CN106803770A - Satellite-payload-oriented control and processing system - Google Patents
Satellite-payload-oriented control and processing system Download PDFInfo
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- CN106803770A CN106803770A CN201611113840.4A CN201611113840A CN106803770A CN 106803770 A CN106803770 A CN 106803770A CN 201611113840 A CN201611113840 A CN 201611113840A CN 106803770 A CN106803770 A CN 106803770A
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- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005510 radiation hardening Methods 0.000 description 2
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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
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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
- H04B7/18523—Satellite systems for providing broadcast service to terrestrial stations, i.e. broadcast satellite service
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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
- H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
- H04B7/18532—Arrangements for managing transmission, i.e. for transporting data or a signalling message
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/004—Arrangements for detecting or preventing errors in the information received by using forward error control
- H04L1/0056—Systems characterized by the type of code used
- H04L1/0057—Block codes
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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
- 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
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Abstract
The invention provides a satellite payload control and processing system, which comprises a power module, a first control module, a second control module, a main processing module, a first preprocessing module, a second preprocessing module and a third preprocessing module, wherein the power module is used for converting a 28V primary power supply into a positive 5V power supply to be used by other functional modules and realizing cold and hot switching according to an external instruction, the first control module and the second control module are used for controlling and realizing the satellite payload control and processing system, the main processing module is used for carrying out comprehensive processing and cold and hot backup on digital signals, and the first preprocessing module, the second preprocessing module and the third preprocessing module are used for carrying out preprocessing of intermediate frequency signals and hot backup. The invention has higher reliability and radiation resistance index, stronger single event effect resistance and single event effect protection function, realizes the great reduction of volume and power consumption under the same function, supports a real-time operating system and various load common communication interfaces and control interfaces, and has the functions of control, communication, remote measurement, redundancy backup, application software uploading and the like.
Description
Technical field
The invention belongs to aerospace field, in particular it relates to one kind is towards Satellite Payloads control and processing system.
Background technology
Patent publication No. is that the Chinese invention patent of CN103744754A (publication date is on April 23rd, 2014) discloses one
Plant the parallel board computer system of radiation hardening and its application method.The method passes through three pieces of DSP (Digital Signal Processing) cores
Piece and four pieces of FPGA (field programmable gate array) chips are realized.The system is by a system control unit and three identical
System is constituted, and the system control unit realizes that each subsystem is made up of DSP and one piece of FPGA on one piece of FPGA,
And be connected with system control unit.The system uses the structure of " two Jia parallel backs up ", two spaceborne of DSP parallel processings
Business, used as backup, when unrecoverable failure occurs in the DSP of concurrent working, backup DSP replaces failure DSP to another DSP.
The shortcoming of the method is mainly and there is single-point.The invention implement the parallel board computer system of radiation hardening as shown in Fig. 2
System control unit is single-point, so as to reduce the reliability of whole system.
Patent publication No. is that the Chinese invention patent of CN103473156A (publication date is on December 25th, 2013) is disclosed
A kind of spaceborne computer three-level Hot Spare fault-tolerance approach based on real time operating system.The method is based on the star of real time operating system
The machine Hot Spare fault-tolerance approach of computer three is carried, three computers equipped with identical real time operating system are built first.In each control
In cycle processed, every unit all obtains the data of other two machine by the data exchange between three machines.Then according to the machine and separately
Totally three kinds of situations are compared for one machine, the machine and the 3rd machine, another machine and the 3rd machine, further according to comparing result whether one
Cause, whether the factors such as whether reset, " cutting machine command word " effective occurred with reference to unit, set the machine whether the mark of health.
Three per-unit synchronous operations, the external output control state of three machines is identical, and final external output is responsible for by when airliner.In failure
During treatment, because three units run simultaneously, state need not be again obtained when airliner switches, so failure recovery time
Short, real-time is high, and system control does not exist gap in handoff procedure, and system control can realize system with smooth transition
Autonomous Reconfiguration.The method it is main from software respective to illustrating the fault-tolerance approach of spaceborne computer.
The content of the invention
For defect of the prior art, controlled and treatment towards Satellite Payloads it is an object of the invention to provide one kind
System, it has reliability and radioresistance index higher, is protected with stronger anti-single particle effect capability and single particle effect
Protective function, realizes greatly reducing for equal function lower volume and power consumption, supports that real time operating system and various load are conventional logical
Letter interface, control interface, possess control, communication, remote measurement, redundancy backup, the function such as note in application software.
According to an aspect of the present invention, there is provided towards Satellite Payloads control and processing system, its feature exists one kind
In it includes：
Power module, uses and according to outside for 28V primary power sources to be converted into positive 5V power supplys for other functions module
Cold and hot switching is realized in instruction, and the inside of the power module is Redundancy Design；
First control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
The control realization of system；
Second control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
The control realization of system；
Main processing block, is connected with first control module, the second control module, the synthesis for carrying out data signal
Treatment and cold and hot backup；
First pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, first pretreatment module is made up of a DSP circuit and an AD circuit；
Second pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, second pretreatment module is made up of a DSP circuit and an AD circuit；
3rd pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, the 3rd pretreatment module is made up of a DSP circuit and an AD circuit.
Preferably, the circuit module includes the first relay, the second relay, the 3rd relay, the 4th relay, the
Five relays, the 6th relay, the first wave filter, the second wave filter, the 3rd wave filter, a DC/DC modules, the 2nd DC/DC
Module, the 3rd DC/DC modules, the 4th DC/DC modules, the 5th DC/DC modules, the first relay and the first wave filter, the 3rd filter
Ripple device is connected, and the second relay is connected with the second wave filter, the 3rd wave filter, the first wave filter and a DC/DC modules, the 3rd
DC/DC modules are connected, and the second wave filter is connected with the 2nd DC/DC modules, the 4th DC/DC modules, a DC/DC modules, second
DC/DC modules are connected with the 3rd relay respectively, and the 3rd relay is connected with the 4th relay, the 4th relay and described first
Control module, the second control module are connected, and the 3rd DC/DC modules, the 4th DC/DC modules are connected with the 5th relay respectively, the
Five relays are connected with the 6th relay, and the 6th relay is connected with the main processing block, the 3rd wave filter and the 5th DC/DC
Module is connected, and the 5th DC/DC modules are connected with first pretreatment module, the second pretreatment module, the 3rd pretreatment module.
Preferably, first control module includes a CPU, the first SRAM module, a PROM modules, first
FLASH modules, the first clock module, the first Bus isolation module, the first CAN, a LVDS buses, an OC output
Control module, the first remote measurement amount receiver module, the first command output module, when the first SRAM module, a PROM modules, first
Clock module, a FLASH modules, the first Bus isolation module are connected with a CPU respectively, the first Bus isolation module and first
CAN, a LVDS buses, OC output control module, the first remote measurement amount receiver module, first command output module
It is connected.
Preferably, second control module includes the 2nd CPU, the second SRAM module, the 2nd PROM modules, second
FLASH modules, second clock module, the second Bus isolation module, the second CAN, the 2nd LVDS buses, the 2nd OC output
Control module, the second remote measurement amount receiver module, the second command output module, when the second SRAM module, the 2nd PROM modules, second
Clock module, the 2nd FLASH modules, the second Bus isolation module are connected with the 2nd CPU respectively, the second Bus isolation module and second
CAN, the 2nd LVDS buses, the 2nd OC output control module, the second remote measurement amount receiver module, the second command output module
It is connected.
Preferably, a guiding software is respectively equipped with a CPU and the 2nd CPU, the guiding software is responsible for setting
Standby hardware initialization, power-on self-test, data transmission subsystem sum pipe compunication interaction, according to guiding mode of operation and Star Service meter
The instruction of calculation machine is uploaded, stored, bootload.
Preferably, the main processing block includes FPGA, the first DSP circuit, the 3rd SRAM module, the 3rd PROM modules,
FPGA is connected with the first DSP circuit, and the first DSP circuit is connected with the 3rd SRAM module, the 3rd PROM modules.
Compared with prior art, the present invention has following beneficial effect：The present invention has reliability and anti-spoke higher
Index is penetrated, wherein reliability can reach for 3 year ends 0.995；Radioresistance index is TID >=100kRad (Si), with stronger anti-list
Particle effect ability and single particle effect defencive function, realize greatly reducing for equal function lower volume and power consumption, support real
When operating system and various load often use communication interface, control interface, possess control, communication, remote measurement, redundancy backup, using soft
The function such as note on part, unit integral data is calculated and signal handling capacity, is aimed at medium and low earth orbit satellites payload and is provided solution party
Case, to reach in middle low earth orbital environment efficiently and reliably each resource of management and control payload.
Brief description of the drawings
The detailed description made to non-limiting example with reference to the following drawings by reading, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the structural representation controlled towards Satellite Payloads with processing system of the invention.
Fig. 2 is the present invention towards Satellite Payloads control and the composition frame chart of processing system.
Fig. 3 is the structural representation of power module of the invention.
Fig. 4 is the structural representation of the first control module of the invention.
Fig. 5 is the structural representation of the second control module of the invention.
Fig. 6 is the structural representation of main processing block of the invention.
Fig. 7 is the frame diagram of guiding software of the invention.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in Fig. 1 and Fig. 3 to Fig. 7, the present invention includes towards Satellite Payloads control with processing system：
Power module, uses and according to outside for 28V primary power sources to be converted into positive 5V power supplys for other functions module
Cold and hot switching is realized in instruction, and the inside of the power module is Redundancy Design；
First control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
The control realization of system；
Second control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
The control realization of system；
Main processing block, is connected with first control module, the second control module, the synthesis for carrying out data signal
Treatment and cold and hot backup, the main processing block can be switched by power supply；
First pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, first pretreatment module is made up of DSP (Digital Signal Processing) circuit and AD (analog-to-digital conversion) circuit；
Second pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, second pretreatment module is made up of a DSP circuit and an AD circuit；
3rd pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out heat
Backup, the 3rd pretreatment module is made up of a DSP circuit and an AD circuit.
The circuit module includes the first relay, the second relay, the 3rd relay, the 4th relay, the 5th relay
Device, the 6th relay, the first wave filter, the second wave filter, the 3rd wave filter, DC/DC (DC-DC) module, second
DC/DC modules, the 3rd DC/DC modules, the 4th DC/DC modules, the 5th DC/DC modules, the first relay and the first wave filter,
Three wave filters are connected, and the second relay is connected with the second wave filter, the 3rd wave filter, the first wave filter and a DC/DC modules,
3rd DC/DC modules are connected, and the second wave filter is connected with the 2nd DC/DC modules, the 4th DC/DC modules, a DC/DC modules,
2nd DC/DC modules are connected with the 3rd relay respectively, and the 3rd relay is connected with the 4th relay, the 4th relay with it is described
First control module, the second control module be connected, the 3rd DC/DC modules, the 4th DC/DC modules respectively with the 5th relay phase
Even, the 5th relay is connected with the 6th relay, and the 6th relay is connected with the main processing block, the 3rd wave filter and the 5th
DC/DC modules are connected, the 5th DC/DC modules and first pretreatment module, the second pretreatment module, the 3rd pretreatment module
It is connected, the circuit module realizes cold and hot switching by the opening and closing of each relay.
First control module includes a CPU (central processing unit), a SRAM (static RAM)
Module, PROM (programmable read only memory) module, FLASH (animation) module, the first clock module, first
Bus isolation module, CAN (controller local area network) bus, LVDS (low-voltage differential signal) bus, an OC
(open-collector gate) door output control module, the first remote measurement amount receiver module, the first command output module, a SRAM moulds
Block, a PROM modules, the first clock module, a FLASH modules, the first Bus isolation module are connected with a CPU respectively,
First Bus isolation module connects with the first CAN, a LVDS buses, OC output control module, a first remote measurement amount
Module, the first command output module is received to be connected.
Second control module include the 2nd CPU, the second SRAM module, the 2nd PROM modules, the 2nd FLASH modules,
Second clock module, the second Bus isolation module, the second CAN, the 2nd LVDS buses, the 2nd OC output control module,
Second remote measurement amount receiver module, the second command output module, the second SRAM module, the 2nd PROM modules, second clock module,
Two FLASH modules, the second Bus isolation module are connected with the 2nd CPU respectively, the second Bus isolation module and the second CAN,
2nd LVDS buses, the 2nd OC output control module, the second remote measurement amount receiver module, the second command output module are connected.
A guiding software is respectively equipped with first CPU and the 2nd CPU, at the beginning of the guiding software is responsible for device hardware
Beginningization, power-on self-test, data transmission subsystem sum pipe compunication interaction, according to guiding mode of operation and house keeping computer instruction
Uploaded, stored, bootload.
The main processing block includes FPGA, the first DSP circuit, the 3rd SRAM module, the 3rd PROM modules, FPGA and the
One DSP circuit is connected, and the first DSP circuit is connected with the 3rd SRAM module, the 3rd PROM modules.
Weight of the invention is 16KG (± 0.5KG), and appearance and size is 210 × 332 × 262mm (tolerances：± 1mm), respectively
Signal interconnection between module is connected by big base plate and printed board connector, control computer software section include guiding software,
Adhesive logic management software and application software, the present invention are applied to long-life LEO satellite, and the system architecture of whole machine is can
The cold standby system of reconstruct, you can realized switching the master backup of each identical function module of the invention by external command, be available for cutting
The hardware resource for changing has：A DC/DC modules, the 2nd DC/DC modules, the 3rd DC/DC modules, the 4th inside power module
DC/DC modules, the 5th DC/DC modules, the first control module, the second control module, main processing block, the first pretreatment module,
Second pretreatment module, the 3rd pretreatment module.
The structure type of the invention is stacked, and each module is a box, and all modules pass through big base plate and spiral shell long
Bar is grouped together into modular assembly, and big base plate is arranged on cabinet lamina tecti in side, socket, is so conducive to module
Radiating and resistance to shock, cabinet surface carries out anodized.
The distribution of the internal memory of the first control module and the second control module and service condition are as follows：
The memory size of the first PROM modules and the memory size of the 2nd PROM modules all be 192KB, all by six 32K ×
The chip composition of 8, distribution is to Boot PROM (root is programmable to pay internal memory) internal memory interval with CPU；
The memory size of the memory size of the first SRAM module and the second SRAM module is all 2MB, all with EDAC (mistakes
Detection and correction) function, all it is made up of the chip of two panels 512K × 32, wherein the distribution of a piece of chip is the one of corresponding CPU
Individual RAM (random access memory) block is interval, and another chip piece is used as the EDAC verifications of corresponding SRAM module；
The memory size of the first FLASH modules and the memory size of the 2nd FLASH modules are all 2MB, all by a piece of 512K
The chip composition of × 32, FLASH module partition managements, be stored with multiple softwares such as control software, main process task software, pretreatment
Software, each software has multiple versions.
First control module and the second control module all have reset function, mainly solve powered on moment device original state
Determination, supply voltage decline when device again reset and the external reset to control computer.
A house dog is respectively equipped with first CPU and in the 2nd CPU, house dog is designed for software runs winged, guards the gate
Dog enables control for being controlled to the house dog in corresponding CPU, prevents " dog stings " problem.House dog enables signal
GPI (general-purpose interface) mouth of TSC695F (chip model) a kind of is delivered to after latch.
Guiding software when software Starting mode is electricity upper for control is to start from PROM, start or by soft from FLASH
Part uploads startup, GPI mouthfuls that TSC695F is delivered to after software Starting mode signal latch.
Emergency flight control include it is emergent enable control and emergent command status, emergency parachute is shaped and delivers to after latching
GPI mouthfuls of TSC695F, while emergent command signal is interrupted.
First Bus isolation module and the second Bus isolation module all except to complete correspondence bus data driving with every
From also solving the main part (power-up state) of correspondence with the corresponding latent topic of corresponding backed up between (not power-up state) circuit.
A decoding and control circuit are respectively equipped with inside first control module and the second control module, are respectively used to produce
Decoded signal, the control signal of the function elements such as correspondence CPU, Bus isolation module, PROM modules, SRAM module.
Guiding software is used to complete following functions：
Complete hardware initialization, resource allocation；
That realizes control card software uploads, guides and deletes function；
After software uploads, it is stored in erasable corresponding FLASH modules, the memory is divided into 3 intervals, deposits respectively
Put control card application software, main process task software and pretreatment software, be each software distribution space size respectively 256KB,
64KB and 64KB.
Upload software is injected by corresponding CAN framing, and software block message is contained per frame, and guiding software is according to software
The software that block sequence number will be uploaded is stored in different positions.After the instruction of " software deletion " is received, will be corresponding according to parameter
Software deleted.
The present invention provides the management control and signal transacting solution of high reliability long life for medium and low earth orbit satellites payload
Scheme, the present invention by aerospace level device and whole machine level cold standby design, support real time operating system, possess control, communication,
Remote measurement, redundancy backup, the function such as note in application software, realize at highly reliable management control and the signal of Satellite Payloads
Reason.The invention aims at the reception and parsing, the configuration pipe of system that control instruction is managed under middle low earth orbital environmental requirement
Reason, and the resources such as treatment, interface inter-link can be provided, realized the management control between each device resource of payload by upper layer software (applications)
The functions such as system, task scheduling and reconstruct；Multiple signals processing function is incorporated simultaneously, the function and property of unit is greatly strengthen
Energy.
In sum, the present invention has reliability higher and radioresistance index, with stronger anti-single particle effect energy
Power and single particle effect defencive function, realize greatly reducing for equal function lower volume and power consumption, support real time operating system
And various load often use communication interface, control interface, possess control, communication, remote measurement, redundancy backup, the work(such as note in application software
Energy.
Specific embodiment of the invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can within the scope of the claims make various deformations or amendments, this not shadow
Sound substance of the invention.
Claims (6)
1. one kind is towards Satellite Payloads control and processing system, it is characterised in that it includes：
Power module, uses and according to external command for 28V primary power sources to be converted into positive 5V power supplys for other functions module
Cold and hot switching is realized, the inside of the power module is Redundancy Design；
First control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
Control realization；
Second control module, is connected with the power module, for being responsible for towards Satellite Payloads control and processing system
Control realization；
Main processing block, is connected with first control module, the second control module, the integrated treatment for carrying out data signal
And cold and hot backup；
First pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out Hot Spare,
First pretreatment module is made up of a DSP circuit and an AD circuit；
Second pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out Hot Spare,
Second pretreatment module is made up of a DSP circuit and an AD circuit；
3rd pretreatment module, is connected with the main processing block, for carrying out the pretreatment of intermediate-freuqncy signal and carrying out Hot Spare,
3rd pretreatment module is made up of a DSP circuit and an AD circuit.
2. it is according to claim 1 towards Satellite Payloads control and processing system, it is characterised in that the circuit mould
Block includes the first relay, the second relay, the 3rd relay, the 4th relay, the 5th relay, the 6th relay, first
Wave filter, the second wave filter, the 3rd wave filter, a DC/DC modules, the 2nd DC/DC modules, the 3rd DC/DC modules, the 4th
DC/DC modules, the 5th DC/DC modules, the first relay are connected with the first wave filter, the 3rd wave filter, the second relay and
Two wave filters, the 3rd wave filter are connected, and the first wave filter is connected with a DC/DC modules, the 3rd DC/DC modules, the second filtering
Device is connected with the 2nd DC/DC modules, the 4th DC/DC modules, a DC/DC modules, the 2nd DC/DC modules respectively with the 3rd relay
Device is connected, and the 3rd relay is connected with the 4th relay, the 4th relay and first control module, the second control module phase
Even, the 3rd DC/DC modules, the 4th DC/DC modules be connected with the 5th relay respectively, the 5th relay and the 6th relay phase
Even, the 6th relay is connected with the main processing block, and the 3rd wave filter is connected with the 5th DC/DC modules, the 5th DC/DC modules
It is connected with first pretreatment module, the second pretreatment module, the 3rd pretreatment module.
3. it is according to claim 1 towards Satellite Payloads control and processing system, it is characterised in that first control
Molding block includes a CPU, the first SRAM module, a PROM modules, a FLASH modules, the first clock module, first total
Line isolation module, the first CAN, a LVDS buses, OC output control module, the first remote measurement amount receiver module,
First command output module, it is the first SRAM module, a PROM modules, the first clock module, a FLASH modules, first total
Line isolation module is connected with a CPU respectively, the first Bus isolation module and the first CAN, a LVDS buses, an OC
Door output control module, the first remote measurement amount receiver module, the first command output module are connected.
4. it is according to claim 1 towards Satellite Payloads control and processing system, it is characterised in that second control
Molding block includes the 2nd CPU, the second SRAM module, the 2nd PROM modules, the 2nd FLASH modules, second clock module, second total
Line isolation module, the second CAN, the 2nd LVDS buses, the 2nd OC output control module, the second remote measurement amount receiver module,
Second command output module, it is the second SRAM module, the 2nd PROM modules, second clock module, the 2nd FLASH modules, second total
Line isolation module is connected with the 2nd CPU respectively, the second Bus isolation module and the second CAN, the 2nd LVDS buses, the 2nd OC
Door output control module, the second remote measurement amount receiver module, the second command output module are connected.
5. according to claim 3 and claim 4 towards Satellite Payloads control and processing system, its feature exists
In, be respectively equipped with a CPU and the 2nd CPU one guiding software, the guiding software be responsible for device hardware initialization,
Power-on self-test, data transmission subsystem sum pipe compunication interaction, are carried out according to guiding mode of operation and house keeping computer instruction
Upload, store, bootload.
6. it is according to claim 1 towards Satellite Payloads control and processing system, it is characterised in that the main process task
Module includes FPGA, the first DSP circuit, the 3rd SRAM module, the 3rd PROM modules, and FPGA is connected with the first DSP circuit, first
DSP circuit is connected with the 3rd SRAM module, the 3rd PROM modules.
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