CN115483963B - Architecture of high-integration-level satellite comprehensive platform - Google Patents
Architecture of high-integration-level satellite comprehensive platform Download PDFInfo
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- CN115483963B CN115483963B CN202211083082.1A CN202211083082A CN115483963B CN 115483963 B CN115483963 B CN 115483963B CN 202211083082 A CN202211083082 A CN 202211083082A CN 115483963 B CN115483963 B CN 115483963B
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- 238000012545 processing Methods 0.000 claims abstract description 74
- 230000005540 biological transmission Effects 0.000 claims abstract description 36
- 238000005259 measurement Methods 0.000 claims abstract description 30
- 238000001514 detection method Methods 0.000 claims abstract description 9
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 4
- 238000006243 chemical reaction Methods 0.000 claims abstract description 4
- 230000003993 interaction Effects 0.000 claims abstract description 4
- 238000007726 management method Methods 0.000 claims description 47
- 238000009826 distribution Methods 0.000 claims description 16
- 238000004891 communication Methods 0.000 claims description 15
- 238000004364 calculation method Methods 0.000 claims description 9
- 230000003044 adaptive effect Effects 0.000 claims description 7
- 230000003321 amplification Effects 0.000 claims description 5
- 230000010354 integration Effects 0.000 claims description 5
- 238000003199 nucleic acid amplification method Methods 0.000 claims description 5
- 238000013523 data management Methods 0.000 claims description 3
- 238000013500 data storage Methods 0.000 claims description 3
- 230000036541 health Effects 0.000 claims description 3
- 238000003860 storage Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000005070 sampling Methods 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 2
- 238000011438 discrete method Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
- G01S19/10—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing dedicated supplementary positioning signals
- G01S19/12—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing dedicated supplementary positioning signals wherein the cooperating elements are telecommunication base stations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18517—Transmission equipment in earth stations
-
- 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
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Abstract
The invention discloses a framework of a high-integration satellite comprehensive platform, wherein an interface processing board is respectively in bidirectional data interaction with a core processing board, a power subsystem and a front-end transceiver component; the interface processing board distributes power for the core processing board, realizes interface conversion and configuration of the core processing board, configures pins of hardware input and output of the satellite comprehensive platform in the core processing board, and realizes modularization of corresponding configuration software; the interface processing board detects and controls a power subsystem, and the power subsystem distributes power to the interface processing board; the interface processing board distributes power for the front-end transceiver component, converts and interconnects detection and control signals between the front-end transceiver component and the core processing board, and provides receiving intermediate frequency sampling of measurement and control data transmission, and the measurement and control data transmission transmitting intermediate frequency modulation output. The invention reduces the manufacturing cost and the launching cost of the satellite, and the integral satellite comprehensive platform can realize one-stop production.
Description
Technical Field
The invention relates to the technical field of satellite platforms, in particular to a framework of a high-integration-level satellite comprehensive platform.
Background
The satellite platform electronic is used as an important part of a satellite, and various functions such as power supply and distribution, telemetry, remote control, thermal control, propulsion control, satellite and rocket separation control, initiating explosive device control and the like of the whole satellite are realized. With the progress of satellite technology and the continuous expansion of satellite applications, the space tasks to be performed by satellite products are increasingly complex, and the challenges in satellite electronic system design and implementation are becoming more and more serious.
In the prior art, currently, a discrete method is mostly adopted to realize each module of a satellite electronic platform, and the modules are stacked to form the satellite integrated electronic platform. The satellite electronic platform realized by the discrete method has low integration level, is difficult to reduce the volume and the power consumption, is difficult to reduce the weight and is complicated in coordination and joint adjustment; each module has power supply processing and control, power supply load distribution is unbalanced, and good overall power supply efficiency is difficult. The modules are connected by sockets or wires, so that the number of wires is large; the productivity is low, and it is difficult to adapt to the requirement of rapidly arranging satellites.
It is therefore desirable to design a highly integrated satellite platform that is a direction of further improvement.
Disclosure of Invention
In order to solve the above technical problems, the present invention provides an architecture of a high-integration satellite integrated platform, where the satellite integrated platform includes: the interface processing board is respectively in bidirectional data interaction with the core processing board, the power subsystem and the front-end transceiver component; the interface processing board distributes power for the core processing board, realizes interface conversion and configuration of the core processing board, and configures pins of hardware input and output of the satellite comprehensive platform in the core processing board pair, and realizes modularization of corresponding configuration software; the interface processing board detects and controls a power subsystem, and the power subsystem distributes power to the interface processing board; the interface processing board distributes power for the front-end transceiver component, converts and interconnects detection and control signals between the front-end transceiver component and the core processing board, provides receiving intermediate frequency sampling of measurement and control data transmission, and transmits intermediate frequency modulation output of the measurement and control data transmission.
Preferably, the core processing board comprises a satellite-borne computer, a satellite-borne communication machine, a baseband SOC system and an internal secondary power supply, wherein the satellite-borne computer integrates power distribution switch control, satellite management, attitude and orbit control calculation and intelligent calculation, and at least realizes the functions of power supply and distribution control, data management, time management, autonomous task management, health management, thermal control acquisition, attitude and orbit control calculation and management, attitude and orbit control sensor information acquisition, actuator driving and an on-board intelligent algorithm; the satellite-borne communication machine establishes communication between a satellite body and other satellites or ground stations and realizes functions of remote control receiving, telemetry transmitting, data storage and data transmission; and the baseband SOC system is respectively and electrically interacted with the satellite-borne computer and the satellite-borne communication machine, and the internal secondary power supply is used for supplying power to the baseband SOC system in an auxiliary way.
Preferably, the front-end transceiver component comprises a measurement and control data transmission receiving circuit, a measurement and control data transmission transmitting circuit and a GNSS receiving circuit, wherein the measurement and control data transmission receiving circuit receives an air signal received by a receiving antenna, performs low-noise amplification, then converts the air signal into an intermediate frequency, amplifies the intermediate frequency to an adaptive output level, outputs the intermediate frequency to the interface processing board and samples the intermediate frequency; the measurement and control data transmission circuit receives measurement and control data transmission signals which are modulated by the interface processing board, up-converts the signals to air frequency, amplifies the power to enough transmission power and outputs the power to a satellite transmission antenna; and the GNSS receiving circuit receives GPS or Beidou navigation positioning signals received by the receiving GNSS antenna, performs low-noise amplification, then converts the signals into intermediate frequency, amplifies the signals to an adaptive output level, outputs the signals to the interface processing board and samples the signals.
Preferably, the power subsystem comprises a power management module and a power distribution management module, wherein the power management module comprises solar cell array management and storage battery pack management, and the solar cell array management comprises solar energy shunt management, battery charge and discharge management, battery temperature detection and control management; the power distribution management module realizes external power supply of energy sources, converts bus voltage into voltages required by other circuit modules, and simultaneously controls the bus voltage output to the thermal control system.
Preferably, the baseband SOC system comprises an SOC chip, a measurement and control baseband and a GNSS baseband, wherein the SOC chip collects data signals transmitted by an interface processing board, converts and outputs the data signals to a satellite-borne computer and a satellite-borne communication machine to execute related functions; the measurement and control baseband is electrically connected with the measurement and control data transmission receiving circuit and the measurement and control data transmission transmitting circuit; the GNSS baseband is electrically connected with the GNSS receiving circuit.
Preferably, the power subsystem amplifies the input power to the rated output power while leaving a margin of 0.8-1.2 dB.
Preferably, the core processing board is electrically connected with the power subsystem, the power subsystem is used for distributing power to the core processing board, and the core processing board monitors a circuit of the power subsystem and performs adjustment management.
Compared with the prior art, the invention has the following beneficial effects:
(1) The integrated satellite integrated platform has a simple integral structure, interfaces of various parts of the satellite are adapted through the interface processing board, the core framework of the main body of the core processing board connected with the interface processing board is stable, the requirements of a power subsystem and the interfaces can be kept to be minimized, the minimization of the volume, the weight and the power consumption is realized, the high-integration satellite electronic platform is realized through the single chip scheme of the SOC chip, meanwhile, the power subsystem and the interface processing board are adapted to the power distribution of the satellite and the customization requirements of the interfaces, the volume, the weight and the size are reduced, the producibility of the satellite is improved, the manufacturing cost and the transmitting cost of the satellite are reduced, and the integrated satellite integrated platform can realize one-stop production and avoid coordination and joint adjustment of multiple suppliers of multiple enterprises;
(2) The invention can internally pinch various buses and low-frequency and low-speed wires such as power supply, control, detection and the like which are backed up and output through the power subsystem, thereby reducing wire interweaving of the whole satellite assembly, and the functional circuit of the interface processing board, the core processing board and the front-end receiving and transmitting assembly is changed into a circuit backup design by a module backup design, so that the area and the space can be fully utilized.
Drawings
Fig. 1 is an overall flow diagram of the present invention.
Fig. 2 is a flow chart of the front-end transceiver module of the present invention.
FIG. 3 is a flow chart of the power subsystem of the present invention.
Detailed Description
The invention will be further described with reference to the drawings and detailed description.
In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "head," "tail," and the like are used as an orientation or positional relationship based on that shown in the drawings, merely to facilitate description of the invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "connected," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1 to 3, the satellite integrated platform includes: the interface processing board is respectively in bidirectional data interaction with the core processing board, the power subsystem and the front-end transceiver component;
the interface processing board is used for distributing power to the core processing board, realizing interface conversion and configuration of the core processing board, configuring pins of hardware input and output of the satellite comprehensive platform in the core processing board, and realizing modularization of corresponding configuration software; the core processing board comprises a satellite-borne computer, a satellite-borne communication machine, a baseband SOC system and an internal secondary power supply, wherein the satellite-borne computer integrates power distribution switch control, satellite management, attitude and orbit control calculation and intelligent calculation, at least realizes the functions of power supply and distribution control, data management, time management, autonomous task management, health management, thermal control acquisition, attitude and orbit control calculation and management, attitude and orbit control sensor information acquisition, actuator driving and an on-board intelligent algorithm, is used for configuring the working point of a power amplifier tube, and firstly electrifies a grid according to the requirement of the power amplifier tube on the power supply time sequence, and then electrifies a drain;
the satellite-borne communication machine establishes communication between a satellite body and other satellites or ground stations, realizes functions of remote control receiving, telemetry transmitting, data storage and data transmission, is electrically connected with the power amplifier, realizes unidirectional transmission signals, absorbs reflected power during reflection, and avoids the action of reflected power and the action of the power amplifier, thereby playing a role in protecting the power amplifier;
the baseband SOC system is respectively and electrically interacted with the spaceborne computer and the spaceborne communication machine, the internal secondary power supply is used for supplying power to the baseband SOC system in an auxiliary mode, and concretely, the baseband SOC system comprises an SOC chip, a measurement and control baseband and a GNSS baseband, the SOC chip collects data signals transmitted by the interface processing board, converts and outputs the data signals to the spaceborne computer and the spaceborne communication machine, and executes related functions; the measurement and control baseband is electrically connected with the measurement and control data transmission receiving circuit and the measurement and control data transmission transmitting circuit; the GNSS baseband is electrically connected with the GNSS receiving circuit.
The interface processing board detects and controls a power supply subsystem, the power supply subsystem distributes power to the interface processing board, and the power supply subsystem amplifies input power to rated output power while leaving 0.8-1.2 dB of margin; the power subsystem comprises a power management module and a power distribution management module, wherein the power management module comprises solar cell array management and storage battery pack management, and the solar cell array management comprises solar energy shunt management, battery charge and discharge management, battery temperature detection and control management; the power distribution management module realizes external power supply of energy sources, converts bus voltage into voltage required by other circuit modules, controls the bus voltage output to the thermal control system, and the power subsystem performs backup output on various buses and low-frequency low-speed wiring such as power supply, control, detection and the like, so that wire interweaving of the whole satellite assembly is reduced; the functional circuit backup design of the interface processing board, the core processing board and the front-end receiving and transmitting component is changed into a circuit backup design, so that the area and the space can be fully utilized.
The interface processing board distributes power for the front-end transceiver component, converts and interconnects detection and control signals between the front-end transceiver component and the core processing board, provides receiving intermediate frequency samples of measurement and control data transmission, and transmits intermediate frequency modulation output of the measurement and control data transmission; the measurement and control data transmission circuit receives measurement and control data transmission signals which are modulated by the interface processing board, up-converts the signals to air frequency, amplifies the power to enough transmission power and outputs the power to a satellite transmission antenna; the GNSS receiving circuit receives GPS or Beidou navigation positioning signals received by the GNSS antenna, performs low-noise amplification, then converts the GPS or Beidou navigation positioning signals into intermediate frequency, amplifies the intermediate frequency to an adaptive output level, outputs the intermediate frequency to the interface processing board and samples the intermediate frequency, the GNSS receiving circuit is connected with the GNSS antenna to realize accurate positioning and accurate time synchronization of satellite positions, and simultaneously provides GPS/BDS positioning data and UTC time for the satellite comprehensive platform.
According to the invention, the interface processing board is adapted to the requirements of different satellites on interfaces, so that the interfaces of all the components of the satellites are adapted, the core processing board main body connected with the interface processing board is stable, the requirements of a power subsystem and the interfaces can be kept to be minimized, the minimization of the volume, the weight and the power consumption is realized, the core processing board realizes a satellite electronic platform with high integration through a single chip scheme of an SOC chip, meanwhile, the power subsystem and the interface processing board are adapted to the power distribution of the satellites and the customization requirements of the interfaces, the volume, the weight and the size are reduced, the producibility of the satellites is improved, the manufacturing cost and the transmitting cost of the satellites are reduced, and the whole satellite comprehensive platform can realize one-stop production and avoid coordination and joint adjustment of multiple suppliers of multiple enterprises.
The above-described embodiments are only preferred embodiments of the present invention and should not be construed as limiting the scope of the invention, and thus, modifications, equivalent variations, improvements, etc. made in accordance with the claims of the present invention still fall within the scope of the invention.
Claims (3)
1. A high integration satellite integrated platform, the satellite integrated platform comprising: the interface processing board is respectively in bidirectional data interaction with the core processing board, the power subsystem and the front-end transceiver component; the interface processing board distributes power for the core processing board, realizes interface conversion and configuration of the core processing board, and configures pins of hardware input and output of the satellite comprehensive platform in the core processing board pair, and realizes modularization of corresponding configuration software; the interface processing board detects and controls a power subsystem, and the power subsystem distributes power to the interface processing board; the interface processing board distributes power for the front-end transceiver component, converts and interconnects detection and control signals between the front-end transceiver component and the core processing board, provides receiving intermediate frequency samples for measuring and controlling data transmission, and transmits intermediate frequency modulation output for measuring and controlling data transmission;
the core processing board comprises a satellite-borne computer, a satellite-borne communication machine, a baseband SOC system and an internal secondary power supply, wherein the satellite-borne computer integrates power distribution switch control, satellite management, attitude and orbit control calculation and intelligent calculation, and at least realizes the functions of power supply and distribution control, data management, time management, autonomous task management, health management, thermal control acquisition, attitude and orbit control calculation and management, attitude and orbit control sensor information acquisition, actuator driving and an on-board intelligent algorithm; the satellite-borne communication machine establishes communication between a satellite body and other satellites or ground stations and realizes functions of remote control receiving, telemetry transmitting, data storage and data transmission; the baseband SOC system is respectively and electrically interacted with the satellite-borne computer and the satellite-borne communication machine, and the internal secondary power supply is used for supplying power to the baseband SOC system in an auxiliary way;
the front-end transceiver component comprises a measurement and control data transmission receiving circuit, a measurement and control data transmission transmitting circuit and a GNSS receiving circuit, wherein the measurement and control data transmission receiving circuit receives an air signal received by a receiving antenna, performs low-noise amplification, then converts the air signal into an intermediate frequency, amplifies the intermediate frequency to an adaptive output level, outputs the adaptive output level to the interface processing board and samples the adaptive output level; the measurement and control data transmission circuit receives measurement and control data transmission signals which are modulated by the interface processing board, up-converts the signals to air frequency, amplifies the power to enough transmission power and outputs the power to a satellite transmission antenna; the GNSS receiving circuit receives GPS or Beidou navigation positioning signals received by the receiving GNSS antenna, performs low-noise amplification, then converts the signals into intermediate frequency, amplifies the signals to an adaptive output level, outputs the signals to the interface processing board and samples the signals;
the power subsystem comprises a power management module and a power distribution management module, wherein the power management module comprises solar cell array management and storage battery pack management, and the solar cell array management comprises solar energy shunt management, battery charge and discharge management, battery temperature detection and control management; the power distribution management module realizes external power supply of energy sources, converts bus voltage into voltages required by other circuit modules, and simultaneously controls the bus voltage output to the thermal control system;
the baseband SOC system comprises an SOC chip, a measurement and control baseband and a GNSS baseband, wherein the SOC chip collects data signals transmitted by an interface processing board, converts and outputs the data signals to a satellite-borne computer and a satellite-borne communication machine to execute related functions; the measurement and control baseband is electrically connected with the measurement and control data transmission receiving circuit and the measurement and control data transmission transmitting circuit; the GNSS baseband is electrically connected with the GNSS receiving circuit.
2. The high integration satellite platform according to claim 1, wherein: the power subsystem amplifies the input power to the rated output power while leaving a margin of 0.8-1.2 dB.
3. The high integration satellite platform according to claim 1, wherein: the core processing board is electrically connected with the power subsystem, the power subsystem is used for distributing power to the core processing board, and the core processing board monitors a circuit of the power subsystem and performs adjustment management.
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| CN202211083082.1A CN115483963B (en) | 2022-09-06 | 2022-09-06 | Architecture of high-integration-level satellite comprehensive platform |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201774643U (en) * | 2009-09-04 | 2011-03-23 | 北京天航信民航通信网络发展有限公司 | Satellite network integrated service access device |
| CN108153183A (en) * | 2017-12-05 | 2018-06-12 | 山东航天电子技术研究所 | Integrated Electronic System on a kind of high functional density star of microminiature |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20070029446A1 (en) * | 2005-05-02 | 2007-02-08 | Mosher Todd J | Modular platform architecture for satellites |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201774643U (en) * | 2009-09-04 | 2011-03-23 | 北京天航信民航通信网络发展有限公司 | Satellite network integrated service access device |
| CN108153183A (en) * | 2017-12-05 | 2018-06-12 | 山东航天电子技术研究所 | Integrated Electronic System on a kind of high functional density star of microminiature |
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