Results 151 to 160 of about 449 (191)
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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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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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Assessing the Mixedness of Composite Solid Rocket Propellants Using Fluorescent Particles
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008A new diagnostic technique was developed for assessing the effectiveness of mixing techniques of solid composite propellants using nanoparticle additives. The diagnostic uses nanosized quantum dots in suspension or micron-sized powders that are mixed into the propellant in place of the additives.
Sammet, T. E. +3 more
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Thermal decomposition kinetics of PBAN-binder and composite solid rocket propellants
Combustion and Flame, 1999Abstract Thermogravimetric analysis at heating rates between 0.5 and 10°C min −1 has been used to study the decomposition kinetics of the PBAN binder and three propellants based on ammonium perchlorate (AP) with PBAN, HTPB, or BAMO-AMMO binders. Thermal runaway was observed for the PBAN and HTPB propellants at heating rates faster than 4.5 and 3°C ...
Thorsten Sell +2 more
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Application of Nano‐Aluminum/Nitrocellulose Mesoparticles in Composite Solid Rocket Propellants
Propellants, Explosives, Pyrotechnics, 2015AbstractIn this work we investigate the potential application of nano‐aluminum/nitrocellulose mesoparticles as an ingredient for solid composite rocket propellants. The basic strategy is to incorporate nanoaluminum in the form of a micrometer scale particle containing a gas‐generator, to enable easier processing, and potential benefits resulting from ...
Gregory Young +2 more
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Tailoring burning rates using reactive wires in composite solid rocket propellants
Proceedings of the Combustion Institute, 2017Abstract Tailoring solid propellant burning rates is a perpetual goal of solid propellant designers. Many methods have been used to alter the burning rate including changing the propellant formulation, adding burning rate modifiers, and changing the propellant core shape.
Sarah Isert +3 more
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Microstructural damage and fracture processes in a composite solid rocket propellant
Journal of Spacecraft and Rockets, 1995A study has been made of the microstructural damage and fracture processes associated with the fracturetoughness behavior of a polymer-matrix composite solid rocket-propellant material. Specifically, nonlinear-elastic fracture-mechanics tests were performed, as a function of displacement rate and temperature (—54 to 71°C), on center-cracked sheet test ...
C. D. Bencher +2 more
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