CN112583002B - 28V/270V composite energy system for carrier rocket - Google Patents
28V/270V composite energy system for carrier rocket Download PDFInfo
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- CN112583002B CN112583002B CN202011378874.2A CN202011378874A CN112583002B CN 112583002 B CN112583002 B CN 112583002B CN 202011378874 A CN202011378874 A CN 202011378874A CN 112583002 B CN112583002 B CN 112583002B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
- H02J7/0014—Circuits for equalisation of charge between batteries
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0069—Charging or discharging for charge maintenance, battery initiation or rejuvenation
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/007—Regulation of charging or discharging current or voltage
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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
- H02J2207/00—Indexing scheme relating to details of circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J2207/20—Charging or discharging characterised by the power electronics converter
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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
- H02J2207/00—Indexing scheme relating to details of circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J2207/40—Indexing scheme relating to details of circuit arrangements for charging or depolarising batteries or for supplying loads from batteries adapted for charging from various sources, e.g. AC, DC or multivoltage
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/10—Technologies relating to charging of electric vehicles
- Y02T90/14—Plug-in electric vehicles
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Abstract
The invention relates to a 28V/270V composite energy system for a carrier rocket, which comprises a 28V instrument battery, a 270V high-voltage battery, a 270V fluid power supply, instrument bus energy management equipment, high-voltage bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power module, a power distribution module and a time sequence module, wherein the instrument bus energy management equipment is connected with the high-voltage bus energy management equipment; the instrument power supply area consists of a 28V instrument battery, instrument bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power module, a power distribution module and a time sequence module, wherein the power module, the power distribution module and the time sequence module are arranged in an instrument cabin/box interval; the instrument power supply area is arranged in an instrument cabin/box section of the carrier rocket sublevel; the 28V instrument battery is connected with the instrument bus energy management device through a cable, and the 28V instrument battery outputs DC 28V voltage. The invention adopts a DC 270V bus system, which can obviously reduce the line loss, reduce the weight of the power supply cable network on the arrow and simultaneously contribute to reducing the weight and the volume of the high-power motor.
Description
Technical Field
The invention relates to a 28V/270V composite energy system for a carrier rocket, and belongs to the technical field of electric systems on carrier rocket rockets.
Background
An electric system on a launch vehicle rocket in China generally adopts a power supply of a direct-current 28V voltage system for power supply and power distribution at present, and an rocket battery is adopted to provide energy for an electric load on the rocket.
The main electric loads on the next generation carrier rocket in China are gradually transferred to a high-power electromechanical servo mechanism through electronic instrument equipment, an engine electromagnetic valve and initiating explosive devices, a thrust adjusting motor, a utilization adjusting motor and a precooling circulating pump of a power system are adopted, and the high-power loads are mainly inductive loads; the power supply power is also increased from the scale of the power load of the whole rocket at 10kW level to the scale of the power load of the whole rocket at 200kW level in the existing carrier rocket in China, and the power load power of the whole rocket can be increased by one magnitude along with the fact that an electric control air valve of the engine can be gradually replaced by motor drive; the number of the electric equipment is greatly increased, the distance between the equipment is farther, and the distribution range is larger.
Therefore, from the perspective of the overall design of the whole rocket energy source, it is necessary to develop improved designs from multiple aspects such as power supply sources, bus voltage levels, energy transmission modes and the like to form the top layer architecture design of the next generation of carrier rocket energy system.
Disclosure of Invention
The technical problem solved by the invention is as follows: the 28V/270V composite energy system for the carrier rocket is provided, adopts a composite energy system structure with direct current 28V and direct current 270V power supply bus voltage standard, and is used for a subsequent electric system on a large and medium carrier rocket.
The technical scheme of the invention is as follows:
A28V/270V composite energy system for a launch vehicle comprises a 28V instrument battery, a 270V high-voltage battery, a 270V hydrodynamic power supply, instrument bus energy management equipment, high-voltage bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power supply module, a power distribution module and a time sequence module;
the instrument power supply area consists of a 28V instrument battery, instrument bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power module, a power distribution module and a time sequence module, wherein the power module, the power distribution module and the time sequence module are deployed in an instrument cabin/box interval; the instrument power supply area is arranged in an instrument cabin/box section of the carrier rocket sublevel;
the 28V instrument battery is connected with the instrument bus energy management device through a cable, and the 28V instrument battery outputs DC 28V voltage.
The ground wireless power supply transmitting equipment transmits the electric energy to the wireless power supply receiving device in a wireless mode, the wireless power supply receiving device adjusts the voltage to DC 28V in a floating mode, and the electric energy is connected with the instrument bus energy management equipment through a cable;
the power module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and outputs a secondary power supply to load equipment by performing DC/DC conversion on an instrument bus through the internal power module;
the power distribution module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to load equipment through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the time sequence module of the instrument power supply area is connected with the high-voltage bus energy management equipment through an external bus bar, receives a 28V secondary power bus power supply, adopts a floating mode, and provides an initiating explosive device and an electromagnetic valve with an instrument bus through an electromagnetic relay switch or an MOS tube switch.
A power supply area consists of a 270V high-voltage battery, a 270V fluid power supply, high-voltage bus energy management equipment, a power supply module, a power distribution module and a time sequence module, wherein the power supply module, the power distribution module and the time sequence module are arranged in an instrument cabin/box section; the power supply area is arranged in the tail cabin of the carrier rocket sublevel;
the 270V high-voltage battery outputs a primary power bus of DC 270V voltage, primary power supply is provided for power equipment of an electric system on the rocket, a floating mode is adopted, 75 battery monomers are contained in the battery and connected in series, and a plurality of groups of 75 battery monomers connected in series are connected in parallel according to different capacities;
the 270V fluid power supply is powered by a carrier rocket engine to generate 270V high-voltage power supply output, and a floating mode is adopted;
the 270V high-voltage battery, the 270V hydrodynamic power supply and the high-voltage bus energy management equipment are connected through cables, and the DC 270V voltage is output; the instrument bus energy management equipment is connected with the high-voltage bus energy management equipment through an external bus bar, and the instrument bus energy management equipment outputs DC 28V voltage;
the power supply module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and outputs a secondary power supply to load equipment by performing DC/DC conversion on an instrument bus through the internal power supply module;
the power distribution module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to load equipment through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the time sequence module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V secondary power bus power supply, and provides an instrument bus for initiating explosive devices and electromagnetic valves through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the servo drive controller is connected with the high-voltage bus energy management equipment through a cable and receives a 270V high-voltage bus power supply.
Furthermore, a 28V instrument battery outputs a DC 28V voltage primary instrument bus to provide primary power supply for the instruments and equipment of the rocket-mounted electrical system, and a floating mode is adopted.
Furthermore, the instrument bus energy management device comprises a charging control module, a discharging control module and a central control module,
the charging control module acquires electric energy from the wireless power supply receiving device, converts the electric energy into proper battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize 28V standard battery charging management, monitors the single state of the battery, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharging control module provides a discharging interface of a 28V battery for a power supply bus, controls discharging of the battery pack, keeps stable fluctuation of bus voltage, and meanwhile ensures that the bus is in a disconnected state during transportation and storage to prevent the bus from being electrified;
the central control module monitors the bus voltage state, executes a control strategy, controls the charging control module and the discharging control module, and keeps the bus voltage stable by regulating the input power, the battery charging power and the battery discharging power to keep the load power demand.
Furthermore, the high-voltage bus energy management equipment comprises a charging control module, a discharging control module, a center control module and a high-voltage control module, adopts a floating mode,
the charging control module acquires electric energy from the instrument bus energy management equipment, converts the electric energy into proper battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize the charging management of a 270V standard battery, monitors the single state of the battery, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharge control module is used for providing a discharge interface of the 270V battery to the power supply bus, controlling the discharge of the battery pack, keeping the voltage of the bus stable in a smaller fluctuation range, and simultaneously ensuring that the bus is in a disconnected state during transportation and storage to prevent the bus from being electrified;
the central control module monitors the voltage state of the bus, executes a control strategy, controls the charging control module and the discharging control module, and keeps the bus voltage stable by regulating the input power, the battery charging power and the battery discharging power to keep the load power demand;
the high-voltage control module completes charging management on the high-voltage battery, realizes power distribution output of a 270V high-voltage bus, has a 28V voltage reduction conversion function and outputs a 28V power bus; the fluid power supply and the arrow high-voltage battery are connected in parallel inside the high-voltage module for output; the 28V power bus is generated by 270V high-voltage bus through isolated direct-current voltage conversion, the voltage of the bus is subjected to voltage stabilization control through the direct-current voltage conversion, and the positive end and the negative end of the power bus are isolated from the positive end and the negative end of the high-voltage bus.
Furthermore, the bus working voltage fluctuation within DC 28V +/-1V is output through primary instrument bus energy management, the voltage adaptive range of a load end is reduced, and the power supply quality is improved.
Further, the 270V high voltage bus is an unregulated bus, i.e. the bus voltage is not externally regulated.
Furthermore, the power module of the instrument power supply area carries out DC/DC conversion on the instrument bus to output a +15V/+5V/+3.3V secondary power supply.
Furthermore, a 270V fluid power supply can be provided by adopting a high-pressure kerosene liquid motor for power generation, starting power generation integrated equipment for generating power by an oxygen precompression pump of the engine and adopting a hydrogen turbine for power generation.
Furthermore, the power supply module of the power supply area carries out DC/DC conversion on the instrument bus to output a +15V/+5V/+3.3V secondary power supply.
Furthermore, the battery comprises 8 battery monomers which are connected in series, and a plurality of groups of 8 series-connected monomers are connected in parallel according to different capacities.
Compared with the prior art, the invention has the beneficial effects that:
(1) the direct-current 270V bus system is adopted, so that the line loss is obviously reduced, the weight of a power supply cable network on an arrow is reduced, the weight and the volume of a high-power motor are reduced, and the direct-current 270V bus system is suitable for primary power supply of a subsequent high-power electromechanical servo mechanism, power generation of an engine on the arrow, a high-power electric valve and driving motor equipment;
(2) the invention realizes that the power 28V secondary bus is formed by the isolation and voltage transformation of the 270V bus and is used for supplying power to the firearms and the 28V power supply load of the electromagnetic valve, and is effectively isolated from the 28V bus of the instrument;
(3) the rocket is respectively provided with a direct current 28V instrument battery and a direct current 270V power battery, the rocket adopts a fluid power supply to generate power (including hydrogen turbine power generation, kerosene liquid motor power generation and engine starting/power generation integration) and the 270V power battery to be output in a grid-connected mode, the 270V bus power supply on the rocket is provided, the weight of the battery is obviously reduced through autonomous power generation on the rocket, meanwhile, dozens of kW-level power supply power is provided for the electric load on the rocket, the energy guarantee is provided for the subsequent high-power electric load application on the rocket, and the foundation is laid for the subsequent multi-electric rocket application.
Drawings
FIG. 1 is a schematic diagram of an energy system according to the present invention;
FIG. 2 is a functional diagram of the bus power management of the instrument of the present invention;
fig. 3 is a functional diagram of the high-voltage bus power management of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The carrier rocket comprises different sublevels such as a core first level, a core second level, a core third level and a boosting level, energy system schemes of all sublevels are the same, and for a certain sublevel energy system architecture, the structure is shown in figure 1, wherein arrow-top equipment mainly comprises a 28V instrument battery, a 270V high-voltage battery, a 270V fluid power supply, instrument bus energy management equipment, high-voltage bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power supply module, a power distribution transmission line module, a time sequence module, a power supply transmission line and load equipment.
The above-mentioned devices are placed in the instrument bay/bay section and the tail bay of the launch vehicle substage, respectively.
The instrument power supply area is composed of a 28V instrument battery, an instrument bus energy management device, a wireless power supply receiving device, a wireless power supply transmitting device, a power supply module, a power distribution module and a time sequence module, wherein the power supply module, the power distribution module and the time sequence module are deployed in an instrument cabin/stage section.
The power supply area consists of a 270V high-voltage battery, a 270V fluid power supply, high-voltage bus energy management equipment, a power supply module, a power distribution module and a time sequence module, wherein the power supply module, the power distribution module and the time sequence module are arranged in an instrument cabin/stage section.
A28V instrument battery outputs a DC 28V voltage primary instrument bus to provide primary power supply for electrical system instrument equipment on the arrow, and a floating mode is adopted. The battery comprises 8 battery monomers which are connected in series, and a plurality of groups of 8 series-connected monomers are connected in parallel according to different capacities.
As shown in fig. 2, the 28V instrument cell is connected to the instrument bus energy management device via a cable, and the 28V instrument cell outputs DC 28V voltage.
The ground wireless power supply transmitting equipment transmits the electric energy to the wireless power supply receiving device in a wireless mode, the wireless power supply receiving device adjusts the voltage to be DC 28V in a floating mode, and the electric energy is connected with the instrument bus energy management equipment through a cable.
The functional topological structure of the instrument bus energy management device is shown in fig. 2, and the power management device consists of a charging control module, a discharging control module and a central control module and adopts a floating mode.
The functions realized by the functional modules are as follows:
the charging control module acquires power from the wireless power supply receiving device, converts the power into proper battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize 28V standard battery charging management, monitors the single state of the battery, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharge control module is used for providing a discharge interface of a 28V battery to a power supply bus, controlling the discharge of a battery pack, keeping the voltage of the bus stable in a smaller fluctuation range, and simultaneously ensuring that the bus is in a disconnected state during transportation and storage to prevent the bus from being electrified;
the central control module monitors the bus voltage state, executes a control strategy, controls the charging control module and the discharging control module, and keeps the bus voltage stable by regulating the input power, the battery charging power and the battery discharging power to keep the load power demand.
The bus working voltage fluctuation within DC 28V +/-1V is output through primary instrument bus energy management, the voltage adaptation range of a load end is reduced, and the power supply quality is improved.
The power module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable to receive a 28V instrument primary bus power supply, and the internal power module outputs +15V/+5V/+3.3V secondary power supply to other load equipment after DC/DC conversion is carried out on the instrument bus.
The power distribution module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to other load equipment through an internal switch (an electromagnetic relay switch or an MOS tube switch) in a floating mode.
The time sequence module of the instrument power supply area is connected with the high-voltage bus energy management equipment through an external bus bar, receives a 28V secondary power bus power supply, and provides an instrument bus to other load equipment (initiating explosive devices and electromagnetic valves) through an internal switch (an electromagnetic relay switch or an MOS tube switch) in a floating mode.
The 270V high-voltage battery outputs a DC 270V voltage primary power bus to provide primary power supply for power equipment of an electric system on an arrow, and a floating mode is adopted. The battery comprises 75 battery monomers which are connected in series, and a plurality of groups of 75 battery monomers which are connected in series are connected in parallel according to different capacities.
The 270V fluid power supply is powered by a carrier rocket engine to generate 270V high-voltage power supply output, a floating mode is adopted, the high-voltage kerosene liquid engine is adopted for power generation, and the engine oxygen precompression pump power generation and the hydrogen turbine power generation are carried out by starting power generation integrated equipment, and the power generation integrated equipment is collectively called as the fluid power supply. Generally, each substage of the launch vehicle uses a plurality of engines, and each engine is provided with a fluid power supply.
The 270V high-voltage battery, the fluid power supply and the high-voltage bus energy management equipment are connected through cables, and the DC 270V voltage is output; the instrument bus energy management equipment is connected with the high-voltage bus energy management equipment through an external bus bar, and the instrument bus energy management equipment outputs DC 28V voltage
The functional topological structure of the high-voltage bus energy management device is shown in fig. 3, and the power management device comprises a charging control module, a discharging control module, a central control module and a high-voltage control module and adopts a floating mode.
The functions realized by the functional modules are as follows:
the charging control module acquires power from the instrument bus energy management equipment, converts the power into appropriate battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize 270V standard battery charging management, monitors the single battery state, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharge control module is used for providing a discharge interface of the 270V battery to the power supply bus, controlling the discharge of the battery pack, keeping the voltage of the bus stable in a smaller fluctuation range, and simultaneously ensuring that the bus is in a disconnected state during transportation and storage to prevent the bus from being electrified;
the central control module monitors the bus voltage state, executes a control strategy, controls the charging control module and the discharging control module, and keeps the bus voltage stable by regulating the input power, the battery charging power and the battery discharging power to keep the load power demand.
The high-voltage control module completes charging management of the high-voltage battery, realizes power distribution output of a 270V high-voltage bus, and has a 28V voltage reduction conversion function to output a 28V power bus. And the fluid power supply and the arrow high-voltage battery are connected in parallel and output in the high-voltage module. The 28V power bus is generated by 270V high-voltage bus through isolated direct-current voltage conversion, the voltage of the bus is subjected to voltage stabilization control through the direct-current voltage conversion, and the positive end and the negative end of the power bus are isolated from the positive end and the negative end of the high-voltage bus.
The 270V high-voltage bus is an unregulated bus, i.e. the bus voltage is not subjected to external voltage stabilization control.
The power supply module of the power supply area is connected with the high-voltage bus energy management equipment through a cable to receive a 28V instrument primary bus power supply, and the internal power supply module outputs +15V/+5V/+3.3V and other secondary power supplies to other load equipment after DC/DC conversion is carried out on the instrument bus.
The power distribution module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to other load equipment through an internal switch (an electromagnetic relay switch or an MOS tube switch) in a floating mode.
The time sequence module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V secondary power bus power supply, and provides an instrument bus to other load equipment (initiating explosive devices and electromagnetic valves) through an internal switch (an electromagnetic relay switch or an MOS tube switch) in a floating mode.
The servo drive controller is connected with the high-voltage bus energy management equipment through a cable and receives a 270V high-voltage bus power supply.
The direct-current 270V bus system is adopted, so that the line loss is obviously reduced, the weight of a power supply cable network on the rocket is reduced, the weight and the volume of a high-power motor are reduced, and the direct-current 270V bus system is suitable for primary power supply of subsequent equipment such as a high-power electromechanical servo mechanism, rocket engine power generation, a high-power electric valve, a driving motor and the like;
according to the invention, fluid power generation and 270V power battery grid-connected output are adopted on the rocket, power supply of a 270V bus on the rocket is provided, the weight of the battery is obviously reduced through autonomous power generation on the rocket, the power supply capability of providing dozens of kW-level power supply for electrical loads on the rocket is provided, energy supply guarantee is provided for subsequent high-power electrical load application on the rocket, and a foundation is laid for subsequent multi-electric rocket application;
the invention adopts a sublevel independent application mode and a subarea power supply mode, cancels a sublevel power supply line, greatly reduces the power supply cables in the sublevel, and adopts a high-capacity rigid bus bar to replace the traditional copper cable, thereby effectively reducing the weight of a power supply transmission line;
the invention adopts the isolation transformation of the power 270V primary bus to form the power 28V secondary bus which is used for supplying power to 28V power supply loads such as initiating explosive devices, electromagnetic valves and the like, and forms electrical isolation with the 28V instrument bus, thereby preventing the interference generated when transient loads such as initiating explosive devices, electromagnetic valves and the like act from influencing instrument equipment;
according to the invention, the positive end and the negative end of the 28V instrument bus and the 270V high-voltage bus are isolated, so that the influence of interference generated during the transient action of a 270V high-power load on instrument equipment is prevented;
the invention realizes the charging of the battery on the arrow without going down the arrow on the ground, and the charging of the ground simultaneously charges the 28V bus battery and the 270V bus battery of the instrument through the isolation transformation; and the battery on the arrow integrates a charging management function, and the battery state is monitored in real time.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above, and therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention are within the protection scope of the present invention.
Claims (10)
1. A28V/270V composite energy system for a launch vehicle is characterized by comprising a 28V instrument battery, a 270V high-voltage battery, a 270V fluid power supply, instrument bus energy management equipment, high-voltage bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power module, a power distribution module and a time sequence module;
the instrument power supply area consists of a 28V instrument battery, instrument bus energy management equipment, a wireless power supply receiving device, wireless power supply transmitting equipment, a power module, a power distribution module and a time sequence module, wherein the power module, the power distribution module and the time sequence module are arranged in an instrument cabin/box interval; the instrument power supply area is arranged in an instrument cabin/box section of the carrier rocket sublevel;
the 28V instrument battery is connected with the instrument bus energy management equipment through a cable, and the 28V instrument battery outputs DC 28V voltage;
the ground wireless power supply transmitting equipment transmits the electric energy to the wireless power supply receiving device in a wireless mode, the wireless power supply receiving device adjusts the voltage to DC 28V in a floating mode, and the electric energy is connected with the instrument bus energy management equipment through a cable;
the power module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and outputs a secondary power supply to load equipment by performing DC/DC conversion on an instrument bus through the internal power module;
the power distribution module of the instrument power supply area is connected with the instrument bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to load equipment through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the time sequence module of the instrument power supply area is connected with the high-voltage bus energy management equipment through an external bus bar, receives a 28V secondary power bus power supply, and provides an initiating explosive device and an electromagnetic valve for an instrument bus through an electromagnetic relay switch or an MOS tube switch in a floating mode;
a power supply area consists of a 270V high-voltage battery, a 270V fluid power supply, high-voltage bus energy management equipment, a power supply module, a power distribution module and a time sequence module, wherein the power supply module, the power distribution module and the time sequence module are arranged in an instrument cabin/box section; the power supply area is arranged in the tail cabin of the carrier rocket sublevel;
the 270V high-voltage battery outputs a primary power bus of DC 270V voltage, primary power supply is provided for power equipment of an electric system on the rocket, a floating mode is adopted, 75 battery monomers are contained in the battery and connected in series, and a plurality of groups of 75 battery monomers connected in series are connected in parallel according to different capacities;
the 270V fluid power supply is powered by a carrier rocket engine to generate 270V high-voltage power supply output, and a floating mode is adopted;
the 270V high-voltage battery and the 270V fluid power supply are connected with the high-voltage bus energy management equipment through cables, and the DC 270V voltage is output; the instrument bus energy management equipment is connected with the high-voltage bus energy management equipment through an external bus bar, and the instrument bus energy management equipment outputs DC 28V voltage;
the power supply module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and outputs a secondary power supply to load equipment by performing DC/DC conversion on an instrument bus through the internal power supply module;
the power distribution module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V instrument primary bus power supply, and provides an instrument bus to load equipment through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the time sequence module of the power supply area is connected with the high-voltage bus energy management equipment through a cable, receives a 28V secondary power bus power supply, and provides an instrument bus for initiating explosive devices and electromagnetic valves through an electromagnetic relay switch or an MOS tube switch in a floating mode;
the servo drive controller is connected with the high-voltage bus energy management equipment through a cable and receives a 270V high-voltage bus power supply.
2. The 28V/270V hybrid energy system for a launch vehicle according to claim 1, wherein the 28V instrument battery outputs a DC 28V voltage primary instrument bus to provide primary power supply for the rocket electrical system instrument equipment in a floating manner.
3. The 28V/270V hybrid energy system for a launch vehicle of claim 1, wherein said instrumentation bus energy management device comprises a charging control module, a discharging control module, and a central control module,
the charging control module acquires electric energy from the wireless power supply receiving device, converts the electric energy into proper battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize 28V standard battery charging management, monitors the single state of the battery, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharging control module provides a discharging interface of the 28V battery to the power supply bus, controls discharging of the battery pack, keeps stable fluctuation of bus voltage, and simultaneously ensures that the bus is in a disconnected state during transportation and storage to prevent the bus from being electrified;
the central control module monitors the voltage state of the bus, executes a control strategy, controls the charging control module and the discharging control module, and keeps the power consumption requirement of the load by adjusting the input power, the battery charging power and the battery discharging power so as to keep the voltage of the bus stable.
4. The 28V/270V hybrid power system for a launch vehicle of claim 1 wherein said high voltage bus power management device comprises a charging control module, a discharging control module, a central control module and a high voltage control module, in a floating manner,
the charging control module acquires electric energy from the instrument bus energy management equipment, converts the electric energy into proper battery charging voltage, adopts a constant-current and constant-voltage charging strategy to realize 270V standard battery charging management, monitors the single battery state, performs balance control on the unbalanced phenomenon of the battery and predicts the service life of the battery;
the discharge control module is used for providing a discharge interface of a 270V battery to a power supply bus, controlling discharge of a battery pack, keeping the voltage of the bus stable in a small fluctuation range, ensuring the bus to be in a disconnected state during transportation and storage and preventing the bus from being electrified;
the central control module monitors the voltage state of the bus, executes a control strategy, controls the charging control module and the discharging control module, and keeps the bus voltage stable by regulating input power, battery charging power and battery discharging power to keep the power demand of the load;
the high-voltage control module completes charging management on the high-voltage battery, realizes power distribution output of a 270V high-voltage bus, has a 28V voltage reduction conversion function and outputs a 28V power bus; the fluid power supply and the arrow high-voltage battery are connected in parallel inside the high-voltage module for output; the 28V power bus is a 270V high-voltage bus generated by isolated direct-current voltage conversion, the bus voltage is subjected to voltage stabilization control through the direct-current voltage conversion, and the positive end and the negative end of the power bus and the positive end and the negative end of the high-voltage bus are isolated.
5. The 28V/270V hybrid energy system for a launch vehicle of claim 3, wherein the voltage adaptation range to the load side is reduced and the power supply quality is improved by outputting bus operating voltage fluctuations within DC 28V ± 1V through primary instrument bus energy management.
6. The 28V/270V hybrid energy system for a launch vehicle of claim 4, wherein the 270V high voltage bus is an unregulated bus, i.e., no external voltage regulation of the bus voltage is performed.
7. The 28V/270V hybrid energy system for a launch vehicle of claim 1, wherein the power module of the instrument power supply area performs DC/DC conversion on the instrument bus to output +15V/+5V/+3.3V secondary power.
8. The 28V/270V hybrid energy system for a launch vehicle of claim 1, wherein the 270V hydrodynamic power source can be generated by a high-pressure kerosene hydraulic motor, and is provided by starting a power generation integrated device to generate power by an oxygen pre-pressure pump of the engine and by a hydrogen turbine.
9. The 28V/270V hybrid energy system for a launch vehicle of claim 1, wherein the power module of the power supply area performs DC/DC conversion on the instrument bus to output +15V/+5V/+3.3V secondary power.
10. The 28V/270V hybrid energy system for a launch vehicle of claim 2, wherein said battery comprises 8 battery cells connected in series, and wherein multiple groups of 8 battery cells connected in series are connected in parallel according to different capacities.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006013600A2 (en) * | 2004-08-04 | 2006-02-09 | Universita' Degli Studi Di Roma 'la Sapienza' | Distributed system for electrically supplying a power bus and method of controlling power supply using such system |
| CN108494072A (en) * | 2018-05-30 | 2018-09-04 | 南京麦格安倍电气科技有限公司 | A kind of modularization accumulator aviation startup power supply system |
| CN110932349A (en) * | 2019-11-29 | 2020-03-27 | 北京宇航系统工程研究所 | Energy efficient topological system on arrow based on wireless power supply |
| CN111769766A (en) * | 2020-06-17 | 2020-10-13 | 新乡航空工业(集团)有限公司 | Miniaturized aviation high-voltage motor controller |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7701082B2 (en) * | 2006-10-30 | 2010-04-20 | Honeywell International Inc. | Aerospace electrical power DC subsystem configuration using multi-functional DC/DC converter |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006013600A2 (en) * | 2004-08-04 | 2006-02-09 | Universita' Degli Studi Di Roma 'la Sapienza' | Distributed system for electrically supplying a power bus and method of controlling power supply using such system |
| CN108494072A (en) * | 2018-05-30 | 2018-09-04 | 南京麦格安倍电气科技有限公司 | A kind of modularization accumulator aviation startup power supply system |
| CN110932349A (en) * | 2019-11-29 | 2020-03-27 | 北京宇航系统工程研究所 | Energy efficient topological system on arrow based on wireless power supply |
| CN111769766A (en) * | 2020-06-17 | 2020-10-13 | 新乡航空工业(集团)有限公司 | Miniaturized aviation high-voltage motor controller |
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