Results 241 to 250 of about 2,466 (307)

Fatigue failure of prefabricated crack HTPB(hydroxyl-terminated polybutadiene) propellant under strain control. [PDF]

Sci Rep
Li G, Gao B, Hu H, Cui R, Feng J, He J.
europepmc   +1 more source

Improving Mechanical Properties of Carboxyl-Terminated Polybutadiene (CTPB) Binder System Using a Cure Accelerator. [PDF]

Molecules
Qu X, Hu P, Ma X, Liu Y, Yang H, Zhang W, Chen Y.   +6 more
europepmc   +1 more source

Interfacial engineering of aluminum powder with a tannic acid/Fe³⁺ complex and fluorosilane for high-performance energetic composites. [PDF]

Sci Rep
Liu B, Gou X, Li Y, Liang J, Yan S, Guo X, Nie J.   +6 more
europepmc   +1 more source

An Investigation into Mechanical Failure of Composite Propellants

, 2010
openaire   +1 more source

Modelling of composite propellant properties

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
State-of-the-art composite propellants are based on solid particles (AP, Aluminium) in a polymeric HTPB based binder system. The usability of a propellant for a particular application is dependent on a large number of properties. These different properties sometimes result in contradictory requirements and design trade-off need to be made.
Keizers, H.L.J., Hordijk, A.C., Vliet, L.D. van, Bouquet, F.   +3 more
openaire   +3 more sources

Some of the next articles are maybe not open access.

Related searches:

Detonability of Solid Composite Propellants

ARS Journal, 1961
The thin film pla t inum resistance thermometer (heat flux gage) has been successfully applied to measurement of heat fluxes from initiators for solid propellants. Hea t fluxes measured were as high as 1000 Btu/ft-sec from hot, particleladen reaction products of pyrotechnic igniters.
Andersen, W. H., Chaiken, R. F.
openaire   +2 more sources

Composite propellant combustion

AIAA Journal, 1970
Temperature measurements in gaseous reaction zone near surface of burning composite solid propellant, using modified line reversal ...
R. L. DERR, J. R. OSBORN
openaire   +1 more source

Prediction of the Critical Diameter of Composite Propellants

AIAA Journal, 1972
A theoretical model which predicts the critical diameter of composite propellants is presented. A previously published detonation model is corrected and refined by use of a new model which considers both single grain size AP and dual grain size AP configuration s, for both porous and nonporous propellants.
P. SALZMAN, T. DUNCAN
openaire   +1 more source

Nano-composites for rocket solid propellants

Composites Science and Technology, 2005
Aim of this work is the study of different components (binder and aluminum powders) of solid propellants used for rocket propulsion to improve ballistic performance. New propellant formulations have been tested and characterised. Combustion residues were collected by a proprietary method and analyzed both from the morphological and chemical point of ...
MEDA, LUISA MARINA, G. Marra, GALFETTI, LUCIANO, DE LUCA, LUIGI, F. Severini, S. Inchingalo   +5 more
openaire   +2 more sources

HNF/HTPB BASED COMPOSITE PROPELLANTS

International Journal of Energetic Materials and Chemical Propulsion, 2002
In a search for new storable high performance propellants for the European Space Agency (ESA), the solid oxidiser Hydrazinium Nitroformate (HNF) was identified as a very promising ingredient for a new storable composite propellant. Two distinct advantages of HNF based propellants over presently used Ammonium Perchlorate (AP) based propellants rvere the
Heijden, A.E.D.M. van der, Keizers, H.L.J., Veltmans, W.H.M.   +2 more
openaire   +2 more sources