CN204979274U - Small satellite appearance rail accuse computer system based on soPC - Google Patents
Small satellite appearance rail accuse computer system based on soPC Download PDFInfo
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- CN204979274U CN204979274U CN201520660719.8U CN201520660719U CN204979274U CN 204979274 U CN204979274 U CN 204979274U CN 201520660719 U CN201520660719 U CN 201520660719U CN 204979274 U CN204979274 U CN 204979274U
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- computer system
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Abstract
The utility model discloses a small satellite appearance rail accuse computer system based on soPC, including bottom plate and core board, the core board sets up the intermediate position at the bottom plate, the upper and lower both sides of core board are provided with the slot, still install clock circuit, power, serial circuits, AD converting circuit and DA converting circuit on the bottom plate, be provided with FPGA chip, JTAG interface and memory circuit on the core board, the FPGA chip is connected with clock circuit, power, serial circuits, AD converting circuit, DA converting circuit, JTAG interface and memory circuit electricity. The utility model discloses a small satellite appearance rail accuse computer system based on soPC, based on good, the low power dissipation of appearance rail accuse computing power of soPC technique, reconfiguration's peripheral hardware interface makes it to adapt to the requirement of multiple appearance rail accuse mode but it is abundant, becomes multi -functional appearance rail accuse computer.
Description
Technical field
The utility model relates to a kind of computerized equipment, is specifically related to a kind of microsatellite Attitude and orbit control computer system based on SoPC, belongs to computer equipment technical field.
Background technology
Microsatellite relies on a series of advantages such as it is launched flexibly, cost is low, functional density is high, the lead time is short, becomes the focus of current international space technical study; Developed country walks in prostatitis in this technical field, all benefits from it in civilian and military aspect; Along with the potentiality of microsatellite in remote sensing, communication, navigation and Space Attack etc. are constantly excavated, people wish that microsatellite possesses quick response, without the need to abilities such as ground maintenances after transmitting, and possessing of these abilities is closely-related with Attitude and orbit control system.Attitude and orbit control computer plays a part very important in Attitude and orbit control system, and it has needed multiple functions such as sensor data acquisition, gesture stability, orbits controlling.In current domestic microsatellite Attitude and orbit control computer design, the chip such as employing 386, ARM, DSP is had to carry out designing.Adopt the method arithmetic speed of 386CPU on the low side, and volume and power consumption all undesirable; Adopt the method hardware configuration of ARM comparatively fixing, limit commonality; There is lotus root and close the problems such as loose, the hardware debug cycle is long in the method adopting DSP and MCU to combine.Therefore, the Attitude and orbit control computer of fpga chip design High Performance, low-power consumption, rich interface is adopted, to make up the deficiency of technique scheme.
Summary of the invention
(1) technical matters that will solve
For solving the problem, the utility model proposes a kind of microsatellite Attitude and orbit control computer system based on SoPC, performance is good, low in energy consumption, and rich interface.
(2) technical scheme
Microsatellite Attitude and orbit control computer system based on SoPC of the present utility model, comprises base plate and core board; Described core board is arranged on the midway location of base plate; The upper and lower both sides of described core board are provided with slot; Described base plate is also provided with clock circuit, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit; Described core board is provided with fpga chip, jtag interface and memory circuit; Described 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 memory circuit.
Preferably, described base plate and core board are Demountable.
Further, described memory circuit is made up of SRAM, SDRAM and FLASH.
Further, described serial port circuit comprises multichannel RS232, RS422 digital interface, and the input end of described RS422 digital interface is electrically connected with GPS.
Further, described A/D change-over circuit comprises the A/D acquisition interface of duplex high precision, and the input end of described A/D acquisition interface is electrically connected with magnetometer, sun sensor and gyro.
Further, described D/A change-over circuit comprises D/A output interface, and the mouth of described D/A output interface is electrically connected with momentum wheel and magnetic torquer.
(3) beneficial effect
Compared with prior art, microsatellite Attitude and orbit control computer system based on SoPC of the present utility model, Attitude and orbit control computer performance based on SoPC technology is good, low in energy consumption, it is abundant and reconfigurable Peripheral Interface makes it the requirement that can adapt to multiple rail control pattern, becomes multi-functional Attitude and orbit control computer.
Accompanying drawing explanation
Fig. 1 is integral structure schematic diagram of the present utility model.
Detailed description of the invention
A kind of microsatellite Attitude and orbit control computer system based on SoPC as shown in Figure 1, comprises base plate 1 and core board 2; Described core board 2 is arranged on the midway location of base plate 1; The upper and lower both sides of described core board 2 are provided with slot 3; Described base plate 1 is also provided with clock circuit (not shown), power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit; Described core board is provided with fpga chip, jtag interface and memory circuit; Described 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 memory circuit.
Described base plate 1 is Demountable with core board 2.
Described memory circuit is made up of SRAM, SDRAM and FLASH.
Described serial port circuit comprises multichannel RS232, RS422 digital interface, and the input end of described RS422 digital interface is electrically connected with GPS.
Described A/D change-over circuit comprises the A/D acquisition interface of duplex high precision, and the input end of described A/D acquisition interface is electrically connected with magnetometer, sun sensor and gyro.
Described D/A change-over circuit comprises D/A output interface, and the mouth of described D/A output interface is electrically connected with momentum wheel and magnetic torquer.
Embodiment recited above is only be described preferred implementation of the present utility model, not limits design of the present utility model and scope.Under the prerequisite not departing from the utility model design concept; the various modification that this area ordinary person makes the technical solution of the utility model and improvement; protection domain of the present utility model all should be dropped into; the technology contents of the utility model request protection, all records in detail in the claims.
Claims (6)
1., based on a microsatellite Attitude and orbit control computer system of SoPC, it is characterized in that: comprise base plate and core board; Described core board is arranged on the midway location of base plate; The upper and lower both sides of described core board are provided with slot; Described base plate is also provided with clock circuit, power supply, serial port circuit, A/D change-over circuit and D/A change-over circuit; Described core board is provided with fpga chip, jtag interface and memory circuit; Described 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 memory circuit.
2. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, is characterized in that: described base plate and core board are Demountable.
3. the microsatellite Attitude and orbit control computer system based on SoPC according to claim 1, is characterized in that: described memory 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 characterized in that: described serial port circuit comprises multichannel RS232, RS422 digital interface, and the input end of described 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 characterized in that: described A/D change-over circuit comprises the A/D acquisition interface of duplex high precision, and the input end of described 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 characterized in that: described D/A change-over circuit comprises D/A output interface, and the mouth of described D/A output interface is electrically connected with momentum wheel and magnetic torquer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520660719.8U CN204979274U (en) | 2015-08-30 | 2015-08-30 | Small satellite appearance rail accuse computer system based on soPC |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520660719.8U CN204979274U (en) | 2015-08-30 | 2015-08-30 | Small satellite appearance rail accuse computer system based on soPC |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204979274U true CN204979274U (en) | 2016-01-20 |
Family
ID=55113668
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520660719.8U Expired - Fee Related CN204979274U (en) | 2015-08-30 | 2015-08-30 | Small satellite appearance rail accuse computer system based on soPC |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204979274U (en) |
-
2015
- 2015-08-30 CN CN201520660719.8U patent/CN204979274U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160120 Termination date: 20160830 |