Test Method for Solid Rocket Propellant Specific Impulse Measurements

10.1520/d2508 ◽  
2003 ◽  
Author(s):  
Keyword(s):  
Specific Impulse ◽  
Test Method ◽  
Solid Rocket Propellant ◽  
Rocket Propellant ◽  
Solid Rocket

scholarly journals Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant

2021 ◽  
Vol 6 (2) ◽  
pp. 34-41
Author(s):  
Gbadebo Omoniyi Adeniyi ◽  
Inkechukwu Nkere ◽  
Lanre Moshood Adetoro ◽  
Olusegun Samuel Sholiyi
Keyword(s):  
Cell Model ◽  
Single Point ◽  
Specific Impulse ◽  
Potassium Nitrate ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Dual Fuel ◽  
Solid Rocket Propellant ◽  
Rocket Propellant ◽  
Solid Rocket

The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delivered specific impulse, delivered characteristic velocity, and the chamber pressure. The formulations tested were potassium nitrate–sucrose propellant (65% KNO3 and 35% sucrose (C12H22O11)) (KNSU); potassium nitrate-sorbitol propellant (65% KNO3 and 35% sorbitol (C6H14O6)) (KNSB); modified potassium nitrate-sucrose propellant (65% KNO3, 32% sucrose (C12H22O11)), and 3% carbon (C) (MODKNSU); potassium nitrate-sucrose-sorbitol propellant (65% KNO3, 25% sucrose (C12H22O11)), and 10% sorbitol (C6H14O6) (KNERK); potassium nitrate-sucrose-sorbitol-carbon propellant (65% KNO3, 24% sucrose (C12H22O11), 10% sorbitol (C6H14O6), and 1% carbon (C)) (MODKNERK); and finally a propellant made from KNO3, sucrose (C12H22O11), sorbitol (C6H14O6), carbon (C) and iron II oxide(Fe2O3) combinations in 65, 30, 3, 1, 1% proportion respectively. The novel result obtained from these experiments was applied to boost the performance of a KNSB rocket propellant motor during a rocket launch experiment. Both static and dynamic rocket motor internal ballistic parameters were then compared. The measured delivered motor average thrust and the effective propellant burn times were recorded as: (164.15N, 3.97s); (102.95N, 6.53s); (65.66N, 9.38s); (79.09N, 3.77s); (243.98N, 3.77s) and (92.6N, 5.89s) respectively. The MODKNERK, was established to produce a most efficient motor and with the full delivery of its ballistic energy. It was also established, that the ballistic and rocket motor efficiency of a lower energy rocket motor can be improved by starting the ignition of such motor with fast burning dual-fuel rocket propellant (MODKNERK).

Analysis of aluminum particle combustion in a downward burning solid rocket propellant

Fuel ◽  
2019 ◽  
Vol 237 ◽  
pp. 405-412 ◽  
Author(s):  
Castillo Griego ◽  
Nadir Yilmaz ◽  
Alpaslan Atmanli
Keyword(s):  
Aluminum Particle ◽  
Solid Rocket Propellant ◽  
Rocket Propellant ◽  
Particle Combustion ◽  
Solid Rocket

scholarly journals EMERGENCY BURNING OF SOLID ROCKET PROPELLANT: DAMAGE RISK ASSESSMENT TO PEOPLE IN THE WORKPLACE

2020 ◽  
Vol 0 (3(87)) ◽  
pp. 7-15
Author(s):  
M. M. Biliaiev ◽  
O. V. Berlov ◽  
V. V. Biliaieva ◽  
V. A. Kozachyna ◽  
I. V. Kalashnikov
Keyword(s):  
Risk Assessment ◽  
Solid Rocket Propellant ◽  
Rocket Propellant ◽  
Solid Rocket ◽  
Damage Risk

THE ENVIRONMENT CREATED BY AN OPEN-AIR SOLID ROCKET PROPELLANT FIRE

2007 ◽  
Vol 179 (5) ◽  
pp. 1003-1027 ◽  
Author(s):  
L. W. Hunter ◽  
Y. Chang ◽  
H. N. Oguz ◽  
J. T. Wilkerson ◽  
A. M. Lennon ◽  
...  
Keyword(s):  
Solid Rocket Propellant ◽  
Rocket Propellant ◽  
Solid Rocket
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