INTEGRATED FIRE AND OVERHEAT DETECTION SYSTEM FOR AIRCRAFT.

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Abstract:

The object of the program was to design and build an operational fire and overheat detection system, which used continuous sensors, PIN sensors, silicon solar cell sensors, and silicon carbide sensors for manned flight vehicles. The system consists of sensitizing modules, detection circuits and logic circuits. Operational capability ranges from -55C to 125C. The system is designed to drive a readout with four separate notations, FIRE, OVERHEAT, FAIL and OK. Author

Author(s):
Raskauskas, Bernard J.
Author Organization(s):
GENERAL MOTORS CORP KOKOMO IND DELCO RADIO DIV
Descriptive Note:
Technical rept. 15 Nov 68-15 Sep 69,
Pagination:
0072

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFAPL-TR-69-97
Contract/Grant Number(s):
F33615-69-C-1196
Project Number(s):
AF-3048
Monitor Series:
TR-69-97
 Subject Terms
Modernization Areas:
Microelectronics
Communities of Interest:
Air Platforms
Descriptor(s):
(*FIRE ALARM SYSTEMS, AIRCRAFT EQUIPMENT), (*TEMPERATURE WARNING SYSTEMS, AIRCRAFT EQUIPMENT), AIRCRAFT ENGINES, DETECTORS, TEMPERATURE SENSITIVE ELEMENTS, PHOTODIODES, SOLAR CELLS, SILICON, SILICON CARBIDES, SEMICONDUCTOR DIODES, INTEGRATED CIRCUITS, LOGIC CIRCUITS, MODULES(ELECTRONICS)
Field(s)/Group(s):
Aircraft, Safety Engineering
Keyword(s):
OVERHEATING
Report Date:
1969 Dec 01