New Additives for Modifying the Burn Rate of Composite Solid Propellants

2006 ◽  
Author(s):  
Matthew Stephens ◽  
Thomas Sammet ◽  
Rodolphe Carro ◽  
Alexander LePage ◽  
David Reid ◽  
...  
Keyword(s):  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Composite Solid

scholarly journals Cu–Co–O nano-catalysts as a burn rate modifier for composite solid propellants

2016 ◽  
Vol 12 (4) ◽  
pp. 297-304 ◽  
Author(s):  
D. Chaitanya Kumar Rao ◽  
Narendra Yadav ◽  
Puran Chandra Joshi
Keyword(s):  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Burn Rate Modifier ◽  
Nano Catalysts ◽  
Burn Rate ◽  
Composite Solid

Modified iron oxide nanoparticles as burn rate enhancer in composite solid propellants

Vacuum ◽  
2018 ◽  
Vol 156 ◽  
pp. 483-491 ◽  
Author(s):  
A.S. Budhwar ◽  
Aashish Gautam ◽  
Priyesh V. More ◽  
Chandra Shekhar Pant ◽  
Shaibal Banerjee ◽  
...  
Keyword(s):  
Iron Oxide ◽  
Iron Oxide Nanoparticles ◽  
Oxide Nanoparticles ◽  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Composite Solid

Selective Radiative Preheating of Aluminum in Composite Solid Propellant Combustion

1987 ◽  
Vol 109 (1) ◽  
pp. 179-184 ◽  
Author(s):  
M. Q. Brewster ◽  
R. Patel
Keyword(s):  
Catalyst Particle ◽  
Radiation Absorption ◽  
Solid Propellants ◽  
Two Phase ◽  
Mass Fractions ◽  
The Matrix ◽  
Composite Solid Propellant ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Composite Solid

A two-phase model has been developed to study aluminum (Al) particle preheating through selective radiation absorption in composite solid propellants. The two phases considered are one strongly absorbing particle (Al) phase and another weakly absorbing matrix (ammonium perchlorate (AP), binder and catalyst particle) phase surrounding the Al phase. Separate energy balance equations for the Al and matrix phases are developed. Both the matrix and the Al phase are assumed to be nonemitting, anisotropically scattering, absorbing media. The parameters identified which strongly influence Al preheating and melting are Al size, mass fraction, burn rate, and level of incident radiant flux. It was found that large Al mass fractions and small Al particle sizes promote lower Al temperatures. The effect of adding submicron iron oxide burn rate catalyst particles on aluminum preheating was also investigated. It was found that the addition of small amounts of catalyst can theoretically reduce Al temperatures significantly by dominating the optical properties. These results should prove useful to propellant formulators in trying to reduce the problem of unwanted Al agglomeration.

Energetic Nanocomposites as Burn Rate Catalyst for Composite Solid Propellants

2017 ◽  
Vol 43 (2) ◽  
pp. 136-143 ◽  
Author(s):  
Vrushali Bagalkote ◽  
Dan Grinstein ◽  
Benveniste Natan
Keyword(s):  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Composite Solid

scholarly journals Study on Friction Sensitivity of Passive and Active Binder based Composite Solid Propellants and Correlation with Burning Rate

2020 ◽  
Vol 70 (2) ◽  
pp. 159-165
Author(s):  
Ehtasimul Hoque ◽  
Chandra Shekhar Pant ◽  
Sushanta Das
Keyword(s):  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Influential Factors ◽  
Solid Propellants ◽  
Test Results ◽  
Nitrate Esters ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Friction Sensitivity ◽  
Composite Solid

   Friction sensitivity of composite propellants and their ingredients is of significant interest to mitigate the risk associated with the accidental initiation while processing, handling, and transportation. In this work, attempts were made to examine the friction sensitivity of passive binder: Hydroxy Terminated Polybutadiene/Aluminium/Ammonium Perchlorate and active binder: (Polymer + Nitrate Esters)/Ammonium Perchlorate/Aluminium/Nitramine based composite propellants by using BAM Friction Apparatus. As per the recommendation of NATO standard STANAG–4487, the friction sensitivity was assessed by two methods: Limiting Frictional load and Frictional load for 50% probability of initiation (F50). The test results showed that the active binder based formulations were more vulnerable to frictional load as compared to the formulations with passive binders. Examination of a comprehensive set of propellant compositions revealed that the particle size distribution of Ammonium Perchlorate and burn rate catalysts were the most influential factors in dictating the friction sensitivity for HTPB/Al/AP composite propellants. For active binder/AP/Al/Nitramine composite propellants, the formulation with RDX was found more friction sensitive with a sensitivity value of 44 N as compared to its HMX analog (61 N). The correlation studies of friction sensitivity, burning rate, and thermal decomposition characteristics of HTPB/Al/AP composite propellants is described.

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