Results 261 to 270 of about 7,425 (303)

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
openaire   +1 more source

Photothermoelastic analysis of bonded propellant grains

Experimental Mechanics, 1961
A two-dimensional model of the transversal cross section of a bonded rocket propellant grain was subjected to uniform and steady thermal loading and, alternatively, to mechanically applied uniform radial displacements on the outer boundary. The optimization of perforation contours (attained in previous research programs by applying uniform pressure on ...
I. M. Daniel, A. J. Durelli
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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
openaire   +1 more source

The migration of plasticizer in solid propellant grains

Polymer International, 1993
Abstract The migration of the plasticizer, dioctyl adipate (DOA) in the accelerated ageing of composite propellant has been studied. The method is based on the extraction of DOA with carbon tetrachloride and its estimation by gas chromatography.
D. Venkatesan, M. Srinivasan, K. Audisesha Reddy, V. V. Pendse   +3 more
openaire   +1 more source

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.
openaire   +2 more sources

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
openaire   +1 more source

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
openaire   +1 more source

Propellant Grain with Maximum Combustion Efficiency of Metal

Key Engineering Materials, 2016
This paper reports on the ways of allocating the metal particles in the propellant grain of tube cross-sectional type to provide maximum combustion efficiency of metal. Two-dimensional flow field and the burning rate law govern a transport of the burning metal particles.
Leonid Minkov, Ernst R. Shrager, Elizaveta V. Pikushchak   +2 more
openaire   +1 more source

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.
openaire   +1 more source

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.
openaire   +1 more source