Sensor data distribution network fault tolerance architecture and method

A technology for data distribution and network failure, applied to redundancy in computing for data error detection, electrical digital data processing, instrumentation, etc. and other problems, to achieve the effect of fast fault tolerance, fast exchange speed, and improved reliability

Pending Publication Date: 2020-04-21
XIAN AVIATION COMPUTING TECH RES INST OF AVIATION IND CORP OF CHINA
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Problems solved by technology

[0002] In the previous signal processing subsystem, various front-end sensors on the aircraft were connected point-to-point with the corresponding signal processing unit, resulting in the signal processing subsystem not having comprehensive processing capabilities, and unable to support the system to realize multi-sensor collaborative detection and multi-sensor data fusion And other functions, and when the signal processing unit corresponding to a certain type of sensor fails, the system will lose the signal processing function of this type of sensor, and the reliability is low
[0003] With the application of integrated modular avionics system technology,

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  • Sensor data distribution network fault tolerance architecture and method
  • Sensor data distribution network fault tolerance architecture and method
  • Sensor data distribution network fault tolerance architecture and method

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[0025] A sensor data distribution network fault-tolerant framework provided by the present invention includes the following:

[0026] 1. The front-end sensors on the aircraft include: communication and navigation identification sensors, radar sensors, photoelectric image sensors, etc. These sensor signals are input to the sensor data distribution network of the integrated signal processing subsystem through the optical fiber channel, such as figure 1 shown;

[0027] 2. The sensor data distribution network can realize the unimpeded exchange of front-end sensor signals of 40 channels × 40 channels at most, and output the sensor signals to different signal processing modules of the integrated signal processing unit according to the network configuration table specified by the system;

[0028] 3. The sensor data distribution network adopts a dual-redundancy design, such as figure 2 As shown, the software and hardware of the two switching networks are exactly the same, and the ho...

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Abstract

The invention provides a sensor data distribution network fault tolerance architecture and method, aiming at the requirement of an integrated avionics system on the reliability of an integrated signalprocessing subsystem. A sensor data distribution network adopts a dual-redundancy design, redundancy adopts a hot backup working mode, fault detection is performed through a heartbeat mechanism, anda system controller manages the sensor data distribution network through a dual-redundancy control channel. According to the fault tolerance method of the sensor data distribution network, the reliability of the comprehensive signal processing subsystem can be effectively improved.

Description

technical field [0001] The invention belongs to the technical field of comprehensive core processing system design, and in particular relates to a sensor data distribution network fault tolerance framework and method. Background technique [0002] In the previous signal processing subsystem, various front-end sensors on the aircraft were connected point-to-point with the corresponding signal processing unit, resulting in the signal processing subsystem not having comprehensive processing capabilities, and unable to support the system to realize multi-sensor collaborative detection and multi-sensor data fusion And other functions, and when the signal processing unit corresponding to a certain type of sensor fails, the system will lose the signal processing function of this type of sensor, and the reliability is low. [0003] With the application of integrated modular avionics system technology, the integrated signal processing subsystem needs to realize the integrated process...

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Application Information

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IPC IPC(8): G06F11/14
CPCG06F11/1489
Inventor 姜琳琳王卫东韩强王纯委张彬海钰琳
Owner XIAN AVIATION COMPUTING TECH RES INST OF AVIATION IND CORP OF CHINA
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