of the direct current voltage Vdc is realized;
step 1203: synchronous rectification from three-phase alternating-current voltage vM output by the main motor to direct-current voltage Vdc is realized through the three-phase full bridge of the MOS tube, and boosting control when the voltage Vdc is too low is realized.
Referring to the operating schematic diagram of the voltage regulator shown in fig. 7 and the operating schematic diagram of the asymmetric half bridge in the voltage regulator shown in fig. 8, the voltage regulation control of the voltage regulator described in step 1202 in step 12 will be described, which includes the following steps:
step 12021: generating a driving signal G of a voltage regulator in a control circuit C1 Generating the power tube Q by using dual-loop control C1 Drive signal G C1 In the double-loop control, the voltage loop is an outer loop, the exciting current loop is an inner loop, and the voltage outer loop is used for outputting the voltage V dc Tracking parameter voltage V ref And generates a current inner loop reference signal I fref The current inner loop is used for leading the excitation current i of the main exciter F Tracking reference signal I fref The current inner ring output is used for controlling the power tube Q C1 Drive signal G C1 Duty cycle D of (2);
step 12022: according to the output DC current I dc Determining the voltage outer loop reference voltage V ref Set the rated current as I N In I dc <2I N When making V ref 28V, in I dc From 2I N To 3I N When changed, make V ref Reducing the voltage from 28V to 0V;
step 12023: determining the maximum exciting current I allowed by the output of the voltage loop according to the input rotating speed n fmax ，I fmax At a rotation speed n, 1.5I N Lower, output voltage V dc The excitation current corresponds to the expected voltage stabilization value;
step 12024: at an input voltage V dc <At 40V, drive signal G C3 Power tube Q1 C3 Constant-conduction power tube Q C2 Drive signal G C2 And a power tube Q C1 Drive signal G of C1 Complementary conduction to make the follow current flow through the power tube Q C2 Instead of Q C2 The anti-parallel diode of (1);
step 12025: at an input voltage V dc >At 40V, make the driving signal G C1 ～G C3 Are all equal to 0, power tube Q C1 ～Q C3 Constant off, mainExciting current of exciter through power tube Q C2 And the reverse parallel diode and the diode DC7 feed energy back to the direct current bus V G In the above way, the rapid demagnetization is realized.
Compared with a mode of combining an analog single voltage ring and current soft feedback control, the digital double-loop control of the voltage outer ring and the current inner ring is adopted, the control precision is higher, and the control parameter setting is easier.
With output current I dc The voltage ring is input with a parameter voltage V which is changed from 2 times of rated current to 3 times of rated current ref The maximum voltage during load shedding can be effectively inhibited by reducing the voltage from 28V to 0V.
The voltage loop is output with the allowed maximum exciting current I fmax The excitation current value under the working speed n and the rated current of 1.5 times is limited, and the maximum voltage during load shedding can be effectively inhibited.
When the voltage regulator works normally, the follow current tube Q C2 Work in synchronous rectification mode, for diode freewheel mode, efficiency is showing and is promoting.
The voltage regulator adopts an asymmetric half-bridge structure to replace a traditional Buck circuit, and when overvoltage is output, the voltage regulator can disconnect the power tube Q C3 The method realizes quick de-excitation and has quicker response speed.
With reference to the schematic diagram of generating the synchronous rectification driving signal of the three-phase full-bridge MOS transistor shown in fig. 9 and the schematic diagram of generating the boosting and voltage stabilizing control driving signal of the three-phase full-bridge MOS transistor shown in fig. 10, the step 1203 in step 12 of the three-phase full-bridge MOS transistor boosting control will be described, which includes the following steps:
step 12031: according to three-phase current i A 、i B And i C Determining a drive signal G for synchronous rectification control A1G ～G A6G Defining a three-phase current i A 、i B And i C The direction of the outflow starting generator controller is positive direction, I refH And I refL Respectively +1/5 and-1/5 of rated current when i A >I refH When making G A2G 1, otherwise G A2G When i is equal to 0 B >I refH When making G A4G 1, otherwise G A4G When i is equal to 0 C >I refH When making G A6G 1, otherwise G A6G When i is equal to 0 A <I refL While making G A1G 1, otherwise G A1G When i is equal to 0 B <I refL When making G A3G 1, otherwise G A3G When i is equal to 0 C <I refL When making G A5G 1, otherwise G A5G ＝0；
Step 12032: according to a DC voltage V dc D.c. current I dc Determining a driving signal G for boost voltage stabilization control A1O ～G A6O Defining a driving signal G A2O The falling edge lag theta is 180 DEG and the angle delta 1 Driving signal G A2O High level pulse width of delta 2 When the DC voltage V is dc <24V and I dc <2I N By increasing delta 2 To increase the active current i q The direct current voltage is stabilized at 24V by adjusting delta 1 To make a reactive current i d Decrease delta 0 1 Corresponding reduction of demagnetization reactive current i d ，δ 1 The adjustment range of (1) is 0-60 DEG, delta 2 The adjusting range of G is 0-90 DEG A1O ～G A6O Having the same positive pulse width, in accordance with G A2O 、G A5O 、G A4O 、 G A1O 、G A6O 、G A3O The boosting and voltage stabilizing control drive signal G is formed by sequentially 60 degrees of phase difference A1O ～G A6O ；
Step 12033: according to the driving signal G controlled by synchronous rectification A1G ～G A6G And a voltage-boosting and voltage-stabilizing control drive signal G A1O ～G A6O Determining three-phase full-bridge driving signal G of MOS transistor A ，
Figure BDA0003653101410000201
Figure BDA0003653101410000202
During the electricity generation, MOS pipe three-phase full-bridge work is in synchronous rectification mode, and relative diode three-phase full-bridge rectification, the power tube switches on the pressure drop and is showing and reduce, and efficiency is showing and is promoting.
FIG. 11 is a vector diagram illustrating uncontrolled commutation control and controlled commutation control. For the conventional uncontrolled rectification, the reason that the uncontrollable rectification causes the output voltage overshoot during load shedding is explained by combining the uncontrollable rectification phasor diagram in fig. 11, which is mainly caused by two reasons, namely that the energy stored on the main armature inductor of the motor is released to a bus, and the armature winding inductor stores energy 1/2 & LI s 2 Is responsible for the first voltage spike. On the other hand, under heavy load, in order to overcome the voltage drop on the inductance of the armature winding of the main motor (I in the uncontrollable rectification phasor diagram of FIG. 11) d1 X d And I q1 X q1 Caused) and armature current I s1 Medium field weakening current i d1 Component induced back-emf drop (I in FIG. 11 uncontrollable rectified phasor diagram d1 X d Caused by the voltage drop) is increased, so that the exciting current is too high, and the counter potential under the corresponding no-load is larger (as shown in an uncontrollable rectification phasor diagram E in a figure 11) 01 Shown); after load shedding, the voltage drop on the armature winding inductance of the main motor is obviously reduced, the armature reaction forming the weak magnetic effect is also lower, the over-high counter potential is directly transmitted to the output end, and meanwhile, the exciting current of the main motor cannot be quickly recovered due to the large electromechanical constant of the main motor; this is responsible for the second voltage spike.
When the boost voltage stabilization control is adopted, the power generation voltage stabilization principle is explained by combining a controllable rectification phasor diagram in fig. 11. By regulating the phase of the current by hysteresis U in uncontrolled rectification s Becomes advanced U s Make the current phasor I s2 Counter-potential to no-load E 02 The phases are opposite. At this time, the armature current i s2 Absence of weak magnetic component i d2 Output voltage amplitude | U s Is greater than no-load back-emf magnitude E 02 Of and the output voltage amplitude | U under uncontrolled rectification s Is lower than no-load back-emf magnitude E 01 L are quite different. At the same output voltage amplitude | U s In case of | corresponding no-load counter potential | E 02 | is significantly less than | E under uncontrolled rectification 01 L. the method is used for the preparation of the medicament. Simultaneous phase current I s2 All ofThe components are active current components I q2 And I under uncontrolled rectification q1 Equalisation without the presence of a non-power current component I during uncontrolled commutation d1 So that the amplitude | I of the armature winding current s2 I is also significantly lower than I in uncontrolled rectification s1 |。
For the first spike, because
Figure BDA0003653101410000211
Is less than
Figure BDA0003653101410000212
Therefore, the first peak under the controllable rectification is smaller; for the second spike, due to no-load back-emf | E 02 | is significantly less than | E under uncontrolled rectification 01 Therefore, the controllable second class peak is smaller.
For the sudden loading condition, because a large exciting current is needed under a heavy load, on one hand, the current rise time caused by the inductance of the armature winding is limited, and a first voltage drop peak is caused; on the one hand, it takes a certain time for the excitation current to rise due to the main motor, causing a second voltage dip peak. After the controllable rectification is adopted, when the output voltage is detected to be lower than a certain value, the voltage boosting controller can be started to control the rectification to boost, and because the response time of the voltage boosting and stabilizing control is 1/6 electric frequency periods, the response is quick, and the compensation effect is realized on two voltage drop peaks.
By adopting the MOS tube voltage boosting and stabilizing control, the dynamic characteristic of the three-level starter generator system can be improved, and the maximum voltage during load shedding can be effectively inhibited. The design method of the power system of the three-stage starting generator for the aviation low-voltage direct current is suitable for aviation manned machines with high reliability requirements, and compared with a power system of a direct-current brush starting generator, the power system of the three-stage starting generator is higher in reliability and more convenient to maintain, and compared with a power system of a permanent magnet starting generator, the power system of the three-stage starting generator can be demagnetized when in failure, so that the safety is higher.

Claims (10)

1. Aviation low-voltage direct currentWith tertiary formula generator power system, its characterized in that: the three-level starter generator comprises a permanent magnet auxiliary exciter, a main exciter, a rotary rectifying tube, a main motor and a rotary transformer; the starter generator controller comprises an MOS tube three-phase full bridge, an AC excitation power supply, a voltage regulator, an auxiliary power supply, a control circuit and a current sensor S F And a current sensor S dc ；
The permanent magnet auxiliary excitation stator armature winding W PMG Outputting three-phase alternating current v PWM A, B and the C terminal of the secondary power supply and the voltage regulator are connected with the A, B and the C input terminal of the voltage regulator respectively,
rotor armature winding W of the main exciter EM Outputting three-phase alternating current v EM Through rotating rectifier and main motor rotor excitation winding W ME Stator field winding W of connected main exciter EE The F + end and the F-end are connected with the output end of the alternating current excitation power supply and the output end of the voltage regulator,
stator armature winding W of the main motor MM Three-phase alternating current v M A, B and the C terminal of the MOS transistor are respectively connected with the A, B and the C terminal of the MOS transistor three-phase full bridge,
the rotary transformer stator outputs a rotating speed position signal P which is connected with a control circuit,
DC bus Vdc The + end and the-end of the direct current bus are respectively connected with a three-phase full bridge of the MOS tube Adc Plus and minus terminals of AC excitation power supply input V Bi The + end and the-end of the output power supply input, the + end and the-end of the output power supply input and a control circuit are connected,
end of voltage regulator and DC bus V dc Is connected with the end of the main body,
three-phase alternating current signal i output by three-phase full bridge of MOS (metal oxide semiconductor) tube ABC Is connected with the control circuit and is connected with the control circuit,
driving signal G output by control circuit A A driving signal G connected with the three-phase full bridge of the MOS tube and output by the control circuit B And a switch control signal S B A driving signal G connected with the AC excitation power supply and output by the control circuit C And a switch control signal S C Is connected with a voltage regulator and is connected with the voltage regulator,
two ways of auxiliary power supplyPower supply output V c1 、V c2 A current signal I connected with the control circuit and output by the auxiliary power supply D Is connected with the control circuit and is connected with the control circuit,
power supply enable signal E output by control circuit n Is connected with an auxiliary power supply and is provided with a power supply,
current sensor S dc Power terminal, output signal I dc Respectively connected with the DC bus V dc The + end of the switch is connected with the control circuit,
current sensor S F The power end and the output signal iF are respectively connected with the excitation winding W EE The F + end of the switch is connected with the control circuit.
2. The aero low voltage dc three-stage generator power system as claimed in claim 1 wherein: the MOS three-phase full bridge comprises an A-phase bridge arm, a B-phase bridge arm, a C-phase bridge arm and a filter capacitor C dc Current sensor S A1 、S A2 And S A3 Driving signal G A Comprising G A1 、G A2 、G A3 、G A4 、G A5 And G A6 Three-phase alternating current i ABC Includes i A 、i B And i C ；
A end of the MOS three-phase full bridge and an A-phase bridge arm upper tube Q A1 Source and lower tube Q A2 The drain electrode of the bridge arm A is connected with the upper tube Q A1 Drain electrode of and DC bus V Adc The + end of the A-phase bridge arm is connected with the lower tube Q A2 Source S and dc bus V Adc Is connected with the end B of the MOS three-phase full bridge and the upper tube Q of the B-phase bridge arm A3 Source S and lower tube Q of A4 Drain electrode D of the bridge arm B is connected with a tube Q on the bridge arm B A3 Drain electrode of and DC bus V Adc Is connected with the positive end of the B-phase bridge arm lower tube Q A4 Source electrode and DC bus V Adc Is connected with the end C of the MOS three-phase full bridge and the upper tube Q of the C-phase bridge arm A5 Source and lower tube Q A6 Drain electrode of (1) is connected, and the upper tube Q of C-phase bridge arm A5 Drain electrode of and DC bus V Adc Is connected with the positive end of the C-phase bridge arm lower tube Q A6 Source electrode and DC bus V Adc Is connected to the terminal of the filter capacitor C Adc Both ends are respectivelyAnd a DC bus V Adc Is connected with the positive terminal and the negative terminal, and a current sensor S A1 、S A2 And S A3 Respectively connected to terminals A, B and C, a current sensor S A1 、S A2 And S A3 Respectively with the output signal i A 、i B And i C Corresponding connection, the drive signal G A1 、G A2 、G A3 、G A4 、G A5 And G A6 Are respectively connected with Q A1 、Q A2 、Q A3 、Q A4 、Q A5 And Q A6 The corresponding gate is connected.
3. The three-stage generator power system for aviation low voltage direct current of claim 2, wherein: the AC excitation power supply comprises a diode D B1 A plurality of boost DC/DC modules and a filter capacitor C B Power tube Q B1 、Q B2 、Q B3 And Q B4 Relay SCR, drive signal G B Comprising G B1 、G B2 、G B3 And G B4 (ii) a Is formed by an input V Bi And a diode D B1 Is connected to the anode of diode D B1 Is respectively connected with the input + ends of a plurality of boosting DC/DC modules, and the input V Bi Is connected with the input-ends of the plurality of boosting DC/DC modules, and the output + ends and the output-ends of the plurality of boosting DC/DC modules are respectively connected with the direct current bus V s Are connected to the + terminal and the-terminal of, an input V Bi End of and DC bus V s Is connected to the terminal of the filter capacitor C B DC bus V with two ends respectively s Are connected to the + terminal and the-terminal of Q B1 Drain electrode of and DC bus V s The + end of the terminal is connected; the relay SCR is provided with two switches, wherein the input end of the first switch is connected with Q B1 Source and Q of B2 Drain electrode connection of, Q B2 Source electrode and DC bus V s Is connected to the minus terminal, Q B3 Drain electrode of and DC bus V s Is connected with the + terminal of the relay SCR, the input terminal of the second switch of the relay SCR is connected with Q B3 Source electrodes S and Q of B4 Drain electrode connection of, Q B4 Source electrode and DC bus V s Is connected to the terminal, and is relayedOutput terminal and output v of switch in SCR Bo Connecting, driving signal G B1 、G B2 、G B3 And G B4 Are respectively connected with Q B1 、Q B2 、Q B3 And Q B4 Is connected to the gate of, switches the control signal S B And is connected with the control end of the relay SCR.
4. The three-stage generator power system for aviation low voltage direct current of claim 3, wherein: the voltage regulator comprises a diode D C1 、D C2 、D C3 、D C4 、D C5 、D C6 And D C7 Power tube Q C1 、Q C2 And Q C3 Filter capacitor C C Relay GCR, drive signal G C Comprising G C1 ～G C3 (ii) a A terminal and D terminal of voltage regulator C1 And D C2 Is connected with the cathode of the voltage regulator, and the B end of the voltage regulator is connected with the D end C3 And D C4 Is connected with the cathode of the voltage regulator, the C end of the voltage regulator is connected with the D end C5 And D C6 The cathode of (a) is connected; d C1 、D C3 And D C5 Cathode and DC bus V G Is connected to the + terminal, D C2 、D C4 And D C6 Anode and dc bus V G Is connected to the terminal of the filter capacitor C C DC bus V with two ends respectively G Are connected to the + terminal and the-terminal of Q C1 Drain electrode of and DC bus V G Is connected with the + terminal of the relay GCR, the input terminal of the first switch of the relay GCR and Q C1 Source and Q of C2 Drain electrode connection of, Q C2 Source electrode and DC bus V G Is connected at one end to D C7 Cathode and DC bus V G Is connected with the input end of a second switch in the relay GCR and D C7 And Q C3 Drain electrode connection of, Q C3 Source electrode and DC bus V G Of the relay GCR and the output v of the switch Co Is connected with the + terminal and the-terminal of the driving signal G C1 、G C2 And G C3 Are respectively connected with Q C1 、Q C2 And Q C3 Is connected to the gate of, switches the control signal S C And relay SCAnd the control end of R is connected.
5. The aviation low-voltage direct-current three-stage generator power system and the design method thereof as claimed in claim 4, wherein: the auxiliary power supply comprises a diode D D1 、D D2 、D D3 And D D4 A non-isolated DC/DC module, a first isolated DC/DC module, a second isolated DC/DC module, a current sensor S D (ii) a + terminal and D of auxiliary power supply D1 Anodic bonding, D D1 Cathode connected to the + terminal of the non-isolated DC/DC module output, D D2 、D D3 And D D4 The anode is respectively connected with A, B and the C terminal, D D2 、D D3 And D D4 The cathode is connected with a + end of the input of the non-isolated DC/DC module, an-end of the auxiliary power supply is connected with a-end of the input of the non-isolated DC/DC module, an-end of the output of the first isolated DC/DC module and an-end of the output of the second isolated DC/DC module, and the + end and the-end of the output of the non-isolated DC/DC module are respectively connected with the + end and the-end of the input of the first isolated DC/DC module and the + end and the-end of the input of the second isolated DC/DC module; the DC/DC converter also comprises two power supplies, wherein the positive end and the negative end of the output of the first isolation DC/DC module are connected with the first power supply V c1 Is connected with the + terminal and the-terminal of the second isolated DC/DC module output and a second power supply V c2 Is connected with the positive terminal and the negative terminal, a current sensor S D Power terminal and second power source V c2 Is connected to the + terminal of the current sensor S D Output signal I D Power supply enable signal E n And the enabling terminal E of the input of the second isolation DC/DC module is connected.
6. The method for designing a three-stage generator power system for aviation low-voltage direct current according to claim 5, comprising the steps of:
step 1: rated current is set as I N And the output of 1.5I can be ensured under the conditions of the lowest generating speed and the voltage stabilization of the three-stage starting generator N ；
Step 2: ensuring that the output voltage of the three-level starter generator does not exceed 45V when the highest power generation rotating speed and the load current are switched from 150% to 20%;
and step 3: let the average inductance L ═ L (L) of the armature winding of the main motor d +L q ) /2, inductive reactance X at maximum generating speed max ＝ω max L, 1.5I N X max <35V；
And 4, step 4: the inductive reactance of the armature winding of the main exciter at the lowest generating rotating speed is set as X emin The resistance of the excitation winding of the main motor at the highest working temperature is R emax Ensure X emin /R emax >0.5；
And 5: let the inductance of the main motor excitation winding be L e The resistance at the lowest operating temperature is R emin Guaranteed time constant L e /R emin <50ms；
Step 6: ensuring the voltage V after the permanent magnet auxiliary excitation output rectification in the three-stage starting generator within the range of the generating rotating speed and under the condition that the load of the voltage regulator is from no load to the maximum load G In the range of 12V to 45V;
and 7: setting the frequency of AC exciting power supply as f, the maximum AC exciting current effective value of main exciter as I Fmax Excitation inductance of the main exciter is L ee To make 130V<2πfL ee I Fmax <170V；
And 8: the rotation speed position signal P output by the rotation transformer stator comprises a rotation speed signal n and a position signal theta, and the position signal theta is 0 degrees and corresponds to the zero crossing point of the phase voltage descending section A of the main motor under no load;
and step 9: for the direct current bus V in the voltage regulator G Capacitor C of C， Ensuring that the energy on the main excitation winding is totally fed back to the capacitor C C Upper time, capacitance C C The voltage on is still within the allowable range;
step 10: the power supply to the control circuit is realized by an auxiliary power supply, a power supply V c2 For supplying power to power tube driving circuit in control circuit, power supply V c1 For supplying power to other circuits in the control circuit, if the power supply V c2 Output current I of D In case of abnormality, the power supply enables signal E n The isolation DC/DC module 2 in the isolation power supply is forbidden to work;
step 11: in the starting process, the starter generator controller drives the three-stage starter generator to rotate to the ignition speed of the engine from rest;
step 12: after the engine reaches the generating rotation speed, the engine enters the generating process, and when the generating rotation speed and the load change, the voltage regulator and the MOS tube three-phase full-bridge control stably output the direct-current voltage V dc 。
7. The method for designing an aviation low-voltage direct-current three-stage generator power system as claimed in claim 6, wherein the step 11 starting process comprises the steps of:
step 1101: outputting a switch control signal S through a control circuit B And S C Switching on a SCR switch of the relay and switching off a GCR switch of the relay;
step 1102: the input voltage V of 28V is boosted by the DC/DC modules 1 and 2 … … n in the AC excitation power supply Bi Converted into a voltage V of 270V s Increasing output power by connecting a plurality of boosting DC/DC modules in parallel;
step 1103: by Q in AC excitation power supply B1 ～Q B4 The formed single-phase H bridge provides alternating current exciting current for the main exciter;
step 1104: the control circuit adopts a control strategy of a quasi-speed outer ring and a current inner ring, and generates a driving signal G of an MOS tube three-phase full bridge through sinusoidal Space Vector Pulse Width Modulation (SVPWM) control A The starting process is operated in a maximum torque to current ratio mode.
8. The method for designing a three-stage generator power system for aviation low-voltage direct current according to claim 6, wherein the power generation process of the step 12 comprises the following steps:
step 1201: outputting a switch control signal S through a control circuit B And S C Switching off the SCR switch of the relay and switching on the GCR switch of the relay;
step 1202: the output of three-phase alternating current voltage value of the main motor is regulated by the exciting current output by the voltage regulator, and then direct current voltage V is regulated dc Voltage stabilization control of (3);
step 1203: the three-phase alternating current voltage v output by the main motor is realized through the three-phase full bridge of the MOS tube M To a direct voltage V dc On the other hand to achieve a voltage V dc And boost control when the voltage is too low.
9. The method of claim 8, wherein the step 1202 of controlling the voltage of the three-stage generator comprises the steps of:
step 12021: generating a driving signal G of a voltage regulator in a control circuit C1 Generating the power tube Q by using dual-loop control C1 Drive signal G C1 In the double-loop control, the voltage loop is an outer loop, the exciting current loop is an inner loop, and the voltage outer loop is used for outputting the voltage V dc Tracking parameter voltage V ref And generates a current inner loop reference signal I fref The current inner loop is used for leading the excitation current i of the main exciter F Tracking reference signal I fref The current inner ring output is used for controlling the power tube Q C1 Drive signal G C1 Duty cycle D of (2);
step 12022: according to the output DC current I dc Determining the voltage outer loop reference voltage V ref Set the rated current as I N In I dc <2I N When making V ref 28V, in I dc From 2I N To 3I N When changed, make V ref Reducing the voltage from 28V to 0V;
step 12023: determining the maximum exciting current I allowed by the output of the voltage loop according to the input rotating speed n fmax ，I fmax At a rotation speed n, 1.5I N Lower, output voltage V dc The excitation current corresponds to the expected voltage stabilization value;
step 12024: at an input voltage V dc <At 40V, drive signal G C3 Power tube Q1 C3 Constant-conduction power tube Q C2 Drive signal G C2 And a power tube Q C1 Drive signal G C1 Complementary conduction to make the follow current flow through the power tube Q C2 Instead of Q C2 The anti-parallel diode of (1);
step 12025: at an input voltage V dc >At 40V, make the driving signal G C1 ～G C3 Are all equal to 0, power tube Q C1 ～Q C3 Constant turn-off, exciting current of main exciter passing through power tube Q C2 And the reverse parallel diode and the diode DC7 feed energy back to the direct current bus V G In the above way, the rapid demagnetization is realized.
10. The method of claim 8, wherein the step 1203 of controlling the boost pressure comprises the steps of:
step 12031: according to three-phase current i A 、i B And i C Determining a drive signal G for synchronous rectification control A1G ～G A6G Defining a three-phase current i A 、i B And i C The direction of the outflow starting generator controller is positive direction, I refH And I refL Respectively +1/5 and-1/5 of rated current when i A >I refH When making G A2G 1, otherwise G A2G When i is equal to 0 B >I refH When making G A4G 1, otherwise G A4G When i is equal to 0 C >I refH When making G A6G 1, otherwise G A6G When i is equal to 0 A <I refL When making G A1G 1, otherwise G A1G When i is equal to 0 B <I refL While making G A3G 1, otherwise G A3G When i is equal to 0 C <I refL When making G A5G 1, otherwise G A5G ＝0；
Step 12032: according to a DC voltage V dc D.c. current I dc Determining a driving signal G for boost voltage stabilization control A1O ～G A6O Defining a driving signal G A2O The falling edge lag theta is 180 DEG and the angle delta 1 Driving signal G A2O High level pulse width of delta 2 When the DC voltage V is dc <24V and I dc <2I N By increasing delta 2 To increase the active current i q The direct current voltage is stabilized at 24V by adjusting delta 1 To make a reactive current i d Decrease delta 0 1 Corresponding reduction of demagnetization reactive current i d ，δ 1 The adjustment range of (1) is 0-60 DEG, delta 2 The adjusting range of G is 0-90 DEG A1O ～G A6O Having the same positive pulse width, in accordance with G A2O 、G A5O 、G A4O 、G A1O 、G A6O 、G A3O The boosting and voltage stabilizing control drive signal G is formed by sequentially 60 degrees of phase difference A1O ～G A6O ；
Step 12033: according to the driving signal G controlled by synchronous rectification A1G ～G A6G And a voltage-boosting and voltage-stabilizing control drive signal G A1O ～G A6O Determining three-phase full-bridge driving signal G of MOS transistor A ，
Figure FDA0003653101400000081
Figure FDA0003653101400000082
Figure FDA0003653101400000083
CN202210563283.5A 2022-05-19 2022-05-19 Aviation low-voltage direct-current three-stage generator power supply system and design method Pending CN114865965A (en)

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