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Non-similar dual-redundancy atmosphere data processing system and method for civil airliner

A technology for atmospheric data and civil passenger aircraft, which is applied in the fields of electrical digital data processing, combination of various digital computers, computers, etc. The effect of suppressing common mode faults

Pending Publication Date: 2021-12-31
CHENGDU KAITIAN ELECTRONICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current safety index of a certain type of passenger aircraft is: the failure rate of losing the airspeed / altitude signal output by a single ADC should not be greater than 2e-5 / hr, and the average failure rate of commonly used devices is roughly 10 -6 ~10 -5 , the single-redundancy design cannot satisfy the safety index

Method used

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  • Non-similar dual-redundancy atmosphere data processing system and method for civil airliner
  • Non-similar dual-redundancy atmosphere data processing system and method for civil airliner
  • Non-similar dual-redundancy atmosphere data processing system and method for civil airliner

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Embodiment 1

[0031] This embodiment proposes a non-similar dual-redundant atmospheric data processing system for civil airliners, which collects atmospheric data, processes the atmospheric data and then transmits it to the host computer; figure 1 As shown, the processing system includes a pressure sensor group, a central processing unit A, and a central processing unit B;

[0032] The pressure sensor group includes a static pressure sensor and a total pressure sensor;

[0033] Both the central processing unit A and the central processing unit B include a CPU module, an A / D conversion module, an electric bridge, an F / D conversion module, a bus interface, a discrete interface, and a memory;

[0034] The CPU module is connected to the A / D conversion module, the F / D conversion module, the bus interface, the discrete interface and the memory respectively; the bridge module is connected to the A / D conversion module; the pressure sensor group is connected to the F / D The conversion module is conn...

Embodiment 2

[0047] This embodiment also proposes a non-similar dual-redundancy air data processing method for civil airliners, such as figure 2 As shown, based on the above-mentioned non-similar double-redundant air data processing system for civil airliners, the dual platforms of central processing unit A and central processing unit B are redundantly paralleled to perform F / D conversion of pressure signals, total temperature resistance acquisition, and external The bus signal is collected, and the air data correction and voting are performed on the collected signal, and the air data after correction and voting are output to the host computer for use.

[0048] Further, in the process of data processing, the central processing unit A is the main redundancy platform, and the central processing unit B is the secondary redundancy platform. The data processing flow of the two platforms is as follows:

[0049] First, perform data interaction between central processing unit A and central proces...

Embodiment 3

[0059] This embodiment provides the calculation of the failure probability of the system of the present invention:

[0060] The non-similar design of the air data computer makes the faults among the various redundancy independent, so as to avoid common mode faults and improve the security and reliability of the computer. According to ARP4761 "Guidelines and methods for the safety assessment process of civil aircraft airborne systems and equipment", there are many methods and models for the analysis of computer system safety, such as fault tree model (FTA), Markov model (MA), correlation diagram (DD) etc., the present invention adopts FTA analysis method, is top event with " air data computer airspeed / altitude signal invalidation ", carries out the fault analysis from top to bottom.

[0061] Such as image 3 As shown, after FTA model modeling, it can be identified that static pressure sensor combination failure X1, full pressure sensor combination failure X2, power supply comb...

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Abstract

The invention provides a non-similar dual-redundancy atmosphere data processing system and method for a civil airliner, and the safety and reliability of the system and the fault-tolerant requirement of fault work are ensured by adopting redundancy design. For performance requirements and technical indexes of the atmospheric data computer, a framework of a redundant parallel type dissimilar dual-redundancy CPU working mode is adopted, possible common-mode faults of software and hardware are effectively restrained, the reliability and safety requirements of the atmospheric data computer are guaranteed, and safety evaluation and analysis are conducted on the atmospheric data computer through a fault tree.

Description

technical field [0001] The invention belongs to the technical field of aerospace atmospheric data collection and processing, and in particular relates to a non-similar dual-redundancy atmospheric data processing system and processing method for civil airliners. Background technique [0002] The air data computer of civil airliner uses the principle of measuring barometric pressure to measure the altitude, speed and other parameters of the aircraft in real time. It is an important system that affects the flight safety of the aircraft and realizes autonomous navigation. Highest). The current safety index of a certain type of passenger aircraft is: the failure rate of losing the airspeed / altitude signal output by a single ADC should not be greater than 2e-5 / hr, and the average failure rate of commonly used devices is roughly 10 -6 ~10 -5 , the single-redundancy design cannot satisfy the safety index. Contents of the invention [0003] Aiming at the above-mentioned defects ...

Claims

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Application Information

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IPC IPC(8): G06F15/17G06F15/177
CPCG06F15/17G06F15/177
Inventor 李旻珺何恩祥谢波杨德祥章德生刘璐
Owner CHENGDU KAITIAN ELECTRONICS
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