IGNITION SYSTEM ON SOLID ROCKET MOTOR FOR 10000 N THRUST, USING HTPB AS AN FUEL AND OXIDISER
Antony Samuel Prabu G
Aeronautical Department & MVJCE , IN
Vishnu Raj
Aeronautical Department & MVJCE , IN
Irfan Khan
Aeronautical Department & MVJCE , IN
Amogh Balloli
Aeronautical Department & MVJCE , IN
Keywords: Pyrogen, HTPB-Hydroxyl terminated polybutadiene, oxidiser
Abstract
In the present study, ignition system on a solid rocket motor is an challenging task. To ignite the solid Rocket propellant Pyrogen technique is been used. Using Catia V5 R21 software, solid rocket motor is modelled & fabricated the same in a scaled down version. HTPB is used as the fuel and oxidiser in the solid rocket motor. Testing of the igniter had been carried out by using different ohms resistors and using the thermal image capture temperature has been calculated around the igniter. Coding is carried out using mat lab software to plot the graph.
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