The current investigation into the development of a new test facility which can reproduce in a controlled manner the fire conditions that would be experienced by an aircraft fuselage following a fuel spillage incident is outlined. The early investigation work has led to the definition of a fire source based upon previous test work in the aircraft industry and industrial pool fires in general. This definition was then used to design a test facility which was built and commissioned. It can create a reproducible thermal insult of up to 1150 C and 210 Kw/m(sup 2). The commissioning program is now complete, however, one particular aspect proved to be of great interest. That is the increased burnthrough rate due to soot deposition during the first few seconds of a pool fire. This phenomena will prove to be very critical as the ultimate aim of the project is to enhance the burnthrough capabilities of aircraft fuselages. The program will look at the determination of burnthrough times of existing fuselages before moving onto investigating the burnthrough capabilities of both improved materials and systems.
Investigation into Aircraft Fuselage Fire Hardening
1993
15 pages
Report
No indication
English
Aircraft , Aeronautics , Laboratory & Test Facility Design & Operation , Transportation Safety , Air Transportation , Aircraft construction materials , Aircraft safety , Burnthrough (Failure) , Fire prevention , Fuselages , Test facilities , Aircraft fuels , Fuel combustion , Heat flux , Spilling , Foreign technology , Aircraft fires
Aircraft fuselage section, aircraft fuselage and aircraft
European Patent Office | 2023
|FUSELAGE SECTION OF AN AIRCRAFT, AIRCRAFT FUSELAGE, AND AIRCRAFT
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