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

Ananda, CM and Kumar, Rakesh (2008) Validation of control parameters for a re-configurable algorithm used in flight critical avionics application. In: International Conference for Avionics, ICAS, 22-23 Feb 2008, Hyderabad, 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 flight critical software applications under integrated time and memory partitioned applications. The algorithm uses four control parameters, which define the re-configurable state of the system in real time. It also preserves the advantages of non-Reconfigurable systems over federated architecture. The availability of the avionics applications increases substantially with the use of this new algorithm The paper presents a detailed validation process, methodology and data dictionary for control parameters namely: re-configurability Information factor, Schedulability Test/TL/UF, Context Adaptability/suitability and Context Flight Safety. The algorithm is data centric and interfaces system health as control input and initiation of the re-configuration is only after successful evaluation of the parameter metrics. The control parameters are validated against the statistical data generated based on the system design analysis like FMEA, FHA, SSA and the basic architecture of the system. Since the control parameters define the re-configuration state, it is very critical to verify and validate the correctness of the control. Parameter characteristic data as it leads to critical action in flight. This enhances the availability and reliability of the system under failed conditions by efficient selection and procedural re-configuration with safe state exit. Invalid failure of control parameter validation brings the system to safe state. The scheme, algorithm and the control parameters validation metrics and their validation approach are described with experimentation using VxWorks environment.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Flight avionics;Flight safety;VxWorks environment;Defect density measure (DDM)
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Avionics & Aircraft Instrumentation
Division/Department: Aerospace Electronics and Controls Division, Aerospace Electronics and Controls Division
Depositing User: Ms. Alphones Mary
Date Deposited: 10 Nov 2009
Last Modified: 24 May 2010 09:57
URI: http://nal-ir.nal.res.in/id/eprint/5219

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