CN209642671U - Satellite load system and satellite system - Google Patents
Satellite load system and satellite system Download PDFInfo
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- CN209642671U CN209642671U CN201920948317.6U CN201920948317U CN209642671U CN 209642671 U CN209642671 U CN 209642671U CN 201920948317 U CN201920948317 U CN 201920948317U CN 209642671 U CN209642671 U CN 209642671U
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Abstract
This application involves a kind of satellite load system and satellite systems, it is related to space industry, the satellite load system includes load mainboard and the interface board that connect with the load mainboard, the interface board includes data converting circuit, for by the data conversion in the load mainboard, at the format being adapted to satellite platform, the load mainboard to be connect by the interface board with the satellite platform.The satellite load system can reduce the degree of coupling between load mainboard and satellite platform.
Description
Technical field
This application involves space industries, and in particular to a kind of satellite load system and satellite system.
Background technique
In recent years, country starts that non-governmental capital is encouraged to enter space industry, and space technology, especially cube star technology obtain
To fast development.For cube star system, satellite platform needs are attached with load system, thus by load system
Realize different functions.
Degree of coupling between the bus of traditional load system and satellite platform is higher, due to different satellite platform sides
Used data format may be inconsistent, causes the product data of different satellite platform sides incompatible.When satellite load system
When system side needs to provide satellite load system for the satellite platform side A, need to customize construction according to the interface protocol of the satellite platform side A
Satellite load system；When satellite load system side needs to provide satellite load system for the satellite platform side B, need to be defended according to B
The interface protocol customization construction satellite load system of star platform side.Therefore, for satellite load system side, for different
Satellite platform side needs to develop design again with regard to satellite load system functionally identical or similar, flat to be adapted to corresponding satellite
Platform, this makes the plenty of time be wasted for carrying out repetitive work, causes the update cycle longer, wastes time and resource.
Utility model content
In view of this, the application's is designed to provide a kind of satellite load system and satellite system, satellite can be reduced
The degree of coupling between load system and satellite platform.
Embodiments herein is achieved in that
In a first aspect, the embodiment of the present application provides a kind of satellite load system, the satellite load system includes load master
Plate and the interface board connecting with the load mainboard, the interface board include data converting circuit, are used for the load mainboard
In data conversion at the format being adapted to satellite platform, the load mainboard is connected by the interface board and the satellite platform
It connects.Compared to traditional scheme, the degree of coupling between satellite load system provided by the embodiments of the present application and satellite platform is lower,
Satellite load system can independent iteration update, meanwhile, different satellite platforms can be adapted to, save development cycle and time.
Embodiment with reference to first aspect, in a kind of possible embodiment, the interface board further includes first interface
Circuit and second interface circuit, the data converting circuit respectively with first interface circuit, the second interface circuit connection, institute
First interface circuit is stated for connecting with load mainboard, the second interface circuit with the satellite platform for connecting.
Embodiment with reference to first aspect, in a kind of possible embodiment, the load mainboard includes first performance
Plate and the second performance board, the first performance plate are connect with second performance board, are provided with electricity on the first performance plate
Power management circuits, the electric power management circuit are used to switch on and off the electric energy provided to second performance board.The power supply
Management circuit can control the open and close of the second performance board, be convenient for power saving.
Embodiment with reference to first aspect is provided on the electric power management circuit in a kind of possible embodiment
Switching circuit, the switching circuit are able to suppress the satellite load system and export surge to the satellite platform.
Embodiment with reference to first aspect, in a kind of possible embodiment, the switching circuit includes thermistor.
Embodiment with reference to first aspect, in a kind of possible embodiment, the switching circuit includes field-effect tube,
Avoid the influence by temperature on satellite.
Embodiment with reference to first aspect, in a kind of possible embodiment, the switching circuit further includes switch control
The drain electrode of unit processed, the field-effect tube is connect with external load, the source electrode connection of field-effect tube second resistance in parallel
And first capacitor, the second resistance are used to connect with external power supply with the first tie point of the first capacitor, described second
Second tie point of resistance and the first capacitor be connected to the field-effect tube grid and the switch control unit it
Between, the grid of the field-effect tube is also connect with the switch control unit.
Embodiment with reference to first aspect is additionally provided with interface on the interface board in a kind of possible embodiment
Circuit is protected, the interface protective circuit is able to suppress the satellite platform and exports surge to the satellite load system.
Embodiment with reference to first aspect, in a kind of possible embodiment, the interface protective circuit is integrated
Interface chip.
Embodiment with reference to first aspect, in a kind of possible embodiment, the interface protective circuit be include steady
The voltage regulator circuit of pressure pipe.
Second aspect, the embodiment of the present application provide a kind of satellite system comprising any embodiment institute in first aspect
The satellite load system and satellite platform stated, the satellite load system are connect with the satellite platform.Compared to traditional
Scheme, satellite system provided by the embodiments of the present application reduce the degree of coupling between satellite load system and satellite platform, satellite
Load system can independent iteration update, saving development cycle and time.
Other feature and advantage of the application will be illustrated in subsequent specification, also, partly be become from specification
It is clear that being understood and implementing the embodiment of the present application.The purpose of the application and other advantages can be by written
Specifically noted structure is achieved and obtained in specification and attached drawing.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the application
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.By the way that shown in attached drawing, above and other purpose, the feature and advantage of the application will be more clear.In whole
Identical appended drawing reference indicates identical part in attached drawing.Attached drawing, emphasis deliberately are not drawn by actual size equal proportion scaling
It is that the purport of the application is shown.
Fig. 1 shows a kind of one of the structural schematic diagram of satellite load system provided by the present application.
Fig. 2A shows a kind of schematic diagram of the interface board of satellite load system provided by the present application.
Fig. 2 B shows a kind of schematic diagram of the data converting circuit of interface board provided by the present application.
Fig. 2 C shows a kind of schematic diagram of the first interface circuit of interface board provided by the present application.
Fig. 2 D shows a kind of schematic diagram of the second interface circuit of interface board provided by the present application.
Fig. 3 A shows a kind of second structural representation of satellite load system provided by the present application.
Fig. 3 B shows a kind of third structural representation of satellite load system provided by the present application.
Fig. 4 shows the four of the structural schematic diagram of a kind of satellite load system provided by the present application.
Fig. 5 shows a kind of schematic diagram of switching circuit comprising metal-oxide-semiconductor provided by the present application.
Fig. 6 shows the five of the structural schematic diagram of a kind of satellite load system provided by the present application.
Fig. 7 shows a kind of structural schematic diagram of satellite system provided by the present application.
Icon: 100- satellite load system；110- load mainboard；111- power management plate；112- first performance plate；113-
Second performance board；120- interface board；121- first interface circuit；122- data converting circuit；123- second interface circuit；200-
Satellite system；210- satellite platform.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present application, technical solutions in the embodiments of the present application is described.It is aobvious
So, the embodiments are a part of the embodiments of the present invention rather than all of the embodiments.
It should also be noted that similar label and letter indicate similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need that it is further defined and explained in subsequent attached drawing.
Meanwhile the terms "include", "comprise" or any other variant thereof is intended to cover non-exclusive inclusion, to make
Obtaining the process, method, article or equipment including a series of elements not only includes those elements, but also including not arranging clearly
Other element out, or further include for elements inherent to such a process, method, article, or device.Not more
In the case where limitation, the element that is limited by sentence " including ... ", it is not excluded that including process, method, the object of the element
There is also other identical elements in product or equipment.
Meanwhile the relational terms of such as " first ", " second " or the like are used merely to one in the description of the present application
Entity or operation are distinguished with another entity or operation, without necessarily requiring or implying between these entities or operation
There are any actual relationship or orders.
Furthermore term "and/or" in the application, only a kind of incidence relation for describing affiliated partner, expression can deposit
In three kinds of relationships, for example, A and/or B, can indicate: individualism A exists simultaneously A and B, these three situations of individualism B.
In addition, being applicant by practicing simultaneously for defect present in satellite load system in the prior art
It is being obtained after carefully studying as a result, therefore, the discovery procedure of defect present in satellite load system in the prior art and
The hereinafter solution that the embodiment of the present application is proposed in view of the foregoing drawbacks all should be that applicant is right during the application
The contribution that the application makes.
In the embodiment of the present application, satellite system includes satellite platform and satellite load system.Satellite platform by with defend
Multiple functions may be implemented in spaceborne G system connection, such as can be realized the functions such as DATA REASONING, data detection.
Optionally, in the embodiment of the present application, satellite can be a cube star.
In order to make it easy to understand, satellite load system provided by the embodiment of the present application will be introduced below.
Referring to Fig. 1, the embodiment of the present application provides a kind of satellite load system 100, may include load mainboard 110 and
The interface board 120 being connect with load mainboard 110.
Wherein, interface board 120 is printed circuit board, is internally provided with modular integrated circuit in printed circuit board.
In the embodiment of the present application, since the integrated circuit in interface board 120 has the effect of signal transmission, load mainboard 110
It can directly be realized and be connected by interface board 120 and satellite platform 210.Further, since integrated circuit is arranged in interface board 120
Portion is hardly damaged.
The data format as used by different satellite platform sides may be inconsistent, leads to the production of different satellite platform sides
Product data are incompatible.In this case, when satellite load system side needs to provide satellite load system for the satellite platform side A
When, it needs to customize construction satellite load system according to the interface protocol of the satellite platform side A；When satellite load system side needs for B
When satellite platform side provides satellite load system, need to customize construction satellite load system according to the interface protocol of the satellite platform side B
System.Therefore, for satellite load system side, for different satellite platform sides, just functionally identical or similar defend is needed
Spaceborne G system develops design again, and to be adapted to corresponding satellite platform, this makes the plenty of time be wasted for being repeated
The work of property, causes the update cycle longer, wastes time and resource.
To solve the above-mentioned problems, Fig. 2A is please referred to, as an alternative embodiment, integrated in interface board 120
Circuit may include first interface circuit 121, second interface circuit 123 and data converting circuit 122.
Wherein, data converting circuit 122 is connect with first interface circuit 121, second interface circuit 123 respectively, and first connects
Mouth circuit 121 with load mainboard 110 for connecting, and second interface circuit 123 with satellite platform 210 for connecting.
Data converting circuit 122 can be used for receiving the load data of the transmitting of load mainboard 110, and load data is converted
At the data format that satellite platform 210 is adapted to, and the load data after change data format is transmitted to satellite platform 210 again,
Satellite platform 210 is enabled to directly obtain the load data of adaptation data format.It is set when in satellite load system 100
After setting data converting circuit 122, for satellite load system platform side, function can be made by the way that interface board 120 is arranged
Identical/similar satellite load system 100 is adapted to the satellite platform 210 of different satellite platform sides, saves development cycle and time.
Further, since the setting of data converting circuit 122, so that satellite load system 100 and the digital signal phase in satellite platform 210
Mutually isolation reduces the degree of coupling of the two, and therefore, satellite load system 100 can keep a relatively independent environment, just
It is updated in the independent iteration of realization.
Optionally, data converting circuit 122 can be the IC chip for having signal handling capacity, for example, Fig. 2 B
Shown in STM32F103C8T6 type single-chip microcontroller.First interface circuit 121 can be the connection with differential signal pooling function
Device, for example, SPI-ETH1 type connector shown in fig. 2 C.Second interface circuit 123 can be with slip sub-signal function
Connector, for example, 52PIN type connector shown in Fig. 2 D.
Incorporated by reference to Fig. 2A-Fig. 2 D, optionally, if load mainboard 110 is communicated using ethernet communication mode, then the
Pin such as the 3rd pin to the 6th pin on one interface circuit 121 can be by Ethernet and data converting circuit 122
Pin such as the 33rd pin to the 36th pin is correspondingly connected with and pin such as the 1st pin on first interface circuit 121 and
2 pins can be connect by Ethernet with load mainboard 110.Certainly, it is worth noting that, above-mentioned connection type is the present embodiment
Exemplary approach, should not be used as the restriction of the present embodiment；For example, by the definition to pin on first interface circuit 121,
Pin such as the 1st pin on first interface circuit 121 can be corresponded to the 4th pin to be connect with data converting circuit 122, and the
Pin such as the 5th pin and the 6th pin on one interface circuit 121 can then be corresponded to and be connect with load mainboard 110.Wherein, number
It can be connected by programming definition with first interface circuit 121 according to any 4 pins in the PB pin on conversion circuit 122
It connects.
Pin on data converting circuit 122 can be adapted to SPI (Serial Peripheral Interface, serially
Peripheral Interface) communication mode connect with second interface circuit 123.For example, the pin on data converting circuit 122, such as the
20 pins to the 23rd pin can be by corresponding pin such as the 19th pin on second interface circuit 123 of spi bus extremely
The connection of 22nd pin.Certainly, data converting circuit 122 is connect using the 20th pin to the 23rd pin with second interface circuit 123
For the exemplary approach of the present embodiment, the restriction of the present embodiment should not be used as；For example, the PA on data converting circuit 122 draws
Any 4 pins in foot can be connect by programming definition with second interface circuit 123.
Certainly, second interface circuit 123 uses the 19th pin to the 22nd pin to connect with data converting circuit 122 also as this
The exemplary approach of embodiment also should not be used as the restriction of the present embodiment；For example, the on second interface circuit 123 the 29th draws
Foot to the 32nd pin can be connect by SPI line with data converting circuit 122.
Pin on second interface circuit 123 can be connect in a manner of being adapted to satellite platform 210 with satellite platform 210.
For example, if the communication mode that uses of satellite platform 210 is CAN (Controller Area Network, controller local area network)
Communication, then pin such as the 1st pin and the 2nd pin on second interface circuit 123 can pass through CAN bus and satellite platform
210 connections.Certainly, second interface circuit 123 is connected as the present embodiment using the 1st pin and the 2nd pin and satellite platform 210
Exemplary approach should not be used as the restriction of the present embodiment；For example, if the communication mode that uses of satellite platform 210 is I2C
(Inter-Integrated Circuit, IC bus) communicates, the 3rd pin and the 4th on second interface circuit 123
Pin can pass through I2C bus is connect with satellite platform 210.
In one embodiment, referring to Fig. 3 A, load mainboard 110 includes first performance plate 112 and the second performance board 113.
Optionally, first performance plate 112 can be used for handling the task of reduction process demand, such as the state for responding satellite system is looked into
The tasks (enquiry frequency of satellite system can achieve nearly once per second) such as inquiry；Second performance board 113 can be used for handling eminence
(frequency for executing high-frequency algorithm at present may be exactly one to the high frequency algorithms such as the task of reason demand, such as execution image procossing
It or unlatching in several days are primary, once possible 10 points of kinds).
Since the task that first performance plate 112 and the second performance board 113 execute is different, satellite load system 100 is right
The work opening time of first performance plate 112 and the second performance board 113 requires different.Preferably, on first performance plate 112
Be provided with electric power management circuit, the electric power management circuit be used to switch on and off the electric energy that is provided to the second performance board 113 with
Realize the power management to the second performance board 113.Such as to control the second performance board 113 not normally open, is only needing to be implemented task
Shi Kaiqi is conducive to through electric power management circuit come power saving, furthermore all concentrates on a performance board compared to all tasks
The mode handled can reduce the cost of satellite load system 100.
In another embodiment, Fig. 3 B is please referred to, individual power supply pipe can also be arranged in the electric power management circuit
It manages on plate 111.In this embodiment, the load mainboard 110 is other than including first performance plate 112 and the second performance board 113,
It can also include power management plate 111, wherein first performance plate 112 is connect with the second performance board 113, and power management plate 111 divides
It is not connect with first performance plate 112 and the second performance board 113, for controlling first performance plate 112 and the second performance board 113
Open and close.After distributing different tasks for first performance plate 112 and the second performance board 113, entire satellite load
Subsystem 100 requires the work opening time of first performance plate 112 and the second performance board 113 different.In this case,
Power management plate 111 controls the open and close of first performance plate 112 and the second performance board 113, realizes different
Power management.Such as to control the second performance board 113 not normally open, control first performance plate 112 is normally open, is conducive to pass through power supply
Management board 111 carrys out power saving.
Further, since the limited mass that satellite itself can carry, therefore, in order to limit itself weight, on satellite
Bus connection wire is generally arranged thinner, causes the internal resistance of satellite platform 210 relatively large.Entire satellite system can be because of load
The variation of electric current generates biggish voltage fluctuation, causes surge, is unfavorable for the stability of entire satellite system.It is entire in order to increase
The stability of satellite system optionally please refers to Fig. 4, can have Surge suppression function by being arranged on first performance plate 112
It is flat to satellite to reduce surge come the surge for inhibiting satellite load system 100 to export to the satellite platform 210 for the switching circuit of energy
The influence of voltage on platform 210.
Switching circuit can have diversified forms, for example, switching circuit can be packet in a kind of possible embodiment
Include the switching circuit of thermistor；In a kind of possible embodiment, switching circuit can be the switch of mechanical structure；One
In the possible embodiment of kind, switching circuit can also be the switching circuit for including field-effect tube (metal-oxide-semiconductor).
When there is sunshine on satellite, temperature is higher on star, and when not having sunshine on satellite, temperature is lower on star, i.e., whether there is or not
Day note causes the temperature on star to generate violent variation.Since the work of thermistor depends on temperature, temperature change is to heat
Quick resistance is affected, therefore, when switching circuit be include the switching circuit of thermistor when, implement as a kind of optional
Mode, satellite load system 100 or satellite platform 210 can also be attached with temperature control subsystem.Temperature control subsystem can be with
Temperature is adjusted, the stability of temperature on star is maintained, so as to thermistor normal work.
Being with switching circuit below includes that the switching circuit of metal-oxide-semiconductor is illustrated.
Please refer to Fig. 5, Fig. 5 shows a kind of circuit diagram of the metal-oxide-semiconductor switching circuit under embodiment.In figure, metal-oxide-semiconductor is opened
Powered-down road may include first diode D1, first resistor R1, second resistance R2,3rd resistor R3, the 4th resistance R4, the first electricity
Hold C1, the first triode Q2 and the first metal-oxide-semiconductor Q1.
Wherein, the first metal-oxide-semiconductor Q1 is p-type metal-oxide-semiconductor.Certainly, in other embodiments, the first metal-oxide-semiconductor Q1 may be N
Type metal-oxide-semiconductor.
The drain D of first metal-oxide-semiconductor Q1 is connect with external load (end Power_out), such as one the second capacitor of connection.The
The second resistance R2 and first capacitor C1 of the source S connection parallel connection of one metal-oxide-semiconductor Q1, the first of second resistance R2 and first capacitor C1
For connecting with external power supply (end Power_in), the second tie point A2 of second resistance R2 and first capacitor C1 connect tie point A1
Connect between the grid G and switch control unit K1 of the first metal-oxide-semiconductor Q1, the grid G of the first metal-oxide-semiconductor Q1 also with switch control list
First K1 connection.
Switch control unit K1 is opened or closed for control switch circuit.Wherein, the grid G of the first metal-oxide-semiconductor Q1 connects
Meet first resistor R1；The collector of first triode Q2 is connect with one end of first resistor R1, the emitter of the first triode Q2
The base stage of ground connection, the first triode Q2 connects 3rd resistor R3；A termination fourth of the 3rd resistor R3 far from the first triode Q2
Resistance R4；4th resistance R4 ground connection；The negative sense conduction terminal of first diode D1 be connected to 3rd resistor R3 and the 4th resistance R4 it
Between, the forward conduction end of first diode D1 is connect with switch terminals (end Switch).
Certainly, it is worth noting that, what said switching circuit was merely exemplary, it will be understood that the structure of switching circuit
It can also be increased and decreased according to actual needs.
In figure, it is assumed that the end Power_in voltage is 5V.When the end Switch is without input, the first metal-oxide-semiconductor Q1 is by the 4th resistance
R4 drop-down effect is in high resistant off state, and the end Power_out is without output electric current；When the input end Switch obtains a high level
When open signal, since the charging of first capacitor C1 acts on, so that the internal resistance of the first metal-oxide-semiconductor Q1 is gradually reduced, subsequent Q1 is complete
It opens, the late-class circuit of the first metal-oxide-semiconductor Q1 enters working condition.Due to the effect of the circuit, completion is powered on after booting to rear class
The precharge of capacitor, but also the electric current of entire start process can inhibit in a lower state, to inhibit surge.
Optionally, when switching circuit be include the switching circuit of metal-oxide-semiconductor when, satellite load system 100 or satellite platform
210 can also be attached with temperature control subsystem.
Certainly, if temperature control subsystem temperature control is unstable or the positional distance temperature control subsystem of switching circuit farther out so that opening
Powered-down road can not adjusting effectively by temperature control subsystem when, be likely to result in certain form of switching circuit (such as comprising heat
The switching circuit of quick resistance) reliably working can not be carried out.At this point, for metal-oxide-semiconductor, when work, is become by temperature and temperature
The influence of change is smaller, and difference variation is depended on unlike thermistor and is worked.Therefore, using the switch electricity comprising metal-oxide-semiconductor
Road can provide the effect of more reliable inhibition surge.
As an alternative embodiment, please refer to Fig. 6, when being provided with interface protective circuit on the interface board 120
When, the interface protective circuit is able to suppress satellite platform 210 and exports surge to satellite load system 100.In general, being used for
Inhibit the interface protective circuit of surge that there is the input/output characteristic of stronger driving capability and high impedance, electricity can be absorbed
The spike of stream, thus the surge for inhibiting the spike due to electric current to be formed.
As an alternative embodiment, the interface protective circuit also can be set on the load mainboard 110.
Optionally, interface protective circuit also can have diversified forms, for example, resistance current-limiting type, pressure stabilizing tubular type, may be used also
Integrated interface chip is thought, for example, the integrated chip of model sn74avc4t774 can be used.
When directlying adopt integrated interface chip, the traffic rate of whole system is higher, meanwhile, it is hardly damaged.
Certainly, it is worth noting that, what the model of said chip was merely exemplary, it will be understood that other have high drive
The integrated chip of the input/output characteristic of kinetic force and high impedance can also be used as interface protective circuit.
In addition, please referring to Fig. 7, the embodiment of the present application provides a kind of satellite system 200, which may include
Satellite load system 100 and satellite platform 210 described in any of the above-described embodiment.
Wherein, satellite load system 100 is connect with satellite platform 210.Certainly, satellite platform 210 is connect with satellite, thus
So that satellite load system 100 and satellite are realized and connected, it is able to be communicated.
Optionally, above-mentioned satellite can be a cube star.
Certainly, as an alternative embodiment, in addition to satellite load system 100, satellite system 200 can also include
Other subsystems, such as heating power subsystem, communication subsystem, temperature control subsystem etc..Other subsystems and satellite platform 210 connect
It connects, provides corresponding function for satellite.Wherein, temperature control subsystem can control temperature, so that the temperature on satellite is protected
It holds within the scope of one metastable, is worked normally convenient for other subsystems.
In conclusion the embodiment of the present application provides a kind of satellite load system 100 and satellite system 200, satellite load
System 100 includes load mainboard 110 and interface board 120.Wherein, interface board 120 includes data converting circuit 122, and being used for will
For data conversion in the load mainboard 110 at the format being adapted to satellite platform 210, load mainboard 110 passes through interface board 120
It is attached with satellite platform 210, so that establishing communication between satellite load system 100 and satellite.Compared to traditional scheme,
The embodiment of the present application reduces the degree of coupling between satellite load system 100 and satellite platform 210, and satellite load system 100 can
With the update of independent iteration, meanwhile, it can be adapted to different satellite platforms 210, save development cycle and time.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Those familiar with the art within the technical scope of the present application, can easily think of the change or the replacement, and should all contain
Lid is within the scope of protection of this application.
It should be noted that all the embodiments in this specification are described in a progressive manner, each embodiment weight
Point explanation is the difference from other embodiments, and the same or similar parts between the embodiments can be referred to each other.
Claims (10)
1. a kind of satellite load system, which is characterized in that the satellite load system include load mainboard and with the load master
Plate connection interface board, the interface board includes data converting circuit, for by the data conversion in the load mainboard at
The format of satellite platform adaptation, the load mainboard are connect by the interface board with the satellite platform.
2. satellite load system according to claim 1, which is characterized in that the interface board further includes first interface circuit
And second interface circuit, the data converting circuit respectively with first interface circuit, the second interface circuit connection, described
One interface circuit with load mainboard for connecting, and the second interface circuit with the satellite platform for connecting.
3. satellite load system according to claim 1, which is characterized in that the load mainboard include first performance plate with
And second performance board, the first performance plate are connect with second performance board, are provided with power supply pipe on the first performance plate
Circuit is managed, the electric power management circuit is used to switch on and off the electric energy provided to second performance board.
4. satellite load system according to claim 3, which is characterized in that the electric power management circuit includes switch electricity
Road, the switching circuit are able to suppress the satellite load system and export surge to the satellite platform.
5. satellite load system according to claim 4, which is characterized in that the switching circuit includes field-effect tube.
6. satellite load system according to claim 5, which is characterized in that the switching circuit further includes switch control list
The drain electrode of member, the field-effect tube is connect with external load, the source electrode of field-effect tube connection second resistance in parallel and the
One capacitor, the second resistance are used to connect with external power supply with the first tie point of the first capacitor, the second resistance
It is connected between the grid and the switch control unit of the field-effect tube with the second tie point of the first capacitor, institute
The grid for stating field-effect tube is also connect with the switch control unit.
7. satellite load system according to claim 1, which is characterized in that be provided with interface protection electricity on the interface board
Road, the interface protective circuit are able to suppress the satellite platform and export surge to the satellite load system.
8. satellite load system according to claim 7, which is characterized in that the interface protective circuit is integrated interface
Chip.
9. satellite load system according to claim 7, which is characterized in that the interface protective circuit be include voltage-stabiliser tube
Voltage regulator circuit.
10. a kind of satellite system, which is characterized in that including satellite load system of any of claims 1-9 and
Satellite platform, the satellite load system are connect with the satellite platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920948317.6U CN209642671U (en) | 2019-06-21 | 2019-06-21 | Satellite load system and satellite system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920948317.6U CN209642671U (en) | 2019-06-21 | 2019-06-21 | Satellite load system and satellite system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111427332A (en) * | 2020-03-31 | 2020-07-17 | 成都星时代宇航科技有限公司 | Space experiment platform and experiment method |
| CN112564763A (en) * | 2020-11-23 | 2021-03-26 | 中国人民解放军国防科技大学 | Universal digital satellite load hardware platform |
-
2019
- 2019-06-21 CN CN201920948317.6U patent/CN209642671U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111427332A (en) * | 2020-03-31 | 2020-07-17 | 成都星时代宇航科技有限公司 | Space experiment platform and experiment method |
| CN111427332B (en) * | 2020-03-31 | 2021-02-02 | 成都星时代宇航科技有限公司 | Space experiment platform and experiment method |
| CN112564763A (en) * | 2020-11-23 | 2021-03-26 | 中国人民解放军国防科技大学 | Universal digital satellite load hardware platform |
| CN112564763B (en) * | 2020-11-23 | 2022-11-01 | 中国人民解放军国防科技大学 | Universal digital satellite load hardware platform |
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