Spaceborne-software reliability design system and method based on software redundancy

A technology for software redundancy and system design, which is applied in the direction of data error detection, calculation, and response error generation, which can solve the problems that cannot fully guarantee the correctness of codes in EEPROM, and meet the requirements of on-orbit Maintainability requirements, improved reliability, avoiding paralysis effects

Inactive Publication Date: 2017-12-26
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

This method can basically solve the software reliability problem when the probability of single event flipping is extremely low, such as low-orbit satellites, but for medium-high orbi

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  • Spaceborne-software reliability design system and method based on software redundancy
  • Spaceborne-software reliability design system and method based on software redundancy
  • Spaceborne-software reliability design system and method based on software redundancy

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Embodiment Construction

[0028] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0029] Such as Figure 1 to Figure 2 As shown, the on-board software reliability design system based on software redundancy of the present invention includes an embedded processor, EEPROM, PROM, and SRAM. The EEPROM is used to store the full-featured application code of the on-board software, and the PROM is used to store the The simplest control mode application code, the embedded processor is used as the hardware core to access and process instructions or data in each memory, and the SRAM is used for static random access to data in the embedded processor.

[0030] The EEPROM adopts the method of triple redundancy to store the full-function application code of the on-board software, that is, store three copies of the same code in three different physical chips, and obtain the correct co...

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Abstract

The invention discloses a spaceborne-software reliability design system and method based on software redundancy. The spaceborne-software reliability design system based on the software redundancy includes an embedded processor, an EEPROM, a PROM and an SRAM. The EEPROM is used for storing full-function application code of spaceborne software. The PROM is used for storing a simplest-control-mode application code of the spaceborne software. The embedded processor is used as a hardware core, and for accessing and processing instructions or data in the various memories. The SRAM is used for statically and randomly accessing data in the embedded processor. According to the spaceborne-software reliability design system and method based on the software redundancy of the invention, breakdown of spaceborne-computer functions is avoided, reliability of the software is improved, and an on-orbit maintainability requirement of the software is satisfied at the same time. The system and method adapt to a development trend that satellite application functions can be upgraded on orbit.

Description

technical field [0001] The invention relates to a system and method for reliability design of on-board software, in particular to a system and method for reliability design of on-board software based on software redundancy. Background technique [0002] As embedded software, the on-board software runs on the satellite platform or a stand-alone payload, and cooperates with other software and hardware on the satellite to complete various functions. The on-board software is generally stored in storage media such as PROM (Programmable Read-Only Memory) or EEPROM (Electrically Erasable Programmable Read-Only Memory) of the on-board computer. PROM has the characteristics of high reliability, but its non-reprogrammable feature increases the difficulty of software on-orbit maintenance. As the scale of on-board software becomes larger and its functions more complex, the RPOM memory can no longer meet the on-orbit maintainability requirements of the software. For example, the upgrade...

Claims

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Application Information

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IPC IPC(8): G06F11/14
CPCG06F11/1417
Inventor 郭艳丽吴侃侃李美光田华张大伟
Owner SHANGHAI SATELLITE ENG INST
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