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- W2022885881 abstract "In order to ensure reliable high altitude ignition of the improved Black Brant Mk 1 sounding rocket, a new igniter was designed and tested. Since traditional theoretical methods for calculating the required igniter charge size gave widely varying requirements, an empirical method was instead utilized. Various igniter models were fired in an enclosed chamber and heat flux and pressure outputs were measured. These data were compared to laser ignitability results obtained for the Black Brant solid propellant to ensure that sufficient igniter output was provided. A static test and flight test demonstrated that the redesigned igniter performed well to ignite the rocket under near vacuum conditions." @default.
- W2022885881 created "2016-06-24" @default.
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- W2022885881 date "2008-07-21" @default.
- W2022885881 modified "2023-09-23" @default.
- W2022885881 title "Design of a Robust High Altitude Rocket Motor Igniter" @default.
- W2022885881 cites W2003581903 @default.
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- W2022885881 doi "https://doi.org/10.2514/6.2008-4785" @default.
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