Results 271 to 280 of about 9,648 (314)

COMBUSTION OF COMPOSITE PROPELLANTS WITH TITANIUM

Journal of Applied Mechanics and Technical Physics, 2023
N. S. Belousova, O. G. Glotov, I. V. Sorokin   +2 more
openaire   +1 more source

Combustion mechanism of an RDX-based composite propellant

Combustion and Flame, 1999
The co mbustion mechanism of a composite propellant having the nominal composition 84% RDX + 16% HTPB has been investigated experimentally. The following steady combustion parameters were collected over the pressure range 0.1 to 8.21 MPa: burn rates, burn surface temperatures, thermal gradients, heat release in the condensed phase, heat feedback from ...
DE LUCA, LUIGI, COZZI, FABIO, G. Germiniasi, I. Ley, A. A. Zenin   +4 more
openaire   +2 more sources

Convective ignition of a granular solid propellant bed: Influence of propellant composition

Symposium (International) on Combustion, 1996
In previous work, the authors designed and built a laboratory apparatus that subjects a confined bed of granular propellant to essentially a planar hot-gas ignition wave. Diagnostics include wall-mounted pressure transducers to monitor the time history of the pressure field, and fast-response thermocouples protected within custom sting-mounted steel ...
Douglas E. Kooker, Stephen L. Howard, Lang-Mann Chang   +2 more
openaire   +1 more source

Studies on Interface Properties of Propellant Liner for Case-Bonded Composite Propellants

Journal of Energetic Materials, 2003
For ensuring a good bond between the insulator and the propellant, a thin layer of liner is applied. Liner compositions should preferably be based on the same binder system used in the propellant formulations. As the liner is to hold the propellant and insulator without debond in all the environmental conditions, the interface properties are very ...
S. D. KAKADE, S. B. NAVALE, V. L. NARSIMHAN   +2 more
openaire   +1 more source

Modelling of Composite-Propellant Flames

2001
Abstract : We examined small deviations from axial symmetry in a solid-propellant rocket motor, and describe a 'bath-tub-vortex' effect, in which substantial axial vorticity is generated in a neighborhood of the chamber centerline. The unperturbed flow field is essentially inviscid at modest Reynolds numbers, even at the chamber walls, as has long been
openaire   +1 more source

Simulation of Composite Propellant Aging

Polymer-Plastics Technology and Engineering, 1993
Abstract Inert polyurethane (PU)-glass elastomeric composites were fabricated to simulate the mechanical behavior of composite propellant systems. A polyether PU system was used in conjunction with 60 wt%, 20 μm glass beads. The mechanical and interfacial properties of model systems were evaluated as a function of time and temperature, using Instron ...
openaire   +1 more source

Review of composite propellant burn rate modeling

17th Aerospace Sciences Meeting, 1979
Steady-state combustion modeling of composite solid propellants is discussed with emphasis on the Beckstead-Derr-Price (BDP) model. The BDP model and some revisions are considered with respect to the analysis of monomodal ammonium perchlorate/inert binder propellants: topics examined include continuity relations, surface area relations, characteristic ...
openaire   +2 more sources

Depressurization extinguishment of composite solid propellants - Influence of composition and catalysts

8th Joint Propulsion Specialist Conference, 1972
Abstract : The experimental results at 100 bar initial pressure emphasize the importance of the condensed phase properties on the depressurization extinguishment. In all cases of alteration of these properties by the change of binder, the particle size distribution, or the addition of Aluminum the critical depressurization rate for extinguishment was ...
openaire   +1 more source

Nonmetallized composite propellant combustion

2013
Naval Ordnance Systems Command, ORD TASK 331 007/551 l/UF 19-332 ...
Netzer, David Willis, Kennedy, J. R., Brown, W. E., Biery, George Monroe   +3 more
openaire   +1 more source

Recent advances in catalytic combustion of AP-based composite solid propellants

Defence Technology, 2021
Dr Narendra Yadav
exaly