Results 21 to 30 of about 12,705 (201)
Burning Properties of Uncured HTPB Propellant
Journal of the Korean Society of Propulsion Engineers, 2016 ABSTRACT In this study, we examined the burning rate of the uncured pr opellant (with and without a curing agent application) in order to inspect the process of the HTPB solid propellant. The burning rate of the uncured propellant, that did not contain the curing agent, was approximately 9.7 mm/s at 1000 psi. In relation to the curing time, the burning
Nakhyun Kim, Jungeun Kim, Myungpyo Hong
openaire +2 more sources
Rocket propellants with reduced smoke and high burning rates
, 2022 S.112-119The material-based ranges of performance and properties of 3 non-aluminized rocket propellants are presented and compared to each other. The selected formulations based on AP/HTPB, AP/PU/TMETN and AP/HMX/GAP/TMETN have roughly the same specific ...
Menke, K., Eisele, S.
core +1 more source
Propulsion and Power Research, 2019 The aim of present study is to investigate the burning rate, ignition delay, and flame characteristics of ammonium perchlorate (AP)-hydroxyl terminated poly-butadiene (HTPB) [AP/HTPB] based composite propellants (CSP's) in sub-atmospheric pressure ...
Pratim Kumar +2 more
doaj +1 more source
Correlation between solid propellant failure and interface debonding in solid rocket motors
Polymer Testing, 2022 In the traditional integrity analysis of solid rocket motors, solid propellants failure and propellant-liner interface debonding were intentionally differentiated. This empirical distinction of failure regions based on the macroscopic phenomenon neglects
Ming Lei +6 more
doaj +1 more source
Effect of Mechanical Heterogeneity on the Structural Integrity of HTPB Propellant Grain
Materials, 2023 To investigate the structural effects of the mechanical heterogeneity of Hydroxyl-terminated polybutadiene (HTPB) propellant grain under ignition pressurization, a gradient finite element method was proposed to evaluate its structural integrity. The heterogeneous mechanical properties of the propellant grain were constructed and assessed.
Xiangyang Liu +4 more
openaire +2 more sources
Preparation and Characterization of Al/HTPB Composite for High Energetic Materials
Nanomaterials, 2020 Nanosized Al (nAl) powders offer increased reactivity than the conventional micron-sized counterpart, thanks to their reduced size and increased specific surface area.
Alexander Vorozhtsov +5 more
doaj +1 more source
Effect of spherical Al-Mg-Zr on the combustion characteristics of composite propellants
FirePhysChem, 2022 In this work, spherical Al-Mg-Zr alloy with intensive heat release were characterized and compared to neat Al powders. The morphology, element distribution and thermal performance were characterized by TEM, SEM, Mapping and TG-DSC.
Zhao Qin +9 more
doaj +1 more source
Application of artificial neural networks for the prediction of aluminium agglomeration processes
International Journal of Aviation, Aeronautics, and Aerospace, 2018 Aluminium is universal and vital constituent in composite propellants and typically used to improve performance. Aluminum agglomeration takes place on the burning surface of aluminized propellants, which leads to reduced combustion efficiency and 2P flow
TEJASVI K +3 more
doaj +1 more source
Polymer Testing, 2023 In this paper, the mechanical properties of a typical four-component composite solid propellants with various designed Al/oxidizer interfaces have been studied.
Xiang Lv +5 more
doaj +1 more source
Modeling and rheology of HTPB based composite solid propellants
Polymer Composites, 1998 AbstractThe propellant with the minimum viscosity required for a defectâfree casting can be obtained by proper selection of the size and fractions of solid components leading to maximum packing density. Furnas' model was used to predict the particulate composition for the maximum packing density.
Erisken, C +4 more
openaire +2 more sources