Accession Number : ADP004120

Title :   The Development of an Airborne Instrumentation Computer System for Flight Test,

Corporate Author : NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

Personal Author(s) : Bever,G. A.

Report Date : JUL 1984

Pagination or Media Count : 13

Abstract : Instrumentation interfacing frequently requires the linking of intelligent systems together, as well as requiring the link itself to be intelligent. The airborne instrumentation computer system (AICS) was developed to address this requirement. Its small size, approximately 254 by 133 by 140-mm, standard bus, and modular-board configuration give it the ability to solve instrumentation interfacing and computation problems without forcing a redesign of the entire unit. This system has been used on the F-15 aircraft digital electronic engine control (DEEC) and its follow-on engine model derivation (EMD) project, and in an OV-1C Mohawk aircraft stall-speed warning system. The AICS is presently undergoing configuration for use on an F-104 pace aircraft and on the advanced fighter technology integration (AFTI) F-111 aircraft.

Descriptors :   *Flight testing, Computer applications, Data acquisition, Digital systems, Pulse code modulation, Modules(Electronics), Instrumentation, Interfaces, Avionics, Digital computers

Distribution Statement : APPROVED FOR PUBLIC RELEASE