2017 |
Volume 2 |
Issue Issue 2
Burning Rate Study of PSAN-HTPB Based Solid Rocket Propellants
1.
Rajan Lakra
– Assist. Prof., Dept. Of Aeronautical Engineering, Bhubaneswar Engg. College, Odisha, India.
2.
Swagat Prasad Das
– Assist. Prof., Dept. Of Aeronautical Engineering, Bhubaneswar Engg. College, Odisha, India.
3.
S. K. Samal
– Assist. Prof., Dept. Of Aeronautical Engineering, Bhubaneswar Engg. College, Odisha, India.
Received
16-Dec-2017
|
Accepted
-
|
Published
16-Dec-2017
|
Abstract
Composite propellants based on Ammonium Perchlorate (AP) as oxidizer are in major role in solid rocket. However, because of their high toxic exhaust, it is not suggested for global environmental pollution issue. Therefore, researchers want to replace AP based propellants with clean exhaust propellant. Ammonium Nitrate (AN) has the properties which can satisfy the present environmental need in the field of propellant. However, the disadvantage for the application of AN - as solid propellant oxidizer is its dimensional instability in different temperature ranges due to phase transformation which causes change of volume and porosity of the propellant grain. This was be resolved by the use of Phase Stabilized Ammonium Nitrate (PSAN) for propellant processing. Synthesized mixed metal oxides were used to enhance burning rate. These propellant samples were then tested for measuring burn rate in a Crawford High Pressure Strand Burner and thermal degradation studies carried out Simultaneously in Thermal Analyzer (STA). It is observed that the thermal decomposition and burn rate of the propellant is maximum by adding anyone of the mixed metal oxide catalyst among 3 different catalysts. In this research the different samples are formulated to test and get results. It has been observed that only two propellants burnt properly as compared to other propellants taken for the analysis.
Keywords Burn rate, Catalytic combustion, Preparation of catalyst, Preparation of PSAN, Solid propellants, Thermal decomposition.
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