Results 161 to 170 of about 7,227 (196)

84-Inch Propellant Grains.

1979
Abstract : This report documents the results obtained during casting a total of 7 84-in. SLSH cartridges with UTP-18,803A propellant (90% solids, 21% aluminum, HTPB) for AFRPL. This program is an extension of the work discussed in AFRPL-TR-77-92 and brings the total amount of UTP-18,803A produced under full-scale production conditions to over 880,000 ...
Albert J. Martel, Terry V. O'Hara
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The Design of Cylindrical Propellant Grains

Journal of Jet Propulsion, 1956
T h e m a t h e m a t i c s of t h e des ign of a cyl indr ical p r o p e l l a n t g ra in is d iscussed in genera l . Only t h e di rect r ix of t h e cyl indr ical b u r n i n g surface ( the in t e r sec t ion of t h e cyl inder w i t h a p l a n e n o r m a l t o i t s l a t e ra l surface) need be s t ud i ed .
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The Morphological Continuum in Solid Propellant Grain Design

1970
Grain configurations for solid propellant rockets are classified by relative web thickness and mean vector direction of burning surface into a topological continuum. This ranges from the thin web dendrite (web equal to 1/6 of charge radius and entirely in the cross-section plane) thru the wagon-wheel- and star-perforated grains (1/4 to 1/2 web range ...
J.S. BILLHEIMER, F.R. WAGNER
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Fracture of solid rocket propellant grains

Engineering Fracture Mechanics, 1992
Abstract The importance of fracture criteria in the failure assessment of solid propellant grains is briefly described. Computation of the crack tip stress intensity factor and the development of the crack growth rate equation through fracture properties essential for fracture analysis are also discussed.
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Embedded Sensors for Monitoring Solid Propellant Grains

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
Rocket motors normally determine missile system service li fe. However, accurate rocket motor service life predictions are difficult and have always been compromised by both complex loading and the non -linear viscoelastic behavior of the highly filled solid propellant grains.
Herb Chelner, Jim Buswell, Danny Evans
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Thermal Stresses in Solid Propellant Grains

Journal of Jet Propulsion, 1956
A method is presented for computing the maximum thermal stress in solid propellant grains tha t can result from temperature cycling. The method is based upon a first approximation obtained from the analytical solution for thermal stresses assuming Young's modulus to be independent of temperature.
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Burning rate anomaly of composite propellant grains

Combustion, Explosion, and Shock Waves, 2013
In this study, characteristics of the burning rate anomaly in composite propellant grains are investigated. The burning rate anomaly has been known as the “midweb anomaly” or the “hump effect.” This paper describes some results of an experimental study on effects of propellant formulations, casting processes, and viscosity of the propellant slurry on ...
H. Hasegawa, M. Fukunaga, K. Kitagawa, T. Shimada   +3 more
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Experimental evaluation of as-processed propellant grains

20th Joint Propulsion Conference, 1984
Grain structural integrity evaluations are generally based upon mechanical properties data obtained from tests of specimens removed from carton samples of propellant. During the past several years, Aerojet has performed numerous sample excisions and motor dissections to verify grain structural capabilities.
P.W. Veit, L.G. Landuk, G.J. Svob
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Flame spreading and ignition transients in solid grain propellants

AIAA Journal, 1964
An analysis of grain ignition and flame spreading in solid-propellant rocket engines was performed to calculate chamber pressure as a function of time during this phase. Assumed for the analysis were isothermal one-dimensional gas flow in the chamber, spatially uniform gas pressure, two-dimensional transient heat conduction in the grain, perfect gas ...
DeSoto, S., Friedman, H. A.
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Dynamic Mechanical Characterization of Composite Solid Propellant for Propellant Grain Structural Integrity Assessment

Macromolecular Symposia, 2019
The objective of this work was to characterize mechanical properties of composite solid propellant in order to conduct the structural integrity assessment of propellant grain. Data required for analyses regarding loads experienced during rocket motor transportation and flight were obtained.
Gustavo Henrique Murari, Fabio Luiz Calciolari, Luis Eduardo Nunes de Almeida   +2 more
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