A system for separating redundancy management of rocket-borne computer processor and external bus interface

Abstract

The invention discloses a system for separated redundancy management between rocket-borne computer processors and external bus interfaces. The system involves the processors, internal bus interface modules, a management module and the external bus interfaces. The processors are used for completing data processing. Data channels between the processors and the management module and between the external bus interfaces and the management module are established through the inner bus interface modules, and data exchange between the processors and the management module and data exchange between the external bus interfaces and the management module are achieved. The management module is used as the kernel of redundancy management. According to the bound redundancy management strategy, data distribution between the different inner bus interface modules is achieved, and functional reconstruction is achieved after one inner bus interface module breaks down. The external bus interfaces are conventional communication interfaces. According to the system structural design method of the system for separated redundancy management between the rocket-borne computer processors and the external bus interfaces, separated redundancy management between the rocket-borne computer processors and the external bus interfaces can be achieved, tight coupling between the processors and the external bus interfaces is eliminated, the reliability of the system is improved, and the system has a high extension capacity.

Description

technical field [0001] The invention relates to a system for separating redundancy management of an rocket-borne processor and an external bus interface, and belongs to the technical field of spacecraft high-reliability computer design. Background technique [0002] In the field of aerospace, various computers, as hardware carriers for realizing functions, require extremely high reliability. At present, high-reliability computers mostly adopt redundant design architecture, and the computer has multiple processing, interfaces and buses inside. Redundancy management strategy to carry out redundancy management. There are many spacecraft systems and stand-alone equipment, and the interfaces between equipment and equipment are complex. At present, in the process of designing spacecraft computers, it is often encountered that the number of processors contained in the computer and the number of external bus interfaces are inconsistent. For example: computer There are 3 processors ...

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Problems solved by technology

With this design method, once the system is designed, the system redundancy management strategy has been determined. Once the external bus interface 1 fails, the corresponding processor 1 will not be able to receive / send data, and it can be determined that the processor 1 will also fail synchronously. , this binding tightly coupled design of the processor and the external bus interface makes the system not capable of dynamic reconfiguration, which invisibly reduces the reliability of the system

[0004] Using the above design method, the system redundancy management framework has been determined. If you want to expand the number of computer processors and external bus interfaces, you need to modify the design of computer hardware and software on a large scale, and the system’s function expansion ability is not strong.

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