CN110854840B - Grid-connected power supply method of spacecraft grid-connected topological structure based on common bus - Google Patents

Grid-connected power supply method of spacecraft grid-connected topological structure based on common bus Download PDF

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CN110854840B
CN110854840B CN201911135694.9A CN201911135694A CN110854840B CN 110854840 B CN110854840 B CN 110854840B CN 201911135694 A CN201911135694 A CN 201911135694A CN 110854840 B CN110854840 B CN 110854840B
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power
grid
spacecraft
bus
power converter
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CN110854840A (en
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于磊
蒋冀
党蓉
王林涛
张璐
王宏佳
仪德英
付丽璋
梁晓锋
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Beijing Space Technology Research and Test Center
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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
    • H02J1/102—Parallel operation of dc sources being switching converters
    • 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
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers

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  • Power Engineering (AREA)
  • Supply And Distribution Of Alternating Current (AREA)

Abstract

The invention relates to a grid-connected power supply method of a spacecraft grid-connected topological structure based on a common bus, wherein a plurality of spacecrafts adopt the grid-connected topological structure based on the common bus to carry out grid-connected power supply; the method comprises the following steps: s1, the spacecraft acquires the actual power of a power grid of the spacecraft, and autonomously judges the power state of the power grid according to the actual power of the power grid; and S2, if the power of the power grid of the spacecraft is rich, transmitting redundant electric energy to the public bus, and if the power of the power grid of the spacecraft is insufficient, receiving the electric energy transmitted on the public bus. The method is suitable for the overall design of grid-connected power supply among a plurality of spacecrafts. The invention can more flexibly and reliably realize the power grid connection among a plurality of spacecrafts, has high expandability and can meet the requirement of on-orbit networking of large and complex spacecrafts.

Description

Grid-connected power supply method of spacecraft grid-connected topological structure based on public bus
Technical Field
The invention relates to the field of overall design of spacecraft systems, in particular to a grid-connected power supply method of a spacecraft grid-connected topological structure based on a common bus.
Background
Along with the development of aerospace technology, the loads and functions of the spacecrafts are continuously increased, and each independent spacecraft is provided with a power supply system and can support power utilization during independent flight. The load requirements of each spacecraft in different working modes are different, and the configuration requirements of a power supply system are also different. It is indispensable when multiple spacecraft are docked in orbit and networked to build a large complex spacecraft system. At present, due to the task requirement and the spacecraft scale, only two spacecrafts have the case of realizing energy grid-connected transmission through a single power converter. The method has poor expandability and small transmitted power magnitude, and when the number of on-orbit grid-connected spacecrafts exceeds two, only a 'two-by-two grid-connected' mode can be adopted, so that more equipment is configured, and the power loss cost is high.
Disclosure of Invention
The invention aims to provide a grid-connected power supply method of a spacecraft grid-connected topological structure based on a common bus, which is used for optimizing the electric energy utilization efficiency of a plurality of spacecrafts during on-orbit grid connection.
In order to achieve the purpose, the invention provides a grid-connected power supply method of a spacecraft grid-connected topological structure based on a common bus, wherein a plurality of spacecrafts adopt the grid-connected topological structure based on the common bus to carry out grid-connected power supply; the method comprises the following steps:
s1, the spacecraft acquires the actual power of a power grid of the spacecraft, and autonomously judges the power state of the power grid according to the actual power of the power grid;
and S2, if the power of the power grid of the spacecraft is rich, transmitting redundant electric energy to the public bus, and if the power of the power grid of the spacecraft is insufficient, receiving the electric energy transmitted on the public bus.
According to one aspect of the invention, the power grid bus in the spacecraft is connected with the common bus through an input power converter and an output power converter respectively;
the power grid in the spacecraft receives the electric energy transmitted on the public bus through the input power converter;
and the power grid in the spacecraft transmits redundant electric energy to the public bus through the output power converter.
According to one aspect of the invention, the input power converter receives the electric energy transmitted on the public bus and transmits the electric energy to the power grid of the spacecraft in a constant current mode.
According to one aspect of the invention, the input power converter and the output power converter on each of the spacecraft are connected to an energy management center;
the energy management center is used for counting and analyzing the power gap amount or the power surplus amount of each spacecraft power grid, and controlling the power magnitude of the on, off and transmission of each input power converter and each output power converter.
According to one aspect of the invention, when the power grid of a plurality of the spacecraft is rich, the output voltages of the output power converters connected to the common bus are equal.
According to one aspect of the invention, a plurality of said output power converters operate in a master-slave mode, wherein one of said output power converters is a master module and the others are slave modules;
the output power converter serving as the main module adopts voltage and current double closed-loop control, the outer ring is a voltage closed loop and is used for realizing voltage regulation of the common bus, and the inner ring is a current closed loop;
the output power converter as a slave module employs current closed loop control.
According to one aspect of the invention, the output power converters and the input power converters in a single spacecraft may be arranged in one or more parallel connections, respectively;
when the output power converters or the input power converters in a single spacecraft are respectively arranged in parallel, the output power converters or the input power converters work in parallel when the power gap amount or the power surplus amount of the spacecraft exceeds a set threshold value.
According to one scheme of the invention, the method is suitable for the overall design of grid-connected power supply among a plurality of spacecrafts. The invention can more flexibly and reliably realize the power grid connection among a plurality of spacecrafts, has high expandability and can meet the requirement of on-orbit networking of large and complex spacecrafts.
According to one scheme of the invention, during the on-orbit period of a plurality of spacecrafts, the independent power supply systems of the spacecrafts are supplied with power by grid connection to form a large power supply system, so that mutual supply of energy is realized, redundant energy of the spacecrafts with abundant power is transmitted to the spacecrafts with insufficient power, the expansion of power and the overall management and comprehensive utilization of energy can be realized, the complementary supply of energy under faults is realized, and the reliability and the robustness of the whole system are improved.
According to the scheme of the invention, the bus synchronization among different spacecrafts is realized through the energy conversion and transmission of the power converter, so that the conversion and controllable transmission of power (voltage and current) as required can be realized, the reliable isolation among the buses can be realized, the energy utilization rate of the grid-connected power supply among the spacecrafts is improved, and the safety of the grid-connected spacecrafts is effectively improved.
According to the scheme of the invention, grid-connected power supply among not less than 3 spacecrafts can be satisfied, and the spacecrafts are connected with the public bus, so that the connection or disconnection of the power grid among the spacecrafts is more convenient, the impact of the power grid among the spacecrafts is small, and the safety of the whole spacecraft group is ensured.
Drawings
FIG. 1 schematically represents a block diagram of steps according to an embodiment of the present invention;
FIG. 2 is a schematic representation of a topology diagram of a common bus based multi-spacecraft grid-connected power supply system according to an embodiment of the present invention;
FIG. 3 is a schematic representation of a diagram of a multiple output power converter parallel output topology according to one embodiment of the present invention;
FIG. 4 schematically illustrates a parallel output control block diagram for a multiple output power converter, according to an embodiment of the invention;
fig. 5 schematically shows an expanded structure diagram of a grid-connected power supply system according to an embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer" are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience in describing and simplifying the description, and is not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore the terms described above are not to be construed as limiting the invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
As shown in fig. 1, according to an embodiment of the present invention, in the grid-connected power supply method for a common bus based spacecraft grid-connected topology structure of the present invention, a plurality of spacecraft adopt a common bus based grid-connected topology structure for grid-connected power supply.
The method of the invention comprises the following steps:
s1, acquiring the actual power of a power grid of a spacecraft, and autonomously judging the power state of the power grid according to the actual power of the power grid;
and S2, if the power of the power grid of the spacecraft is rich, transmitting redundant electric energy to the public bus, and if the power of the power grid of the spacecraft is insufficient, receiving the electric energy transmitted on the public bus.
According to one embodiment of the invention, as shown in fig. 2, a power bus in the spacecraft is connected to the common bus by an input power converter and an output power converter, respectively. In the embodiment, the power grid in the spacecraft receives the electric energy transmitted on the public bus through the input power converter; and the power grid in the spacecraft transmits redundant electric energy to the public bus through the output power converter. Through the arrangement, the bus of the power grid of each spacecraft is connected to a common bus through the power converter, and any spacecraft can receive power from one or more other spacecrafts when the power is insufficient. Any spacecraft can also deliver power to the common bus to power other aircraft when the power is rich.
For example: referring to fig. 2, when the power of the spacecraft a is insufficient and the power of the spacecraft B/C/… N is abundant, the spacecraft B/C/… N converts respective power buses and then uniformly transmits the converted power buses to a grid-connected common bus through an output power converter B _ O, C _ O … N _ O, and the spacecraft a converts the power of the grid-connected common bus through an input power converter a _ I, then is connected to the grid of the spacecraft a bus, and jointly supplies power to the load of the spacecraft a.
For another example: referring to fig. 2, when the power of the spacecraft A, B is insufficient, the power of the spacecraft C/… M is abundant, and the power of the spacecraft M +1/… N is only self-sufficient, the spacecraft C/… M converts the respective power buses through the output power converter C _ O, C +1_ O … M _ O and then uniformly transmits the converted power buses to the grid-connected common bus, and the spacecraft A, B converts the power of the grid-connected common bus through the input power converter a _ I, B _ I and then respectively grid-connects the converted power buses with the spacecraft A, B bus to supply power to the load of the spacecraft A, B; and the input power converter M +1_ I … N _ I and the output power converter M +1_ O … N _ O of the spacecraft M +1/… N are not switched on, so that the power supply state of the spacecraft is maintained.
According to one embodiment of the invention, the input power converter receives the electric energy transmitted on the public bus and transmits the electric energy to the power grid of the spacecraft in a constant current mode. In the present embodiment, referring to fig. 2, a spacecraft a is taken as an example. The input power converter A _ I receives power from a grid-connected common bus, outputs constant current, and supplies power to electric equipment after being converged with a primary bus of a spacecraft A power supply system; the bus voltage is completely determined by a spacecraft A power supply system, and the input power converter A _ I outputs constant current without participating in bus voltage control of the power supply system. The electric energy transmission by adopting the constant current mode has the advantages that the input power converter outputs the constant current, and the input power converter is converged with a primary bus of a power supply system of the powered spacecraft to supply power to electric equipment; the bus voltage is completely determined by closed-loop regulation of a power supply system of the powered spacecraft, and the power converter outputs constant current and does not participate in bus voltage control of the power supply system. The bus voltage oscillation which is possibly generated by mutual competition of two control systems is avoided.
As shown in fig. 2, according to an embodiment of the present invention, the input power converter and the output power converter on each of the spacecraft are connected to an energy management center. In the embodiment, the energy management center is used for counting and analyzing the power gap amount or the power surplus amount of each spacecraft power grid, and controlling the power magnitude of the on, off and transmission of each input power converter and each output power converter.
Referring to fig. 2 and 3, according to an embodiment of the present invention, when the power grids of a plurality of spacecraft are power-rich, the output voltages of the output power converters connected to the common bus are equal. In the present embodiment, when a plurality of spacecraft transmit electric power to the common bus, there is a mode in which a plurality of output power converters B _ O, C _ O … N _ O are collectively transmitted in parallel to the grid-connected power bus. In the present embodiment, the output power converter B _ O, C _ O … N _ O converts the voltages of the plurality of buses, and then outputs the converted voltages directly to the common bus, thereby outputting the voltage VBO_O、VCO_O…VNO_OAre all equal and are the common bus voltage Vbus_COM，Vbus_COMIs preset to a known value. Output power P of each output power converterBO、PCO…PNOThe energy management center calculates the power surplus of each spacecraft, and the calculation values can be different. The power relationship of each output power converter is shown as the following formula:
Vbus_B·IBO_I·ηB＝PB_IN·ηB＝PBO＝VBO_O·IBO_O (1)
Vbus_C·ICO_I·ηC＝PC_IN·ηC＝PCO＝VCO_O·ICO_O (2)
……
Vbus_N·INO_I·ηN＝PN_IN·ηN＝PNO＝VNO_O·INO_O (3)
VBO_O＝VCO_O＝......＝VNO_O＝Vbus_COM (4)
wherein: vbus_B、Vbus_C……Vbus_NThe voltage of each spacecraft power grid bus; i isBO_I、ICO_I……INO_IInputting current for each power converter; etaB、ηB……ηNConverting efficiency for each power converter; pB_IN、PC_IN……PN_INInputting power for each power converter; pBO、PCO……PNOOutputting power for each power converter; vBO_O、VCO_O……VNO_OOutputting a voltage for each power converter; i isBO_O、ICO_O……INO_OOutputting current for each power converter; vbus_COMIs the common bus voltage.
As shown in FIG. 2, according to one embodiment of the present invention, a plurality of output power converters operate in a master-slave mode, wherein one of the output power converters is a master module and the remaining output power converters are slave modules. In this embodiment, the output power converter as the main module adopts voltage and current dual closed-loop control, the outer loop is a voltage closed loop for realizing voltage regulation of the common bus, and the inner loop is a current closed loop; the output power converter as a slave module adopts current closed loop control. In this embodiment, the power converter B _ O, C _ O … N _ O operates in a master-slave mode, one module is used as a master module (for example, the module B), and voltage and current dual closed-loop control is adopted, and the outer loop is a voltage closed loop for realizing the common bus voltage Vbus_COMAnd adjusting, wherein the inner ring is a current closed ring. The other modules C, D … N are slave modules, which have only a closed loop of current. The control moves away as shown in fig. 4. Wherein: gBVAdjusting a gain for the slave module voltage; gBI、GCI…GNIAdjusting a gain for the module current; vrefFor common bus voltage referenceA test signal; vcom_fSampling a signal for a common bus voltage; i isB_f、IC_f…IN_fOutputting current values for all modules distributed by all energy management centers; i isB_Lf、IC_Lf…IN_LfSampling signals for the inductor current of each module; vRAMP_B、VRAMP_C…VRAMP_NPWM signals for each module. Through the arrangement, 1) the main module is responsible for maintaining the stability of the grid-connected public bus, and the rest of the slave modules are current sources, do not participate in voltage control of the grid-connected bus, do not compete with each other, and are easy to realize the stability of a grid-connected system; 2) the output current of each module can be respectively given by the energy management center in combination with the power surplus condition, so that the optimal utilization of the energy of the whole system is realized.
According to one embodiment of the invention, the output power converter and the input power converter in a single spacecraft may be arranged in one or more parallel connections, respectively. In this embodiment, when a plurality of output power converters and a plurality of input power converters in a single spacecraft are respectively arranged in parallel, the output power converters or the input power converters work in parallel when the spacecraft power gap amount or the spacecraft power surplus exceeds a set threshold. In this embodiment, the input power converter a _ I, B _ I … N _ I and the output power converter a _ O, B _ O … N _ O can be designed in a universal manner, and the power configuration parameters are consistent. When a power gap/surplus power of a certain spacecraft is large, a plurality of input power converters or output power converters can be connected in parallel for use, and are directly connected in parallel without additional control, as shown in fig. 5.
As shown in fig. 5, according to an embodiment of the present invention, when a certain spacecraft M is connected to the grid in-orbit, the power converter can be directly connected to the grid-connected common bus, so as to integrate into the whole grid-connected system.
The foregoing is merely exemplary of particular aspects of the present invention and devices and structures not specifically described herein are understood to be those of ordinary skill in the art and are intended to be implemented in such conventional ways.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (1)

1. A grid-connected power supply method of a spacecraft grid-connected topological structure based on a common bus is characterized in that at least three spacecrafts adopt the grid-connected topological structure based on the common bus to carry out grid-connected power supply; the method comprises the following steps:
s1, the spacecraft acquires the actual power of a power grid of the spacecraft, and autonomously judges the power state of the power grid according to the actual power of the power grid;
s2, if the power of the power grid of the spacecraft is rich, transmitting redundant electric energy to the public bus, and if the power of the power grid of the spacecraft is insufficient, receiving the electric energy transmitted on the public bus;
the power grid bus in the spacecraft is connected with the public bus through an input power converter and an output power converter respectively;
the output power converters work in a master-slave mode, wherein one output power converter is used as a master module for maintaining the voltage stability of the common bus, and the rest output power converters are used as slave modules and current sources and do not participate in the voltage control of the common bus;
the input power converter receives the electric energy transmitted on the public bus and then transmits the electric energy to a power grid of the spacecraft in a constant current mode;
the input power converter and the output power converter on each spacecraft are connected with an energy management center;
the energy management center is used for counting and analyzing the power gap amount or the power surplus amount of each spacecraft power grid and controlling the power magnitude of the on, off and transmission of each input power converter and each output power converter;
the power grid in the spacecraft receives the electric energy transmitted on the public bus through the input power converter;
the power grid in the spacecraft transmits redundant electric energy to the public bus through the output power converter;
when the power of the power grid of the plurality of spacecrafts is rich, the output voltage of each output power converter connected with the public bus is equal;
the output power converter serving as the main module adopts voltage and current double closed-loop control, the outer ring is a voltage closed loop and is used for realizing voltage regulation of the common bus, and the inner ring is a current closed loop;
the output power converter as a slave module adopts current closed loop control;
the output power converters and input power converters in a single spacecraft may be arranged in one or more parallel connections, respectively;
when the output power converters and the input power converters in a single spacecraft are respectively arranged in parallel, when the power gap amount or the power surplus amount of the spacecraft exceeds a set threshold value, the output power converters or the input power converters work in parallel.
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