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A fluidic sounding rocket motor ignition system.Fluidic sounding rocket motor ignition has been found to be feasible using a system without stored energy and with the complete absence of electrical energy and wiring. The fluidic ignitor is based on a two component aerodynamic resonance heating device called the pneumatic match. Temperatures in excess of 600 C were generated in closed resonance tubes which were excited by a free air jet from a simple convergent nozzle. Using nitrocellulose interface material, ignition of boron potassium nitrate was accomplished with air supply pressures as low as 45 psi. This paper describes an analytical and experimental program which established a fluidic rocket motor ignition system concept incorporating a pneumatic match with a simple hand pump as the only energy source.
Document ID
19730028684
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Marchese, V. P.
Rakowsky, E. L.
(Singer Co. Little Falls, N.J., United States)
Bement, L. J.
(NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1972
Subject Category
Auxiliary Systems
Report/Patent Number
AIAA PAPER 72-1197
Meeting Information
Meeting: Joint Propulsion Specialist Conference
Location: New Orleans, LA
Country: US
Start Date: November 29, 1972
End Date: December 1, 1972
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
73A13486
Funding Number(s)
CONTRACT_GRANT: NAS1-10680
Distribution Limits
Public
Copyright
Other

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