Results 191 to 200 of about 7,758 (239)
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Thermostructural composite materials for liquid propellant rocket engines
23rd Joint Propulsion Conference, 1987Since more than twenty years the possible utilisation of high temperature and oxydation resistance of ceramics was considered by rocket engines designers but brittleness and poor thermal choc resistance was a major disadvantage for those materials emergence.
A. MELCHIOR, M. POULIQUEN, E. SOLER
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Intermetallic Compounds as Fuels for Composite Rocket Propellants
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011Aluminized composite propellants have long suffered from efficiency and thermal challenges related to production of condensed phase slag droplets during operation. In an effort to mitigate the production of large droplets, a mechanically activated intermetallic forming nickel-aluminum compound was substituted for a portion of a propellant’s aluminum ...
David Reese +3 more
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Integrated model of a composite propellant rocket
AIP Conference Proceedings, 2016The combustion of composite solid propellants was investigated and an available numerical model was improved for taking into account the change of pressure, when the process occurs in a confined environment, as inside a rocket. The pressure increase upon ignition is correctly described by the improved model for both sandwich and dispersed particles ...
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Generating Plateau Burning Segments for Composite Solid Rocket Propellants
Propellants, Explosives, Pyrotechnics, 2019AbstractPlateau burning is a highly desired phenomenon for composite solid rocket propellants. Three composite propellant compositions were prepared in an attempt to generate plateau burning segments. In these compositions the curative type was changed along with controlling the coarse to fine ratio of the oxidizer particles.
Sameh A. El‐Basuony +3 more
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Burning rate of a trimodal composite rocket propellant
Journal of Propulsion and Power, 1990Some new perceptions in the field of composite propellants are considered. The effects of trimodal oxidizer distribution on the burning rate of composite propellants are considered. It is note that reducing the oxidizer particles in the presence of depressors reduces the burning rate of these propellants. In the formulation of the experimental approach,
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Fracture Mechanics of Composite Solid Rocket Propellant Grains: Material Testing
Journal of Propulsion and Power, 2009Following a detailed literature survey on the fracture-mechanics properties of solid rocket propellants, this paper reports on an innovative set of fracture tests performed on a composite solid propellant based on ammonium perchlorate hydroxyl-terminated polybutadiene.
TUSSIWAND, GIUSEPPE +3 more
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Smokeless GAP‐RDX Composite Rocket Propellants Containing Diaminodinitroethylene (FOX‐7)
Propellants, Explosives, Pyrotechnics, 2017AbstractComposite rocket propellants prepared from nitramine fillers (RDX or HMX), glycidyl azide polymer (GAP) binder and energetic plasticizers are potential substitutes for smokeless double‐base propellants in some rocket motors. In this work, we report GAP‐RDX propellants, wherein the nitramine filler has been partly or wholly replaced by 1,1 ...
Tomas L. Jensen +2 more
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Some new results of chuffing in composite solid propellant rockets
Journal of Spacecraft and Rockets, 1985Chuffing is one of the low-frequency instabilities in solid propellant rockets functioning at low chamber pressures. In chuffing, the rocket motor experiences brief spurts of combustion and consequent pressure buildup, followed by periods of near ambient pressures in the combustion chamber.
Raghunandan, BN, Bhaskariah, P
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Bonding of composite propellant in cast-in-case rocket motors.
Journal of Spacecraft and Rockets, 1966The apparent bond strength of some composite solid-rocket propellants to elastomeric substrates is governed by the propellant cohesive strength. When these propellants are tested (whether by the tensile or peel method), failure is invariably cohesive within the propellant near the interface.
CLARENCE GUSTAVSON +2 more
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Isocyanate‐Free and Dual Curing of Smokeless Composite Rocket Propellants
Propellants, Explosives, Pyrotechnics, 2012AbstractTraditional composite rocket propellants are cured by treatment of hydroxyl‐terminated prepolymers with polyfunctional aliphatic isocyanates. For development of smokeless composite propellants containing nitramines and/or ammonium dinitramide (ADN), energetic binder systems using glycidyl azide polymer (GAP) are of particular interest ...
Eva Landsem +5 more
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