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.
![[img]](https://nal-ir.nal.res.in/style/images/fileicons/application_pdf.png) |
PDF
INCAST_2008-013.pdf Download (256kB) |
![[img]](https://nal-ir.nal.res.in/style/images/fileicons/other.png) |
Indexer Terms (Generate index codes conversion from application/pdf to indexcodes)
indexcodes.txt Download (4kB) |
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) |
| Depositing User: | Ms. Alphones Mary |
| Date Deposited: | 24 Feb 2009 |
| Last Modified: | 17 Jun 2010 08:49 |
| URI: | http://nal-ir.nal.res.in/id/eprint/4987 |
Actions (login required)
 |
View Item |
