NiCoZn Ferrite: burn rate enhancer for AP/HTPB based propellant and its catalytic study on the decomposition of ammonium perchlorate

2021 ◽  
pp. 1-28
Author(s):  
Pragnesh Dave ◽  
Riddhi Thakkar ◽  
Ruksana Sirach ◽  
Dilip M. Badgujar ◽  
Milind Deshpande
Keyword(s):  
Ammonium Perchlorate ◽  
Burn Rate

scholarly journals Solid Fuel rich Propellant Development for use in a Ramjet to Propel an Artillery Shell

2020 ◽  
Vol 70 (3) ◽  
pp. 329-335
Author(s):  
Velari Yogeshkumar ◽  
Nikunj Rathi ◽  
P. A. Ramakrishna
Keyword(s):  
High Pressure ◽  
Tensile Strength ◽  
Ammonium Perchlorate ◽  
Solid Fuel ◽  
Pressure Index ◽  
Time Period ◽  
Ballistic Properties ◽  
Base Bleed ◽  
Burn Rate ◽  
Artillery Shell

This study describes the development of a fuel-rich propellant to be used in a solid fuel ramjet to provide active propulsion to a 155 mm artillery shell. Fuel-rich propellants consisting of aluminum, ammonium perchlorate and hydroxyl terminated polybutadiene were developed and their ballistic properties were measured to choose the appropriate fuel for the ramjet application. The attempts made were to enhance the burn rates of the propellant to provide required burn rates at lowest possible pressures in primary combustor of the ramjet. The propellant selection was done with reference of working time period of the base bleed unit, to calculate the required burn rate and corresponding pressure in primary combustor. It was observed that the fuel rich propellant of composition 35% ammonium perchlorate with 1 % Iron oxide embedded on it, 30 % mechanically activated aluminum with 10% polytetrafluoroethylene, and 25 % HTPB was found suitable for the above application. This provided the higher burn rates among all developed propellants with high pressure index of 0.58. This makes it suitable for the ramjet requiring higher burn rates at lower possible primary chamber pressures. The Young’s modulus and tensile strength of this propellant was measured to be 1.73 MPa and 0.24 MPa, respectively.

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.

Graphene-iron oxide nanocomposite (GINC): an efficient catalyst for ammonium perchlorate (AP) decomposition and burn rate enhancer for AP based composite propellant

RSC Advances ◽  
2015 ◽  
Vol 5 (3) ◽  
pp. 1950-1960 ◽  
Author(s):  
Abhijit Dey ◽  
Javaid Athar ◽  
Pankaj Varma ◽  
Hima Prasant ◽  
Arun K. Sikder ◽  
...  
Keyword(s):  
Iron Oxide ◽  
Ammonium Perchlorate ◽  
Composite Propellant ◽  
Efficient Catalyst ◽  
Burn Rate

Development of a facile and ecofriendly route for the synthesis of GINC, followed by characterization and evaluation in propellants for missiles.

α-Fe2O3 hexagonal cones synthesized from the leaf extract of Azadirachta indica and its thermal catalytic activity

2015 ◽  
Vol 39 (9) ◽  
pp. 7105-7111 ◽  
Author(s):  
Jitendra Kumar Sharma ◽  
Pratibha Srivastava ◽  
M. Shaheer Akhtar ◽  
Gurdip Singh ◽  
Sadia Ameen
Keyword(s):  
Thermal Decomposition ◽  
Catalytic Activity ◽  
Green Synthesis ◽  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Azadirachta Indica ◽  
Leaf Extract ◽  
Burn Rate

This work reports the synthesis of α-Fe2O3 hexagonal cones by green synthesis using Azadirachta indica leaf extract and their utilization as an efficient burn rate catalyst for the thermal decomposition of ammonium perchlorate (AP) and enhancing the burning rate of CSPs.

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