A dual-cpu single-bus computer system for deep space probes

Abstract

The invention relates to spaceflight control devices, and discloses a double central processing unit (CPU) unibus computer system for a deep space probe. The double CPU unibus computer system comprises a power module (101), a CPU module (102) composed of a CPU A board and a CPU B board, an internal bus (103), a function module (104), an independent monitoring module (105), and a switching module (106). The CPU A board and the CPU B board form dual redundancy. The independent monitoring module (105) is provided with a monitoring circuit on health signals of an A machine and a machine switching control circuit. The switching module (106) is controlled by independent instructions of the independent monitoring module, and opens B and closes A. by adopting an incomplete redundancy and unibus architecture, the double CPU unibus computer system has the functions of independent fault diagnosis and system reconfiguration, all functions of a comprehensive electronic computer can be finished reliably, and a deep space probe platform computer is minimized, lightened, low in energy consumption, and high in reliability.

Description

technical field [0001] The invention relates to aerospace control equipment, in particular to a dual-CPU single-bus computer system for deep space probes. Background technique [0002] In the design and development of traditional aircraft platform computers, the system structure of full dual-machine symmetrical redundancy is generally adopted. That is, a main machine A plus a standby machine B with the same design. The main machine and the standby machine each include a complete power supply module, CPU module and function module. The two machines have independent internal buses and work independently. They are only isolated at the external interface. in parallel. In the cold backup state, the working status of the heat engine is monitored by its own watchdog hardware. There is no independent monitoring module, and the switching command is also issued by the heat engine itself. [0003] Because the aircraft platform computer in the prior art adopts a full-duplex symmetrica...

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Problems solved by technology

[0003] Because the aircraft platform computer in the prior art adopts a full-duplex symmetrical redundant architecture, the volume is too large. For deep space probes, on the one hand, it cannot be miniaturized and lightweight. On the other hand, non-independent monitoring Modules may also affect the reliability of the whole machine

[0004] At present, there is no explanation or report on related technologies similar to the present invention in the field of aerospace control, and similar materials at home and abroad have not been collected yet.

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