CN205608461U - Star carries synthesizes next machine of electron - Google Patents
Star carries synthesizes next machine of electron Download PDFInfo
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- CN205608461U CN205608461U CN201620407488.4U CN201620407488U CN205608461U CN 205608461 U CN205608461 U CN 205608461U CN 201620407488 U CN201620407488 U CN 201620407488U CN 205608461 U CN205608461 U CN 205608461U
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- plate
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- slave computer
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- power supply
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Abstract
The utility model discloses a star carries synthesizes next machine of electron adopts picture peg formula structure, it is including power module and a plurality of functional module, a plurality of the functional module includes electromagnetism valve plate, magnetic control board, panel, priming sytem board, bus control board and telemetry -acquisition board, power module, electromagnetism valve plate, magnetic control board, panel, priming sytem board, bus control board and telemetry -acquisition board carry out the interconnection through inserting the bottom plate. The utility model discloses a system optimization, comprehensive integration design, rationally divide the module, collect five traditional stars such as far putting terminal, propulsion circuit box, comprehensive circuit box, distribution board and priming sytem the control unit at an unit and carry electronic equipment unit function in an organic whole, have obtained very big reduction star and have carried beneficial effect such as weight of equipment, volume, consumption and improvement modularization degree.
Description
Technical field
This utility model relates to a kind of electronic equipment on satellite, particularly to a kind of spaceborne integrated electronics slave computer.
Background technology
The slave computer of satellite platform mainly completes the exporting for distribution, telemetry-acquisition, instruction, drive of satellite
Etc. function, generally to collect and far put terminal, propelling circuit box, comprehensive circuit box, distribution board and priming system
The multiple stage units such as control unit complete.
Launching the task that satellite is a high cost, the weight of its Satellite, volume are to determine into power consumption
This key factor.Completing the multiple stage unit of above-mentioned satellite platform slave computer function, every has been required to knot
Component supports electronic circuit, and each unit electronic unit is each independent, it is impossible to realize being total to of software and hardware resources
Enjoy, cause the weight of unit, volume and power consumption the biggest, need undoubtedly to spend the biggest cost.
Utility model content
Based on the shortcoming in the presence of prior art, the utility model proposes under a kind of spaceborne integrated electronics
Position machine, improves the functional density of satellite platform slave computer, effectively reduce satellite borne equipment weight, volume and
Power consumption.
The technical scheme that this utility model is used by its technical problem of solution is as follows:
A kind of spaceborne integrated electronics slave computer, uses board plug type structure, including supply module and multiple function mould
Block, multiple described functional modules include electromagnetic valve plate, magnetic control plate, panel, priming system plate, bus marco
Plate and telemetry-acquisition plate, described supply module, electromagnetism valve plate, magnetic control plate, panel, priming system plate,
Bus marco plate and telemetry-acquisition plate interconnect by inserting base plate.
Further, the primary power source that input voltage is 28V is converted to output voltage by described supply module
For the secondary power supply of 5V, and by base plate be described electromagnetism valve plate, magnetic control plate, panel, priming system plate,
Bus marco plate and telemetry-acquisition plate provide power supply.
Further, described electromagnetism valve plate one end and described base plate grafting, the other end and described satellite platform
The electromagnetic valve of propulsion subsystem and heater connect, respectively in order to complete the electricity of satellite platform propulsion subsystem
Magnet valve drives and the heating installation power supply of propulsion subsystem, and wherein, the way of described solenoid-driven is many
In 8 tunnels, the way of described heating installation power supply is no less than 8 tunnels.
Further, described magnetic control plate one end and described base plate grafting, the other end and described satellite platform appearance
3 magnetic torquers of control subsystem connect, in order to 3 magnetic torquers to satellite platform appearance control subsystem
It is driven, and gathers telemetry.
Further, described panel one end and described base plate grafting, the other end and described satellite platform appearance
Control subsystem connect, with think satellite platform appearance control subsystem provide no less than 48 tunnels 28V power supply,
No less than 3 tunnels ± 12V power supply and no less than 3 tunnels ± 5V power supply.
Further, described priming system plate provides the priming system power supply control no less than 6 tunnels, described firer
Product plate uses ground wire break-make to control relay to conciliate lock control relay to the ground wire break-make of priming system and unblock
It is controlled.
Preferably, described ground wire break-make control relay uses the M302-J2AH type magnetic of LEACH company to protect
Holding relay, described solution lock control relay uses the M230-J2A type electromagnetic relay of LEACH company.
Further, described bus marco plate is externally connected by 1553B bus, and as far putting terminal
Slow data transmission network in the 1553B of RT access satellite, receives satellite platform instruction, and by collection
Telemetry is sent to satellite platform.
Further, described telemetry-acquisition plate provides the analog quantity telemetering channel being not more than 181 tunnels, in institute
State under the control module gating signal control in bus marco plate, gate the distant of respective mode analog quantity telemetering channel
Survey data, be sent to the control module in described bus marco plate through the backplane bus of slave computer, and carry out
A/D analog digital conversion.
Preferably, described telemetry-acquisition plate provides the analog quantity telemetering channel on 176 tunnels.
This utility model is low by taking such scheme to overcome existing spaceborne slave computer functional density, defends
Star platform slave computer is completed control by multiple stage unit and processes the weight of function, volume and power consumption relatively greatly, soft or hard
The problem such as the degree of share of part resource is low, obtains following beneficial effect:
1) greatly reducing the weight of satellite slave computer, volume and power consumption, a unit completes five units
Function, loss of weight reaches 70%, reduces power consumption 45%；
2) improve aerospace slave computer assembly mould massing, modularization degree, use the 240 of AMP Inc.'s standard
Core interface, complete machine is made up of standard module, has unified electromechanical interface；
3) this utility model passes through system optimization, comprehensive integration design, classifying rationally module, improves star
Carry the generalization of slave computer, the degree of modularity, far put terminal, propelling circuit box at a unit collection, combine
Close traditional five the electronic equipment on satellite unit functions such as circuit box, distribution board and priming system control unit
In one, achieve and greatly alleviate satellite borne equipment weight, volume, power consumption and the raising degree of modularity etc. and have
Benefit effect.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme of this utility model embodiment, embodiment will be described below
The accompanying drawing used required in is briefly described.It is clear that the accompanying drawing in describing below is only this
Some embodiments of utility model, for those skilled in the art, are not paying creative work
Under premise, it is also possible to obtain other accompanying drawing according to these accompanying drawings.In accompanying drawing:
Fig. 1 is to realize composition frame chart of the present utility model；
Fig. 2 is the theory diagram of priming system plate of the present utility model；
Fig. 3 is the theory diagram of telemetry-acquisition plate of the present utility model.
Detailed description of the invention
Below with reference to accompanying drawing of the present utility model, the technical scheme in this utility model embodiment is carried out
Clear, complete description and discussion, it is clear that as described herein is only a part of the present utility model
Example, is not whole examples, based on the embodiment in this utility model, ordinary skill people
The every other embodiment that member is obtained on the premise of not making creative work, broadly falls into this practicality
Novel protection domain.
As it is shown in figure 1, present embodiment discloses a kind of spaceborne integrated electronics slave computer, use board plug type structure,
Including supply module and multiple functional module, multiple described functional modules include electromagnetic valve plate, magnetic control plate, join
Electroplax, priming system plate, bus marco plate and telemetry-acquisition plate, described supply module, electromagnetism valve plate, magnetic
Control plate, panel, priming system plate, bus marco plate and telemetry-acquisition plate interconnect by inserting base plate.
The slave computer of above-mentioned module composition is integrated by employing high integrity, modularity, General design, one
Realize whole star distribution, thermal control driving and management, propulsion management on platform unit, priming system manages, appearance control is held
The function that star telemetered signal collection capable, whole, telecommand pulse output etc. need multiple stage unit to complete.
In the present embodiment, the function of described supply module is by Power convert, is 28V by input voltage
Primary power source be converted to the secondary power supply that output voltage is 5V, and by base plate be described electromagnetism valve plate,
The Digital Logical Circuits of magnetic control plate, panel, priming system plate, bus marco plate and telemetry-acquisition plate provides
Power supply.
In the present embodiment, described electromagnetism valve plate one end and described base plate grafting, the other end is put down with described satellite
The electromagnetic valve of platform propulsion subsystem and heater connect, respectively in order to complete satellite platform propulsion subsystem
Solenoid-driven and the heating installation power supply of propulsion subsystem, wherein, the way of described solenoid-driven is not
Less than 8 tunnels, the way of described heating installation power supply is no less than 8 tunnels.Concrete, use VMOS pipe 2N6800U
Drive electromagnetic valve.
In the present embodiment, described magnetic control plate one end and described base plate grafting, the other end and described satellite platform
3 magnetic torquers of appearance control subsystem connect, in order to 3 magnetic torques to satellite platform appearance control subsystem
Device is driven, and gathers corresponding telemetry.And by controlling the switching of relay, through power tube
Output is to corresponding bar magnet.
In the present embodiment, described panel one end and described base plate grafting, the other end and each point of satellite platform
System connects, with thinking that satellite platform appearance control subsystem provides the 28V power supply, no no less than 48 tunnels
Less than 3 tunnels ± 12V power supply and no less than 3 tunnels ± 5V power supply.Concrete, use
MTR2812DF, OM1320STM transfer power subsystem 28V to ± 12V ,+5V；With MSA2805D by electricity
Source subsystem 28V transfers ± 5V to；The 28V of maximum operating currenbt 11A is controlled with metal-oxide-semiconductor IRHY9130CM
Power supply；The 28V realizing maximum operating currenbt 3A with VMOS pipe 2N6800U powers.
In the present embodiment, described priming system plate provides the priming system power supply control no less than 6 tunnels, including fire
The ground wire on-off of work product, unblock.Described priming system plate uses ground wire break-make to control relay reconciliation
Ground wire break-make and the unblock of priming system are controlled by lock control relay.Preferably, described ground wire break-make
Control relay K 1, K2 use the M302-J2AH type magnetic latching relay of LEACH company, described unblock
Control relay K 3, K4 use the M230-J2A type electromagnetic relay of LEACH company.
In the present embodiment, described bus marco plate is externally connected by 1553B bus, and as far putting end
Slow data transmission network in the 1553B of end RT access satellite, receives satellite platform instruction, and will gather
Telemetry be sent to satellite platform.CPU on described bus marco plate uses atmel corp
80C32E, as bus communication core, is controlled 1553B bus communication by CPU, completes high-rise universal serial bus
Agreement, and use 7.2 ten thousand anti-fuse FPGA, it is used for indirect instruction decoding function, by 422
Asynchronous serial communication is carried out between serial ports and outside, internal interface.
In the present embodiment, described telemetry-acquisition plate provides the analog quantity telemetering channel being not more than 181 tunnels,
Under control module gating signal in described bus marco plate controls, gating respective mode analog quantity telemetering channel
Telemetry, the backplane bus in slave computer is sent to control module and carries out A/D analog digital conversion.Described
Telemetry-acquisition plate uses General design, compatible voltage, Temperature Quantity telemetry-acquisition.Preferably, described
Telemetry-acquisition plate provides the analog quantity telemetering channel on 176 tunnels.
In the present embodiment, spaceborne integrated electronics slave computer uses board plug type structure, and every piece of printed board is arranged on
Individually in peripheral frame, in the middle of peripheral frame, there is reinforcement, reinforce in the middle part of printed board, improve printed board rigidity.
Printed board is inserted in casing, is fixed by securing member and screw, and casing can play shielding and fixing work
With.
It is the theory diagram of priming system plate of the present utility model as shown in Figure 2.Wherein, described priming system plate
Use relay that unblock and the ground wire break-make of priming system are controlled.Ground wire break-make control relay K 1,
K2 uses LEACH company magnetic latching relay M302-J2AH, solution lock control relay K 3, K4 to use LEACH
Company's M230-J2A electromagnetic relay.All relays all take Redundancy Design.For output electricity can be controlled
Flow at 5A～7.5A, in controlling loop, seal in current-limiting resistance R1, R4, simultaneously for preventing owing to electrostatic tires out
Manufacture into priming system by mistake the most quick-fried, devise Electro-static Driven Comb path the most in circuit, described resistance R1, R2 and
R3 is sequentially connected in series composition the first static release circuit, and wherein, resistance R1 one end connects control relay
K3, the other end is connected with resistance R2, one end that resistance R2 and R3 connects ground connection simultaneously, resistance R3's
The other end connects control relay K 1, and the series circuit that bridge wire resistance A and resistance R2 and R3 is formed is in parallel；
Described resistance R4, R5 and R6 are sequentially connected in series composition the second static release circuit, wherein, resistance R4
One end connects control relay K 4, and the other end is connected with resistance R5, and one end that resistance R5 and R6 connects is same
Time ground connection, the other end of resistance R6 connects and controls relay K 2, bridge wire resistance B and resistance R5 and R6 shape
The series circuit become is in parallel.
It is the theory diagram of telemetry-acquisition plate of the present utility model as shown in Figure 3.Wherein, described remote measurement is adopted
Collection plate designs 176 analog quantity telemetering channels, tunnel, and maximum support 181 tunnel telemetry-acquisitions, at bus marco plate
Control module gating signal control under, gate respective channel telemetry, through backplane bus be sent to control
Molding block carries out A/D conversion and gathers.Telemetry-acquisition uses General design compatibility voltage, Temperature Quantity distant
Survey and gather.
Telemetry-acquisition plate will organize MUX16 (single-chip 16 channel analog multiplexer) by outside connector more
Composition matrix switch, and gate analog quantity telemetering channel, the most any one road, the telemetry data packet that will gather
Include voltage and Temperature Quantity (collection period is fixed tentatively and adopted complete being not less than 2 times for every 0.5 second) is sent into amplifier and adjusted
Whole circuit, the telemetry after amplified process carries out analog digital conversion through AD574 pattern number converter again
Rear feeding FPGA (Field-Programmable Gate Array, i.e. field programmable gate array),
The most at last process after telemetry group bag after be stored in SRAM (Stat ic Random Access Memory,
I.e. static RAM), receive the remote measurement that bus marco plate is sent by asynchronous serial communication mouth
Data packet request signal, FPGA by regulation requirement will process after telemetry group bag after pass through asynchronous serial port
Return bus marco plate.
This utility model is low by taking such scheme to overcome existing spaceborne slave computer functional density, defends
Star platform slave computer is completed control by multiple stage unit and processes the weight of function, volume and power consumption relatively greatly, soft or hard
The problem such as the degree of share of part resource is low, obtains following beneficial effect:
1) greatly reducing the weight of satellite slave computer, volume and power consumption, a unit completes five units
Function, loss of weight reaches 70%, reduces power consumption 45%；
2) improve aerospace slave computer assembly mould massing, modularization degree, use the 240 of AMP Inc.'s standard
Core interface, complete machine is made up of standard module, has unified electromechanical interface；
3) this utility model passes through system optimization, comprehensive integration design, classifying rationally module, improves star
Carry the generalization of slave computer, the degree of modularity, far put terminal, propelling circuit box at a unit collection, combine
Close traditional five the electronic equipment on satellite unit functions such as circuit box, distribution board and priming system control unit
In one, achieve and greatly alleviate satellite borne equipment weight, volume, power consumption and the raising degree of modularity etc. and have
Benefit effect.
The above, only this utility model preferably detailed description of the invention, but protection of the present utility model
Scope is not limited thereto, the skill that any those familiar with the art discloses at this utility model
In the range of art, the change that can readily occur in or replacement, all should contain protection domain of the present utility model it
In.Therefore, protection domain of the present utility model should be as the criterion with scope of the claims.
Claims (10)
1. a spaceborne integrated electronics slave computer, use board plug type structure, including supply module and functional module, it is characterized in that, described functional module includes electromagnetic valve plate, magnetic control plate, panel, priming system plate, bus marco plate and telemetry-acquisition plate, and described supply module, electromagnetism valve plate, magnetic control plate, panel, priming system plate, bus marco plate and telemetry-acquisition plate interconnect by inserting base plate.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, the primary power source that input voltage is 28V is converted to the secondary power supply that output voltage is 5V by described supply module, and provides power supply by base plate for described electromagnetism valve plate, magnetic control plate, panel, priming system plate, bus marco plate and telemetry-acquisition plate.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described electromagnetism valve plate one end and described base plate grafting, the other end is connected with electromagnetic valve and the heater of satellite platform propulsion subsystem, the heating installation power supply of the solenoid-driven and propulsion subsystem in order to complete satellite platform propulsion subsystem respectively, wherein, the way of described solenoid-driven is no less than 8 tunnels, and the way of described heating installation power supply is no less than 8 tunnels.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described magnetic control plate one end and described base plate grafting, the other end is connected with 3 magnetic torquers of satellite platform appearance control subsystem, in order to 3 magnetic torquers of satellite platform appearance control subsystem to be driven, and gather telemetry.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described panel one end and described base plate grafting, the other end is connected with satellite platform appearance control subsystem, with think satellite platform appearance control subsystem provide no less than 48 tunnels 28V power supply, no less than 3 tunnels ± 12V power supply and no less than 3 tunnels ± 5V power supply.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described priming system plate provides the priming system power supply control no less than 6 tunnels, and described priming system plate uses ground wire break-make to control relay reconciliation lock control relay and is controlled ground wire break-make and the unblock of priming system.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 6, it is characterized in that, described ground wire break-make controls relay and uses the M302-J2AH type magnetic latching relay of LEACH company, and described solution lock control relay uses the M230-J2A type electromagnetic relay of LEACH company.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described bus marco plate is externally connected by 1553B bus, and as far put terminal RT access satellite 1553B in slow data transmission network, reception satellite platform instructs, and the telemetry of collection is sent to satellite platform.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 1, it is characterized in that, described telemetry-acquisition plate provides the analog quantity telemetering channel being not more than 181 tunnels, under control module gating signal in described bus marco plate controls, the telemetry of gating respective mode analog quantity telemetering channel, it is sent to the control module in described bus marco plate through the backplane bus of slave computer, and carries out A/D analog digital conversion.
A kind of spaceborne integrated electronics slave computer the most as claimed in claim 9, it is characterised in that described telemetry-acquisition plate provides the analog quantity telemetering channel on 176 tunnels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620407488.4U CN205608461U (en) | 2016-05-06 | 2016-05-06 | Star carries synthesizes next machine of electron |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620407488.4U CN205608461U (en) | 2016-05-06 | 2016-05-06 | Star carries synthesizes next machine of electron |
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| CN205608461U true CN205608461U (en) | 2016-09-28 |
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| CN201620407488.4U Active CN205608461U (en) | 2016-05-06 | 2016-05-06 | Star carries synthesizes next machine of electron |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106547224A (en) * | 2016-10-14 | 2017-03-29 | 上海微小卫星工程中心 | Universal micro-nano satellite integrated electronicses framework based on bus |
| CN106772462A (en) * | 2016-11-22 | 2017-05-31 | 上海卫星工程研究所 | Real-time controllable formula satellite telemetry signal source |
| CN108106670A (en) * | 2017-12-15 | 2018-06-01 | 北京卫星环境工程研究所 | Low Earth Orbit space environment and the integrated detection system of effect |
| CN110471341A (en) * | 2019-08-15 | 2019-11-19 | 中国空间技术研究院 | A kind of spaceborne intelligent menu mode Integrated Electronic System |
| CN116513493A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Overall circuit controller and satellite platform |
-
2016
- 2016-05-06 CN CN201620407488.4U patent/CN205608461U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106547224A (en) * | 2016-10-14 | 2017-03-29 | 上海微小卫星工程中心 | Universal micro-nano satellite integrated electronicses framework based on bus |
| CN106547224B (en) * | 2016-10-14 | 2019-10-15 | 上海微小卫星工程中心 | Universal micro-nano satellite integrated electronics framework based on bus |
| CN106772462A (en) * | 2016-11-22 | 2017-05-31 | 上海卫星工程研究所 | Real-time controllable formula satellite telemetry signal source |
| CN108106670A (en) * | 2017-12-15 | 2018-06-01 | 北京卫星环境工程研究所 | Low Earth Orbit space environment and the integrated detection system of effect |
| CN110471341A (en) * | 2019-08-15 | 2019-11-19 | 中国空间技术研究院 | A kind of spaceborne intelligent menu mode Integrated Electronic System |
| CN116513493A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Overall circuit controller and satellite platform |
| CN116513493B (en) * | 2023-07-05 | 2023-09-15 | 北京未来宇航空间科技研究院有限公司 | Overall circuit controller and satellite platform |
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