CN111082506A - Energy management system and method suitable for autonomous multifunctional service aircraft - Google Patents
Energy management system and method suitable for autonomous multifunctional service aircraft Download PDFInfo
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- CN111082506A CN111082506A CN201911360798.XA CN201911360798A CN111082506A CN 111082506 A CN111082506 A CN 111082506A CN 201911360798 A CN201911360798 A CN 201911360798A CN 111082506 A CN111082506 A CN 111082506A
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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
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/425—Power storage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
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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
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
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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
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
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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
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/007—Regulation of charging or discharging current or voltage
Abstract
The invention discloses an energy management system and method suitable for an autonomous multifunctional service aircraft, which comprises the following steps: the system comprises a solar cell array, a solar energy adjusting unit, a storage battery adjusting unit, a bus capacitor array Cbus, a control system, a Load and a primary bus; the solar cell array is connected with the solar energy adjusting unit; the storage battery is connected with the storage battery adjusting unit; the solar energy adjusting unit adjusts the output power of the solar cell array; the storage battery adjusting unit is used for controlling the charging and discharging of the storage battery; the bus capacitor array Cbus is connected between the primary bus output positive return wires; the control system collects system state information, performs control calculation and outputs control signals. The invention designs three control modes of bus constant voltage control, storage battery charging control and MPP control, so that the space energy system can be automatically switched to a corresponding working mode according to specific working conditions.
Description
Technical Field
The invention belongs to the general technical field of aerospace, and particularly relates to an energy management system and method suitable for an autonomous multifunctional service aircraft.
Background
With the rapid advance of aerospace science and technology in China, spacecraft energy systems develop towards high power and intellectualization, and the traditional centralized energy management system cannot meet the energy requirements of future aircrafts more and more due to the defects of large volume, complex control and low power density.
Disclosure of Invention
The technical problem solved by the invention is as follows: the traditional space energy manager consisting of three converters of SA + BCR + BDR needs to be switched among three working domains, the control logic is complex, and in addition, the three converters are large in size and weight due to the formation mode, and modularization and power level extension are not easy to realize. The invention overcomes the defects of the prior art, provides an energy management system and an energy management method suitable for an autonomous multifunctional service aircraft, and designs three control modes of bus constant voltage control, storage battery charging control and MPP control and a logic switching mode among the three modes in order to adapt to complex and changeable space environments and system state changes caused by load changes, so that a space energy system can be autonomously switched to a corresponding working mode according to specific working conditions.
The purpose of the invention is realized by the following technical scheme: an energy management system adapted for use with an autonomous multifunction service aircraft, comprising: the system comprises a solar cell array, a solar energy adjusting unit, a storage battery adjusting unit, a bus capacitor array Cbus, a control system, a Load and a primary bus; the solar energy adjusting unit, the storage battery adjusting unit, the bus capacitor array Cbus, the control system and the Load are all connected with a primary bus; the solar cell array is connected with the solar energy adjusting unit; the storage battery is connected with the storage battery adjusting unit; the solar energy adjusting unit is powered by the solar cell array and adjusts the output power of the solar cell array according to the energy; the storage battery adjusting unit is powered by a storage battery and performs charge and discharge control on the storage battery; the bus capacitor array Cbus is connected between the primary bus output positive return wires and used for outputting filtering and providing instantaneous power; the control system collects system state information, performs control calculation, outputs control signals and controls the switch tube of the solar energy adjusting unit and the charging switch tube of the storage battery to act.
In the above energy management system for an autonomous multifunctional service aircraft, the solar energy conditioning unit comprises four identical DC/DC converters; the output voltages of the four mutually independent solar cell arrays are output in parallel after passing through the corresponding DC/DC converters to form a primary bus.
In the above energy management system for an autonomous multifunctional service aircraft, the battery regulation unit includes a charge switching tube, a charge diode Dc, and a discharge diode Dd; the drain electrode of the charging switch tube is connected with the primary bus, the source electrode of the charging switch tube is connected with the anode of the charging diode Dc, and the cathode of the charging diode Dc is connected with the storage battery; the storage battery is connected with the anode of the discharge diode Dd, and the cathode of the discharge diode Dd is connected with the primary bus; charging a storage battery via: the primary bus current enters a drain electrode of the charging switch tube, flows out of a source electrode of the charging switch tube, enters an anode of the charging diode Dc, flows out of a cathode of the charging diode Dc, and enters the storage battery; discharging path to the storage battery: the storage battery is connected with the anode of the discharge diode Dd, and the cathode of the discharge diode Dd is connected with the primary bus.
In the energy management system suitable for the autonomous multifunctional service aircraft, the bus capacitor array Cbus is a capacitor array with a capacitance value of 2 mF.
In the energy management system for the autonomous multifunctional service aircraft, the control system comprises an information acquisition unit, a logic operation unit and a control output unit; the information acquisition unit acquires a primary bus output voltage value, an output current value of the solar energy regulation unit, a terminal voltage value of the storage battery, a charging current value of the storage battery, an output voltage value of the solar cell array and an output current value of the solar cell array, and transmits the primary bus output voltage value, the output current value of the solar energy regulation unit, the terminal voltage value of the storage battery, the charging current value of the storage battery, the output voltage value of the solar cell array and the output current value of the solar cell array to the logic operation unit; the logic operation unit outputs control signals to control the switch tube of the DC/DC converter and the charging switch tube of the storage battery to act after logic operation.
A method of energy management for an autonomous multifunction service aircraft, the method comprising the steps of: (1) calculating a bus constant voltage control voltage reference value by a droop method; (2) injecting or appointing a constant voltage charging voltage reference value of the storage battery by the upper computer; (3) injecting or appointing a constant current charging current reference value of the storage battery by the upper computer; (4) collecting a primary bus output voltage value, and entering a logic operation unit through an information collection unit; (5) collecting the output current value of the solar energy adjusting unit, and entering a logic operation unit through an information collecting unit; (6) acquiring a terminal voltage value of the storage battery, and entering a logic operation unit through an information acquisition unit; (7) collecting the charging current value of the storage battery, and entering a logic operation unit through an information collection unit; (8) collecting the output voltage value of the solar cell array, and entering a logic operation unit through an information collection unit; (9) collecting the output current value of the solar cell array, and entering a logic operation unit through an information collection unit; (10) obtaining a difference value by making a difference between a bus constant voltage control voltage reference value and a primary bus output voltage value, sending the difference value to a voltage controller in a logic operation unit to obtain a current reference signal, and sending the difference value to a current controller in the logic operation unit to obtain a first modulation signal by making a difference between the current reference signal and an output current value of a solar energy adjusting unit to realize voltage-current double closed loop control; (11) the current reference value of the constant-current charging current of the storage battery is summed with the current sampling value of the load to obtain a current reference value of the solar energy adjusting unit, and the current reference value is subtracted from the output current value of the solar energy adjusting unit and sent to a current controller in the logic operation unit to obtain a second modulation signal, so that the constant-current charging control of the storage battery is realized; (12) the difference between the constant voltage charging voltage reference value of the storage battery and the output voltage value of the primary bus is sent to a voltage controller in a logic operation unit to obtain a third modulation signal, so that the constant voltage charging control of the storage battery is realized; (13) and taking the output voltage value of the solar cell array and the output current value of the solar cell array as controlled quantities of the MPPT control loop, calculating a voltage reference value at the maximum power point under the current illumination by adopting an incremental conductance method, making a difference with the output voltage value of the solar cell array, and sending the difference value into a logic operation unit to obtain a fourth modulation signal so as to realize the MPPT control.
In the above energy management method for the autonomous multifunctional service aircraft, in step (1), the formula of the bus constant voltage control voltage reference value is as follows:
Vref1＝kf×Io+Vref；
wherein Vref1 is a bus constant voltage control voltage reference value; kf is the droop coefficient; io is load current; and Vref is a bus constant voltage control voltage reference value when the droop method is not added.
Compared with the prior art, the invention has the following beneficial effects:
1) the invention adopts a semi-regulation type bus structure, connects the photovoltaic cell to the primary bus through the DC/DC converter, connects the storage battery to the primary bus through the switch circuit composed of the switch tube and the diode, compared with the traditional full regulation type energy manager, saves two DC/DC converters for charging and discharging the storage battery, reduces the type and the number of the parallel converters on the bus, reduces the volume and the weight of the system, reduces the loss caused by the DC/DC conversion, and improves the efficiency.
2) The photovoltaic cell DC/DC converter realizes three control modes of bus constant voltage control, storage battery charging and discharging control and MPPT control of a nested droop method, and the three control modes automatically switch control modes along with the change of external light intensity and load working conditions. Compared with the traditional energy manager control method, the method is more flexible in control, can adapt to the space environment, skillfully increases MPPT control on the basis of greatly simplifying the control logic of the traditional method, and greatly improves the utilization rate of space energy.
3) The invention adopts a modularized distributed design concept, parallel current sharing control is added in bus constant voltage control, and compared with the traditional centralized energy manager, the invention solves the problem that the power of the energy manager is not easy to expand, and lays a foundation for the requirement of extra-high power of the spacecraft in the future.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
fig. 1 is a block diagram of an energy management system suitable for an autonomous multifunctional service aircraft according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of a system circuit according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of a system control method according to an embodiment of the present invention.
Fig. 4 is a schematic control flow diagram of the system according to the embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a block diagram of an energy management system suitable for an autonomous multifunctional service aircraft according to an embodiment of the present invention. As shown in fig. 1, the energy management system for an autonomous multifunctional service aircraft comprises: the system comprises a solar cell array, a solar energy adjusting unit, a storage battery adjusting unit, a bus capacitor array Cbus, a control system, a Load and a primary bus; wherein the content of the first and second substances,
the solar energy adjusting unit, the storage battery adjusting unit, the bus capacitor array Cbus, the control system and the Load are all connected with a primary bus; the solar cell array is connected with the solar energy adjusting unit; the storage battery is connected with the storage battery adjusting unit; the solar energy adjusting unit is powered by the solar cell array and adjusts the output power of the solar cell array according to the energy; the storage battery adjusting unit is powered by a storage battery and performs charge and discharge control on the storage battery; the bus capacitor array Cbus is connected between the primary bus output positive return wires and used for outputting filtering and providing instantaneous power; the control system collects system state information, performs control calculation, outputs control signals and controls the switch tube of the solar energy adjusting unit and the charging switch tube of the storage battery to act.
The solar energy adjusting unit comprises four same DC/DC converters; the output voltages of the four mutually independent solar cell arrays are output in parallel after passing through the corresponding DC/DC converters to form a primary bus.
As shown in fig. 1, the battery adjusting unit includes a charge switching tube, a charge diode Dc, and a discharge diode Dd; the drain electrode of the charging switch tube is connected with the primary bus, the source electrode of the charging switch tube is connected with the anode of the charging diode Dc, and the cathode of the charging diode Dc is connected with the storage battery; the storage battery is connected with the anode of the discharge diode Dd, and the cathode of the discharge diode Dd is connected with the primary bus; charging a storage battery via: the primary bus current enters a drain electrode of the charging switch tube, flows out of a source electrode of the charging switch tube, enters an anode of the charging diode, flows out of a cathode of the charging diode and enters the storage battery; discharging path to the storage battery: the accumulator is connected with the anode of the discharge diode, and the cathode of the diode is connected with the primary bus.
The bus capacitor array Cbus is a capacitor array with the capacitance value of 2 mF; the capacitor array is connected between the positive return lines of the primary bus of the energy manager and is close to the output port.
As shown in fig. 1, the control system includes an information acquisition unit, a logical operation unit, and a control output unit; the information acquisition unit acquires a primary bus output voltage value, an output current value of the solar energy regulation unit, a terminal voltage value of the storage battery, a charging current value of the storage battery, an output voltage value of the solar cell array and an output current value of the solar cell array, and transmits the primary bus output voltage value, the output current value of the solar energy regulation unit, the terminal voltage value of the storage battery, the charging current value of the storage battery, the output voltage value of the solar cell array and the output current value of the solar cell array to the logic operation unit; the logic operation unit outputs control signals to control the switch tube of the DC/DC converter and the charging switch tube of the storage battery to act after logic operation.
Specifically, fig. 1 is a system architecture of a distributed energy manager based on a half regulation BUS adopted in the present invention, a solar cell array SA is connected to a BUS through a DC/DC converter, a battery BAT is connected to the BUS through a battery regulation unit composed of a battery charging switch S, a charging diode DC and a discharging diode Dd, where Cbus represents a BUS capacitor array, and Load represents a Load.
Fig. 2 is a circuit diagram of a distributed energy manager based on a half-regulated bus adopted in the invention, SA 1-SA 4 represent four solar panels, BAT represents a storage battery, and the whole circuit is composed of two parts as shown in the figure: an energy conversion part composed of four identical DC/DC converters and a storage battery regulating unit composed of a charging switch and a diode.
The DC/DC converter will be described by taking a first circuit as an example, and includes an input filter circuit, an energy conversion circuit, and an output filter circuit. The input filter circuit consists of Lin1, Cin1, Cd1 and Rd1, the output voltage of the solar cell array SA1 is connected with one end of an inductor Lin1, the other end of the Lin1 is connected with a capacitor Cin1, the other end of the Cin1 is connected with an SA1 loop, the capacitor Cd1 is connected with a resistor Rd1 in series and then connected with the Cin1 in parallel, and the design of the filter circuit ensures that the input current of the converter is continuous and the pulsation amount is small, improves the quality of input electric energy and is beneficial to prolonging the service life of the solar cell array. The energy conversion circuit consists of a power switch tube S01 and a freewheeling diode Dx1, the drain of the S01 is connected with the output end of the input filter circuit, the source of the S01 is connected with the cathode of the Dx1, the anode of the Dx1 is connected with an SA1 return wire, and the S01 and the Dx1 realize the control of the input/output voltage/current of the converter through high-frequency switching action. The output filter circuit consists of Lf1 and Co1, one end of Lf1 is connected with the cathode of Dx1, the other end of Lf1 is connected with one end of Co1 and the anode of an output diode Do1, the other end of Co1 is connected with an SA1 return wire, and the output filter circuit is used for ensuring the output voltage and current of the converter to be stable. D01 is the inverter output isolation diode to prevent internal circulating currents when the inverters are connected in parallel.
The battery charge/discharge management circuit is described as including a battery charge switch S, a battery charge diode Dc, a battery discharge diode Dd, and a battery switch S3. Charging a storage battery via: the primary bus current enters the S drain electrode of the charging switch tube, flows out of the S source electrode of the charging switch tube, enters the anode of the charging diode Dc, flows out of the cathode of the charging diode Dc, enters the S3 source electrode of the storage battery switch, and the S3 drain electrode is connected with the output end of the storage battery; when the charging switch is conducted, the bus voltage is clamped to the voltage of the storage battery, the system is switched to a storage battery charging and discharging control mode, and storage battery charging management control is carried out according to space illumination and load conditions. Dc is a charging diode and is used for preventing the current of the storage battery from flowing into the bus through the S body diode and increasing the charging and discharging reliability of the system. Discharging path to the storage battery: the accumulator is connected with the anode of the discharge diode Dd, and the cathode of the diode is connected with the primary bus. And the Dd is a storage battery discharge diode, and when the output power of the photovoltaic cell is not enough to be supplied to a load or the photovoltaic is not output in a shadow period, the storage battery supplies power to the load through the diode Dd.
Fig. 3 is a control block diagram of the distributed energy management technique proposed in the present invention, which includes: constant voltage loop control, storage battery charging management control, MPPT control and control logic judgment based on a droop current sharing method.
The constant pressure control technology based on the droop method comprises the following steps: the reference voltage is a bus voltage reference value obtained by a droop curve, the reference value is different from a bus voltage feedback value, the difference value is sent to the controller Gcl to obtain a current reference signal Io _ ref, the difference between the current reference signal and the feedback value is sent to the controller Gc5, and finally a modulation signal Uc1 is generated.
And (3) storage battery charging management control: the charging current reference value is a constant current charging instruction Ibat _ ref and can be set in an upper computer or a control program according to actual conditions, the charging current feedback value is obtained by subtracting load current from output current of the photovoltaic cell converter SA _ DCDC, the charging current reference value and the feedback value are differed, and the difference value is sent to the controller Gc2 to obtain a modulation signal Uc 2; the charging voltage reference value is a constant voltage charging instruction Vbat _ ref, can be set in an upper computer or a control program according to actual conditions, the charging voltage feedback value is the voltage of the storage battery, the charging voltage reference value is different from the feedback value, and the difference value is sent to a controller Gc3 to obtain a modulation signal Uc 3; the modulation signals Uc2 and Uc3 are used as output quantities of control logic judgment 1, and the modulation signals Uc23 are obtained after logic operation.
MPPT electric control: the output voltage sampling value Vsa _ fb and the output current sampling value Isa _ fb of the solar cell array are used as controlled quantities of the MPPT control loop, the output voltage reference value Vsa _ ref of the photovoltaic cell is calculated by adopting an incremental conductance method, the reference value is different from the sampling value Vsa _ fb, and the difference value is sent to a controller Gc4 to obtain a modulation signal Uc 4.
And (4) judging by the control logic: the modulation signals Uc1, Uc23 and Uc4 obtained by constant voltage control, storage battery charge and discharge control and MPPT control are used as input quantity of a control logic judgment 2, the modulation signal Uc is obtained after logic operation, the modulation signal Uc is used as the current-sharing loop control input of each power component in the SA _ DCDC converter to obtain four modulation signals Ucx1, Ucx2, Ucx3 and Ucx4, the four modulation signals are compared with carrier signals to obtain duty ratios, and PWM pulse signals are generated and sent to each power component driving circuit of the SA _ DCDC converter.
Fig. 4 is a control flow chart of the distributed energy management method according to the present invention, and the control flow chart provides specific implementation modes of three control modes of bus voltage control, battery charging control and MPPT control according to the nested droop method, and determination conditions for mode switching. As shown in fig. 4, the method includes the steps of:
(1) calculating a bus constant voltage control voltage reference value (Vref1 ═ kf × Io + Vref) by a droop method; wherein Vref1 is a bus constant voltage control voltage reference value; kf is the droop coefficient; io is load current; and Vref is a bus constant voltage control voltage reference value when the droop method is not added.
(2) Injecting or appointing a constant voltage charging voltage reference value of the storage battery by the upper computer;
(3) injecting or appointing a constant current charging current reference value of the storage battery by the upper computer;
(4) collecting a primary bus output voltage value, and entering a logic operation unit through an information collection unit;
(5) collecting the output current value of the solar energy adjusting unit, and entering a logic operation unit through an information collecting unit;
(6) acquiring a terminal voltage value of the storage battery, and entering a logic operation unit through an information acquisition unit;
(7) collecting the charging current value of the storage battery, and entering a logic operation unit through an information collection unit;
(8) collecting the output voltage value of the solar cell array, and entering a logic operation unit through an information collection unit;
(9) collecting the output current value of the solar cell array, and entering a logic operation unit through an information collection unit;
(10) obtaining a difference value by making a difference between a bus constant voltage control voltage reference value and a primary bus output voltage value, sending the difference value to a voltage controller in a logic operation unit to obtain a current reference signal, and sending the difference value to a current controller in the logic operation unit to obtain a first modulation signal by making a difference between the current reference signal and an output current value of a solar energy adjusting unit to realize voltage-current double closed loop control;
(11) the current reference value of the constant-current charging current of the storage battery is summed with the current sampling value of the load to obtain a current reference value of the solar energy adjusting unit, and the current reference value is subtracted from the output current value of the solar energy adjusting unit and sent to a current controller in the logic operation unit to obtain a second modulation signal, so that the constant-current charging control of the storage battery is realized;
(12) the difference between the constant voltage charging voltage reference value of the storage battery and the output voltage value of the primary bus is sent to a voltage controller in a logic operation unit to obtain a third modulation signal, so that the constant voltage charging control of the storage battery is realized;
(13) and taking the output voltage value of the solar cell array and the output current value of the solar cell array as controlled quantities of the MPPT control loop, calculating a voltage reference value at the maximum power point under the current illumination by adopting an incremental conductance method, making a difference with the output voltage value of the solar cell array, and sending the difference value into a logic operation unit to obtain a fourth modulation signal so as to realize the MPPT control.
(14) The control logic judgment 1 selects the minimum value through a small value taking circuit and judges the charging mode of the storage battery, so that the switching between the constant-current charging mode and the constant-voltage charging mode of the storage battery is realized;
(15) and (3) the control logic judgment 2 divides the system into three working domains by setting two threshold values and judging the state quantity (0 or 1) of the charging switch of the storage battery, and judges which working domain the modulation signal is in to determine the actual control mode of the system.
The distributed energy management method works in four working modes according to actual load working conditions and working environment systems, and comprises bus constant voltage control, storage battery constant current charging control, storage battery constant voltage charging control and MPPT control of a nested droop method.
When the illumination is sufficient and the charging instruction of the storage battery is not sent to the working condition, the bus constant voltage control of the nested droop method is operated, the steps (1), (4), (5), (10) and (15) are executed to realize primary bus constant voltage output, and the parallel current sharing capability is realized; when the illumination is sufficient and a storage battery charging instruction is sent, the storage battery charging control is carried out, if the voltage of the storage battery is lower than the design voltage of the storage battery by 2V, the steps (3), (5), (7), (11), (14) and (15) are executed to realize the constant-current charging control of the storage battery until a charging switch is closed or the constant-voltage charging control of the storage battery is carried out; under the control of the constant-current charging of the storage battery, when the voltage of the storage battery is not lower than 1V of a design value, executing the steps (2), (4), (6), (12), (14) and (15) to realize the control of the constant-voltage charging of the storage battery until a charging switch is closed; when the illumination is insufficient, the output power of the solar cell array is smaller than the load power, the solar cell array works in MPPT control, the steps (8), (9), (13) and (15) are executed, the storage battery discharges to work, and the photovoltaic cell adjusting unit enters an MPPT working mode to generate the maximum power under the current illumination intensity.
Specifically, the storage battery is used as an auxiliary energy source of the system, and when the system is started and works when being powered on for the first time, the steps are as follows:
(1) judging whether the storage battery is mounted to the deck;
(2) judging whether a storage battery access switch is turned on or not;
(3) acquiring input voltage and current, output voltage and current, inductive current and various switch state quantities required in system control;
(4) judging whether the system has overvoltage and overcurrent conditions through voltage and current, if so, blocking PWM pulse, and turning off a power switch tube to perform overvoltage and overcurrent protection on the system, and if not, entering the fifth step;
(5) judging whether the storage battery charging open pipe S is opened or not, and if so, further opening (6); if the charging switch of the storage battery is judged not to be switched on, the bus constant voltage control (10) is started;
(6) judging whether the voltage of the storage battery is less than 99V (the set voltage value when the storage battery is fully charged), if so, indicating that the storage battery is not charged to the set voltage value, and entering (7) to adopt a constant current charging mode; if the voltage of the storage battery is greater than or equal to 99V, the constant-current charging of the storage battery is finished, and a constant-voltage charging mode (8) is entered;
(7) entering a constant current charging mode;
(8) entering a constant voltage charging mode;
(9) until the charging of the storage battery is completed or the charging switch is turned off;
(10) controlling the bus voltage to be 100V;
(11) then judging whether the bus voltage is equal to the storage battery voltage, if not, indicating that the photovoltaic cell can meet the load requirement, the storage battery does not participate in control, returning to the step (10) to continue constant voltage control (10), if the bus voltage is equal to the storage battery terminal voltage, indicating that the illumination is insufficient, the bus voltage is clamped by the storage battery terminal voltage, the photovoltaic cell and the storage battery supply power to the load together, and the converter enters (12);
(12) working in an MPPT mode;
each control mode calculates a modulation signal to be sent to the TCMP to generate PWM pulses.
The invention adopts a semi-regulation type bus structure, connects the photovoltaic cell to the primary bus through the DC/DC converter, connects the storage battery to the primary bus through the switch circuit composed of the switch tube and the diode, compared with the traditional full regulation type energy manager, saves two DC/DC converters for charging and discharging the storage battery, reduces the type and the number of the parallel converters on the bus, reduces the volume and the weight of the system, reduces the loss caused by the DC/DC conversion, and improves the efficiency.
The photovoltaic cell DC/DC converter realizes three control modes of bus constant voltage control, storage battery charging and discharging control and MPPT control of a nested droop method, and the three control modes automatically switch control modes along with the change of external light intensity and load working conditions. Compared with the traditional energy manager control method, the method is more flexible in control, can adapt to the space environment, skillfully increases MPPT control on the basis of greatly simplifying the control logic of the traditional method, and greatly improves the utilization rate of space energy.
The invention adopts a modularized distributed design concept, parallel current sharing control is added in bus constant voltage control, and compared with the traditional centralized energy manager, the invention solves the problem that the power of the energy manager is not easy to expand, and lays a foundation for the requirement of extra-high power of the spacecraft in the future.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (7)
1. An energy management system adapted for use with an autonomous multi-function service aircraft, comprising: the system comprises a solar cell array, a solar energy adjusting unit, a storage battery adjusting unit, a bus capacitor array Cbus, a control system, a Load and a primary bus; wherein the content of the first and second substances,
the solar energy adjusting unit, the storage battery adjusting unit, the bus capacitor array Cbus, the control system and the Load are all connected with a primary bus;
the solar cell array is connected with the solar energy adjusting unit;
the storage battery is connected with the storage battery adjusting unit;
the solar energy adjusting unit is powered by the solar cell array and is used for adjusting the output power of the solar cell array;
the storage battery adjusting unit is powered by a storage battery and performs charge and discharge control on the storage battery;
the bus capacitor array Cbus is connected between the primary bus output positive return wires and used for outputting filtering and providing instantaneous power;
the control system collects the state information, outputs a control signal according to the state information and controls the switch tube of the solar energy adjusting unit and the charging switch tube of the storage battery to act.
2. The energy management system for an autonomous multifunctional service aircraft according to claim 1, characterized in that: the solar energy adjusting unit comprises four same DC/DC converters; the output voltages of the four mutually independent solar cell arrays are output in parallel after passing through the corresponding DC/DC converters to form a primary bus.
3. The energy management system for an autonomous multifunctional service aircraft according to claim 1, characterized in that: the storage battery adjusting unit comprises a charging switch tube, a charging diode Dc and a discharging diode Dd; wherein the content of the first and second substances,
the drain electrode of the charging switch tube is connected with the primary bus, the source electrode of the charging switch tube is connected with the anode of the charging diode Dc, and the cathode of the charging diode Dc is connected with the storage battery; the storage battery is connected with the anode of the discharge diode Dd, and the cathode of the discharge diode Dd is connected with the primary bus;
charging a storage battery via: the primary bus current enters a drain electrode of the charging switch tube, flows out of a source electrode of the charging switch tube, enters an anode of the charging diode Dc, flows out of a cathode of the charging diode Dc, and enters the storage battery; discharging path to the storage battery: the storage battery is connected with the anode of the discharge diode Dd, and the cathode of the discharge diode Dd is connected with the primary bus.
4. The energy management system for an autonomous multifunctional service aircraft according to claim 1, characterized in that: and the bus capacitor array Cbus is a capacitor array with the capacitance value of 2 mF.
5. The energy management system for an autonomous multifunctional service aircraft according to claim 3, characterized in that: the control system comprises an information acquisition unit, a logic operation unit and a control output unit; wherein the content of the first and second substances,
the information acquisition unit acquires a primary bus output voltage value, an output current value of the solar energy regulation unit, a terminal voltage value of the storage battery, a charging current value of the storage battery, an output voltage value of the solar cell array and an output current value of the solar cell array, and transmits the primary bus output voltage value, the output current value of the solar energy regulation unit, the terminal voltage value of the storage battery, the charging current value of the storage battery, the output voltage value of the solar cell array and the output current value of the solar cell array to the logic operation unit;
the logic operation unit outputs control signals to control the switch tube of the DC/DC converter and the charging switch tube of the storage battery to act after logic operation.
6. A method of energy management for an autonomous multifunctional service aircraft, the method comprising the steps of:
(1) calculating a bus constant voltage control voltage reference value by a droop method;
(2) injecting or appointing a constant voltage charging voltage reference value of the storage battery by the upper computer;
(3) injecting or appointing a constant current charging current reference value of the storage battery by the upper computer;
(4) collecting a primary bus output voltage value, and entering a logic operation unit through an information collection unit;
(5) collecting the output current value of the solar energy adjusting unit, and entering a logic operation unit through an information collecting unit;
(6) acquiring a terminal voltage value of the storage battery, and entering a logic operation unit through an information acquisition unit;
(7) collecting the charging current value of the storage battery, and entering a logic operation unit through an information collection unit;
(8) collecting the output voltage value of the solar cell array, and entering a logic operation unit through an information collection unit;
(9) collecting the output current value of the solar cell array, and entering a logic operation unit through an information collection unit;
(10) obtaining a difference value by making a difference between a bus constant voltage control voltage reference value and a primary bus output voltage value, sending the difference value to a voltage controller in a logic operation unit to obtain a current reference signal, and sending the difference value to a current controller in the logic operation unit to obtain a first modulation signal by making a difference between the current reference signal and an output current value of a solar energy adjusting unit to realize voltage-current double closed loop control;
(11) the current reference value of the constant-current charging current of the storage battery is summed with the current sampling value of the load to obtain a current reference value of the solar energy adjusting unit, and the current reference value is subtracted from the output current value of the solar energy adjusting unit and sent to a current controller in the logic operation unit to obtain a second modulation signal, so that the constant-current charging control of the storage battery is realized;
(12) the difference between the constant voltage charging voltage reference value of the storage battery and the output voltage value of the primary bus is sent to a voltage controller in a logic operation unit to obtain a third modulation signal, so that the constant voltage charging control of the storage battery is realized;
(13) and taking the output voltage value of the solar cell array and the output current value of the solar cell array as controlled quantities of the MPPT control loop, calculating a voltage reference value at the maximum power point under the current illumination by adopting an incremental conductance method, making a difference with the output voltage value of the solar cell array, and sending the difference value into a logic operation unit to obtain a fourth modulation signal so as to realize the MPPT control.
7. The energy management method for an autonomous multifunctional service aircraft according to claim 6, characterized in that: in the step (1), the formula of the bus constant voltage control voltage reference value is as follows:
Vref1＝kf×Io+Vref；
wherein Vref1 is a bus constant voltage control voltage reference value; kf is the droop coefficient; io is load current; and Vref is a bus constant voltage control voltage reference value when the droop method is not added.
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