FR1076248A -
Improvements made to liquid rocket motor vehicles fitted with an ignition device, in particular liquid rockets of this type with powder pressurization
- Google Patents
Improvements made to liquid rocket motor vehicles fitted with an ignition device, in particular liquid rockets of this type with powder pressurization
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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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FR1076248D1953-02-231953-02-23
Improvements made to liquid rocket motor vehicles fitted with an ignition device, in particular liquid rockets of this type with powder pressurization
ExpiredFR1076248A
(en)
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)
Parametric study of combustion instability in MMHNTO liquid rocket engine(Combustion instability in MMH-NTO liquid rocket engine as affected by propellant mixture ratio, injection velocity, droplet size and distribution and chamber pressure)
Improvements to processes for supplying combustion engines, in particular of the rocket engine type with two liquids, by a system with at least two distinct elements
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)