Results 251 to 260 of about 18,714 (310)
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Stability of Solid Propellant Combustion
Physical Review Letters, 1994The stability of a combustion wave is one of the most important problems in combustion theory. The solution of the problem can be essentially simplified if the characteristic scales of the processes governing the combustion are small in comparison with the characteristic dimensions of the problem.
, Bychkov, , Liberman
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Adiabatic pyrolysis of solid propellants
35th Aerospace Sciences Meeting and Exhibit, 1997Several one-step, irreversible, zero-order pyrolysis models (Arrhcnius, KTSS, and Merzhanov Dubovitskii high activation energy pyrolysis), commonly used to study adiabatic burning of energetic materials with arbitrary pressure and initial temperature, are revisited.
DE LUCA, LUIGI +4 more
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Detonability of Solid Composite Propellants
ARS Journal, 1961The thin film pla t inum resistance thermometer (heat flux gage) has been successfully applied to measurement of heat fluxes from initiators for solid propellants. Hea t fluxes measured were as high as 1000 Btu/ft-sec from hot, particleladen reaction products of pyrotechnic igniters.
Andersen, W. H., Chaiken, R. F.
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SOLID PROPELLANT COMBUSTION INSTABILITY: OSCILLATORY BURNING OF SOLID ROCKET PROPELLANTS
1965Abstract : Contents: The occurrence of combustion instability in solid propellant rocket motors; The morphology of combustion oscillations; Theories of elemental processes in combustion instability - a literature survey; A detailed discussion of pressure coupling with the surface flame zone; Experimental studies on the nature of the pressure - surface ...
Martin Summerfield +1 more
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Solid propellant sandwich deflagration analysis
12th Aerospace Sciences Meeting, 1974A theoretical solution has been obtained for the shape of a deflagrating ammonium perchlorate surface when it is adjacent to an inert, pyrolysing, dry binder. The eigenvalue, the regression rate, is shown to be independent of binder type and very close to the burn rate of pure AP, as has been experimentally observed.
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Solid Propellant Rocket Motors
The Journal of the Royal Aeronautical Society, 1961A solid propellant rocket motor consists essentially of a propellant charge in a container fitted with an expansion nozzle and igniter. Since, before a rocket motor can be designed, it is necessary to have some knowledge of the properties of the propellant to be used, a description will first be given of the propellants which are currently available.
W. R. Maxwell, G. H. S. Young
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UAH Solid Propellant Characterization
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007One of the main properties of solid propellants that must be known before a solid propellant design can be implemented into any use is the burning rate law. The objective of this works is to investigate the temperature sensitivity as a function of pressure for a composite propellant.
Tony Marshall +2 more
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Ignition and Combustion of Solid Propellants
1961Abstract : A model for the ignition response of solid propellants is presented, which predicts ignition behavior with respect to pressure and surface heat flux in qualitative agreement with experimental measurements. Surface regression is treated and a steady-state burning model is employed, which assumes equlibrium vaporization at the surface and a ...
Norman W. Ryan +3 more
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1968
Solid propellants are of two basic types: composites and double base propellants. The latter consist of a backbone of nitrocellulose (guncotton) onto which a quantity of nitroglycerine has been absorbed, resulting in a leathery propellant which can be cast or extruded into desired shapes.
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Solid propellants are of two basic types: composites and double base propellants. The latter consist of a backbone of nitrocellulose (guncotton) onto which a quantity of nitroglycerine has been absorbed, resulting in a leathery propellant which can be cast or extruded into desired shapes.
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Solid Propellant Aging Kinetics
45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009Accelerated aging was used to estimate how solid propellant mechanical properties change over periods spanning many years. Propellant was obtained from dissection of a rocket motor that was removed from a deployed inventory. This unit was about nine years old when tested.
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