scholarly journals Slow-Burn Ammonium Perchlorate Propellants with Oxamide: Burn Rate Model, Testing, and Applications

2021 ◽  
pp. 1-9
Author(s):  
Matthew T. Vernacchia ◽  
Kelly J. Mathesius ◽  
R. J. Hansman
Keyword(s):  
Ammonium Perchlorate ◽  
Model Testing ◽  
Rate Model ◽  
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.

Control of predefined diesel combustion processes by a burn-rate model

2016 ◽  
pp. 433-450
Author(s):  
Reza Rezaei ◽  
Enrico Neumann ◽  
Maximilian Brauer ◽  
Christopher Severin
Keyword(s):  
Diesel Combustion ◽  
Rate Model ◽  
Burn Rate ◽  
Combustion Processes

Simplified Burn-Rate Model for CMDB Propellants

1990 ◽  
Vol 40 (3) ◽  
pp. 255-262 ◽  
Author(s):  
A. R. Kulkarni ◽  
V. K. Bhat ◽  
S. P. Phadke ◽  
R.G.K. Nair
Keyword(s):  
Rate Model ◽  
Burn Rate

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.

Fast predictive burn rate model for gasolineHCCI

2016 ◽  
pp. 155-169 ◽  
Author(s):  
Mahir Tim Keskin ◽  
Michael Bargende ◽  
M. Grill
Keyword(s):  
Rate Model ◽  
Burn Rate

scholarly journals Scale effects on hybrid rocket engine performance

2021 ◽  
Author(s):  
Alexander Velliaris
Keyword(s):  
Computer Program ◽  
Scale Effects ◽  
Rocket Engine ◽  
Engine Performance ◽  
Scaling Up ◽  
Rate Model ◽  
Hybrid Rocket ◽  
Injection Temperature ◽  
Hybrid Rocket Engine ◽  
Burn Rate

In the current study, the effects of scaling up a hybrid rocket engine (HRE) in size has on its performance is investigated. A HRE design from a past RU study is selected as the base model to be progressively increased in size while geometric scale is maintained, up to ten times the original’s size. A computer program employing a quasi-steady convective heat feedback burn rate model is used to conduct simulated engine firings. One finding from this study is that the drop- off in performance for this engine, in going up in size, is not as much as expected. This can be attributed to a conservative oxidizer injection temperature setting in the model, and an oxidizer-fuel ratio mixture influence for this engine that is more impactful. The results presented here however do, to some degree, concur with established trends, with respect to thrust prediction, as the reference HRE is scaled up in size.

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