CN106477073A - A kind of microsatellite Attitude and orbit control computer system based on SoPC - Google Patents
A kind of microsatellite Attitude and orbit control computer system based on SoPC Download PDFInfo
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- CN106477073A CN106477073A CN201510539509.8A CN201510539509A CN106477073A CN 106477073 A CN106477073 A CN 106477073A CN 201510539509 A CN201510539509 A CN 201510539509A CN 106477073 A CN106477073 A CN 106477073A
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Abstract
The invention discloses a kind of microsatellite Attitude and orbit control computer system based on SoPC, including base plate and core board；The core board is arranged on the centre position of base plate；The upper and lower both sides of the core board are provided with slot；Clock circuit, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit is also equipped with the base plate；Fpga chip, jtag interface and storage circuit is provided with the core board；The fpga chip is electrically connected with clock circuit, power supply, serial port circuit, A/D change-over circuit, D/A change-over circuit, jtag interface and storage circuit.The microsatellite Attitude and orbit control computer system based on SoPC of the present invention, Attitude and orbit control computer performance based on SoPC technology is good, low in energy consumption, its abundant and reconfigurable Peripheral Interface makes it possible to adapt to the requirement of multiple rail control patterns, becomes multi-functional Attitude and orbit control computer.
Description
Technical field
The present invention relates to a kind of computerized equipment, and in particular to a kind of microsatellite Attitude and orbit control computer system based on SoPC, belong to computer equipment technical field.
Background technology
Microsatellite launches a series of advantages such as flexible, low cost, functional density are high, the lead time is short by which, becomes the focus of current international space technical research；Developed country is walked in prostatitis in the technical field, civilian all benefits from it with military aspect；As potentiality of the microsatellite at aspects such as remote sensing, communication, navigation and Space Attacks are constantly mined, it is desirable to microsatellite possesses quick response, without the need for abilities such as ground maintenances after transmitting, and possessing for these abilities is closely related with Attitude and orbit control system.Attitude and orbit control computer plays very important effect in Attitude and orbit control system, and it needs to complete multiple functions such as sensor data acquisition, gesture stability, orbits controlling.In current country's microsatellite Attitude and orbit control computer design, have and be designed using chips such as 386, ARM, DSP.Method arithmetic speed using 386CPU is low, and volume and power consumption all undesirable；More fixed using the method hardware configuration of ARM, limit versatility；The method combined using DSP and MCU has that lotus root closes loose, hardware debugging cycle.Therefore, the Attitude and orbit control computer of high-performance, low-power consumption, rich interface is designed using fpga chip, to make up the deficiency of technique scheme.
Content of the invention
（One）Technical problem to be solved
For solving the above problems, the present invention proposes a kind of microsatellite Attitude and orbit control computer system based on SoPC, and performance is good, low in energy consumption, and rich interface.
（Two）Technical scheme
The microsatellite Attitude and orbit control computer system based on SoPC of the present invention, including base plate and core board；The core board is arranged on the centre position of base plate；The upper and lower both sides of the core board are provided with slot；Clock circuit, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit is also equipped with the base plate；Fpga chip, jtag interface and storage circuit is provided with the core board；The fpga chip is electrically connected with clock circuit, power supply, serial port circuit, A/D change-over circuit, D/A change-over circuit, jtag interface and storage circuit.
Preferably, the base plate is Demountable with core board.
Further, the storage circuit is made up of SRAM, SDRAM and FLASH.
Further, the serial port circuit includes multichannel RS232, RS422 digital interface, and the input of the RS422 digital interface is electrically connected with GPS.
Further, the A/D change-over circuit includes the A/D acquisition interface of duplex high precision, and the input of the A/D acquisition interface is electrically connected with magnetometer, sun sensor and gyro.
Further, the D/A change-over circuit includes D/A output interface, and the output end of the D/A output interface is electrically connected with momenttum wheel and magnetic torquer.
（Three）Beneficial effect
Compared with prior art, the microsatellite Attitude and orbit control computer system based on SoPC of the present invention, Attitude and orbit control computer performance based on SoPC technology is good, low in energy consumption, its abundant and reconfigurable Peripheral Interface makes it possible to adapt to the requirement of multiple rail control patterns, becomes multi-functional Attitude and orbit control computer.
Description of the drawings
Fig. 1 is the overall structure diagram of the present invention.
Specific embodiment
A kind of microsatellite Attitude and orbit control computer system based on SoPC as shown in Figure 1, including base plate 1 and core board 2；The core board 2 is arranged on the centre position of base plate 1；The upper and lower both sides of the core board 2 are provided with slot 3；Clock circuit is also equipped with the base plate 1（Not shown）, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit；Fpga chip, jtag interface and storage circuit is provided with the core board；The fpga chip is electrically connected with clock circuit, power supply, serial port circuit, A/D change-over circuit, D/A change-over circuit, jtag interface and storage circuit.
The base plate 1 is Demountable with core board 2.
The storage circuit is made up of SRAM, SDRAM and FLASH.
The serial port circuit includes multichannel RS232, RS422 digital interface, and the input of the RS422 digital interface is electrically connected with GPS.
The A/D change-over circuit includes the A/D acquisition interface of duplex high precision, and the input of the A/D acquisition interface is electrically connected with magnetometer, sun sensor and gyro.
The D/A change-over circuit includes D/A output interface, and the output end of the D/A output interface is electrically connected with momenttum wheel and magnetic torquer.
Embodiment described above is only that the preferred embodiment of the present invention is described, and not the spirit and scope of the present invention is defined.On the premise of without departing from design concept of the present invention; various modifications and improvement that this area ordinary person is made to technical scheme; protection scope of the present invention all should be dropped into, the technology contents that the present invention is claimed, all record in detail in the claims.
Claims (6)
1. a kind of microsatellite Attitude and orbit control computer system based on SoPC, it is characterised in that：Including base plate and core board；The core board is arranged on the centre position of base plate；The upper and lower both sides of the core board are provided with slot；Clock circuit, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit is also equipped with the base plate；Fpga chip, jtag interface and storage circuit is provided with the core board；The fpga chip is electrically connected with clock circuit, power supply, serial port circuit, A/D change-over circuit, D/A change-over circuit, jtag interface and storage circuit.
2. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, it is characterised in that：The base plate is Demountable with core board.
3. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, it is characterised in that：The storage circuit is made up of SRAM, SDRAM and FLASH.
4. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, it is characterised in that：The serial port circuit includes multichannel RS232, RS422 digital interface, and the input of the RS422 digital interface is electrically connected with GPS.
5. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, it is characterised in that：The A/D change-over circuit includes the A/D acquisition interface of duplex high precision, and the input of the A/D acquisition interface is electrically connected with magnetometer, sun sensor and gyro.
6. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, it is characterised in that：The D/A change-over circuit includes D/A output interface, and the output end of the D/A output interface is electrically connected with momenttum wheel and magnetic torquer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510539509.8A CN106477073A (en) | 2015-08-30 | 2015-08-30 | A kind of microsatellite Attitude and orbit control computer system based on SoPC |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510539509.8A CN106477073A (en) | 2015-08-30 | 2015-08-30 | A kind of microsatellite Attitude and orbit control computer system based on SoPC |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106477073A true CN106477073A (en) | 2017-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510539509.8A Pending CN106477073A (en) | 2015-08-30 | 2015-08-30 | A kind of microsatellite Attitude and orbit control computer system based on SoPC |
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| CN (1) | CN106477073A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108072372A (en) * | 2017-11-28 | 2018-05-25 | 西北工业大学 | A kind of integrated attitude measurement system for microsatellite |
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2015
- 2015-08-30 CN CN201510539509.8A patent/CN106477073A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108072372A (en) * | 2017-11-28 | 2018-05-25 | 西北工业大学 | A kind of integrated attitude measurement system for microsatellite |
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Application publication date: 20170308 |