CN106527456A

CN106527456A - FPGA system for micro satellite attitude and orbit control computer

Info

Publication number: CN106527456A
Application number: CN201510565507.6A
Authority: CN
Inventors: 李淑范
Original assignee: Harbin Guangkai Technology Development Co Ltd
Current assignee: Harbin Guangkai Technology Development Co Ltd
Priority date: 2015-09-09
Filing date: 2015-09-09
Publication date: 2017-03-22

Abstract

The invention discloses an FPGA system for a micro satellite attitude and orbit control computer, which comprises an FPGA chip, and a clock circuit, a power supply circuit, a serial port circuit, an A/D conversion circuit, a D/A conversion circuit, a storage circuit and a JTAG interface electrically connected with the FPGA chip, wherein the FPGA chip is internally provided with an Avalon bus, and a 32-bit CPU, a UART controller, an A/D conversion controller, a D/A conversion controller, and a storage circuit controller electrically connected with the Avalon bus. The FPGA system for the micro satellite attitude and orbit control computer is good in performance, low in power consumption, can meet requirements of multiple attitude and orbit control modes due to rich and reconfigurable peripheral interfaces, and becomes a multifunctional attitude and orbit control computer.

Description

A kind of FPGA system of microsatellite Attitude and orbit control computer

Technical field

The present invention relates to a kind of Attitude and orbit control computer, and in particular to a kind of FPGA system of microsatellite Attitude and orbit control computer, 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 to benefit 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 what is be designed using chips such as 386, ARM, DSP.Method arithmetic speed using 386CPU is low, and volume and power consumption are undesirable；More fixed using the method hardware configuration of ARM, limit versatility；The method combined using DSP and MCU has that Rhizoma Nelumbinis close 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 above-mentioned technical proposal.

The content of the invention

（One）Technical problem to be solved

For solving the above problems, the present invention proposes a kind of FPGA system of microsatellite Attitude and orbit control computer, and performance is good, low in energy consumption, and rich interface.

（Two）Technical scheme

The FPGA system of the microsatellite Attitude and orbit control computer of the present invention, the clock circuit electrically connected including fpga chip and with fpga chip, power circuit, serial port circuit, A/D change-over circuits, D/A change-over circuits, storage circuit and jtag interface；The fpga chip is internally provided with Avalon buses, and electrically connect with Avalon buses 32 bit CPUs, UART controller, A/D switching controllers, D/A switching controllers, storage circuit controller.

Further, the serial port circuit is electrically connected with UART controller；The A/D change-over circuits are electrically connected with A/D switching controllers；The D/A change-over circuits are electrically connected with D/A switching controllers；The storage circuit is electrically connected with storage circuit controller.

Further, the storage circuit is made up of SRAM, SDRAM and FLASH；The storage circuit controller includes SRAM, SDRAM and FLASH controller.

Further, the serial port circuit includes multichannel RS232, RS422 digital interfaces, and the input of the RS422 digital interfaces is electrically connected with GPS.

Further, the A/D change-over circuits include the A/D acquisition interfaces of duplex high precision, and the input of the A/D acquisition interfaces is electrically connected with gaussmeter, sun sensor and gyro.

Further, the D/A change-over circuits include D/A output interfaces, and the outfan of the D/A output interfaces is electrically connected with momenttum wheel and magnetic torquer.

（Three）Beneficial effect

Compared with prior art, the FPGA system of the microsatellite Attitude and orbit control computer of the present invention, Attitude and orbit control computer performance is good, low in energy consumption, and its abundant and reconfigurable Peripheral Interface makes it possible to adapt to the requirement of various 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 FPGA system of microsatellite Attitude and orbit control computer as shown in Figure 1, the clock circuit electrically connected including fpga chip 1 and with fpga chip 1, power circuit, serial port circuit, A/D change-over circuits, D/A change-over circuits, storage circuit 2 and jtag interface；The fpga chip 1 is internally provided with Avalon buses, and electrically connect with Avalon buses 32 bit CPUs, UART controller, A/D switching controllers, D/A switching controllers, storage circuit controller 3.

The serial port circuit is electrically connected with UART controller；The A/D change-over circuits are electrically connected with A/D switching controllers；The D/A change-over circuits are electrically connected with D/A switching controllers；The storage circuit 2 is electrically connected with storage circuit controller 3.

The storage circuit 2 is made up of SRAM, SDRAM and FLASH；The storage circuit controller 3 includes SRAM, SDRAM and FLASH controller.

The serial port circuit includes multichannel RS232, RS422 digital interfaces, and the input of the RS422 digital interfaces is electrically connected with GPS.

The A/D change-over circuits include the A/D acquisition interfaces of duplex high precision, and the input of the A/D acquisition interfaces is electrically connected with gaussmeter, sun sensor and gyro.

The D/A change-over circuits include D/A output interfaces, and the outfan of the D/A output interfaces 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 are 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 have been recorded in detail in the claims.

Claims

1. a kind of FPGA system of microsatellite Attitude and orbit control computer, it is characterised in that：Clock circuit, power circuit, serial port circuit, A/D change-over circuits, D/A change-over circuits, storage circuit and the jtag interface electrically connected including fpga chip and with fpga chip；The fpga chip is internally provided with Avalon buses, and electrically connect with Avalon buses 32 bit CPUs, UART controller, A/D switching controllers, D/A switching controllers, storage circuit controller.

2. the FPGA system of microsatellite Attitude and orbit control computer according to claim 1, it is characterised in that：The serial port circuit is electrically connected with UART controller；The A/D change-over circuits are electrically connected with A/D switching controllers；The D/A change-over circuits are electrically connected with D/A switching controllers；The storage circuit is electrically connected with storage circuit controller.

3. the FPGA system of microsatellite Attitude and orbit control computer according to claim 1, it is characterised in that：The storage circuit is made up of SRAM, SDRAM and FLASH；The storage circuit controller includes SRAM, SDRAM and FLASH controller.

4. the FPGA system of microsatellite Attitude and orbit control computer according to claim 1, it is characterised in that：The serial port circuit includes multichannel RS232, RS422 digital interfaces, and the input of the RS422 digital interfaces is electrically connected with GPS.

5. the FPGA system of microsatellite Attitude and orbit control computer according to claim 1, it is characterised in that：The A/D change-over circuits include the A/D acquisition interfaces of duplex high precision, and the input of the A/D acquisition interfaces is electrically connected with gaussmeter, sun sensor and gyro.

6. the FPGA system of microsatellite Attitude and orbit control computer according to claim 1, it is characterised in that：The D/A change-over circuits include D/A output interfaces, and the outfan of the D/A output interfaces is electrically connected with momenttum wheel and magnetic torquer.