CN112994299A - SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method - Google Patents

SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method Download PDF

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Publication number
CN112994299A
CN112994299A CN201911283524.5A CN201911283524A CN112994299A CN 112994299 A CN112994299 A CN 112994299A CN 201911283524 A CN201911283524 A CN 201911283524A CN 112994299 A CN112994299 A CN 112994299A
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China
Prior art keywords
permanent magnet
stator
power generation
auxiliary winding
information
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CN201911283524.5A
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Chinese (zh)
Inventor
万波
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Shanghai Aviation Electric Co Ltd
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Shanghai Aviation Electric Co Ltd
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Priority to CN201911283524.5A priority Critical patent/CN112994299A/en
Publication of CN112994299A publication Critical patent/CN112994299A/en
Pending legal-status Critical Current

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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K3/00—Details of windings
    • H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
    • H02K11/20—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
    • H02K11/21—Devices for sensing speed or position, or actuated thereby
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
    • H02K11/30—Structural association with control circuits or drive circuits
    • 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
    • H02P9/305—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 controlling voltage
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P2101/00—Special adaptation of control arrangements for generators
    • H02P2101/30—Special adaptation of control arrangements for generators for aircraft

Abstract

The invention discloses an aviation power generation permanent magnet power generation structure based on SVPWM vector control and an adjusting method, which only comprise a permanent magnet generator, wherein the permanent magnet generator is provided with a stator auxiliary winding, and the stator auxiliary winding is used for changing the magnetic circuit state of the permanent magnet generator so as to adjust the output voltage of the permanent magnet generator. The invention has the beneficial effects that: based on the principle of magnetic field superposition, the air gap magnetic potential is controlled by adjusting the current vector of the stator auxiliary winding, so that the output voltage of the permanent magnet generator is adjusted, and the structure of the generator set is simplified.

Description

SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method
Technical Field
The invention relates to an aviation power generation permanent magnet power generation structure based on SVPWM vector control and an adjusting method.
Background
Permanent Magnet Generators (PMGs) are widely used due to their high power density. According to the electromagnetic induction principle, the permanent magnet generator converts the rotating mechanical energy into electric energy, and three-phase alternating-current voltage is output on the stator power output winding to provide electric energy for a load.
In the field of aviation power generation, in order to improve reliability, modern airplanes increasingly adopt a variable frequency power generation technology, namely, in a generator set, an original constant speed device is cancelled, the rotating speed of a generator changes in a wide range along with an engine, and the frequency change range is 360-800 Hz. If the permanent magnet power generation technology is adopted, if the magnetic field is not adjusted, the output voltage fluctuates within the range of twice the rated voltage.
In order to achieve the purpose of adjusting the output voltage of the generator, a three-body brushless structure of a permanent magnet generator, an exciter and a main generator is generally adopted on a technical path. Referring to fig. 1, the permanent magnet generator is used as a basic voltage source, and is regulated by a control loop to provide an exciting current for the exciter, and the voltage output of the exciter is rectified by a rotating rectifier to provide an exciting current for the rotor of the main generator. Here, the regulation of the aircraft grid output voltage can be achieved by controlling the exciter current of the exciter machine to regulate the exciter current of the main generator. But because the three-body brushless structure is adopted, the volume and the weight of the generator set are increased.
Disclosure of Invention
The invention solves the technical problem that a novel aviation power generation permanent magnet power generation structure based on SVPWM vector control is provided by adopting a three-body brushless structure in the prior art.
In order to achieve the purpose, the technical scheme of the invention is as follows: the aviation power generation permanent magnet power generation structure based on SVPWM vector control only comprises a permanent magnet generator, wherein the permanent magnet generator is provided with a stator auxiliary winding, and the stator auxiliary winding is used for changing the magnetic circuit state of the permanent magnet generator so as to adjust the output voltage of the permanent magnet generator.
As a preferable scheme of the aeronautical power generation permanent magnet power generation structure based on SVPWM vector control, the permanent magnet power generator further comprises,
a rotor;
a stator surrounding the outside of the rotor, the stator auxiliary winding being disposed on the stator;
a stator power output winding disposed on the stator;
a rotor speed sensor for detecting the speed information of the rotor;
a rotor position sensor for detecting position information of the rotor;
an inverter for outputting three-phase alternating current to the stator auxiliary winding; and the number of the first and second groups,
and an excitation control circuit for adjusting the three-phase alternating current output from the inverter to the stator auxiliary winding, based on voltage information from the stator power output winding, the rotational speed information from the rotor rotational speed sensor, the position information from the rotor position sensor, and current information from the stator auxiliary winding.
The invention also discloses an aviation power generation permanent magnet power generation adjusting method based on SVPWM vector control, which comprises the following steps,
step S1, providing the aeronautical power generation permanent magnet power generation structure of claim 1 or 2;
step S2, the excitation control loop receiving voltage information from the stator power output winding, the rotational speed information from the rotor rotational speed sensor, the position information from the rotor position sensor, and current information from the stator auxiliary winding; the current information is converted into d-axis and q-axis components which are relatively static with the rotor through Clarke conversion and Park conversion, and after the d-axis and q-axis components are compared with a preset reference value, Park inverse transformation is carried out to obtain control voltage of SVPWM (space vector pulse width modulation), so that the three-phase alternating current output to the stator auxiliary winding by the inverter is controlled and adjusted; the reference value of the q-axis component of the stator auxiliary winding is 0, the reference value of the d-axis component of the stator auxiliary winding is respectively derived from the rotating speed information of the stator power output winding and the voltage information from the stator power output winding, and the linear superposition of the rotating speed information and the voltage information generates error information of magnetic flux, so that the reference value of the d-axis current component of the auxiliary winding is generated.
Compared with the prior art, the invention has the beneficial effects that: based on the principle of magnetic field superposition, the air gap magnetic potential is controlled by adjusting the current vector of the stator auxiliary winding, so that the output voltage of the permanent magnet generator is adjusted, and the structure of the generator set is simplified.
Drawings
Fig. 1 shows a structure of a conventional three-body (permanent magnet machine + exciter + main generator) variable frequency generator.
Fig. 2 shows a permanent magnet generator structure proposed by this patent.
Fig. 3 is a control and feedback schematic block diagram of the voltage regulation of a permanent magnet generator according to the present patent.
Fig. 4 shows the operating point of the PMG.
Fig. 5 shows the adjustment range of the PMG operating point.
FIG. 6 shows the d-axis and q-axis of the PMG and the corresponding demagnetization and magnetization adjustment ranges.
Fig. 7 shows the magnetic potential vectors and resultant vectors of the three-phase auxiliary windings.
FIG. 8 is a graph of magnitude and phase relationship of three-phase auxiliary winding current to resultant magnetic potential.
Fig. 9 shows a method for regulating the output voltage of the PMG based on SVPWM vector control proposed by this patent.
Detailed Description
The invention will be described in further detail below with reference to specific embodiments and drawings. Here, the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Referring to fig. 2, in the permanent magnet power generation structure for aviation power generation in this embodiment, the permanent magnet machine and the exciter in the original three-body structure are eliminated, and only the permanent magnet main generator remains. The rotor of the motor is composed of permanent magnets, and an auxiliary winding is added to a stator loop for adjusting a magnetic field. Meanwhile, a rotating speed sensor and a position sensor of the rotor are added and used as feedback signals of a control loop.
Fig. 3 is a schematic block diagram of the control and feedback of the voltage regulation of the permanent magnet generator, according to which an excitation control loop obtains voltage information to be regulated from POR, and obtains position and rotation speed information from a rotor sensor as a reference value for control output.
Fig. 4 shows the operating point of the PM, which operates in the second quadrant of the B-H curve, when the permanent magnet acts as a magnetic source to provide a magnetic potential to the magnetic circuit. Since the three-phase stator power winding of the generator has a demagnetization effect under load, the operating point shifts to the left relative to the no-load curve. However, in designing the PMG, it is ensured that the load working line does not exceed the inflection point G, while a space for adjusting the magnetic field is left.
Fig. 5 shows an adjustment range of the PM operating point, which can adjust the output magnetic flux B of the PM by applying the magnetic field Δ H, thereby adjusting the output voltage of the PMG.
FIG. 6 shows the d-axis and q-axis of PMG and the corresponding demagnetizing and magnetizing adjustment ranges, in order to obtain the maximum magnetic field adjustment effect, the applied magnetic potential is made to coincide with the d-axis of PM, and the applied magnetic potential has the pure magnetizing and pure demagnetizing effects.
Fig. 7 shows a magnetic potential vector and a resultant vector of the three-phase auxiliary winding, and when three-phase ac power is applied to the three-phase auxiliary winding, the resultant magnetic potential is rotated, and if the rotating magnetic field frequency can be controlled to be equal to the PM rotating frequency, the magnetic flux of PM can be adjusted.
Fig. 8 shows the magnitude and phase relationship between the three-phase auxiliary winding current and the resultant magnetic potential, the magnitude of which is 3/2 times the maximum value of the single-phase magnetic potential, and the phase of which coincides with the a-phase current.
Fig. 9 shows the method for regulating the output voltage of the PMG based on SVPWM vector control proposed in this patent, and the feedback parameters of the control loop include the voltage at the PMG output regulation point POR, the rotation speed and rotor position information of the PMG, and the three-phase current output by the inverter to the PMG auxiliary winding. The current information is converted into d and q components which are relatively static with the PMG rotor through Clarke conversion and Park conversion, the d and q components are compared with a preset threshold value, and then Park inverse transformation is carried out to obtain the control voltage of SVPWM, so that the output current of the inverter is controlled. The reference value of the q-axis current component of the auxiliary winding is 0, namely the auxiliary winding plays a role in magnetizing or demagnetizing; and the reference value of the d-axis component is respectively derived from the rotor speed information and the voltage information at POR, and the linear superposition of the two generates the error information of the magnetic flux, so that the reference value of the d-axis current component of the auxiliary winding is generated.
The foregoing merely represents embodiments of the invention, which are described in some detail and detail, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims (3)

1. The aeronautical power generation permanent magnet power generation structure based on SVPWM vector control is characterized by only comprising a permanent magnet generator, wherein the permanent magnet generator is provided with a stator auxiliary winding, and the stator auxiliary winding is used for changing the magnetic circuit state of the permanent magnet generator so as to adjust the output voltage of the permanent magnet generator.
2. The SVPWM vector control-based aeronautical power generation permanent magnet power generation structure of claim 1, wherein said permanent magnet generator further comprises,
a rotor;
a stator surrounding the outside of the rotor, the stator auxiliary winding being disposed on the stator;
a stator power output winding disposed on the stator;
a rotor speed sensor for detecting the speed information of the rotor;
a rotor position sensor for detecting position information of the rotor;
an inverter for outputting three-phase alternating current to the stator auxiliary winding; and the number of the first and second groups,
and an excitation control circuit for adjusting the three-phase alternating current output from the inverter to the stator auxiliary winding, based on voltage information from the stator power output winding, the rotational speed information from the rotor rotational speed sensor, the position information from the rotor position sensor, and current information from the stator auxiliary winding.
3. The aviation power generation permanent magnet power generation adjusting method based on SVPWM vector control is characterized by comprising the following steps,
step S1, providing the aeronautical power generation permanent magnet power generation structure of claim 1 or 2;
step S2, the excitation control loop receiving voltage information from the stator power output winding, the rotational speed information from the rotor rotational speed sensor, the position information from the rotor position sensor, and current information from the stator auxiliary winding; the current information is converted into d-axis and q-axis components which are relatively static with the rotor through Clarke conversion and Park conversion, and after the d-axis and q-axis components are compared with a preset reference value, Park inverse transformation is carried out to obtain control voltage of SVPWM (space vector pulse width modulation), so that the three-phase alternating current output to the stator auxiliary winding by the inverter is controlled and adjusted; the reference value of the q-axis component of the stator auxiliary winding is 0, the reference value of the d-axis component of the stator auxiliary winding is respectively derived from the rotating speed information of the stator power output winding and the voltage information from the stator power output winding, and the linear superposition of the rotating speed information and the voltage information generates error information of magnetic flux, so that the reference value of the d-axis current component of the auxiliary winding is generated.
CN201911283524.5A 2019-12-13 2019-12-13 SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method Pending CN112994299A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911283524.5A CN112994299A (en) 2019-12-13 2019-12-13 SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911283524.5A CN112994299A (en) 2019-12-13 2019-12-13 SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method

Publications (1)

Publication Number Publication Date
CN112994299A true CN112994299A (en) 2021-06-18

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911283524.5A Pending CN112994299A (en) 2019-12-13 2019-12-13 SVPWM vector control-based aeronautical power generation permanent magnet power generation structure and adjusting method

Country Status (1)

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CN (1) CN112994299A (en)

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