FR1076248A - Perfectionnements apportés aux engins à moteur-fusée à liquide muni d'un dispositif d'allumage, notamment aux fusées à liquide de ce genre à mise en pression par poudre
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Perfectionnements apportés aux engins à moteur-fusée à liquide muni d'un dispositif d'allumage, notamment aux fusées à liquide de ce genre à mise en pression par poudre
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AGRIMOBILA Ltd
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AGRIMOBILA Ltd
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F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
F02K—JET-PROPULSION PLANTS
F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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Engineering & Computer Science
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Chemical & Material Sciences
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Combustion & Propulsion
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Mechanical Engineering
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General Engineering & Computer Science
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Air Bags
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FR1076248D1953-02-231953-02-23Perfectionnements apportés aux engins à moteur-fusée à liquide muni d'un dispositif d'allumage, notamment aux fusées à liquide de ce genre à mise en pression par poudre
ExpiredFR1076248A
(fr)
Perfectionnements apportés aux engins à moteur-fusée à liquide muni d'un dispositif d'allumage, notamment aux fusées à liquide de ce genre à mise en pression par poudre
Perfectionnements apportés aux engins à moteur-fusée à liquide muni d'un dispositif d'allumage, notamment aux fusées à liquide de ce genre à mise en pression par poudre
Hydraulic piston velocity and chamber attitude effects on the minimum compression ratio for ignition of a liquid ethyl and propyl nitrate monopropellant
Studies of atomization and injection processes in the liquid propellant rocket engine(Role of atomization and injection processes in liquid propellant rocket engine combustion)
Acceleration of burning rate of composite propellants by sound waves(Effect of helium sound field on burning rate of ammonium perchlorate-polyurethane type solid propellant)
An investigation of the effect of acceleration on the burning rate of composite propellants(Parameters determining magnitude of acceleration effect on burning rate increase of aluminized and nonaluminized composite solid propellants)
The effect of acceleration on solid composite propellant combustion(Characteristic velocity of solid composite propellant combustion decreases with increasing acceleration)
Transonic range tests of 5-inch/54 rocket-assisted projectile(inert)(Aerodynamic characteristics of inert full-scale model of rocket-assisted projectile at Mach 0. 75 to 2. 24)