Extensions to analysis of ignition transients of segmented rocket motors
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The analytical procedures described in NASA CR-150162 were extended for the purpose of analyzing the data from the first static test of the Solid Rocket Booster for the Space Shuttle. The component of thrust associated with the rapid changes in the internal flow field was calculated. This dynamic thrust component was shown to be prominent during flame spreading. An approach was implemented to account for the close coupling between the igniter and head end segment of the booster. The tips of the star points were ignited first, followed by radial and longitudinal flame spreading.Keywords:
Booster (rocketry)
Solid-fuel rocket
Rocket (weapon)
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Abstract : A theoretical and experimental study was made of solid rocket ignition for the purpose of obtaining igniter design criteria. Heat-transfer, ballistic, and ignition data were obtained by firing a rocket-type igniter, venting noncondensable products at an unsteady rate, into a small rocket. Measurements were made of igniter and rocket pressures, grain surface temperatures, and ignition times. In the tests, the heat fluxes ranged from 19 to 48 cal/sq. cm.-sec and ignition times from .002 to .015 sec. It was found that the ignition test data were in fair agreement to those predicted from the von Elbe ignition theory. An igniter design method, developed from test data and the von Elbe theory, is described. (Author)
Rocket (weapon)
Solid-fuel rocket
Rocket propellant
Rocket engine
Autoignition temperature
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Rocket (weapon)
Rocket propellant
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Liquid-propellant rocket
Rocket propellant
Rocket (weapon)
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Measurement data on the performance of Space Shuttle Solid Rocket Motor show wide variations in the head-end pressure changes and the total thrust build-up during the ignition transient periods. To analyze the flow and thermal behavior in the tested solid rocket motors, a 1-dimensional, ideal gas flow model via the SIMPLE algorithm was developed. Numerical results showed that burning patterns in the star-shaped head-end segment of the propellant and the erosive burning rate are two important factors controlling the ignition transients. The objective of this study is to extend the model to include the effects of aluminum particle commonly used in solid propellants. To treat the effects of aluminum-oxide particles in the combustion gas, conservation of mass, momentum, and energy equations for the particles are added in the numerical formulation and integrated by an inter-phase-slip algorithm.
Solid-fuel rocket
Rocket (weapon)
Transient (computer programming)
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Solid-fuel rocket
Rocket (weapon)
Liquid-propellant rocket
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Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.
Rocket (weapon)
Space launch
Liquid-propellant rocket
Rocket engine
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Solid-fuel rocket
Ballistics
Rocket (weapon)
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Abstract : An analysis of solid rocket motors was made in order to find the chamber pressure and thrust during the transient periods of buildup and decay. The results are differential equations and solutions of closed form.
Solid-fuel rocket
Transient (computer programming)
Chamber pressure
Rocket (weapon)
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