CN110620405A - Matrix type power distribution system in multi-power supply mode and control method - Google Patents
Matrix type power distribution system in multi-power supply mode and control method Download PDFInfo
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- CN110620405A CN110620405A CN201911088024.6A CN201911088024A CN110620405A CN 110620405 A CN110620405 A CN 110620405A CN 201911088024 A CN201911088024 A CN 201911088024A CN 110620405 A CN110620405 A CN 110620405A
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- 239000007787 solid Substances 0.000 claims abstract description 11
- 238000011217 control strategy Methods 0.000 claims abstract description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 6
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- 238000013461 design Methods 0.000 description 1
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
Abstract
The invention relates to a matrix type power distribution system and a control method under a multi-power supply mode, which are used in an airplane power supply system, wherein the system comprises m paths of power supply sources, a solid state power controller matrix, a power distribution control center and n paths of loads; the solid-state power controller matrix consists of m rows and n columns of SSPC switches, the m paths of power supply sources are respectively connected with one ends of the m rows of SSPC switches, and the n paths of loads are respectively connected with the other ends of the n columns of SSPC switches; the power distribution control center is respectively connected with the m power supply sources and the n loads and used for detecting the voltage and the current of the power supply source side and the voltage and the current of the load side; the system adopts a matrix architecture formed by a plurality of solid state power controllers, realizes effective control of power supply output and load power supply by combining a power distribution control strategy in a multi-path power supply mode, and ensures that electric energy with corresponding power grade can still be provided for a load in a fault state of the load, a power supply or SSPC.
Description
Technical Field
The invention relates to a matrix type power distribution system in a multi-power supply mode and a control method, and belongs to the field of power systems.
Background
With the development of aviation intelligent power distribution technology, a Solid State Power Controller (SSPC) is gradually becoming a main switching device in a power management and distribution system to replace a traditional electromechanical circuit breaker, so as to realize the distribution of power in an aircraft power system and the protection control of various electrical loads. The components of the SSPC include a power semiconductor switching device, sensors to observe output voltage and current and power semiconductor device temperature, and control circuitry, which may include a microcontroller consisting of an Arithmetic Logic Unit (ALU), memory, timer/counter, serial port, input/output (I/0) port, and clock oscillator. Compared with electromechanical switch equipment, the SSPC is based on a power semiconductor electronic switch device, has no mechanical contact, has no arc discharge phenomenon in the non-contact switching process, and can eliminate the arc discharge in the turn-off transient period and the electric shock bounce phenomenon in the turn-on transient period through circuit control. The SSPCs have the capability to perform monitoring and diagnostic functions to identify and prevent overload and short circuit conditions, facilitating advanced protection and diagnostics, and thereby implementing an efficient power management and distribution architecture.
Therefore, SSPC switches are increasingly adopted by power distribution devices in an aircraft power supply system to replace traditional mechanical contact switches, the aircraft electrical system is divided into key loads, important loads and general loads according to the importance degree of the loads, different redundancy power supply modes need to be configured, priority and redundancy power supply modes need to be adopted by the key loads such as flight control navigation in the aircraft system, power can still be supplied through redundancy power supplies under the condition that the power supply in the aircraft power supply system is in a fault state, and therefore multiple paths of power distribution switches need to be arranged in the power distribution system to connect the power supply and the key loads. Usually, there are x critical loads in the aircraft system, and a power distribution switch with a margin x needs to be added correspondingly, so as to realize high-reliability redundant power supply. Because each key load in the redundancy power supply system is provided with a plurality of power distribution switches, the number of the power distribution switches is large, and under the condition of a certain load or power failure, part or all of the corresponding power distribution switches cannot work, and the power distribution switches cannot be used in other occasions, so that the obvious resource waste phenomenon exists in the power distribution system. Especially in current aircraft intelligent power distribution system, mostly adopt SSPC as the distribution switch under the condition, the monitoring and the control function of full play SSPC switch effectively utilize the SSPC switch, combine power supply and the load demand of power supply system, carry out the design of novel framework, have the significance to further promoting distribution system's control flexibility and the robustness of system, also become the important development direction in distribution technical field among the aircraft power supply system.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides a matrix type power distribution system in a multi-power supply mode in an airplane power supply system and a control method thereof.
In order to achieve the purpose, the technical scheme provided by the invention is as follows: a matrix type power distribution system under a multi-power supply mode is used in an airplane power supply system and comprises m power supply sources, a solid state power controller matrix, a power distribution control center and n loads; the solid-state power controller matrix consists of m rows and n columns of SSPC switches, the m paths of power supplies respectively correspond to the m rows of SSPC switches, the n paths of loads respectively correspond to the n columns of SSPC switches, each path of power supply is respectively connected with one end of the corresponding row of SSPC switches, and each path of load is respectively connected with the other end of the corresponding column of SSPC switches; and the power distribution control center is respectively connected with the m power supply lines and the n loads and is used for detecting the voltage and the current of the power supply line side and the voltage and the current of the load side.
A control method of a matrix type power distribution system in a multi-power supply mode comprises the following steps:
the method comprises the following steps that firstly, a power distribution control center determines a load needing power supply and a load power grade in a power distribution system according to the requirement of a flight control computer;
secondly, the power distribution control center detects current measurement signals of SSPC switches which are connected with the load in the solid power controller matrix, and determines the power requirement of the load side after summing the current measurement signals;
thirdly, the power distribution control center judges the state of the power supply according to the detected voltage and current of the power supply, determines the power level of the power supply for normal power supply, and distributes a proportional coefficient k according to the power level1、k2、……、km-1、kmDetermining a given power value of a power supply;
and fourthly, after the power distribution control center makes a difference between the power set value of each power supply and the actually measured power value, the voltage control value of each power supply is obtained after the adjustment of the proportional integrator, and the voltage control value is sent to each power supply controller to adjust the voltage of the power supply so as to realize the control of the output power.
The technical scheme is further designed as follows: when the distribution control center determines that a single load needs to receive power supply of a plurality of power supplies according to the requirement of the flight control computer, the distribution control center switches on SSPC switches corresponding to the power supplies on the columns, connected with the load, in the solid-state power controller matrix according to the requirement of power distribution; when a single power supply supplies power to a plurality of loads, SSPC switches corresponding to the loads on a row in the solid state power controller matrix connected with the power supply are switched on.
And the power distribution control center judges the operating states of the power supply and the load according to the detected voltage and current values of the power supply and the load, and controls the on and off of the corresponding SSPC switches in the solid power controller matrix when one or more power supplies and one or more loads have faults.
When one path of power supply fails, the power distribution control center controls all the SSPC switches in one row corresponding to the path of power supply to be turned off; when one load fails, the distribution control center controls all SSPC switches in a row corresponding to the load to be turned off.
The given power value of each power supply is the power distribution coefficient of each power supply multiplied by the total power demand of the load.
The m power supply paths are direct current or alternating current power supplies; when the power supply is a direct current power supply, SSPC switches of each column of the solid-state power controller matrix can be simultaneously switched on, so that a plurality of direct current power supplies are connected in parallel to supply power to the same load; when the m-path power supply is an alternating current power supply, the SSPC switches in each column of the matrix of the solid-state power controller only allow one SSPC switch to be switched on under the normal working state of the power supply.
Compared with the prior art, the invention has the following beneficial effects:
(1) the matrix type power distribution system in the multi-power supply mode and the control method thereof can effectively utilize the switch in the SSPC matrix to realize the reliable power supply of each path of load and realize the distribution control of the output power by combining the type of the power supply.
(2) The fault-tolerant control strategy of the matrix power distribution system is adopted, so that under the condition of partial power supply, load or SSPC fault, the normal power supply can be continuously used for supplying power to the load, and the redundancy and fault-tolerant capability of the airplane power supply system are further improved.
Drawings
FIG. 1 is a schematic diagram of a matrix power distribution system according to the present invention;
FIG. 2 is a block diagram of power distribution control in the power distribution control method of the present invention;
fig. 3 is a flow chart of a control method of the power distribution control center of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and the specific embodiments.
As shown in fig. 1, the matrix power distribution system or control method in a multi-power supply mode according to the present invention includes 4 power supplies, a Solid State Power Controller (SSPC) matrix, a power distribution control center, and 3 loads. The solid-state power controller matrix consists of 4 rows and 3 columns of SSPC switches, the 4 paths of power supplies respectively correspond to the 4 rows of SSPC switches, the 3 paths of loads respectively correspond to the 3 columns of SSPC switches, each path of power supply is respectively connected with one end of the corresponding row of SSPC switches, and each path of load is respectively connected with the other end of the corresponding column of SSPC switches; and the power distribution control center is respectively connected with the 4 paths of power supplies and the 3 paths of loads and is used for detecting the voltage and the current of the power supply side and the voltage and the current of the load side.
The 4-path power supply can be an alternating current power supply or a direct current power supply, the SSPC matrix structure is in a 4 x 3 structural form, and the SSPC matrix structure is composed of alternating current SSPCs or direct current SSPCs according to the type of the power supply. The power distribution control center detects power output of a power supply side and power requirements of a load side, power supplies with different power levels are provided according to requirements of different loads through switch control of the SSPC matrix, and fault-tolerant power supply of the load side can be achieved by controlling other switches in the SSPC matrix when part of the power supplies or the SSPC in a power distribution system is abnormal or fails.
As shown in fig. 2, the power distribution control strategy of the matrix power distribution system is shown. The power distribution control center obtains load currents of all paths according to current signals of the SSPC, total power requirements of 3 paths of loads are obtained after summation, power distribution coefficients k1, k2, k3 and k4 of all paths of power supplies are respectively set according to power grades of 4 paths of power supplies, the distribution coefficients are in direct proportion to the power grades of the power supplies, and the sum of the distribution coefficients of four paths of power supplies is 1; the distribution coefficients of the four power supplies are respectively multiplied by the total power demand of the load to serve as the given power value of each power supply, the given power and the detected actual output power are differentiated in a closed-loop control mode, the power control signal of the corresponding power supply is obtained after passing through the proportional-integral regulator, the power control signal is output to the controller of the power supply, and the power is effectively distributed through the control of the output voltage of the power control signal.
The distribution control center judges that one or more power supplies and one or more loads enter a fault-tolerant control strategy under the condition of fault according to the detected voltage and current values of the power supply and the loads, controls the on-off control of the corresponding SSPCs in the SSPC matrix to prevent power supply to the fault loads, isolates the fault power supplies and simultaneously ensures that normal loads can be supplied with power. And under the fault state of a certain path of power supply, a row of SSPCs corresponding to the fault power supply in the SSPC matrix is turned off to isolate the fault power supply, and under the fault state of a certain path of load, a column of SSPCs corresponding to the fault load in the SSPC matrix is turned off to prevent the fault load from being supplied with power.
Fig. 3 is a flow chart of a power distribution control strategy in the matrix power distribution system of the present invention, including the following steps:
(1) the power distribution control center determines the load needing power supply and the power grade thereof in the power distribution system according to the requirement of flight control calculation;
(2) the distribution control center receives current measurement signals from working SSPCs connected with loads in an SSPC matrix, and determines the power requirement of the load side after summing the current measurement signals;
(3) the power distribution control center judges the state of the power supply according to the detected voltage and current of the power supply, determines the power grade of the power supply for normal power supply, and determines the power set value of the power supply according to power distribution proportion coefficients k1, k2, k3 and k 4;
(4) the distribution control center makes a difference between the given power value and the actually measured power value of each power supply, obtains the voltage control value of each power supply after the adjustment of the proportional integrator, sends the voltage control value to each power supply controller, adjusts the voltage of each power supply, and realizes the control of the output power.
(5) In the case where a single load is required to receive power from multiple sources, the SSPC connected to the first source is first turned on to power the load, and the SSPC connected to the second source and to the load is then turned on. If power needs to be supplied to a plurality of loads, the SSPC switches on one power supply and corresponding loads are opened.
The technical solutions of the present invention are not limited to the above embodiments, and all technical solutions obtained by using equivalent substitution modes fall within the scope of the present invention.
Claims (8)
1. The utility model provides a matrix distribution system under many power supply mode for among the aircraft power supply system which characterized in that: the system comprises m paths of power supplies, a solid-state power controller matrix, a power distribution control center and n paths of loads; the solid-state power controller matrix consists of m rows and n columns of SSPC switches, the m paths of power supplies respectively correspond to the m rows of SSPC switches, the n paths of loads respectively correspond to the n columns of SSPC switches, each path of power supply is respectively connected with one end of the corresponding row of SSPC switches, and each path of load is respectively connected with the other end of the corresponding column of SSPC switches; and the power distribution control center is respectively connected with the m power supply lines and the n loads and is used for detecting the voltage and the current of the power supply line side and the voltage and the current of the load side.
2. A method for controlling a matrix power distribution system in a multi-power supply mode according to claim 1, comprising the steps of:
the method comprises the following steps that firstly, a power distribution control center determines a load needing power supply and a load power grade in a power distribution system according to the requirement of a flight control computer;
secondly, the power distribution control center detects current measurement signals of SSPC switches which are connected with the load in the solid power controller matrix, and determines the power requirement of the load side after summing the current measurement signals;
thirdly, the power distribution control center judges the state of the power supply according to the detected voltage and current of the power supply, determines the power level of the power supply for normal power supply, and distributes a proportional coefficient k according to the power level1、k2、……、km-1、kmDetermining a given power value of a power supply;
and fourthly, after the power distribution control center makes a difference between the power set value of each power supply and the actually measured power value, the voltage control value of each power supply is obtained after the adjustment of the proportional integrator, and the voltage control value is sent to each power supply controller to adjust the voltage of the power supply so as to realize the control of the output power.
3. The method for controlling the matrix power distribution system in the multi-power supply mode according to claim 2, wherein: when the distribution control center determines that a single load needs to receive power supply of a plurality of power supplies according to the requirement of the flight control computer, the distribution control center switches on SSPC switches corresponding to the power supplies on the columns, connected with the load, in the solid-state power controller matrix according to the requirement of power distribution; when a single power supply supplies power to a plurality of loads, SSPC switches corresponding to the loads on a row in the solid state power controller matrix connected with the power supply are switched on.
4. The method for controlling the matrix power distribution system in the multi-power supply mode according to claim 2, wherein: and the power distribution control center judges the operating states of the power supply and the load according to the detected voltage and current values of the power supply and the load, and controls the on and off of the corresponding SSPC switches in the solid power controller matrix when one or more power supplies and one or more loads have faults.
5. The fault tolerant control strategy of a matrix power distribution system of claim 4, wherein: when one path of power supply fails, the power distribution control center controls all the SSPC switches in one row corresponding to the path of power supply to be turned off; when one load fails, the distribution control center controls all SSPC switches in a row corresponding to the load to be turned off.
6. The fault tolerant control strategy of a matrix power distribution system of claim 2, wherein: the distribution coefficient of the power supply is in direct proportion to the power grade of the power supply, and the sum of the distribution coefficients of all the power supplies is 1.
7. The fault tolerant control strategy of a matrix power distribution system of claim 6, wherein: the given power value of each power supply is the power distribution coefficient of each power supply multiplied by the total power demand of the load.
8. The fault tolerant control strategy of the matrix power distribution system of claim 2, wherein: the m power supply paths are direct current or alternating current power supplies; when the power supply is a direct current power supply, SSPC switches of each column of the solid-state power controller matrix can be simultaneously switched on, so that a plurality of direct current power supplies are connected in parallel to supply power to the same load; when the m-path power supply is an alternating current power supply, the SSPC switches in each column of the matrix of the solid-state power controller only allow one SSPC switch to be switched on under the normal working state of the power supply.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112104069A (en) * | 2020-11-19 | 2020-12-18 | 南京国信能源有限公司 | M direct current power supply modules and N output load switching module circuits |
| CN112803733A (en) * | 2021-04-08 | 2021-05-14 | 上海鹄恩信息科技有限公司 | Power dispatching system |
| WO2024027043A1 (en) * | 2022-08-02 | 2024-02-08 | 广东汇天航空航天科技有限公司 | Power distribution system and method for flaying car, and flying car |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102780402A (en) * | 2011-05-10 | 2012-11-14 | 株式会社安川电机 | Matrix converter |
| US20140203639A1 (en) * | 2013-01-21 | 2014-07-24 | Hamilton Sundstrand Corporation | Reconfigurable matrix-based power distribution architecture |
| US20140217821A1 (en) * | 2013-02-01 | 2014-08-07 | Hamilton Sundstrand Corporation | Matrix-based power distribution architecture |
| CN105548792A (en) * | 2015-12-28 | 2016-05-04 | 中南大学 | Matrix converter switch open circuit fault diagnosis method based on prediction control |
-
2019
- 2019-11-08 CN CN201911088024.6A patent/CN110620405A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102780402A (en) * | 2011-05-10 | 2012-11-14 | 株式会社安川电机 | Matrix converter |
| US20140203639A1 (en) * | 2013-01-21 | 2014-07-24 | Hamilton Sundstrand Corporation | Reconfigurable matrix-based power distribution architecture |
| US20140217821A1 (en) * | 2013-02-01 | 2014-08-07 | Hamilton Sundstrand Corporation | Matrix-based power distribution architecture |
| CN105548792A (en) * | 2015-12-28 | 2016-05-04 | 中南大学 | Matrix converter switch open circuit fault diagnosis method based on prediction control |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112104069A (en) * | 2020-11-19 | 2020-12-18 | 南京国信能源有限公司 | M direct current power supply modules and N output load switching module circuits |
| CN112803733A (en) * | 2021-04-08 | 2021-05-14 | 上海鹄恩信息科技有限公司 | Power dispatching system |
| CN112803733B (en) * | 2021-04-08 | 2021-06-25 | 上海鹄恩信息科技有限公司 | Power dispatching system |
| WO2024027043A1 (en) * | 2022-08-02 | 2024-02-08 | 广东汇天航空航天科技有限公司 | Power distribution system and method for flaying car, and flying car |
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