Persistent Link:
http://hdl.handle.net/10150/605417
Title:
AIFTDS-4000, A FLEXIBLE HIGH SPEED DATA ACQUISITION SYSTEM
Author:
Borek, Robert W.
Affiliation:
Aeronautics and Space Administration
Issue Date:
1973-10
Rights:
Copyright © International Foundation for Telemetering
Collection Information:
Proceedings from the International Telemetering Conference are made available by the International Foundation for Telemetering and the University of Arizona Libraries. Visit http://www.telemetry.org/index.php/contact-us if you have questions about items in this collection.
Publisher:
International Foundation for Telemetering
Journal:
International Telemetering Conference Proceedings
Abstract:
The data acquisition system of today’s research aircraft generally consists of a multiplicity of “black boxes” linked together by wiring cables of various lengths and sizes. This approach offers the user an “off-the shelf” type of flexibility to which he has become accustomed. It does not, however, provide for all the needs of an results demanded by today’s technology. The rising costs of flight test hours, the sophisticated airframes, and the minimum flight time allotted for actual flight test indicate a need to review existing data acquisition system technology and apply up-to-date technology. The NASA Flight Research Center at Edwards, California, initiated a review of its needs in the area of airborne data acquisition systems. The result was a new and powerful system called “AIFTDS-4000” (Airborne Integrated Flight Test Data System). AIFTDS is a high speed computer-controlled PCM system comprised of three basic units, the remote multiplexer de-multiplexer unit, the PCM processor, and the memory unit. The three units were designed and tested to meet the requirements of pertinent Mil-Specs for high performance aircraft. The signal conditioning, sensor excitation, and time code generator were designed as an integral part of the system and are not separate chassis. This paper discusses the design objectives established prior to actual hardware construction and compares these objectives with the final hardware.
Sponsors:
International Foundation for Telemetering
ISSN:
0884-5123; 0074-9079
Additional Links:
http://www.telemetry.org/

Full metadata record

DC FieldValue Language
dc.language.isoen_USen
dc.titleAIFTDS-4000, A FLEXIBLE HIGH SPEED DATA ACQUISITION SYSTEMen_US
dc.contributor.authorBorek, Robert W.en
dc.contributor.departmentAeronautics and Space Administrationen
dc.date.issued1973-10en
dc.rightsCopyright © International Foundation for Telemeteringen
dc.description.collectioninformationProceedings from the International Telemetering Conference are made available by the International Foundation for Telemetering and the University of Arizona Libraries. Visit http://www.telemetry.org/index.php/contact-us if you have questions about items in this collection.en
dc.publisherInternational Foundation for Telemeteringen
dc.description.abstractThe data acquisition system of today’s research aircraft generally consists of a multiplicity of “black boxes” linked together by wiring cables of various lengths and sizes. This approach offers the user an “off-the shelf” type of flexibility to which he has become accustomed. It does not, however, provide for all the needs of an results demanded by today’s technology. The rising costs of flight test hours, the sophisticated airframes, and the minimum flight time allotted for actual flight test indicate a need to review existing data acquisition system technology and apply up-to-date technology. The NASA Flight Research Center at Edwards, California, initiated a review of its needs in the area of airborne data acquisition systems. The result was a new and powerful system called “AIFTDS-4000” (Airborne Integrated Flight Test Data System). AIFTDS is a high speed computer-controlled PCM system comprised of three basic units, the remote multiplexer de-multiplexer unit, the PCM processor, and the memory unit. The three units were designed and tested to meet the requirements of pertinent Mil-Specs for high performance aircraft. The signal conditioning, sensor excitation, and time code generator were designed as an integral part of the system and are not separate chassis. This paper discusses the design objectives established prior to actual hardware construction and compares these objectives with the final hardware.en
dc.description.sponsorshipInternational Foundation for Telemeteringen
dc.identifier.issn0884-5123en
dc.identifier.issn0074-9079en
dc.identifier.urihttp://hdl.handle.net/10150/605417en
dc.identifier.journalInternational Telemetering Conference Proceedingsen
dc.typetexten
dc.typeProceedingsen
dc.relation.urlhttp://www.telemetry.org/en
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