CN108255772A - A kind of board computer system and micro-nano satellite - Google Patents
A kind of board computer system and micro-nano satellite Download PDFInfo
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- CN108255772A CN108255772A CN201810162763.4A CN201810162763A CN108255772A CN 108255772 A CN108255772 A CN 108255772A CN 201810162763 A CN201810162763 A CN 201810162763A CN 108255772 A CN108255772 A CN 108255772A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F15/00—Digital computers in general; Data processing equipment in general
- G06F15/16—Combinations of two or more digital computers each having at least an arithmetic unit, a program unit and a register, e.g. for a simultaneous processing of several programs
- G06F15/161—Computing infrastructure, e.g. computer clusters, blade chassis or hardware partitioning
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F1/00—Details not covered by groups G06F3/00 - G06F13/00 and G06F21/00
- G06F1/26—Power supply means, e.g. regulation thereof
- G06F1/32—Means for saving power
- G06F1/3203—Power management, i.e. event-based initiation of a power-saving mode
- G06F1/3234—Power saving characterised by the action undertaken
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/07—Responding to the occurrence of a fault, e.g. fault tolerance
- G06F11/16—Error detection or correction of the data by redundancy in hardware
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Abstract
The embodiment of the present application provides a kind of board computer system and micro-nano satellite, which includes：Two spaceborne computers including isomorphism, two spaceborne computers are connected by first set of lines；Spaceborne computer includes Star Service management module, attitude control management module, resets and cut machine module and processing module, and processing module is cut machine module and connect with Star Service management module, attitude control management module and reset respectively；Star Service management module receives control data, and be sent to processing module；The attitude data of attitude control management module acquisition satellite, and attitude data is sent to processing module；Processing module is based on control data and sends satellite control signals to host's satellite；The attitude information of host's satellite is determined based on attitude data, and according to the posture of control data control host's satellite；The transmission of machine module is cut to the reset under setting condition and cut machine instruction, carry out cutting machine so as to reset and cut machine module.The embodiment of the present application provides a kind of relatively low board computer system of power consumption.
Description
Technical field
This application involves House keeping system technical field, in particular to a kind of board computer system and micro-nano
Satellite.
Background technology
Cube star be a kind of structure in cubical microsatellite, belong to the scope of micro-nano satellite, widely should
For space science research and education sector, have the characteristics that at low cost, functional density is big, the lead time is short and enter the orbit fast.
Spaceborne computer carries whole sing data information management task, completes operation procedure operation and the integrated information of satellite
Work is handled, undertakes the function of attitude control computer simultaneously, completes the task of attitude algorithm, gesture stability.
In the prior art, board computer system mostly includes independent house keeping computer and attitude control computer two parts,
This two parts controls respectively carries out Star Service management and attitude control management to satellite, but for small-sized cube star, effectively
Solar cell limited area, and then the satellite energy is caused to be limited, energy deficiency is to support conventional house keeping computer and appearance
Computer is controlled, while is limited to the volume of satellite, spatially can not also accommodate more set board computer systems.
Invention content
In view of this, the application has been designed to provide a kind of board computer system and micro-nano satellite, to provide one
The relatively low and small board computer system of kind power consumption.
In a first aspect, the embodiment of the present application provides a kind of board computer system, the spaceborne calculating of two including isomorphism
Machine, two spaceborne computers are connected by first set of lines；
The spaceborne computer includes Star Service management module, attitude control management module, resets and cut machine module and processing module, institute
Processing module is stated to cut machine module with Star Service management module, attitude control management module and the reset respectively and connect；
The Star Service manages module, for receiving the control data of ground upload, and the control data is sent to institute
State processing module；
The attitude control manages module, for acquiring the attitude data of host's satellite, and the attitude data is sent to institute
State processing module；
The processing module sends satellite control signals for being based on the control data to host's satellite；It is based on
The attitude data determines the attitude information of host's satellite, and the appearance of host's satellite is controlled according to the control data
State；And under setting condition to it is described reset cut machine module transmission cut machine instruction so that it is described reset cut machine module into
Row cuts machine.
With reference to first aspect, the embodiment of the present application provides the first possible embodiment of first aspect, described multiple
It cuts machine module and includes in position：Watchdog reset circuit cuts machine control with machine control module, the watchdog reset circuit is cut with described
Module connects；
The processing module is sent to the watchdog reset electricity after watchdog signal is triggered, by the watchdog signal
Road；
The watchdog reset circuit generates spaceborne computer reset signal, and by the spaceborne computer reset signal simultaneously
It is sent to the processing module and the machine of cutting controls module；
The machine of cutting controls module to detect answering for the processing module after the spaceborne computer reset signal is received
Precedence number after determining that the number of resets is more than setting value, controls the spaceborne computer to carry out cutting machine.
With reference to first aspect, the embodiment of the present application provides second of possible embodiment of first aspect, the star
It carries computer and further includes navigation module, the navigation module is connect with the processing module；
The navigation module, for acquiring the geographical location information and temporal information of host's satellite, and by described
Reason location information and the temporal information are sent to the processing module.
Second of possible embodiment with reference to first aspect, the embodiment of the present application provide the third of first aspect
Possible embodiment, the navigation module include：Global navigation satellite component and Beidou satellite navigation component.
With reference to first aspect, the embodiment of the present application provides the 4th kind of possible embodiment of first aspect, and described
One line group includes two-way CAN bus and I2C buses.
With reference to first aspect, the embodiment of the present application provides the 5th kind of possible embodiment of first aspect, the star
Business management module includes：Memory module, error correction and detection module and temperature monitoring module；
The memory module, for storing the control data that the ground received uploads；
The error correction and detection module, for carrying out error correction and detection to the control data；
The temperature monitoring module, for receiving the temperature number that the temperature sensor being located on host's satellite uploads
According to, and the temperature data is sent to the processing module.
With reference to first aspect, the embodiment of the present application provides the 6th kind of possible embodiment of first aspect, the appearance
Keyholed back plate reason module includes：First attitude sensor, posture determining module and gesture stability module；
First attitude sensor for detecting the attitude information of host's satellite, and the attitude information is sent out
It send to the processing module；
The posture determining module for connecting the second attitude sensor being located on host's satellite, and is described
The second attitude sensor on host's satellite provides power supply and truck；
The gesture stability module, the attitude control control data transmission for the processing module to be sent out extremely are located at the place
Gesture stability component on main satellite.
The 6th kind of possible embodiment with reference to first aspect, the embodiment of the present application provide the 7th kind of first aspect
Possible embodiment, the attitude sensor include optical sensor, inertial sensor, radio frequency sensor and magnetic sensor.
With reference to first aspect, the embodiment of the present application provides the 8th kind of possible embodiment of first aspect, the star
It carries computer and further includes power management module, the power management module is connect with the processing module；
The power management module, for by the voltage of reception be converted into processing module described in the spaceborne computer,
The voltage needed for machine module is cut in Star Service management module, attitude control management module and reset.
Second aspect, the embodiment of the present application provide a kind of micro-nano satellite, including：Satellite body and it is set to described defend
TT＆C system, Data transfer system, power-supply system, heat control system, load system and first aspect on star ontology are to first aspect
Any board computer system in 8th kind of possible embodiment, the board computer system respectively with it is described
TT＆C system, the Data transfer system, the power-supply system, the heat control system, the load system are connected by the second line group.
Compared with prior art, board computer system provided by the embodiments of the present application, two spaceborne meters including isomorphism
Calculation machine, the structure of this two spaceborne computers is identical, and each spaceborne computer is provided with Star Service management module, attitude control
Management module resets and cuts machine module and processing module, manages module by integrated Star Service simultaneously and attitude control manages module, fusion
The dual function of house keeping computer and attitude control computer in existing onboard system, and two spaceborne computers are not while work
Make, under the premise of meeting control host's satellite in this way, save power consumption, and after a spaceborne computer breaks down, it can
It switches to another spaceborne computer and continues to complete control to host's satellite, it is seen then that spaceborne meter provided by the embodiments of the present application
Calculation machine system cost is relatively low, and power consumption is relatively low, while the board computer system passes through needed for the existing satellite of a unitary set
Star Service management and attitude control management function, so volume can be reduced, existing micro-nano satellite is facilitated to use.
For the above-mentioned purpose of the application, feature and advantage is enable to be clearer and more comprehensible, preferred embodiment cited below particularly, and coordinate
Appended attached drawing, is described in detail below.
Description of the drawings
It, below will be to needed in the embodiment attached in order to illustrate more clearly of the technical solution of the embodiment of the present application
Figure is briefly described, it should be understood that the following drawings illustrates only some embodiments of the application, therefore is not construed as pair
The restriction of range, for those of ordinary skill in the art, without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 shows the first board computer system structure diagram that the embodiment of the present application is provided；
Fig. 2 shows second of board computer system structure diagrams that the embodiment of the present application is provided；
Fig. 3 shows that one kind cuts machine circuit diagram in the board computer system that the embodiment of the present application is provided；
Fig. 4 shows the structure diagram of a kind of micro-nano satellite that the embodiment of the present application is provided.
Icon：11- spaceborne computers；12- spaceborne computers；13- first set of lines；101- Star Services manage module；102- appearances
Keyholed back plate manages module；Machine module is cut in 103- resets；104- processing modules；1032- cuts machine control module；1031- watchdog resets electricity
Road；001- processors；1032A- monostable flipflops；1032B- cuts machine control circuit；1032C- switching on and shutting down control circuits；
1032D- command process modules；1032E- power supply circuits；40- satellite bodies；10- board computer systems；41- the second line groups；
401- TT＆C systems；402- Data transfer systems；403- power-supply systems；404- heat control systems；405- load systems.
Specific embodiment
Purpose, technical scheme and advantage to make the embodiment of the present application are clearer, below in conjunction with the embodiment of the present application
The technical solution in the embodiment of the present application is clearly and completely described in middle attached drawing, it is clear that described embodiment is only
It is some embodiments of the present application, instead of all the embodiments.The application being usually described and illustrated herein in the accompanying drawings is real
Applying the component of example can be configured to arrange and design with a variety of different.Therefore, below to the application's for providing in the accompanying drawings
The detailed description of embodiment is not intended to limit claimed scope of the present application, but is merely representative of the selected reality of the application
Apply example.Based on embodiments herein, institute that those skilled in the art are obtained under the premise of creative work is not made
There is other embodiment, shall fall in the protection scope of this application.
Embodiment 1
The embodiment of the present application 1 provides a kind of board computer system, as shown in Figure 1, two including isomorphism spaceborne meters
Spaceborne computer 11 and spaceborne computer 12 in calculation machine, i.e. Fig. 1, two spaceborne computers are connected by first set of lines 13.
Wherein, first set of lines 13 include two-way CAN bus and I2C buses, under normal circumstances, spaceborne computer 11 and spaceborne
Computer 12 is carried out data transmission by CAN bus, when CAN bus go wrong can not normal transmission data when, can switch
To I2C buses, carried out data transmission by I2C buses.
Since the structure of two spaceborne computers is identical, function is identical, for one of spaceborne computer
It illustrates, as shown in Fig. 2, spaceborne computer 11 includes Star Service management module 101, attitude control management module 102, resets and cut machine mould
Group 103 and processing module 104, processing module 104 cut machine with Star Service management module 101, attitude control management module 102 and reset respectively
Module 103 connects.
Star Service manages module 101, for receiving the control data of ground upload, and control data is sent to processing module
104。
Wherein, the effects that Star Service management module is mainly used for realizing Satellite operation management, autonomous control and information transmission, one
Aspect Star Service management module receives each control instruction of the transmission on ground, and these control instructions are sent to processing module,
After the processing by processing module, processing module controls other subsystems on host's satellite by these control instructions,
Such as TT＆C system, Data transfer system, heat control system and load system etc..
Optionally, Star Service management module includes：Memory module, error correction and detection module and temperature monitoring module.
Wherein, memory module, for storing the control data that the ground received uploads；Error correction and detection module, for described
Data is controlled to carry out error correction and detection；Temperature monitoring module, for receiving the temperature sensor being located on host's satellite upload
Temperature data, and temperature data is sent to processing module.
Attitude control manages module 102, for acquiring the attitude data of host's satellite, and attitude data is sent to processing module
104。
Some modules in attitude control management module are responsible for acquiring the attitude data of host's satellite, and the attitude data is sent
To processing module so that processing module can determine the current posture of host's satellite, other modules are receiving processing mould
It, can be according to the posture of gesture stability instruction control host's satellite received after the gesture stability instruction that block is sent.
Wherein, attitude control management module includes：First attitude sensor, posture determining module and gesture stability module.
Attitude information for detecting the attitude information of host's satellite, and is sent to processing module by the first attitude sensor.
Posture determining module, for connecting the second attitude sensor being located on host's satellite, and on host's satellite
Second attitude sensor provides power supply and truck.
Here the first attitude sensor is that the posture in the attitude control management module being located in board computer system is sensitive
Device, the second attitude sensor are the attitude sensors being located on host's satellite.
Gesture stability module, the attitude control control data transmission for processing module to be sent out extremely are located at the appearance on host's satellite
State control assembly.
Optionally, attitude sensor includes optical sensor, inertial sensor, radio frequency sensor and magnetic sensor.
More than, Star Service management module and posture management module be combined with each other and control the operation of host's satellite together.
Processing module 104 sends satellite control signals for being based on control data to host's satellite；It is true based on attitude data
Determine the attitude information of host's satellite, and according to the posture of control data control host's satellite；And under setting condition to
Reset cuts the transmission of machine module 103 and cuts machine instruction, carries out cutting machine so as to reset and cut machine module 103.
Specifically, include as shown in Fig. 2, resetting and cutting machine module 103：Watchdog reset circuit 1031 controls module with machine of cutting
1032, watchdog reset circuit 1031 is connect with cutting machine control module 1032.
Processing module 104 is sent to watchdog reset circuit 1031 after watchdog signal is triggered, by watchdog signal.
Watchdog reset circuit 1031 generates spaceborne computer reset signal, and by the spaceborne computer reset signal simultaneously
It is sent to processing module 104 and cuts machine control module 1032.
It cuts machine and controls module 1032 after spaceborne computer reset signal is received, the reset time of detection process module 104
Number, after determining that number of resets is more than setting value, control spaceborne computer carries out cutting machine.
Processing module in the application can be processor, such as the processor 001 of STM32F429 series, the processor
Rich interface, performance it is stable, powerful.Machine control module 1032 is cut to specifically include monostable flipflop 1032A, cut machine control
Circuit 1032B processed, switching on and shutting down control circuit 1032C, command process module 1032D and power supply circuit 1032E.
The machine control spaceborne computer 11 of module and spaceborne computer 12, circuit diagram such as Fig. 3 institutes are cut including above-mentioned
Show, the acquiescence of processor 001 opens watchdog function, and when processor 001 works normally, it is periodical to seeing according to the designated time
Door dog counter is resetted, therefore will not trigger watchdog signal, when 001 operation exception of processor, house dog counter
Can be untreated and trigger watchdog signal due to being more than the designated time, which will be fed to watchdog reset circuit
So as to generate spaceborne computer reset signal in 1031, while treated by watchdog reset circuit 1031 for watchdog signal
Signal can be fed in monostable flipflop, and monostable flipflop, which generates, opens standby host instruction, i.e., when spaceborne computer 11 is sent out
Spaceborne computer 12 is opened during raw reset, the handling result of monostable flipflop 1032A, which will be fed to, cuts machine control circuit
In 1032B, it is spaceborne according to the input of monostable flipflop 1032A and the condition adjudgement of reset signal to cut machine control circuit 1032B
The current state of computer 11 is to power on cold start-up for the first time or watchdog reset thermal starting occurs, and starting state signal will be sent
It returns in processor 001, processor 001 determines a need for carrying out active and standby spaceborne computer switching, and will according to starting state
Cutting machine signal, which sends back to cut to generate in machine control circuit 1032B, cuts machine instruction.
Machine instruction and standby host enabled instruction is cut to be sent in spaceborne computer 12 after command process module 1032D processing
In switching on and shutting down control circuit 1032C, switching on and shutting down control circuit 1032C is generated to the power supply circuit 1032E's of spaceborne computer 12
Signal is controlled, and then carries out the operation of switching on and shutting down.
The instruction that spaceborne computer 11 is sent out (is closed for ON_12 instructions (opening spaceborne computer 12) and OFF12_ON11
Spaceborne computer 12 is opened spaceborne computer 11 and is instructed), similarly, the instruction that spaceborne 12 machine is sent out (is opened spaceborne for ON_11 instructions
Computer 11) and OFF11_ON12 (close spaceborne computer 11 and open spaceborne computer 12).
The state conversion for resetting machine of cutting is as shown in Figure 3.It, will when for the first time watchdog reset occurs for spaceborne computer 11
ON_12 instructions are sent, open spaceborne computer 12.After the completion of 11 reset initialization of spaceborne computer its to starting state signal into
Row judgement, is determined as single thermal starting, and at this time without switching, and T seconds after the completion of the initialization of spaceborne computer 11 send
OFF12_ON11 signals are so as to close spaceborne computer 12.Spaceborne computer 11 only carries out weight after a watchdog reset occurs
It opens, and does not carry out switch between master and slave machines.The use of the strategy is avoided due to frequently cutting machine caused by the false triggering of watchdog signal.It is right
For answering spaceborne computer 12, spaceborne computer 12 needs to send out within 2T seconds after the completion of initialization after house dog triggers reset signal
OFF11_ON12 signals.After spaceborne computer 11 triggers watchdog signal again, 11 processor of spaceborne computer is according to startup
State can determine that restarts for secondary reset, can send out unlatching spaceborne computer 12 immediately and instruct, and trigger and reset in house dog
It needs to send out OFF12_ON11 signals within 3T seconds after the completion of initialization after signal.Spaceborne computer 12 is to power on cold start-up for the first time at this time,
It will send out OFF11_ON12 signals in 2T seconds after the completion of initialization.The closing spaceborne computer 11 that spaceborne computer 12 is sent out
Early T seconds of the signal that signal closes spaceborne computer 12 than spaceborne computer 11 is sent out.Therefore, when spaceborne computer 11 occurs twice
When reset is restarted, spaceborne computer 11 will be closed, and spaceborne computer 12 is in running order.When spaceborne computer 12 occurs one
Spaceborne computer 11 will be switched back to during secondary watchdog reset.Spaceborne computer 12 occurs that during watchdog reset spaceborne meter will be opened
Calculation machine 11, spaceborne computer 11 will send out the instruction (OFF12_ON11) for closing spaceborne computer 12 in T seconds after the completion of initialization,
And spaceborne computer 12 needs to send out for 2T seconds and closes spaceborne computer 11 and instruct (OFF11_ON12), therefore, closes spaceborne computer
12 instruction is first sent out.Therefore, it carries out cutting machine during 12 single of spaceborne computer triggering watchdog signal, by spaceborne computer 12
Switch back into spaceborne computer 11.Since spaceborne computer 11 and spaceborne computer 12 are by the way of isomorphism, generally pass through ground
The more stable unit of the selected performance of test is as spaceborne computer 11.
TT＆C system can carry out the conversion of on-off state by force by the instruction noted on ground, you can by being noted on ground
Instruction open certain spaceborne unit.Pouring functions on surface instruction can be achieved in UV observing and controlling unit and X observing and controlling unit, and the two is standby each other
Part and will not simultaneously to spaceborne computer send instruct.Switching on and shutting down control of the control instruction to spaceborne computer can be transmitted in observing and controlling unit
Circuit 1032C processed, the instruction of upper note include OFF12_ON11 (close spaceborne computer 12 open spaceborne computer 11 instruct) and
OFF11_ON12 (closes the unlatching spaceborne computer 12 of spaceborne computer 11 to instruct), and it is work at present to set 11 machines and 12 machines respectively
Computer.After command process module 1032D receives the upper note instruction on ground, no matter which kind of work spaceborne computer is currently at
Make state, be switched to the operating mode of instruction agreement immediately.
Optionally, spaceborne computer further includes navigation module, and navigation module is connect with processing module.
Navigate module, for acquiring the geographical location information of host's satellite, and geographical location information is sent to processing mould
Block, processing module can be sent out the geographical location information of host's satellite by such as Data transfer system of other subsystems on host's satellite
Send ground control terminal back to.
Wherein, navigation module includes：Global navigation satellite component and Beidou satellite navigation component.
Optionally, spaceborne computer further includes power management module, and power management module is connect with processing module.
Power management module, for the voltage of reception to be converted into processing module in the spaceborne computer, Star Service management
The voltage needed for machine module is cut in module, attitude control management module and reset.
A kind of preferably embodiment, in the technical solution of the proposition of the embodiment of the present application 1, board computer system also carries
Plate general-purpose interface is supplied, which is integrated with communication interface, instruction interface and the power interface of plurality of classes, is
The interface that different subsystems offer on host's satellite is connect with board computer system.
Embodiment 2
The embodiment of the present application 2 provides a kind of micro-nano satellite, as shown in figure 4, being defended including satellite body 40 and being set to
TT＆C system 401, Data transfer system 402, power-supply system 403, heat control system 404, load system 405 and implementation on star ontology 40
Any board computer system 10 in example 1, board computer system 10 and TT＆C system 401, Data transfer system 402, power supply
System 403, heat control system 404, load system 405 are connected by the second line group 41.
Wherein, the second line group 41 includes two-way CAN bus and I2C buses, and under normal circumstances, board computer system 10 is logical
CAN bus and TT＆C system 401, Data transfer system 402, power-supply system 403, heat control system 404 and load system 405 are crossed into line number
According to transmission, when CAN bus go wrong can not normal transmission data when, I2C buses can be switched to, by I2C buses into line number
According to transmission.
Compared with prior art, board computer system provided by the embodiments of the present application, two spaceborne meters including isomorphism
Calculation machine, the structure of this two spaceborne computers is identical, and each spaceborne computer is provided with Star Service management module, attitude control
Management module resets and cuts machine module and processing module, manages module by integrated Star Service simultaneously and attitude control manages module, fusion
The dual function of house keeping computer and attitude control computer in existing onboard system, and two spaceborne computers are not while work
Make, under the premise of meeting control host's satellite in this way, save power consumption, and after a spaceborne computer breaks down, it can
It switches to another spaceborne computer and continues to complete control to host's satellite, it is seen then that spaceborne meter provided by the embodiments of the present application
Calculation machine system cost is relatively low, and power consumption is relatively low, while the board computer system passes through needed for the existing satellite of a unitary set
Star Service management and attitude control management function, so volume can be reduced, existing micro-nano satellite is facilitated to use.
It should be noted that：Similar label and letter represents similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need to that it is further defined and explained in subsequent attached drawing.
In the description of the present application, it should be noted that term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instructions such as " level ", " interior ", " outer " are based on orientation shown in the drawings or position relationship or are somebody's turn to do
Invention product using when the orientation usually put or position relationship, be for only for ease of description the application and simplify and describe, without
It is instruction or implies that signified device or element there must be specific orientation, with specific azimuth configuration and operation, therefore not
It is understood that as the limitation to the application.In addition, term " first ", " second ", " third " etc. are only used for distinguishing description, and cannot manage
It solves to indicate or implying relative importance.
In the description of the present application, it is also necessary to which explanation is unless specifically defined or limited otherwise, term " setting ",
" installation ", " connected ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected or one
Connect to body；Can be mechanical connection or electrical connection；It can be directly connected, it can also be indirect by intermediary
It is connected, can is the connection inside two elements.For the ordinary skill in the art, on being understood with concrete condition
State the concrete meaning of term in this application.
Finally it should be noted that：The specific embodiment of embodiment described above, only the application, to illustrate the application
Technical solution, rather than its limitations, the protection domain of the application is not limited thereto, although with reference to the foregoing embodiments to this Shen
It please be described in detail, it will be understood by those of ordinary skill in the art that：Any one skilled in the art
In the technical scope disclosed in the application, it can still modify to the technical solution recorded in previous embodiment or can be light
It is readily conceivable that variation or equivalent replacement is carried out to which part technical characteristic；And these modifications, variation or replacement, do not make
The essence of corresponding technical solution is detached from the spirit and scope of the embodiment of the present application technical solution.The protection in the application should all be covered
Within the scope of.Therefore, the protection domain of the application described should be subject to the protection scope in claims.
Claims (10)
1. a kind of board computer system, which is characterized in that two spaceborne computers including isomorphism, two spaceborne calculating
Machine is connected by first set of lines；
The spaceborne computer includes Star Service management module, attitude control management module, resets and cut machine module and processing module, the place
Reason module is cut machine module and is connect with Star Service management module, attitude control management module and the reset respectively；
The Star Service manages module, for receiving the control data of ground upload, and the control data is sent to the place
Manage module；
The attitude control manages module, for acquiring the attitude data of host's satellite, and the attitude data is sent to the place
Manage module；
The processing module sends satellite control signals for being based on the control data to host's satellite；Based on described
Attitude data determines the attitude information of host's satellite, and the posture of host's satellite is controlled according to the control data；
And machine instruction is cut for cutting the transmission of machine module to the reset under setting condition, so that the reset is cut machine module and is cut
Machine.
2. system according to claim 1, which is characterized in that the reset is cut machine module and included：Watchdog reset circuit
Module is controlled with machine of cutting, the watchdog reset circuit is connect with the machine control module of cutting；
The processing module is sent to the watchdog reset circuit after watchdog signal is triggered, by the watchdog signal；
The watchdog reset circuit generates spaceborne computer reset signal, and the spaceborne computer reset signal is sent simultaneously
Module is controlled to the processing module and the machine of cutting；
The machine of cutting controls module after the spaceborne computer reset signal is received, and detects the reset time of the processing module
Number after determining that the number of resets is more than setting value, controls the spaceborne computer to carry out cutting machine.
3. system according to claim 1, which is characterized in that the spaceborne computer further includes navigation module, described to lead
Model plane group is connect with the processing module；
The navigation module, for acquiring the geographical location information and temporal information of host's satellite, and by the geographical position
Confidence ceases and the temporal information is sent to the processing module.
4. system according to claim 3, which is characterized in that the navigation module includes：Global navigation satellite component and
Beidou satellite navigation component.
5. system according to claim 1, which is characterized in that the first set of lines include two-way CAN bus and I2C is total
Line.
6. system according to claim 1, which is characterized in that the Star Service management module includes：Memory module, error correction and detection
Module and temperature monitoring module；
The memory module, for storing the control data that the ground received uploads；
The error correction and detection module, for carrying out error correction and detection to the control data；
The temperature monitoring module, for receiving the temperature data that the temperature sensor being located on host's satellite uploads, and
The temperature data is sent to the processing module.
7. system according to claim 1, which is characterized in that the attitude control management module includes：First attitude sensor,
Posture determining module and gesture stability module；
First attitude sensor for detecting the attitude information of host's satellite, and the attitude information is sent to
The processing module；
The posture determining module for connecting the second attitude sensor being located on host's satellite, and is the host
The second attitude sensor on satellite provides power supply and truck；
The gesture stability module, the attitude control control data transmission for the processing module to be sent out extremely are defended positioned at the host
Gesture stability component on star.
8. system according to claim 7, which is characterized in that it is quick that the attitude sensor includes optical sensor, inertia
Sensor, radio frequency sensor and magnetic sensor.
9. system according to claim 1, which is characterized in that the spaceborne computer further includes power management module, institute
Power management module is stated to connect with the processing module；
The power management module, for the voltage of reception to be converted into processing module, Star Service described in the spaceborne computer
The voltage needed for machine module is cut in management module, attitude control management module and reset.
10. a kind of micro-nano satellite, which is characterized in that including：Satellite body and the observing and controlling system being set on the satellite body
System, Data transfer system, power-supply system, heat control system, load system and any board computer system of claim 1 to 9,
The board computer system respectively with the TT＆C system, the Data transfer system, the power-supply system, the heat control system,
The load system is connected by the second line group.
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