Validation of control parameters for a re-configurable algorithm in a flight critical avionics application

Ananda, CM (2008) Validation of control parameters for a re-configurable algorithm in a flight critical avionics application. In: Proceedings of the International Conference on Aerospace Science and Technology, 26-28 Jun 2008, Bangalore, India.

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    Abstract

    Earlier generation avionics, federated architecture (FA) is used where each function has its own independent, dedicated fault-tolerant computing resources. To overcome few disadvantages of federated architecture, NAL had developed and proposed a re-configurable algorithm for avionics flight13; critical software applications under integrated time and memory partitioned applications. The algorithm13; uses four control parameters, which define the re-configurable state of the system in real time. It also13; preserves the advantages of non-Reconfigurable systems over federated architecture. The availability of13; the avionics applications increases substantially with the use of this new algorithm13; The paper presents a detailed validation process, methodology and data dictionary for control parameters13; namely: re-configurability Information factor, Schedulability Test/TL/UF, Context13; Adaptability/suitability and Context Flight Safety. The algorithm is data centric and interfaces system13; health as control input and initiation of the re-configuration is only after successful evaluation of the13; parameter metrics. The control parameters are validated against the statistical data generated based on the13; system design analysis like FMEA, FHA, SSA and the basic architecture of the system. Since the control13; parameters define the re-configuration state, it is very critical to verify and validate the correctness of the13; control. Parameter characteristic data as it leads to critical action in flight. This enhances the availability13; and reliability of the system under failed conditions by efficient selection and procedural re-configuration13; with safe state exit. Invalid failure of control parameter validation brings the system to safe state. The13; scheme, algorithm and the control parameters validation metrics and their validation approach are13; described with experimentation using VxWorks environment.

    Item Type: Conference or Workshop Item (Paper)
    Additional Information: Copyright for this article belongs to National Aerospace Laboratories
    Uncontrolled Keywords: Flight avionics;Flight safety;VxWorks environment;Defect density measure (DDM)
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Aerospace Electronics and Controls Division
    Depositing User: Ms. Alphones Mary
    Date Deposited: 24 Feb 2009
    Last Modified: 17 Jun 2010 14:19
    URI: http://nal-ir.nal.res.in/id/eprint/4987

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