CN115940317A - Spacecraft energy control circuit, photovoltaic power supply system and power supply control method - Google Patents
Spacecraft energy control circuit, photovoltaic power supply system and power supply control method Download PDFInfo
- Publication number
- CN115940317A CN115940317A CN202211087357.9A CN202211087357A CN115940317A CN 115940317 A CN115940317 A CN 115940317A CN 202211087357 A CN202211087357 A CN 202211087357A CN 115940317 A CN115940317 A CN 115940317A
- Authority
- CN
- China
- Prior art keywords
- power supply
- circuit
- energy storage
- power
- photovoltaic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000004146 energy storage Methods 0.000 claims abstract description 167
- 238000007600 charging Methods 0.000 claims abstract description 106
- 230000000087 stabilizing effect Effects 0.000 claims description 19
- 230000008859 change Effects 0.000 claims description 6
- 238000007599 discharging Methods 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 description 8
- 238000010586 diagram Methods 0.000 description 7
- 239000003990 capacitor Substances 0.000 description 5
- 238000004891 communication Methods 0.000 description 5
- 230000001105 regulatory effect Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 238000010280 constant potential charging Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 230000005669 field effect Effects 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
Landscapes
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention provides a spacecraft energy control circuit, a photovoltaic power supply system and a power supply control method, which relate to the technical field of spaceflight, wherein the spacecraft energy control circuit comprises an energy storage inductor, a first switch circuit, a first power supply circuit and a charging circuit, wherein: the control end of the first switch circuit is connected with the first control signal so as to be switched on or switched off based on the first control signal; the energy storage inductor is connected with the first end of the first switch circuit and the photovoltaic signal so as to charge or discharge based on the photovoltaic signal and the on-off state of the first switch circuit; the first power supply circuit is connected with the photovoltaic signal through the energy storage inductor so as to supply power to the load based on the energy stored by the energy storage inductor and the photovoltaic signal; the charging circuit is connected with the photovoltaic signal through the energy storage inductor so as to charge the energy storage power supply based on the energy stored by the energy storage inductor and the photovoltaic signal, and the problem of low power density caused by the fact that the conventional half-regulation bus is adopted to supply power to a high-power spacecraft load is solved.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to an energy control circuit of a spacecraft, a photovoltaic power supply system and a power supply control method.
Background
In the long-endurance flight process of the spacecraft, a photovoltaic power supply system is generally adopted as an energy source, and the photovoltaic power supply system comprises a solar battery, an energy storage battery and an energy manager. The bus in the energy manager can be divided into a full-adjustment bus, a half-adjustment bus and an unregulated bus according to an adjustment mode, the unregulated bus cannot meet the power supply requirement of the spacecraft load due to the fact that the requirement of the spacecraft load on the quality of the bus and the voltage fluctuation is high, the full-adjustment bus is complex in structure, and the power density of the full-adjustment bus is low, so that the half-adjustment bus is generally adopted as the power supply bus of the spacecraft load in the prior art.
However, as the structures of the spacecraft loads are complicated and the number of the spacecraft loads is increased, the power required by the spacecraft is increased, so that the technical problem of low power density exists in the power supply of the high-power spacecraft loads by using the conventional half-regulated bus.
Disclosure of Invention
The invention provides a spacecraft energy control circuit, a photovoltaic power supply system and a power supply control method, which are used for solving the defect of low power density existing in the prior art that the conventional half-regulation bus is adopted to supply power to a high-power spacecraft load, and the integration level and the power density of the spacecraft energy control circuit are improved.
The invention provides a spacecraft energy control circuit, comprising: energy storage inductance, first switching circuit, first supply circuit and charging circuit, wherein:
the control end of the first switch circuit is connected with a first control signal and used for switching on or off based on the first control signal;
the energy storage inductor is respectively connected with the first end of the first switch circuit and the photovoltaic signal and is used for charging or discharging based on the photovoltaic signal and the on-off state of the first switch circuit;
the first power supply circuit is connected with the photovoltaic signal through the energy storage inductor and used for supplying power to a load based on the energy stored by the energy storage inductor and the photovoltaic signal;
the charging circuit is connected with the photovoltaic signal through the energy storage inductor and used for charging an energy storage power supply based on the energy stored by the energy storage inductor and the photovoltaic signal.
According to the spacecraft energy control circuit provided by the invention, the first power supply circuit comprises a power supply diode; one end of the power supply diode is connected with the energy storage inductor and the first switch circuit respectively, and the other end of the power supply diode is connected with the load; the power supply diode is used for inputting the energy storage inductor and a first power supply current provided by the photovoltaic signal to the load.
According to the spacecraft energy control circuit provided by the invention, the charging circuit comprises a second switching circuit and a charging diode; one end of the second switch circuit is connected with the energy storage inductor, the other end of the second switch circuit is connected with one end of the charging diode, and the other end of the charging diode is connected with the energy storage power supply;
the control end of the second switch circuit is connected with a second control signal and used for being switched on or switched off based on the second control signal; and the charging diode is used for inputting the energy storage inductor and the charging current provided by the photovoltaic signal to the energy storage power supply based on the on-off state of the second switch circuit.
According to the spacecraft energy control circuit provided by the invention, the charging circuit further comprises a current buffer circuit; one end of the current buffer circuit is connected with the charging diode, and the other end of the current buffer circuit is connected with a load and used for absorbing the sudden change current on the charging circuit.
The spacecraft energy control circuit provided by the invention also comprises a second power supply circuit; the second power supply circuit is respectively connected with the energy storage power supply and the load and used for supplying power to the load based on the energy stored by the energy storage power supply.
The energy control circuit of the spacecraft, provided by the invention, further comprises a first voltage stabilizing circuit and a second voltage stabilizing circuit; the first voltage stabilizing circuit is connected with the load and used for stabilizing the voltage at two ends of the load; the second voltage stabilizing circuit is connected with the energy storage power supply and used for stabilizing the voltage at two ends of the energy storage power supply.
The invention also provides a photovoltaic power supply system, comprising: as in any one of the above mentioned spacecraft energy control circuit, photovoltaic power supply, energy storage power supply, load, modulation circuit and controller, wherein:
the spacecraft energy control circuit is respectively connected with the photovoltaic power supply, the energy storage power supply and the load and is used for controlling the photovoltaic power supply to supply power to the load and charge the energy storage power supply based on a generated photovoltaic signal or supply power to the load based on energy stored by the energy storage power supply;
the modulation circuit is respectively connected with a first switch circuit and a second switch circuit in the spacecraft energy control circuit;
the controller is connected with the modulation circuit and used for controlling the modulation circuit to output a first control signal and a second control signal, inputting the first control signal to the first switch circuit and inputting the second control signal to the second switch circuit.
The photovoltaic power supply system further comprises an input end monitor, an energy storage end monitor and an output end monitor of the spacecraft energy control circuit; wherein:
the input end monitor is connected with the controller and used for collecting the input power of the spacecraft energy control circuit and transmitting the input power to the controller;
the energy storage end monitor is connected with the controller and used for collecting charging voltage and charging current of the spacecraft energy control circuit and transmitting the charging voltage and the charging current to the controller;
the output end monitor is connected with the controller and used for collecting the output power of the spacecraft energy control circuit and transmitting the output power to the controller;
the controller is connected with the modulation circuit and used for controlling the modulation circuit to output a first control signal and a second control signal based on the received input power, charging voltage, charging current and output power.
The invention also provides a power supply control method, which is applied to any one of the photovoltaic power supply systems, and comprises the following steps:
acquiring input power and output power of a space vehicle energy control circuit in the photovoltaic power supply system, and judging whether the input power is greater than the output power;
under the condition that the input power is smaller than or equal to the output power, controlling a modulation circuit in the photovoltaic power supply system to output a first control signal so that a first power supply circuit supplies power to a load, and outputting a second control signal so as to turn off a second switch circuit;
under the condition that the input power is larger than the output power, acquiring the current residual electric quantity of an energy storage power supply in the photovoltaic power supply system, and judging whether the energy storage power supply reaches a full-power state or not based on the current residual electric quantity;
and under the condition that the energy storage power supply does not reach a full power state, the modulation circuit is controlled to output a first control signal so that the first power supply circuit supplies power to a load, and a second control signal is output so that the charging circuit charges the energy storage power supply.
According to a power supply control method provided by the invention, the method further comprises the following steps:
judging whether the input power is smaller than a preset power threshold value or not, and acquiring the current residual electric quantity of the energy storage power supply and the predicted photovoltaic power supply waiting time under the condition that the input power is smaller than the preset power threshold value;
determining the longest power supply duration of the energy storage power supply based on the current residual electric quantity, and judging whether the longest power supply duration is less than the predicted photovoltaic power supply waiting duration;
determining a power decrement coefficient based on the longest power supply time and the predicted photovoltaic power supply waiting time under the condition that the longest power supply time is less than the predicted photovoltaic power supply waiting time;
and determining the current load power based on the rated load power and the power decrement coefficient, and controlling the energy storage power supply to supply power to the load based on the current load power.
According to the spacecraft energy control circuit, the photovoltaic power supply system and the power supply control method, the same energy storage inductor is multiplexed by the two paths of the first power supply circuits with independent functions and the charging circuit, so that the circuit structure of the spacecraft energy control circuit is simplified, the weight of the spacecraft energy control circuit is reduced, and the integration level of the circuit is improved on the basis of not influencing the functions of the circuit; in addition, the first switch circuit, the energy storage inductor and the first power supply circuit jointly form a boosting power supply circuit for supplying power to a load, and the output voltage of the boosting power supply circuit is greater than the input voltage, so that the output voltage can be guaranteed to reach the rated voltage of the load, the power supply requirement of the load is met while the circuit structure is simplified, the power density of the energy control circuit of the space vehicle is improved, and the technical problem that the power density is lower when the conventional half-regulation bus is adopted to supply power to a high-power space vehicle load in the prior art is solved.
Drawings
In order to more clearly illustrate the technical solutions of the present invention or the prior art, the drawings needed for the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 is one of the schematic electrical circuit diagrams of a spacecraft energy control circuit provided by an embodiment of the present invention;
FIG. 2 is a second schematic circuit diagram of an energy control circuit for a spacecraft in accordance with an embodiment of the present invention;
FIG. 3 is a circuit diagram of a spacecraft energy control circuit in accordance with an embodiment of the present invention;
fig. 4 is one of schematic structural diagrams of a photovoltaic power supply system provided by an embodiment of the invention;
fig. 5 is a second schematic structural diagram of a photovoltaic power supply system according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a controller in a photovoltaic power supply system according to an embodiment of the present invention;
fig. 7 is a schematic flow chart of a power supply control method according to an embodiment of the present invention;
fig. 8 is a second flowchart of a power supply control method according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The spacecraft energy control circuit 100 of the present invention is described below in conjunction with fig. 1-2. As shown in fig. 1, the present invention provides a spacecraft energy control circuit 100 comprising: energy storage inductance 10, first switching circuit 11, first power supply circuit 20 and charging circuit 30, wherein:
the control terminal of the first switch circuit 11 is connected to the first control signal, and is configured to be turned on or off based on the first control signal.
The first control signal is a pulse signal, and the first switch circuit 11 is turned on or off according to the high-low level change of the first pulse signal. Further, the first switch circuit 11 may be a transistor or a field effect transistor.
The energy storage inductor 10 is connected to the first end of the first switch circuit 11 and the photovoltaic signal, and is configured to charge or discharge based on the photovoltaic signal and the on/off state of the first switch circuit 11. The first power supply circuit 20 is connected to the photovoltaic signal through the energy storage inductor 10, and is configured to supply power to a load (reference numeral of the load is not shown in fig. 1, and reference numeral is shown in fig. 4 below) based on the energy stored in the energy storage inductor 10 and the photovoltaic signal. Further, the photovoltaic signal is a solar photovoltaic signal.
The charging circuit 30 is connected to the photovoltaic signal through the energy storage inductor 10, and is configured to charge an energy storage power source (reference numeral of the energy storage power source is not shown in fig. 1, and reference numeral is shown in fig. 4 below) based on the energy stored in the energy storage inductor 10 and the photovoltaic signal.
Specifically, when the first switch circuit 11 is turned on, the energy storage inductor 10 is in a charging state, that is, the energy storage inductor 10 is charged based on the energy provided by the photovoltaic signal. When the first switching circuit 11 is turned off, the energy storage inductor 10 is in a discharging state, that is, the load is powered and the energy storage power supply is charged based on the energy stored in the energy storage inductor 10 and the energy provided by the photovoltaic signal.
It should be noted that, in the case that the energy provided by the photovoltaic signal is sufficient to meet the power supply requirement of the load and there is a surplus, the load is powered and the energy storage power supply is charged based on the energy provided by the photovoltaic signal; under the condition that the energy provided by the photovoltaic signal can only meet the power supply requirement of the load, the load is only supplied with power, and the energy storage power supply is not charged.
The first switch circuit 11, the energy storage inductor 10 and the first power supply circuit 20 together form a boost power supply circuit, and the output voltage of the boost power supply circuit is greater than the input voltage, so as to ensure that the output voltage of the boost power supply circuit meets the power supply requirement of the load.
According to the spacecraft energy control circuit 100, the same energy storage inductor 10 is reused for the two independent-function first power supply circuits 20 and the two independent-function charging circuits 30, so that the circuit structure of the spacecraft energy control circuit 100 is simplified, the weight of the spacecraft energy control circuit 100 is reduced, and the integration level of the circuit is improved on the basis of not influencing the circuit function; in addition, the first switch circuit 11, the energy storage inductor 10 and the first power supply circuit 20 jointly form a boost power supply circuit for supplying power to a load, and because the output voltage of the boost power supply circuit is greater than the input voltage, the output voltage can be guaranteed to reach the rated voltage of the load, so that the power supply requirement of the load is met, the power supply requirement of the load is met while the circuit structure is simplified, the power density of the spacecraft energy control circuit 100 is improved, and the technical problem that the power density is lower when the conventional half-regulation bus is adopted to supply power to a high-power spacecraft load in the prior art is solved.
The power density is the maximum power that can be output by the power supply system divided by the weight or volume (or area) of the entire power supply system.
In one embodiment, as shown in fig. 2, the first power supply circuit 20 includes a power supply diode 21; one end of the power supply diode 21 is connected to the energy storage inductor 10 and the first switch circuit 11, and the other end is connected to the load.
The supply diode 21 is used for inputting the energy storage inductor 10 and the first supply current provided by the photovoltaic signal to the load.
In the spacecraft energy control circuit 100 provided by this embodiment, the power supply diode 21 in the first power supply circuit 20 inputs the energy storage inductor 10 and the first power supply current provided by the photovoltaic signal to the load, so as to prevent the photovoltaic power supply from being damaged due to the fact that the first power supply current reversely flows into the photovoltaic power supply generating the photovoltaic signal, thereby improving the reliability and safety of the spacecraft energy control circuit 100.
In one embodiment, as shown in fig. 2, the charging circuit 30 includes a second switching circuit 31 and a charging diode 32.
One end of the second switch circuit 31 is connected to the energy storage inductor 10, the other end is connected to one end of the charging diode 32, and the other end of the charging diode 32 is connected to the energy storage power supply.
The control terminal of the second switch circuit 31 is connected to the second control signal, and is configured to be turned on or off based on the second control signal.
The second control signal is a pulse signal, and the second switch circuit 31 is turned on or off according to the high-low level change of the second pulse signal. Further, the second switch circuit 31 may be a transistor or a field effect transistor.
The charging diode 32 is used for inputting the charging current provided by the energy storage inductor 10 and the photovoltaic signal to the energy storage power supply based on the on-off state of the second switch circuit 31.
In the spacecraft energy control circuit 100 provided by this embodiment, the charging current provided by the energy storage inductor 10 and the photovoltaic signal is input to the energy storage power supply through the charging diode 32 in the charging circuit 30, so as to prevent the photovoltaic power supply from being damaged due to the charging current reversely flowing into the photovoltaic power supply generating the photovoltaic signal, and thus the reliability and the safety of the spacecraft energy control circuit 100 are improved.
In one embodiment, as shown in fig. 2, the charging circuit 30 further includes a current buffer circuit 33; the current buffer circuit 33 has one end connected to the charging diode 32 and the other end connected to the load, and is configured to absorb an abrupt current flowing through the charging circuit 30.
Wherein the abrupt current represents an instantaneous large current generated when the on-off state of the switching circuit is changed. Further, the current buffer circuit 33 may be an inductor, or may be another current buffer as long as it can absorb the abrupt current in the charging circuit 30.
The spacecraft energy control circuit 100 provided by the embodiment absorbs the sudden change current on the charging circuit 30 based on the current buffer circuit 33, so as to prevent the sudden change current with a large current value generated when the on-off states of the first switch circuit 11 and the second switch circuit 31 are switched from burning the second switch circuit 31 and the charging diode 32 on the charging circuit 30, thereby improving the reliability and the safety of the spacecraft energy control circuit 100.
In one embodiment, as shown in fig. 2, the spacecraft energy control circuit 100 further comprises a second power supply circuit 40; the second power supply circuit 40 is connected to the energy storage power source and the load, respectively, and is configured to supply power to the load based on energy stored in the energy storage power source.
The spacecraft energy control circuit 100 provided by the embodiment supplies power to a load through a boosting power supply circuit and a photovoltaic signal, wherein the boosting power supply circuit is composed of the first switch circuit 11, the energy storage inductor 10 and the first power supply circuit 20 in the daytime, so as to meet the energy requirement of the spacecraft for executing a long-endurance flight task in the daytime, and supplies power to the load through the energy stored by the second power supply circuit 40 and the energy storage power supply at night, so as to meet the basic energy requirement of the spacecraft at night, namely, the energy requirement of the spacecraft in the long-endurance flight process is met through the energy balance between day and night, and the energy is supplied according to the specific energy requirements of the spacecraft at different times, so that the utilization rate of energy can be improved while the energy requirement of the spacecraft in the long-endurance flight process is met.
In one embodiment, as shown in FIG. 2, the spacecraft energy control circuitry 100 further includes a first regulated circuit 50 and a second regulated circuit 60. The first voltage stabilizing circuit 50 is connected to the load and is configured to stabilize the voltage across the load. The second voltage stabilizing circuit 60 is connected to the energy storage power supply, and is configured to stabilize the voltage across the energy storage power supply.
Further, the first regulator circuit 50 and the second regulator circuit 60 may be capacitors, or other regulator circuits.
The energy control circuit 100 of the spacecraft provided by the embodiment stabilizes the voltage at two ends of the load through the first voltage stabilizing circuit 50, so that the stability of the output voltage is improved, and the problem that the load cannot normally operate due to unstable voltage output is avoided; the photovoltaic power supply 110 is controlled by the second voltage stabilizing circuit 60 to perform voltage stabilizing charging on the voltage at the two ends of the energy storage power supply, so that the problem that the energy storage power supply cannot work normally due to unstable voltage applied to the two ends of the energy storage power supply is avoided, and the stability and reliability of the energy control circuit 100 of the spacecraft are improved.
An exemplary embodiment is provided below to further illustrate the spacecraft energy control circuit 100 of the present invention.
As shown in fig. 3, the spacecraft energy control circuit 100 according to the present embodiment includes: energy storage inductance 10, first switching circuit 11, first power supply circuit 20, charging circuit 30, second power supply circuit 40, first voltage stabilizing circuit 50 and second voltage stabilizing circuit 60, wherein:
v in FIG. 3 in Representing the input voltage, V, of the spacecraft energy control circuit 100 in Negative pole, V, representing the input port of the spacecraft energy control circuit 100 in + denotes the positive pole of the input port of the spacecraft energy control circuit 100, PV denotes the photovoltaic power supply, V out + denotes the positive pole, V, of the output port of the spacecraft energy control circuit 100 out Negative pole representing the output port of the spacecraft energy control circuit 100. Wherein, the negative pole V of the input port in -positive pole V of input port connected to negative pole of photovoltaic power source PV in + is connected to the positive pole of the photovoltaic power source PV. The energy storage inductor 10 is the energy storage inductor L in fig. 3, and the load is the load R in fig. 3 L The energy storage power supply is the energy storage power supply V in figure 3 B The first switch circuit 11 is the MOS transistor S in FIG. 3 1 The photovoltaic signal is the photovoltaic signal I in FIG. 3 in The first power supply circuit 20 is a power supply diode D1.
MOS transistor S 1 The grid (G pole) of the MOS transistor is connected with a first control signal, and the MOS transistor S 1 Source (i.e., S-pole) of (a) and negative pole V of the input port in -connection, MOS tube S 1 The drain electrode (i.e., the D pole) of the power amplifier is connected with the positive pole V of the input port through the energy storage inductor L in + connected. MOS transistor S 1 For deriving based on a first control signalAnd switching on or switching off, wherein the first control signal is a pulse signal.
One end of the energy storage inductor L and the anode V of the input port in Photovoltaic signal I on + in The other end of the power supply diode is respectively connected with the anode of the power supply diode D1 and the MOS tube S 1 Drain electrode of and MOS transistor S 2 For the photovoltaic signal I based on in And MOS tube S 1 Is charged based on the on state of the MOS transistor S 1 To discharge to the load R L Power supply and energy storage power supply V B And (6) charging. Cathode of power supply diode D1 and load R L Connection for MOS transistor S 1 Under the condition of conduction, the energy storage inductor L and the photovoltaic signal I are connected in The provided first supply current is input to a load R L To a load R L And supplying power.
The charging circuit 30 includes a MOS transistor S 2 Charging diode D2 and current buffer inductor L f . MOS transistor S 2 The gate of the transistor is connected with a second control signal for switching on or off based on the second control signal, wherein the second control signal is a pulse signal. MOS transistor S 2 The drain electrode of the MOS tube S is connected with an energy storage inductor L and the MOS tube S 2 Is connected with the anode of a charging diode D2, and the cathode of the charging diode D2 passes through a current buffer inductor L f And an energy storage power supply V B Connection of MOS transistor S 2 Under the condition of conduction, the energy storage inductor L and the photovoltaic signal I in The provided charging current is input into an energy storage power supply V B To the energy storage power supply V B And (6) charging. Current buffer inductor L f For sinking an abrupt current on the charging circuit 30.
The second power supply circuit 40 is the MOS transistor S in FIG. 3 3 MOS transistor S 3 The gate of (a) is connected with a third control signal for turning on or off based on the third control signal, wherein the third control signal is a pulse signal. MOS transistor S 3 Drain and load R L Connected, MOS transistor S 2 Source and energy storage power supply V B Connection for connecting the energy storage power supply V B Providing a second supply circuit input to the load R L To a load R L To carry outAnd (5) supplying power.
The first voltage regulating circuit 50 is the voltage-stabilizing filter capacitor C shown in FIG. 3 1 Voltage stabilizing filter capacitor C 1 Respectively with the load R L Are connected at both ends for absorbing the load R L Ripple in the voltage across the load to regulate the voltage across the load. The second voltage regulating circuit 60 is the voltage-stabilizing filter capacitor C in FIG. 3 2 Voltage stabilizing filter capacitor C 2 Respectively connected with an energy storage power supply V B Is connected at both ends and is used for absorbing an energy storage power supply V B Ripple in voltage across to the energy storage source V B The voltage at both ends is stabilized.
The invention also provides a photovoltaic power supply system, which is applied to a spacecraft, as shown in fig. 4, the photovoltaic power supply system comprises: the spacecraft energy control circuitry 100, the photovoltaic power source 110, the storage power source 120, the load 130, the modulation circuitry 140, and the controller 150 as provided in any of the above embodiments, wherein:
the spacecraft energy control circuit 100 is respectively connected to the photovoltaic power source 110, the stored energy power source 120 and the load 130, and is configured to control the photovoltaic power source 110 to supply power to the load 130 and charge the stored energy power source 120 based on the generated photovoltaic signal, or to supply power to the load 130 based on the energy stored by the stored energy power source 120. Specifically, the photovoltaic power source 110 is a solar photovoltaic power source. The photovoltaic power supply system is a solar photovoltaic power supply system. The modulation circuit 140 is connected to the first switching circuit 11 and the second switching circuit 31 in the spacecraft energy control circuit 100, respectively.
The controller 150 is connected to the modulation circuit 140, and is configured to control the modulation circuit 140 to output a first control signal and a second control signal, input the first control signal to the first switch circuit 11, and input the second control signal to the second switch circuit 31.
In one embodiment, as shown in fig. 4, the photovoltaic power supply system further includes an input monitor 70, a storage monitor 80, and an output monitor 90 of the spacecraft energy control circuit 100; wherein:
the input monitor 70 is connected to the controller 150 for collecting input power from the spacecraft energy control circuit 100 and transmitting it to the controller 150.
Further, as shown in fig. 5, the input terminal monitor 70 includes an input terminal voltage monitor 71, and the input terminal voltage monitor 71 is connected to the controller 150 for collecting the input voltage of the spacecraft energy control circuit 100 and transmitting the collected input voltage to the controller 150.
It should be noted that, since the input voltage is output by the photovoltaic power source 110 of the solar power generator, the input power P of the spacecraft energy control circuit 100 can be directly calculated according to the input voltage and other solar power generation parameters PV 。
The energy storage end monitor 80 is connected to the controller 150, and is configured to collect the charging voltage and the charging current of the spacecraft energy control circuit 100 and transmit the charging voltage and the charging current to the controller 150.
Further, as shown in fig. 5, the energy storage end monitor 80 includes an energy storage end voltage monitor 81 and an energy storage end current monitor 82; the energy storage terminal voltage monitor 81 is connected to the controller 150, and is configured to collect the charging voltage of the spacecraft energy control circuit 100 and transmit the charging voltage to the controller 150. The energy storage end current monitor 82 is connected with the controller 150 and is used for collecting the charging current of the spacecraft energy control circuit 100 and transmitting the charging current to the controller 150.
It should be noted that the energy storage end bidirectional power P of the spacecraft energy control circuit 100 can be directly calculated and obtained based on the charging voltage collected by the energy storage end voltage monitor 81 and the charging current collected by the energy storage end current monitor 82 B I.e., the input power or the output power of the energy storage power supply 120.
The output monitor 90 is connected to the controller 150 for collecting the output power of the spacecraft energy control circuit 100 and transmitting it to the controller 150.
Further, as shown in fig. 5, the output monitor 90 includes an output current monitor 91 and an output voltage monitor 92; the output end current monitor 91 is connected to the controller 150, and is configured to collect the output current of the spacecraft energy control circuit 100 and transmit the output current to the controller 150. The output voltage monitor 92 is connected to the controller 150 for collecting the output voltage of the spacecraft energy control circuit 100 and transmitting it to the controller 150.
It should be noted that the output power P of the spacecraft energy control circuit 100 may be directly calculated based on the output current collected by the output terminal current monitor 91 and the output voltage collected by the output terminal voltage monitor 92 out 。
The controller 150 is connected to the modulation circuit 140, and is configured to control the modulation circuit 140 to output the first control signal and the second control signal based on the received input power, the charging voltage, the charging current, and the output power.
The photovoltaic power supply system provided by this embodiment, real-time collection spacecraft energy control circuit 100's input power through input monitor 70, real-time collection spacecraft energy control circuit 100's charging voltage and charging current through energy storage monitor 80, and real-time collection spacecraft energy control circuit 100's output power through output monitor 90, and then through controller 150 based on the input power received, charging voltage, charging current and output power, real-time update first control signal and second control signal, so that the first control signal and the second control signal of output suit with spacecraft energy control circuit 100's current operating condition, thereby can improve the control effect to spacecraft energy control circuit 100, realize the tracking control to photovoltaic power supply 110's maximum output power and realize the charge-discharge control to energy storage power supply 120.
In an embodiment, fig. 6 illustrates a physical structure diagram of a controller 150 in a photovoltaic power supply system, and as shown in fig. 6, the controller 150 may include: a processor (processor) 510, a communication Interface (Communications Interface) 520, a memory (memory) 530 and a communication bus 540, wherein the processor 510, the communication Interface 520 and the memory 530 communicate with each other via the communication bus 540. Processor 510 may invoke logic instructions in memory 530 to perform the power control method provided by embodiments of the present invention.
In addition, the logic instructions in the memory 530 may be implemented in the form of software functional units and stored in a computer readable storage medium when the logic instructions are sold or used as a stand-alone product. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, an optical disk, or other various media capable of storing program codes.
The spacecraft energy control circuit provided by the present invention is described below in conjunction with fig. 7-8. As shown in fig. 7, the present invention provides a power supply control method, which is applied to the photovoltaic power supply system provided in any of the above embodiments, and the execution subject is the controller 150 in the photovoltaic power supply system, and the method includes:
and S11, acquiring the input power and the output power of the energy control circuit of the space vehicle in the photovoltaic power supply system, and judging whether the input power is greater than the output power.
And S12, under the condition that the input power is less than or equal to the output power, controlling a modulation circuit in the photovoltaic power supply system to output a first control signal so that the first power supply circuit supplies power to the load, outputting a second control signal so as to turn off the second switch circuit, and returning to the step S11.
It should be noted that "the input power is less than or equal to the output power" indicates that the energy provided by the photovoltaic power supply is not enough to supply power to the load, or is just enough to supply power to the load, and no remaining energy is used to charge the energy storage power supply, so that the first control signal is output at this time to enable the first power supply circuit to supply power to the load, and the second control signal is output to turn off the second switch circuit, so as not to charge the energy storage power supply.
And S13, under the condition that the input power is greater than the output power, acquiring the current residual electric quantity of the energy storage power supply in the photovoltaic power supply system, and judging whether the energy storage power supply reaches a full-power state or not based on the current residual electric quantity.
And step S14, under the condition that the energy storage power supply does not reach the full power state, controlling the modulation circuit to output a first control signal to enable the first power supply circuit to supply power to the load, and outputting a second control signal to enable the charging circuit to charge the energy storage power supply, and returning to the step S11.
Further, under the condition that the input power is greater than the output power, whether the energy storage power supply is in a constant-voltage charging state or not is judged, and under the condition that the energy storage power supply is in the constant-voltage charging state, whether the energy storage power supply reaches a full-power state or not is judged; and in the case that the energy storage power supply does not reach the full power state or is not in the constant voltage charging state, executing the step S14 to supply power to the load and charge the energy storage power supply, and returning to the step S11.
Further, in the case that the energy storage power supply reaches the full power state, the modulation circuit is controlled to output a first control signal to enable the first power supply circuit to supply power to the load, and output a second control signal to enable the charging circuit to charge the energy storage power supply, and the process returns to step S11.
It should be noted that "the input power is greater than the output power" indicates that the energy provided by the photovoltaic power supply is sufficient to supply power to the load, and the remaining energy is used to charge the energy storage power supply, so that the load can be simultaneously supplied with power and the energy storage power supply can be simultaneously charged when the energy storage power supply does not reach a full power state.
According to the power supply control method provided by the embodiment, the first power supply circuit is controlled to supply power to the load and the second switch circuit is switched off under the condition that the input power is less than or equal to the output power, so that the power supply requirement of the load is preferentially ensured under the condition that the energy provided by the photovoltaic power supply is less, and the spacecraft can smoothly complete a long-endurance flight task.
In one embodiment, as shown in fig. 8, the power supply control method provided by the present invention further includes steps S21 to S24, where:
and S21, judging whether the input power is smaller than a preset power threshold, and acquiring the current residual electric quantity of the energy storage power supply and the predicted photovoltaic power supply waiting time under the condition that the input power is smaller than the preset power threshold.
The fact that the input power is smaller than the preset power threshold value indicates that the photovoltaic power supply system cannot normally supply power to the load, and at the moment, the energy storage power supply needs to be started to supply power to the load. The estimated photovoltaic power supply waiting time represents the waiting time between the current moment and the moment of normal power supply of the photovoltaic power supply system after the day is bright.
And S22, determining the longest power supply time of the energy storage power supply based on the current residual capacity, and judging whether the longest power supply time is less than the predicted photovoltaic power supply waiting time.
And S23, under the condition that the longest power supply time is shorter than the predicted photovoltaic power supply waiting time, determining a power decrement coefficient based on the longest power supply time and the predicted photovoltaic power supply waiting time.
And S24, determining the current load power based on the rated load power and the power decrement coefficient, controlling the energy storage power supply to supply power to the load based on the current load power, and returning to the step S11.
Wherein the power decrement coefficient is determined based on actual energy consumption data of the spacecraft. It should be noted that the "longest power supply duration is less than the expected photovoltaic power supply waiting duration" indicates that the current remaining capacity of the energy storage power supply is not enough to last until the normal power supply of the photovoltaic power supply system, so that the power provided by the energy storage power supply to the load needs to be reasonably reduced based on the power decrement coefficient, so as to prolong the power supply duration of the energy storage power supply to the load in the case of energy shortage of the energy storage power supply.
In one embodiment, the charging voltage and the charging current of the energy control circuit of the spacecraft are obtained, and whether the energy storage power supply is in an overvoltage charging state or an overcurrent charging state is judged based on the charging voltage, the charging current and the maximum charging voltage and the maximum charging current of the energy storage power supply; and under the condition that the energy storage power supply is in an overvoltage charging state or an overcurrent charging state, terminating the control flow to prevent the energy storage power supply from being damaged. And returning to the step S11 under the condition that the energy storage power supply is not in the overvoltage charging state and is not in the overcurrent charging state.
It should be noted that, after each control flow is completed, the control flow needs to return to step S11, continue to monitor the input power and the output power of the spacecraft energy control circuit, and repeat the control flow until the energy storage power supply is in the overvoltage charging state or the overcurrent charging state, and terminate the control flow.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment may be implemented by software plus a necessary general hardware platform, and may also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A spacecraft energy control circuit, comprising: energy storage inductance, first switching circuit, first supply circuit and charging circuit, wherein:
the control end of the first switch circuit is connected with a first control signal and used for switching on or off based on the first control signal;
the energy storage inductor is respectively connected with the first end of the first switch circuit and the photovoltaic signal and is used for charging or discharging based on the photovoltaic signal and the on-off state of the first switch circuit;
the first power supply circuit is connected with the photovoltaic signal through the energy storage inductor and used for supplying power to a load based on the energy stored by the energy storage inductor and the photovoltaic signal;
the charging circuit is connected with the photovoltaic signal through the energy storage inductor and used for charging an energy storage power supply based on the energy stored by the energy storage inductor and the photovoltaic signal.
2. The spacecraft energy control circuitry of claim 1, wherein said first power supply circuitry comprises a power supply diode;
one end of the power supply diode is connected with the energy storage inductor and the first switch circuit respectively, and the other end of the power supply diode is connected with the load;
the power supply diode is used for inputting the energy storage inductor and a first power supply current provided by the photovoltaic signal to the load.
3. The spacecraft energy control circuit of claim 1, wherein the charging circuit comprises a second switching circuit and a charging diode;
one end of the second switch circuit is connected with the energy storage inductor, the other end of the second switch circuit is connected with one end of the charging diode, and the other end of the charging diode is connected with the energy storage power supply;
the control end of the second switch circuit is connected with a second control signal and used for switching on or off based on the second control signal;
and the charging diode is used for inputting the energy storage inductor and the charging current provided by the photovoltaic signal to the energy storage power supply based on the on-off state of the second switch circuit.
4. A spacecraft energy control circuit according to any of claims 1 to 3, wherein the charging circuit further comprises a current snubber circuit;
one end of the current buffer circuit is connected with the charging diode, and the other end of the current buffer circuit is connected with a load and used for absorbing the sudden change current on the charging circuit.
5. A spacecraft energy control circuit according to claim 1, further comprising a second power supply circuit;
the second power supply circuit is respectively connected with the energy storage power supply and the load and used for supplying power to the load based on the energy stored by the energy storage power supply.
6. The spacecraft energy control circuit of claim 1, further comprising a first regulation circuit and a second regulation circuit;
the first voltage stabilizing circuit is connected with the load and used for stabilizing the voltage at two ends of the load;
the second voltage stabilizing circuit is connected with the energy storage power supply and used for stabilizing the voltage at two ends of the energy storage power supply.
7. A photovoltaic power supply system, comprising: the spacecraft energy control circuitry, photovoltaic power source, energy storage power source, load, modulation circuitry, and controller of any one of claims 1 to 6, wherein:
the spacecraft energy control circuit is respectively connected with the photovoltaic power supply, the energy storage power supply and the load and is used for controlling the photovoltaic power supply to supply power to the load and charge the energy storage power supply based on a generated photovoltaic signal or supply power to the load based on energy stored by the energy storage power supply;
the modulation circuit is respectively connected with a first switch circuit and a second switch circuit in the spacecraft energy control circuit;
the controller is connected with the modulation circuit and used for controlling the modulation circuit to output a first control signal and a second control signal, inputting the first control signal to the first switch circuit and inputting the second control signal to the second switch circuit.
8. The photovoltaic power supply system of claim 7, further comprising an input monitor, an energy storage monitor, and an output monitor of the spacecraft energy control circuit; wherein:
the input end monitor is connected with the controller and used for collecting the input power of the spacecraft energy control circuit and transmitting the input power to the controller;
the energy storage end monitor is connected with the controller and used for collecting charging voltage and charging current of the spacecraft energy control circuit and transmitting the charging voltage and the charging current to the controller;
the output end monitor is connected with the controller and used for collecting the output power of the spacecraft energy control circuit and transmitting the output power to the controller;
the controller is connected with the modulation circuit and used for controlling the modulation circuit to output a first control signal and a second control signal based on the received input power, charging voltage, charging current and output power.
9. A power supply control method applied to the photovoltaic power supply system according to claim 7 or 8, comprising:
acquiring input power and output power of a space vehicle energy control circuit in the photovoltaic power supply system, and judging whether the input power is greater than the output power;
under the condition that the input power is smaller than or equal to the output power, controlling a modulation circuit in the photovoltaic power supply system to output a first control signal so that a first power supply circuit supplies power to a load, and outputting a second control signal so as to turn off a second switch circuit;
under the condition that the input power is larger than the output power, acquiring the current residual electric quantity of an energy storage power supply in the photovoltaic power supply system, and judging whether the energy storage power supply reaches a full-power state or not based on the current residual electric quantity;
under the condition that the energy storage power supply does not reach the full power state, the modulation circuit is controlled to output a first control signal so that the first power supply circuit supplies power to the load, and a second control signal is output so that the charging circuit charges the energy storage power supply.
10. The power supply control method according to claim 9, characterized by further comprising:
judging whether the input power is smaller than a preset power threshold value or not, and acquiring the current residual electric quantity of the energy storage power supply and the predicted photovoltaic power supply waiting time under the condition that the input power is smaller than the preset power threshold value;
determining the longest power supply duration of the energy storage power supply based on the current residual electric quantity, and judging whether the longest power supply duration is less than the predicted photovoltaic power supply waiting duration;
determining a power decrement coefficient based on the longest power supply duration and the predicted photovoltaic power supply waiting duration under the condition that the longest power supply duration is less than the predicted photovoltaic power supply waiting duration;
and determining the current load power based on the rated load power and the power decrement coefficient, and controlling the energy storage power supply to supply power to the load based on the current load power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211087357.9A CN115940317B (en) | 2022-09-07 | 2022-09-07 | Spacecraft energy control circuit, photovoltaic power supply system and power supply control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211087357.9A CN115940317B (en) | 2022-09-07 | 2022-09-07 | Spacecraft energy control circuit, photovoltaic power supply system and power supply control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115940317A true CN115940317A (en) | 2023-04-07 |
| CN115940317B CN115940317B (en) | 2023-07-14 |
Family
ID=86651397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211087357.9A Active CN115940317B (en) | 2022-09-07 | 2022-09-07 | Spacecraft energy control circuit, photovoltaic power supply system and power supply control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115940317B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103855790A (en) * | 2014-03-24 | 2014-06-11 | 电子科技大学 | Intelligent photovoltaic power generation system with energy storage function and control method of system |
| CN105490306A (en) * | 2016-02-03 | 2016-04-13 | 合肥聚能新能源科技有限公司 | Photovoltaic energy storage grid-connected power supply system |
| CN105656169A (en) * | 2014-11-28 | 2016-06-08 | 比亚迪股份有限公司 | Power supply system and control method of power supply system |
| CN108695841A (en) * | 2018-06-08 | 2018-10-23 | 哈尔滨工程大学 | A kind of low-power independent photovoltaic generating system control method and its main circuit |
| CN110336459A (en) * | 2019-07-31 | 2019-10-15 | 南通大学 | A kind of novel three ports Boost integrated form converter and control method for photovoltaic energy storage system |
| CN110912246A (en) * | 2019-11-28 | 2020-03-24 | 兰州交通大学 | Power coordination controller applied to optical storage system |
| CN110912245A (en) * | 2019-11-22 | 2020-03-24 | 南通大学 | Three-port integrated photovoltaic energy storage converter |
| US20220032780A1 (en) * | 2020-07-28 | 2022-02-03 | Zhejiang University | Energy management control system suitable for solar-powered unmanned aerial vehicle and control method thereof |
| CN114123449A (en) * | 2021-11-26 | 2022-03-01 | 华能清能通榆电力有限公司 | Independent photovoltaic power generation energy storage system and energy management method |
-
2022
- 2022-09-07 CN CN202211087357.9A patent/CN115940317B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103855790A (en) * | 2014-03-24 | 2014-06-11 | 电子科技大学 | Intelligent photovoltaic power generation system with energy storage function and control method of system |
| CN105656169A (en) * | 2014-11-28 | 2016-06-08 | 比亚迪股份有限公司 | Power supply system and control method of power supply system |
| CN105490306A (en) * | 2016-02-03 | 2016-04-13 | 合肥聚能新能源科技有限公司 | Photovoltaic energy storage grid-connected power supply system |
| CN108695841A (en) * | 2018-06-08 | 2018-10-23 | 哈尔滨工程大学 | A kind of low-power independent photovoltaic generating system control method and its main circuit |
| CN110336459A (en) * | 2019-07-31 | 2019-10-15 | 南通大学 | A kind of novel three ports Boost integrated form converter and control method for photovoltaic energy storage system |
| CN110912245A (en) * | 2019-11-22 | 2020-03-24 | 南通大学 | Three-port integrated photovoltaic energy storage converter |
| CN110912246A (en) * | 2019-11-28 | 2020-03-24 | 兰州交通大学 | Power coordination controller applied to optical storage system |
| US20220032780A1 (en) * | 2020-07-28 | 2022-02-03 | Zhejiang University | Energy management control system suitable for solar-powered unmanned aerial vehicle and control method thereof |
| CN114123449A (en) * | 2021-11-26 | 2022-03-01 | 华能清能通榆电力有限公司 | Independent photovoltaic power generation energy storage system and energy management method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115940317B (en) | 2023-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9365175B2 (en) | Power supply system for vehicle | |
| JP5838006B1 (en) | Power distribution equipment | |
| JP2008131736A (en) | Distributed power system and step-up/step-down chopper device | |
| JP7189861B2 (en) | Charging device and charging method | |
| CN106961150B (en) | Control method and system of composite energy storage battery | |
| CN112383092B (en) | Energy scheduling method, device and system | |
| CN105846419A (en) | Photovoltaic and diesel complementary power supply system based on DC microgrid | |
| CN106159980B (en) | Power generation system and energy management method | |
| CN110829464A (en) | Photovoltaic energy storage battery frequency modulation system and method based on direct current side | |
| CN110048497B (en) | Control method of direct-current micro-grid | |
| CN112600216B (en) | Bus voltage and power control method | |
| JP3181423B2 (en) | Photovoltaic power generation equipment with battery | |
| CN110289632A (en) | A kind of new energy power grid control method | |
| CN117713321A (en) | Vehicle DCDC output voltage control method, storage medium and electronic equipment | |
| CN106026174B (en) | A kind of grid-connected photovoltaic system with intelligent power dividing function | |
| JP4267541B2 (en) | Power supply | |
| CN109193885B (en) | Control system of photovoltaic energy storage inverter | |
| CN115940317B (en) | Spacecraft energy control circuit, photovoltaic power supply system and power supply control method | |
| JP2021027749A (en) | Charge/discharge control device, battery including the same, and dc power supply system | |
| WO2023005422A1 (en) | Off-grid power supply system and control method thereof | |
| CN114243872B (en) | Charging pile direct-current power supply device and charging equipment | |
| CN115378003A (en) | Electric energy scheduling method | |
| CN213185554U (en) | Battery management circuit and battery management control system | |
| CN113852061A (en) | Photovoltaic power generation-containing DC micro-grid work control method | |
| JP6795082B2 (en) | DC power supply system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |