Universiti Teknologi Malaysia Institutional Repository

Propellant development for small rockets

Rahmat, Mohd. Zaki Yamani and Mohd. Jaafar, Mohammad Nazri and Abdul-Latif, Ainullotfi and Wan Ali, Wan Khairuddin and Mat Yajid, Zuriana Mariati and Kimsin, Intan Noryanah (2008) Propellant development for small rockets. In: 2nd Regional Conference on Vehicle Engineering & Technology, 15 - 16 July 2008, Hotel Istana, Kuala Lumpur.



The solid propellant rocket is the basis for most recent rocket inventions where it is utilized mostly in military rockets. Solid propellants are the simplest of all rocket propulsion systems and have a variety of materials and methods for development. The purpose of this research is to develop solid propellant based on potassium nitrate, carbon, and sulphur mixture. To obtain an optimum propellant composition and performance, a number of propellant burning-rate tests have been conducted. Seven sets of propellants with different compositions have been produced using the compression method. The results obtained from the burning-rate tests show that propellants at stoichiometric composition gave the highest burning-rate of 0.2734 cm/s.

Item Type:Conference or Workshop Item (Paper)
Uncontrolled Keywords:rockets, solid propellants, potassium nitrate, burning-rate, stoichiometry
Subjects:T Technology > TJ Mechanical engineering and machinery
Divisions:Mechanical Engineering
ID Code:7409
Deposited By: Shamsuri Ehsan
Deposited On:07 Jan 2009 01:46
Last Modified:07 Sep 2017 04:07

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