A standard bus controller

Abstract

A standard bus controller comprises an order interface, a bus output interface, a bus input interface, a data interface, a contact configuring and enabling interface, a configuration register interface, a clock input interface, an IFU module, a TXU module, an RXU module, an LSU module, a CTU module, an REG module and a CKU module. The IFU module, the TXU module, the RXU module, the LSU module, the CTU module, the REG module and the CKU module are correspondingly connected with the order interface, the bus output interface, the bus input interface, the data interface, the contact configuring and enabling interface, the configuration register interface and the clock input interface. According to the bus controller, a computer with architecture based on an ARINC659 fault tolerant bus or other electronic systems can be designed. The standard bus controller can be transplanted to different platforms, especially various platforms, such as a high-reliability-level anti-fuse wire and an FPGA and SOC chip, the various platforms are capable of meeting the space radiation preventing characteristics, and the designing and using requirements of spaceborne computers or other spaceborne electronic systems can be met.

Description

technical field [0001] The invention relates to the bus architecture of the on-board system, in particular to a bus controller conforming to the standard of "ARINC Backplane Data Bus, ARINC Specification 659[S].1993.". Background technique [0002] Traditional spaceborne systems generally adopt the architecture of "multi-mode redundancy + result arbitration" to improve reliability. Although this architecture is simple and easy to implement, the distribution of various functions is highly concentrated, which brings the following problems: wiring management is complicated , and different wiring must be used for different functional modules, making the design more difficult; due to the centralized distribution of functions and the sharing of clocks, peripheral circuits, etc., it is extremely difficult to detect, isolate and reconstruct faults; the control between functional modules Interrelated, any local modification will affect a wide range of other functional modules, which ...

AI Technical Summary

Problems solved by technology

[0002]Traditional spaceborne systems generally adopt the architecture of "multi-mode redundancy + result arbitration" to improve reliability. Although this architecture is simple and easy to implement, the The distribution is highly concentrated, which brings the following problems: the wiring management is complicated, and different wiring must be used for different functional modules, which increases the difficulty of design; due to the centralized function distribution and shared clocks, peripheral circuits, etc., fault detection, failure Isolation and reconstruction are extremely difficult; the controls between functional modules are interrelated, and any local modification will affect a wide range of other functional modules, which is not conducive to the software and hardware upgrade of subsequent products

[0007] Disadvantages: Although the functions of the ARINC 659 communication protocol can be fully realized, its chip products do not have radiation resistance hardening indicators, so they cannot be applied to aerospace electronic equipment; and because HK659 is a hard-core product, it is not portable, so It cannot meet the application requirements of aerospace by transplanting to high-level devices

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