Accession Number : AD0431309


Title :   THEORY, DEVELOPMENT AND TEST OF A CRASH FIREINERTING SYSTEM FOR RECIPROCATING ENGINE HELICOPTERS


Corporate Author : AVIATION SAFETY ENGINEERING AND RESEARCH PHOENIX AZ


Personal Author(s) : Robertson, S H ; Turnbow, James W ; Carroll, Donald F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/431309.pdf


Report Date : Dec 1963


Pagination or Media Count : 84


Abstract : This report describes the theory, development, and test of a fire- inerting system for helicopters powered with reciprocating engines. The feasibility of constructing a lightweight system capable of operating under typical crash conditions is demonstrated. Areas requiring additional development are discussed. It is concluded that: (1) a fire-inerting system for helicopters should be in operation within 0.20 second or less after first impact; (2) a time to operate of 0.20 second can be attained in an operational fire-inerting system; (3) a fireinerting system can be installed in a 10,000pound aircraft with as little as 80 pounds increase in overall weight including coolant; and (4) the construction and installation into service aircraft of a combination manual-automatic fire-inerting system meeting the above weight and time-to- operate limitations is possible with the present state of the art.


Descriptors :   *AIRCRAFT FIRES , *FIRE SAFETY , *HELICOPTER ENGINES , AVIATION ACCIDENTS , AVIATION FUELS , AVIATION SAFETY , CARBON DIOXIDE , COOLANTS , COUNTERMEASURES , FIRE EXTINGUISHERS , HELICOPTERS , IGNITION , INTERNAL COMBUSTION ENGINES , NITROGEN , SPRAYS , WATER


Subject Categories : Military Aircraft Operations
      Helicopters


Distribution Statement : APPROVED FOR PUBLIC RELEASE