CN107968394B - System construction method for master-slave spacecraft grid-connected power supply - Google Patents
System construction method for master-slave spacecraft grid-connected power supply Download PDFInfo
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- CN107968394B CN107968394B CN201711284224.XA CN201711284224A CN107968394B CN 107968394 B CN107968394 B CN 107968394B CN 201711284224 A CN201711284224 A CN 201711284224A CN 107968394 B CN107968394 B CN 107968394B
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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
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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
- H02J1/08—Three-wire systems; Systems having more than three wires
- H02J1/082—Plural DC voltage, e.g. DC supply voltage with at least two different DC voltage levels
Abstract
The invention relates to a system construction method for master-slave spacecraft grid-connected power supply, which comprises the following steps: s1, generating a connection structure scheme for grid-connected power supply between two power supply systems according to a main power supply system of a main spacecraft and a slave power supply system of a slave spacecraft; s2, generating an electric energy transmission scheme for grid-connected power supply according to the main power supply system and the auxiliary power supply system; and S3, establishing a power supply mode scheme of grid-connected power supply according to the main power supply system and the auxiliary power supply system. The design, construction requirements and technical indexes of high-low voltage and high-power grid-connected power supply between the master spacecraft and the slave spacecraft are determined through a connection structure scheme, an electric energy transmission scheme, a power supply mode scheme and a load adaptation scheme generated by the master power supply system and the slave power supply system. According to the system construction method, the slave spacecraft can be butted, connected and powered on in different directions of the master spacecraft, and the grid connection requirements of low-voltage high-power grid connection and large grid connection power fluctuation of the slave spacecraft are met.
Description
Technical Field
The invention relates to a system construction method for grid-connected power supply, in particular to a system construction method for grid-connected power supply of a master spacecraft and a slave spacecraft.
Background
With the development of manned aerospace technology, spacecrafts are increasingly large and complex, and flying tasks are also increasingly abundant. Therefore, the rendezvous and docking of the spacecraft in space is more and more frequent, but the main spacecraft generally adopts a 100V bus, and the visiting slave spacecraft adopts a 28V bus. After the slave spacecraft is in butt joint with the master spacecraft, the power generation capacity of the slave spacecraft is insufficient due to the influence of flight attitude and shielding. Therefore, the master spacecraft will provide stable and continuous power supply for the slave spacecraft through grid-connected power supply.
In the prior art, a main spacecraft in a manned space meeting docking task converts a 100V bus voltage into a 28V voltage, and the voltage and a manned spacecraft power supply system are connected to the power grid and then supply power to a load of a slave spacecraft together. The grid-connected power supply mode adopts a constant-voltage grid-connected control method and does not support the condition of constant-power grid-connected requirement. Meanwhile, the existing grid-connected power supply method only aims at the condition of low-power grid-connected power supply. In the prior art, a design method for realizing grid-connected power supply between two high-voltage system spacecrafts based on a constant-current voltage-limiting power converter is provided, but the mode is not suitable for the working condition that a visiting aircraft has no power generation capacity, and only aims at grid-connected power supply from high voltage to high voltage.
Disclosure of Invention
The invention aims to provide a system construction method for grid-connected power supply of a master spacecraft and a slave spacecraft, which can be used for high-low voltage high-power grid-connected power supply between different power supply systems between the master spacecraft and the slave spacecraft.
In order to achieve the purpose, the invention provides a system construction method for grid-connected power supply of a master spacecraft and a slave spacecraft, which comprises the following steps:
s1, generating a connection structure scheme for grid-connected power supply between two power supply systems according to a main power supply system of a main spacecraft and a slave power supply system of a slave spacecraft;
s2, generating an electric energy transmission scheme for grid-connected power supply according to the main power supply system and the auxiliary power supply system;
and S3, establishing a power supply mode scheme of grid-connected power supply according to the main power supply system and the auxiliary power supply system.
According to one aspect of the invention, the connection structure scheme comprises: a grid-connected topology sub-scheme, a system interface sub-scheme and a safety isolation sub-scheme.
According to one aspect of the invention, the grid-connected topology sub-scheme includes a grid-connected power supply topology between the main power supply system and the slave power supply system, wherein the topology is a single-stage topology that combines at least two input buses of the main power supply system into one output bus through a grid-connected controller;
the system interface sub-scheme comprises a connection structure for grid-connected power supply between the main power supply system and the slave power supply system, wherein the connection structure is used for connecting the main power supply system and the slave power supply system through a circuit floating disconnector or a manual connection connector;
the safety isolation sub-scheme comprises that grid-connected power supply between the main power supply system and the auxiliary power supply system adopts an electrical isolation mode.
According to one aspect of the invention, a power transfer scheme includes: a conversion topology sub-scheme, a conversion efficiency sub-scheme, a heat dissipation sub-scheme, and a transmission path sub-scheme.
According to an aspect of the present invention, the conversion topology sub-scheme includes a conversion topology of the grid-connected controller, and the conversion topology is a multi-module parallel current-sharing operating topology.
The conversion efficiency sub-scheme includes: the conversion efficiency parameter is more than 87%, and the transmission loss power parameter is less than 10%.
According to one aspect of the invention, a power mode scheme comprises: a mode type sub-scheme, a system state sub-scheme, and a mode transition sub-scheme.
According to an aspect of the invention, the schema type sub-scheme comprises:
if the slave power supply system has power generation capacity, grid-connected power supply between the main power supply system and the slave power supply system adopts a constant current mode for power supply;
if the slave power supply system lacks the power generation capacity, the grid-connected power supply between the main power supply system and the slave power supply system adopts the constant voltage mode for power supply,
under the condition that the slave power supply system continuously changes between the power generation capacity and the non-power generation capacity along with the flight state, the power supply mode adopted by grid-connected power supply between the master power supply system and the slave power supply system is automatically switched between the constant current mode and the constant voltage mode.
According to one aspect of the invention, a system state sub-scheme comprises: grid-connected current I and voltage-limiting point parameter U;
the grid-connected current I satisfies: i < (P1/Ubus) and I < (P2/Ubus), wherein P1 is the master power supply system maximum output power, P2 is the load power of the slave spacecraft, Ubus is the bus voltage;
the voltage limiting point parameter U includes: an upper limit of pressure limiting point U1 and a lower limit of pressure limiting point U2;
the upper limit of the pressure limiting point U1 satisfies: u1 is less than Umax _ bus, wherein Umax _ bus is the maximum bus voltage;
the lower limit U2 of the pressure limiting point satisfies: u2> Upower + U loss, wherein Upower is the power supply voltage of the slave power supply system, and U loss is the transmission voltage drop.
According to one aspect of the invention, a mode conversion sub-scheme comprises: a constant current to constant voltage mode and a constant voltage to constant current mode;
when the constant current is converted into the constant voltage mode, the amplitude of the voltage overshoot is lower than 5% of the rated voltage of the slave power supply system, and the time is lower than 10 ms;
when the constant voltage is converted into the constant current mode, the amplitude of the current overshoot is lower than 10% of the rated current of the slave power supply system, and the time is lower than 10 ms.
According to an aspect of the invention, further comprising:
s4, formulating a load adaptation scheme of the main power supply system according to the main power supply system and the auxiliary power supply system;
the load adaptation scheme comprises a grid connection requirement sub-scheme, a load steady-state change sub-scheme and a load step impact sub-scheme;
the grid-connected demand sub-scheme comprises a maximum power value, a variation value of power generation capacity, a maximum step value of grid-connected demand power, a maximum voltage tolerance capacity during grid-connected power supply and a bus voltage of a slave spacecraft during grid-connected power supply, which are obtained according to the main power supply system and the slave power supply system;
the load steady state change sub-scheme comprises the following steps of obtaining the maximum output current, the maximum output voltage, the maximum output power, the cable voltage drop parameter, the voltage control precision in a constant voltage mode and the current control precision in a constant current mode according to the main power supply system and the slave power supply system;
the load step impulse sub-scheme comprises voltage jump parameters under a constant-current to constant-voltage mode, current jump parameters under a constant-voltage to constant-current mode and load step response characteristics under a constant-voltage mode, which are obtained by the main power supply system and the auxiliary power supply system.
According to one scheme of the invention, the design, construction requirements and technical indexes of high-low voltage and high-power grid-connected power supply between the master spacecraft and the slave spacecraft are determined by generating a connection structure scheme, an electric energy transmission scheme, a power supply mode scheme and a load adaptation scheme through the master power supply system and the slave power supply system. According to the system construction method, the slave spacecraft can be butted, connected and supplied with power in different directions (forward, backward and radial) of the master spacecraft, the grid connection requirements of low-voltage high-power grid connection, large grid connection power fluctuation, high grid connection voltage precision requirement and complex mode of the slave spacecraft are met, and the safe and reliable grid connection and high-performance grid connection of the master spacecraft and the slave spacecraft are realized.
According to one scheme of the invention, the system is suitable for any spacecraft model for carrying out high-low voltage and high-power grid-connected power supply, can cover the design requirement of a low-power grid-connected power supply system, and can directly support designers to carry out the design of different spacecraft power supply systems.
According to one scheme of the invention, the single-stage topological structure is adopted to adapt to high-power grid-connected power supply transmission between two power supply systems, so that the power supply efficiency of grid-connected power supply between the two power supply systems is improved. Through the arrangement mode, the grid-connected controller enables high-voltage and low-voltage grid-connected power transmission between the main spacecraft and the slave spacecraft through the multi-module parallel current-sharing working topology, the output current of a single module is reduced, and the electrical stress redundancy of devices in the grid-connected controller is improved.
According to one scheme of the invention, the conversion efficiency parameter of the grid-connected controller is greater than 87%, so that the high-voltage power of the main power supply system is effectively converted into the low-voltage power of the slave power supply system, the stability of power conversion in the high-voltage and low-voltage conversion process is ensured, and the slave power supply system can obtain enough power to ensure the normal operation of the load in the grid-connected power supply process of the main power supply system 1 and the slave power supply system. Meanwhile, the transmission loss power of the electric energy on the grid-connected cable is less than 10%, the stability of the voltage or the current of the electric energy in the transmission process is ensured, the fluctuation of the voltage or the current in the transmission process is reduced, the heating on the grid-connected cable is also reduced, the loss of the electric energy is reduced, and the high-power transmission of the electric energy between the main power supply system and the auxiliary power supply system is favorably ensured.
Drawings
FIG. 1 schematically represents a block diagram of the steps of a system construction method according to one embodiment of the invention;
FIG. 2 schematically shows a block diagram of a master power supply system and a slave power supply system connection according to an embodiment of the invention;
fig. 3 schematically shows a diagram of a conversion topology of a networked controller according to an embodiment of the present invention;
fig. 4 schematically shows a block diagram of a power module 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," and the like 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 and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present 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, a system construction method for master-slave spacecraft grid-connected power supply of the present invention includes:
s1, generating a connection structure scheme for grid-connected power supply between two power supply systems according to a main power supply system of a main spacecraft and a slave power supply system of a slave spacecraft;
s2, generating an electric energy transmission scheme for grid-connected power supply according to the main power supply system and the auxiliary power supply system;
s3, establishing a power supply mode scheme of grid-connected power supply according to the main power supply system and the auxiliary power supply system;
and S4, formulating a load adaptation scheme of the main power supply system according to the main power supply system and the auxiliary power supply system.
For a detailed explanation of the present invention, the method of the present invention will be described in detail with reference to the accompanying drawings.
In step S1, according to an embodiment of the present invention, the connection structure scheme includes: a grid-connected topology sub-scheme, a system interface sub-scheme and a safety isolation sub-scheme. In the present embodiment, the grid-connected topology sub-scheme includes a topology of grid-connected power supply between the master power supply system 1 and the slave power supply system 2. Referring to fig. 2, the topology between the main power supply system 1 and the slave power supply system 2 is a single-stage topology in which at least two input buses of the main power supply system 1 are combined into one output bus by the grid-connected controller 11. In the present embodiment, the main power supply system 1 includes two bus bars, i.e., a first bus bar a and a second bus bar B. Through the arrangement, the single-stage topological structure is adopted to adapt to high-power grid-connected power supply transmission between two power supply systems, and the power supply efficiency of grid-connected power supply between the two power supply systems is improved.
According to one embodiment of the invention, the grid connection of the power supply system between the master spacecraft and the slave spacecraft is realized by a physical connection structure. In the present embodiment, the system interface sub-scheme includes a connection structure for grid-connected power supply between the master power supply system 1 and the slave power supply system 2, and the connection structure is a circuit floating disconnector or a manual connection connector. The main spacecraft is in butt joint with the slave spacecraft, and after the butt joint is completed, the main power supply system 1 and the slave power supply system 2 are in rigid connection through a connecting structure, so that the connection of the two power supply systems is realized. Of course, during the actual connection process, the master power supply system 1 and the slave power supply system 2 may be connected by a manual cord.
According to one embodiment of the invention, in order to ensure the safety of grid-connected power supply between the master spacecraft and the slave spacecraft, a safety isolation measure needs to be arranged between the master power supply system 1 and the slave power supply system 2. In the present embodiment, the safety isolation sub-scheme includes a safety isolation manner of grid-connected power supply between the master power supply system 1 and the slave power supply system 2. In the present embodiment, an electrical isolation method is used when grid-connected power is supplied between the master power supply system 1 and the slave power supply system 2.
In step S2, according to an embodiment of the present invention, the power transmission scheme includes: a conversion topology sub-scheme, a conversion efficiency sub-scheme, a heat dissipation sub-scheme, and a transmission path sub-scheme.
According to one embodiment of the present invention, the main power supply system 1 merges the buses of the main power supply system through the grid-connected controller 2, so as to implement power conversion of the main power supply system 1 of the main spacecraft. In the present embodiment, the conversion topology sub-scheme includes a conversion topology of the grid controller 11. And the grid controller 11 combines the electric energy transmitted by the two buses into the output electric energy of one bus by converting the topology structure. In this embodiment, referring to fig. 3, the parallel network controller 11 is configured to convert the topology into a multi-module parallel current-sharing operating topology. The input terminals of the first power module 111 and the second power module 112 connected in parallel to each other are connected to the bus a, respectively, and the third power module 113 and the fourth power module 114 connected in parallel to each other are connected to the bus B, respectively. The output terminals of the first power module 111, the second power module 112, the third power module 113 and the fourth power module 114 are connected to each other. Through the arrangement mode, the grid-connected controller 11 enables high-low voltage grid-connected power transmission between the main spacecraft and the slave spacecraft through the multi-module parallel current-sharing working topology, the output current of a single module is reduced, and the electrical stress redundancy of devices in the grid-connected controller 11 is improved.
As shown in fig. 4, according to an embodiment of the present invention, the first power module 111, the second power module 112, the third power module 113, and the fourth power module 114 are connected to each other, and the first power module 111 is taken as an example for description. In this embodiment, the first power module 111 includes a fuse 1111, a surge suppression circuit 1112, an input stage filter circuit 1113, a main power stage 1114, an isolation stage 1115, and a control stage 1116. In this embodiment, the fuse 1111, the surge suppression circuit 1112, the input stage filter circuit 1113, the main power stage 1114, and the isolation stage 1115 are connected in sequence, wherein the fuse 1111 is connected to the bus a, and the electric energy transmitted by the bus a is output through the fuse 1111, the surge suppression circuit 1112, the input stage filter circuit 1113, the main power stage 1114, and the isolation stage 1115 in sequence.
As shown in fig. 4, the control stage 1116 is connected to the input stage filter circuit 1113 and the main power stage 1114, respectively, according to an embodiment of the present invention. In this embodiment, the control stage 1116 includes an auxiliary power supply 1116a, an isolation driver 1116b, a control circuit 1116c, an intelligent component 1116d, a voltage sampling circuit 1116e, and a current sampling circuit 1116 f. The auxiliary power 1116a is connected to the input stage filter circuit 1113, and the auxiliary power 1116a is supplied through the input stage filter circuit 1113. The auxiliary power supply 1116a is connected to the isolation driver 1116b and the control circuit 1116c, respectively. The control circuit 1116c is connected to the isolation driver 1116b, the intelligent component 1116d, the voltage sampling circuit 1116e, and the current sampling circuit 1116f, respectively. The intelligent module 1116d receives a command for starting the first power module 111, and the control circuit 1116c controls the isolation driver 1116b to operate, so that the main power stage 1114 operates, and the first power module 111 is turned on. After the first power module 111 is turned on, the current sampling circuit 1116f samples the main power stage 1114 and sends the sampling result to the control circuit 1116 c. The voltage sampling circuit 1116e samples the voltage of the output after the isolation stage 1115, and sends the sampling result to the control circuit 1116 c. By the above arrangement, the control stage 1116 can stably control power conversion and transmission of the first power control module 111, and the grid-connected controller 11 can stably operate. Meanwhile, different power control modules can be controlled to be switched on through the control instruction, and the stability of the output electric energy of the main power supply system is further ensured.
According to one embodiment of the invention, the conversion efficiency sub-scheme comprises: a conversion efficiency parameter and a transmission loss power parameter. In the present embodiment, the grid-connected transmission of the power between the master power supply system 1 and the slave power supply system 2 requires the power in the master power supply system 1 to be converted by the grid-connected controller 11 and output to the slave power supply system 2. Therefore, the conversion efficiency parameter is greater than 87%. The transmission loss power parameter of the grid-connected transmission electric energy of the main power supply system 1 and the auxiliary power supply system 2 on the grid-connected cable is less than 10%. Through the above arrangement, the conversion efficiency parameter of the grid-connected controller 11 is greater than 87%, so that the high-voltage power of the main power supply system 1 is effectively converted into the low-voltage power of the slave power supply system 2, the stability of the electric energy conversion in the high-voltage and low-voltage conversion process is ensured, and the main power supply system 1 and the slave power supply system 2 can obtain enough electric energy to ensure the normal operation of the load in the grid-connected power supply process. Meanwhile, the transmission loss power of the electric energy on the grid-connected cable is less than 10%, the stability of the voltage or the current of the electric energy in the transmission process is ensured, the fluctuation of the voltage or the current in the transmission process is reduced, the heating on the grid-connected cable is also reduced, the loss of the electric energy is reduced, and the high-power transmission of the electric energy between the master power supply system 1 and the slave power supply system 2 is favorably ensured.
According to one embodiment of the present invention, the heat generation amount is large when the master power supply system 1 and the slave power supply system 2 perform grid-connection power transmission. In the present embodiment, in the heat dissipation sub-scheme, heat dissipation measures are set for the main power supply system 1 and the slave power supply system 2 according to the heating condition under the maximum steady-state output power, cold plates are configured, and meanwhile ventilation equipment needs to be set for good ventilation. By means of the heat dissipation measures, damage to load equipment or cables caused by out-of-control temperature due to large heat generation when the main power supply system 1 and the slave power supply system 2 carry out grid-connected power transmission is avoided, and service lives of the load equipment and the cables of the main power supply system 1 and the slave power supply system 2 are further guaranteed.
As shown in fig. 2, according to one embodiment of the present invention, the transmission path sub-scheme defines the path for the grid controller 11 to draw power to draw a 100V power input from the bus distributor 12, and the grid controller 11 converts the 100V high voltage to a 28V low voltage output by isolation conversion. The transmission path from the output end of the grid-connected controller 11 to the grid-connected interface is a grid-connected power supply cable, and the number of the connection points, the line diameter and the length of the transmission cable are set through a transmission path sub-scheme.
In step S3, according to an embodiment of the present invention, the power supply mode scheme includes: a mode type sub-scheme, a system state sub-scheme, and a mode transition sub-scheme.
According to one embodiment of the present invention, the type of the mode of the grid-connected power supply between the master power supply system 1 and the slave power supply system 2 in the mode type sub-scheme is selected according to the power generation capacity of the slave power supply system 2. If the slave power supply system 2 has power generation capacity, the grid-connected power supply between the master power supply system 1 and the slave power supply system 2 adopts a constant current mode for power supply. If the slave power supply system 2 lacks the power generation capability, the grid-connected power supply between the master power supply system 1 and the slave power supply system 2 adopts the constant voltage mode for power supply. Under the condition that the slave power supply system 2 continuously changes between the power generation capacity and the non-power generation capacity along with the flight state, the power supply mode adopted by the grid-connected power supply between the master power supply system 1 and the slave power supply system 2 is automatically switched between the constant current mode and the constant voltage mode. Through the arrangement, the grid-connected transmission mode of the main power supply system 1 and the slave power supply system 2 is selected according to the power generation capacity of the slave power supply system 2 of the slave spacecraft, and the two power supply systems can work normally at the same time. Through the arrangement, the mode type of mutual power supply of the two power supply systems is set according to the power generation capacity of the slave power supply system 2, the stability of the power supply power of the two power supply systems in the grid-connected power supply process is ensured, and the working stability of the load in the slave spacecraft is further ensured.
According to one embodiment of the invention, the system state sub-scheme comprises: and areThe network current I and the voltage limiting point parameter U of the output bus. In the present embodiment, the grid-connected current I satisfies: i is<(P1/Ubus) And I<(P2/Ubus) In which P is1For the maximum output power, P, of the main power supply system2For the load power of the slave spacecraft, UbusTo output the bus voltage. In the present embodiment, the voltage limit point parameter U includes: upper limit of pressure limiting point U1And lower limit of pressure limiting point U2. Upper limit of pressure limiting point U1Satisfies the following conditions: u shape1＜Umax_busWherein, Umax_busIs the maximum output bus voltage; lower limit of pressure limiting point U2Satisfies the following conditions: u shape2>Upower+ULoss of powerWherein, UpowerFor the supply voltage of the slave power supply system, ULoss of powerTo deliver a pressure drop. Through the arrangement, the current and the voltage in the main power supply system 1 and the slave power supply system 2 are effectively ensured to be in a reasonable range, the stability of grid-connected power supply is ensured, the power supply performance of the two power supply systems is ensured, and the service lives of the two power supply systems are ensured.
According to one embodiment of the present invention, a mode switching sub-scheme includes: constant current to constant voltage mode and constant voltage to constant current mode. In the present embodiment, due to the control accuracy and the delay characteristic, a voltage current rush occurs at the mode switching when the electric energy is transmitted between the master power supply system 1 and the slave power supply system 2 in a grid-connected manner. In the present embodiment, in the constant current to constant voltage mode, the amplitude of the voltage overshoot is less than 5% of the rated voltage of the slave power supply system, and the time is less than 10 ms. When the constant voltage is converted into the constant current mode, the amplitude of the current overshoot is lower than 10% of the rated current of the slave power supply system, and the time is lower than 10 ms. Through the arrangement, the design margin between the main power supply system 1 and the auxiliary power supply system 2 is ensured, and the safety of the main spacecraft and the auxiliary spacecraft in the grid-connected power supply process is ensured.
In step S4, according to an embodiment of the present invention, the load adaptation scheme includes a grid connection demand sub-scheme, a load steady state change sub-scheme, and a load step impact sub-scheme.
According to one embodiment of the invention, the grid-connected demand sub-scheme is used for determining the maximum power value, the variation value of the power generation capacity, the maximum step value of the grid-connected demand power, the maximum voltage tolerance capacity during grid-connected power supply and the bus voltage of the slave spacecraft during grid-connected power supply of the main power supply system 1 and the slave power supply system 2.
According to one embodiment of the present invention, the load steady state variation sub-scheme is used to specify the maximum output current, the maximum output voltage, the maximum output power, the cable voltage drop parameter, the voltage control accuracy in the constant voltage mode, and the current control accuracy in the constant current mode of the master power supply system 1 and the slave power supply system 2.
According to one embodiment of the present invention, the load step-and-surge sub-scheme is used to define the voltage jump parameter in the constant current to constant voltage mode, the current jump parameter in the constant voltage to constant current mode, and the load step response characteristic in the constant voltage mode of the master power supply system 1 and the slave power supply system 2.
According to the arrangement, the main power supply system 1 can have enough power supply margin by setting the load adaptation scheme, and the defect that the main power supply system cannot stably supply power due to the change of the load is avoided. The stable performance of the main power supply system 1 in the power supply process is ensured by setting a load adaptation scheme, and the service life of the main power supply system 1 is ensured.
According to the system construction method, the design, construction requirements and technical indexes of high-low voltage and high-power grid-connected power supply between the master spacecraft and the slave spacecraft are determined through the connection structure scheme, the electric energy transmission scheme, the power supply mode scheme and the load adaptation scheme generated by the master power supply system 1 and the slave power supply system 2. According to the system construction method, the slave spacecraft can be butted, connected and supplied with power in different directions (forward, backward and radial) of the master spacecraft, the grid connection requirements of low-voltage high-power grid connection, large grid connection power fluctuation, high grid connection voltage precision requirement and complex mode of the slave spacecraft are met, and the safe and reliable grid connection and high-performance grid connection of the master spacecraft and the slave spacecraft are realized.
The system construction method is suitable for any spacecraft model carrying out high-voltage, low-voltage and high-power grid-connected power supply, can cover the design requirement of a low-power grid-connected power supply system, and can directly support designers to design different spacecraft power supply systems.
The foregoing is illustrative of specific embodiments of the present invention and reference should be made to the implementation of apparatus and structures not specifically described herein, which is understood to be a general purpose apparatus and method of operation known in the art.
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 (4)
1. A system construction method for grid-connected power supply of a master spacecraft and a slave spacecraft comprises the following steps:
s1, generating a connection structure scheme for grid-connected power supply between two power supply systems according to a main power supply system of a main spacecraft and a slave power supply system of a slave spacecraft, wherein the connection structure scheme comprises the following steps: the grid-connected topology sub-scheme comprises a grid-connected power supply topology structure between the main power supply system and the auxiliary power supply system, wherein the topology structure is a single-stage topology structure which combines at least two input buses of the main power supply system into one output bus through a grid-connected controller;
s2, generating an electric energy transmission scheme for grid-connected power supply according to the main power supply system and the auxiliary power supply system, wherein the electric energy transmission scheme comprises the following steps: a topology conversion sub-scheme, wherein the topology conversion sub-scheme comprises a multi-module parallel current-sharing working topology structure of the grid-connected controller;
each end of the grid-connected controller connected with the input bus is respectively provided with two power modules in parallel, and each power module comprises a fuse connected with the input bus, a surge suppression circuit connected with the fuse, an input stage filter circuit connected with the surge suppression circuit, a main power stage connected with the input stage filter circuit, an isolation stage connected with the main power stage and a control stage;
the control stage comprises an auxiliary power supply, an isolation drive, a control circuit, an intelligent assembly, a voltage sampling circuit and a current sampling circuit; the auxiliary power supply is connected with the input stage filter circuit, the isolation drive and the control circuit respectively, the control circuit is connected with the isolation drive, the intelligent assembly, the voltage sampling circuit and the current sampling circuit respectively, the main power stage is connected with the isolation drive and the current sampling circuit respectively, and the voltage sampling circuit is connected with the output end of the isolation stage;
s3, a power supply mode scheme of grid-connected power supply is formulated according to the main power supply system and the auxiliary power supply system, and the power supply mode scheme comprises the following steps: a mode type sub-scheme, a system state sub-scheme, and a mode transition sub-scheme;
the pattern type sub-scheme includes:
if the slave power supply system has power generation capacity, grid-connected power supply between the main power supply system and the slave power supply system adopts a constant current mode for power supply;
if the slave power supply system lacks the power generation capacity, the grid-connected power supply between the main power supply system and the slave power supply system adopts the constant voltage mode for power supply,
under the condition that a slave power supply system continuously changes between the power generation capacity and the non-power generation capacity along with the flight state, the power supply mode adopted by grid-connected power supply between a main power supply system and the slave power supply system is automatically switched between the constant current mode and the constant voltage mode;
the system state sub-scheme includes: grid-connected current I and voltage limiting point parameter U of an output bus;
the grid-connected current I satisfies: i is<(P1/Ubus) And I<(P2/Ubus) In which P is1For the maximum output power, P, of the main power supply system2For the load power of the slave spacecraft, UbusTo output bus voltage;
the voltage limiting point parameter U includes: an upper limit of pressure limiting point U1 and a lower limit of pressure limiting point U2;
upper limit of pressure limiting point U1Satisfies the following conditions: u shape1＜Umax_busWherein, Umax_busIs the maximum output bus voltage;
lower limit of pressure limiting point U2Satisfies the following conditions: u shape2>Upower+ULoss of powerWherein, UpowerFor the supply voltage of the slave power supply system, ULoss of powerTo transport the pressure drop;
the mode conversion sub-scheme comprises: a constant current to constant voltage mode and a constant voltage to constant current mode;
when the constant current is converted into the constant voltage mode, the amplitude of the voltage overshoot is lower than 5% of the rated voltage of the slave power supply system, and the time is lower than 10 ms;
when the constant voltage is converted into the constant current mode, the amplitude of the current overshoot is lower than 10% of the rated current of the slave power supply system, and the time is lower than 10 ms.
2. The system building method according to claim 1, wherein the connection structure scheme further comprises: a system interface sub-scheme and a security isolation sub-scheme;
the system interface sub-scheme comprises a connection structure for grid-connected power supply between the main power supply system and the slave power supply system, wherein the connection structure is used for connecting the main power supply system and the slave power supply system through a circuit floating disconnector or a manual connection connector;
the safety isolation sub-scheme comprises that grid-connected power supply between the main power supply system and the auxiliary power supply system adopts an electrical isolation mode.
3. The system building method of claim 1, wherein the power transfer scheme further comprises: a conversion efficiency sub-scheme, a heat dissipation sub-scheme, and a transmission path sub-scheme;
the conversion efficiency sub-scheme includes: the conversion efficiency parameter and the transmission loss power parameter are obtained, wherein the conversion efficiency parameter is more than 87%, and the transmission loss power parameter is less than 10%;
in the heat dissipation sub-scheme, heat dissipation measures are set for the main power supply system and the auxiliary power supply system according to the heating condition under the maximum steady-state output power, a cold plate is configured, and ventilation equipment is arranged;
the transmission path sub-scheme is used for determining a path for obtaining electric energy by the grid-connected controller, namely obtaining 100V power supply input from a bus distributor, converting 100V high voltage into 28V low voltage output by the grid-connected controller through isolation conversion, enabling a transmission path from an output end of the grid-connected controller to a grid-connected interface to be a grid-connected power supply cable, and setting the number of contacts, the line diameter and the length of the transmission cable through the transmission path sub-scheme.
4. The system building method according to claim 1, further comprising:
s4, formulating a load adaptation scheme of the main power supply system according to the main power supply system and the auxiliary power supply system;
the load adaptation scheme comprises a grid connection requirement sub-scheme, a load steady-state change sub-scheme and a load step impact sub-scheme;
the grid-connected demand sub-scheme is used for determining the maximum power value of the main power supply system and the slave power supply system, the variation value of the power generation capacity, the maximum step value of the grid-connected demand power, the maximum voltage tolerance capacity during grid-connected power supply and the bus voltage of the slave spacecraft during grid-connected power supply;
the load steady state variation sub-scheme is used for determining the maximum output current, the maximum output voltage, the maximum output power, the cable voltage drop parameter, the voltage control precision in a constant voltage mode and the current control precision in a constant current mode of the main power supply system and the slave power supply system;
the load step impulse sub scheme is used for determining voltage jump parameters of the main power supply system and the slave power supply system in a constant current to constant voltage mode, current jump parameters of the master power supply system and the slave power supply system in a constant voltage to constant current mode, and load step response characteristics of the master power supply system and the slave power supply system in a constant voltage mode.
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