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Virtual prototyping of solid propellant rockets
Computing in Science & Engineering, 2000Researchers seek a detailed, whole-system simulation of solid propellant rockets under normal and abnormal operating conditions. A virtual prototyping tool for solid propellant rocket motors based on first principles models of rocket components and their dynamic interactions meets this goal. Given a design specification (geometry, materials, and so on),
Michael T. Heath, William A. Dick
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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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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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PARTICIPATION OF THE SOLID PHASE IN THE OSCILLATORY BURNING OF SOLID ROCKET PROPELLANTS
Symposium (International) on Combustion, 1963Interaction between solid and gas phases during oscillatory burning of solid propellants - combustion ...
N.W. Ryan, R.L. Coates, A.D. Baer
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The Future for Solid Propellant Rockets
The Journal of the Royal Aeronautical Society, 1959Ten years ago it seemed that the solid propellant rocket engine could make only a limited contribution to rocketry. Although it was simpler and more compact than its liquid propellant rival it suffered from three serious drawbacks. The nozzle was uncooled and so the burning time had to be short, the entire propellant container was subjected to the full
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Vortex generation in solid propellant rockets
AIAA Journal, 1964Vortices are generated by acoustic oscillations as a second-order viscous effect. Traveling tangential modes in an axially perforated solid propellant rocket give a single vortex swirling about the axis. Tangential velocity at the periphery, typically a few hundred feet per second, can be predicted approximately using acoustic streaming theory modified
G. SOTTER, J. SWITHENBANK
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History of the Development of Solid Rocket Propellant in France
Journal of Propulsion and Power, 1993The real development of solid rocket propellents in France started in 1946 for tactical missiles applications mostly based on cast or extruded double-base propellants. The decision by General de Gaulle at the beginning of the 1960s to develop an independent Strategic Force based on ballistic missiles had a tremendous effect on the research, development,
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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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Igniter performance in solid propellant rocket motors
2nd Propulsion Joint Specialist Conference, 19661 Robbins, J. H. and Rogers, A. C., Jr., "An analysis on predicting thermal stratification in liquid hydrogen," J. Spacecraft Rockets 3, 40-45 (1966). 2 Boudreaux, R. A., "Boundary layer thermodynamic and hydrodynamic characteristics of a flowing liquid hydrogen tank, with and without internal heat generation," Ph.D dissertation, Univ.
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Combustion Instability in Solid Propellant Rockets.
1987Abstract : This report constitutes the principal of a book on combustion stability in solid propellant rockets. The present report contains nine chapters that are each substantially complete except for some editorial, bibliographical and art work in some chapters.
G. A. Flandro, E. W. Price
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