Results 271 to 280 of about 2,289,829 (359)

Stability of Solid Propellant Combustion

Physical Review Letters, 1994
The 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
openaire   +2 more sources

Adiabatic pyrolysis of solid propellants

35th Aerospace Sciences Meeting and Exhibit, 1997
Several 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, VERRI, MAURIZIO, COZZI, FABIO, COLOMBO, GIOVANNI, E. Volpe   +4 more
openaire   +1 more source

Detonability of Solid Composite Propellants

ARS Journal, 1961
The 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.
openaire   +2 more sources

Experimental and model investigation on agglomeration of aluminized fuel-rich propellant in solid fuel ramjet

Combustion and Flame, 2020
In order to gain insight into aluminum agglomeration behaviors and agglomeration processes, the aluminized fuel-rich propellants in solid fuel ramjet are investigated by using sampling method followed by scanning electron microscopy and laser scattering ...
Lian-Bo Li, Xiong Chen, Changsheng Zhou, Weixuan Li, Min Zhu   +4 more
semanticscholar   +1 more source

Silicone bridged iron metallocene butadiene composite solid propellant binder: aspects of thermal decomposition kinetics, pyrolysis and propellant burning rate

Journal of Energetic Materials, 2018
Propellant binders are essential components of composite solid propellants (CSP’s) used in launch vehicles and missiles. Binders act as a fuel and contribute directly to the combustion in conjunction with oxidizer particles and metallic fuel apart from ...
S. Reshmi, M. Ganesan, P. B. Soumyamol, Deepthi Thomas, D.V Athmaja   +4 more
semanticscholar   +1 more source

SOLID PROPELLANT COMBUSTION INSTABILITY: OSCILLATORY BURNING OF SOLID ROCKET PROPELLANTS

1965
Abstract : 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, R. H. Woodward Waesche   +1 more
openaire   +1 more source

Considering Mixing Process of Rocket Solid Propellant Using Mixing Transport Device Simulating Peristaltic Movement of Intestinal Tract

International Conference on Biomedical Robotics and Biomechatronics, 2018
In recent years, because the development of space technology has been increasing for the purpose of improving the social infrastructure, the expansion of space transportation systems based on low-cost and high-frequency rockets is important.
Kyota Ashigaki, Akihiro Iwasaki, D. Hagiwara, Kai Negishi, Kotaro Matsumoto, Yasuyuki Yamada, H. Habu, Taro Nakamura   +7 more
semanticscholar   +1 more source

Solid propellant sandwich deflagration analysis

12th Aerospace Sciences Meeting, 1974
A 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.
openaire   +1 more source

Solid Propellant Rocket Motors

The Journal of the Royal Aeronautical Society, 1961
A 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
openaire   +1 more source

UAH Solid Propellant Characterization

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007
One 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, John Evans, Robert Frederick   +2 more
openaire   +1 more source