IGNITION SYSTEM ON SOLID ROCKET MOTOR FOR 10000 N THRUST, USING HTPB AS AN FUEL AND OXIDISER

Authors

  • Antony Samuel Prabu G Aeronautical Department & MVJCE
  • Vishnu Raj Aeronautical Department & MVJC
  • Irfan Khan Aeronautical Department & MVJC
  • Amogh Balloli Aeronautical Department & MVJCE

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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Published

2019-05-01

How to Cite

Prabu G, A. S. ., Raj, V. ., Khan, I. ., & Balloli, A. . (2019). IGNITION SYSTEM ON SOLID ROCKET MOTOR FOR 10000 N THRUST, USING HTPB AS AN FUEL AND OXIDISER. International Journal of Technical Innovation in Modern Engineering & Science, 5(5), 779–783. Retrieved from https://ijtimes.com/index.php/ijtimes/article/view/2584

Issue

Vol. 5 No. 5 (2019): Vol. 5 No. 5: Volume 5 Issue 5 (May-2019)

Section

Articles