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Satellite-borne software load software and hardware decoupling method

A software, hardware, and satellite-borne technology, applied in software design and other directions, to reduce the delay of data transmission, improve efficiency, and reduce the number of data transmission interactions

Active Publication Date: 2020-01-17
XIAN INSTITUE OF SPACE RADIO TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a software-hardware decoupling method for satellite loads, to solve the problem that the satellite load functions are solidified with the hardware, and to meet the software requirements of satellite loads

Method used

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  • Satellite-borne software load software and hardware decoupling method
  • Satellite-borne software load software and hardware decoupling method
  • Satellite-borne software load software and hardware decoupling method

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Experimental program
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Embodiment

[0051] (1) Define the message structure:

[0052] In this embodiment, the bottom layer adopts the Ethernet protocol, and M=8, N=8, P=784, S=32, and T=11960 bits are set.

[0053] 1) The format of the command message is as follows figure 1 shown.

[0054] The command response message consists of 800 bits. The first 8 bits are always 0xAA, which is the message header of the command message. The 9th to 16th bits are the ID of the command. The remaining bits define the command parameters for each command.

[0055] Table 1 Command ID and command parameters

[0056]

[0057]

[0058] 2) The format of the command response message is as follows: figure 2 shown.

[0059] The command response message consists of 800 bits. The first 8 bits are always 0xBB, which is the message header of the command response message. Bits 9 to 16 are the ID of the command received. The remaining bits are the response data defined for each command.

[0060] Table 2 Command Response Defini...

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Abstract

The invention provides a spaceborne software load software and hardware decoupling method, which is realized by the following steps of: defining a message structure which comprises a message header, amessage identifier and bit message content; configuring satellite-borne software in the processor, and multiplexing the logic address of message transmission to a bottom layer communication protocoladdress; the satellite-borne software organizes and sends messages and analyzes received messages according to the message type and the message structure, and communication among all satellite-borne processors is achieved through the configured underlying communication protocol addresses; the processor comprises an FPGA processor and / or a DSP and / or a CPU.

Description

technical field [0001] The invention relates to a method for decoupling software and hardware of a space-borne software-based load, and belongs to the technical field of space-borne software-based loads. Background technique [0002] In the implementation process of the existing space radio system, corresponding programs must be developed for different hardware, and upper-layer application developers have to pay attention to the implementation of the underlying hardware. When the underlying hardware changes, the upper-layer applications will also change accordingly, which makes the system portable. Reusability and reusability are reduced, and at the same time, it makes software development more difficult and the cycle longer. Therefore, in order to improve the cross-platform, portability and reusability of the system, software radio technology develops rapidly, and the decoupling of software and hardware is a key issue of software radio. [0003] In order to realize the dec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F8/20
CPCG06F8/20
Inventor 方海杨旭白琳陈显舟李聪
Owner XIAN INSTITUE OF SPACE RADIO TECH
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