scholarly journals Combustion stability analysis of composite propellants with octogen

2020 ◽  
Vol 70 (2) ◽  
pp. 22-28
Author(s):  
Marica Bogosavljević ◽  
Slavko Mijatov ◽  
Aleksandar Milojković ◽  
Vesna Rodić
Keyword(s):  
Stability Analysis ◽  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Oxide Powder ◽  
Combustion Stability ◽  
Operating Pressure ◽  
Solid Propellants ◽  
Rate Laws ◽  
Composite Solid Propellants ◽  
Composite Solid

Research of operating pressure levels with irregular combustion and the effect on combustion instability of composite solid propellants with different quantity of octogen (HMX) are presented in this paper. The content of HMX increased in relation to the oxidant, ammonium perchlorate (AP). Combustion stability of the propellants was improved by adding titanium (IV) oxide powder and through the optimal projected ratio of two oxidizer fractions. Parameters of burning rate laws were determined and p-t diagrams were observed and compared.

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.

NUMERICAL SIMULATION OF COMBUSTION OF THE COMPOSITE SOLID PROPELLANT CONTAINING BIDISPERSED BORON POWDER

2021 ◽  
pp. 131-139
Author(s):  
V.A. Poryazov ◽  
◽  
K.M. Moiseeva ◽  
A.Yu. Krainov ◽  
◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Burning Rate ◽  
Solid Propellant ◽  
Mathematical Formulation ◽  
Solid Propellants ◽  
Boron Powder ◽  
Composite Solid Propellant ◽  
Composite Solid Propellants ◽  
Composite Solid ◽  
Propellant Surface

A problem of combustion of the composite solid propellants containing various powders of metals and non-metals is relevant in terms of studying the effect of various compositions of powders on the linear rate of propellant combustion. One of the lines of research is to determine the effect of the addition of a boron powder on the burning rate of a composite solid propellant. This work presents the results of numerical simulation of combustion of the composite solid propellant containing bidispersed boron powder. Physical and mathematical formulation of the problem is based on the approaches of the mechanics of two-phase reactive media. To determine the linear burning rate, the Hermance model of combustion of composite solid propellants is used, based on the assumption that the burning rate is determined by mass fluxes of the components outgoing from the propellant surface. The solution is performed numerically using the breakdown of an arbitrary discontinuity algorithm. The dependences of the linear burning rate of the composite solid propellant on the dispersion of the boron particles and gas pressure above the propellant surface are obtained. It is shown that the burning rate of the composite solid propellant with bidispersed boron powder changes in contrast to that of the composite solid propellant with monodispersed powder. This fact proves that the powder dispersion should be taken into account when solving the problems of combustion of the composite solid propellants containing reactive particles.

Nanocatalysts: Potential Burning Rate Modifier for Composite Solid Propellants

2014 ◽  
Vol 3 (2) ◽  
pp. 81-91 ◽  
Author(s):  
Jitendra K. Sharma ◽  
Pratibha Srivastava ◽  
Gurdip Singh
Keyword(s):  
Burning Rate ◽  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Composite Solid
Sign in / Sign up

Export Citation Format

Share Document