The Total Impulse Study Of Solid Propellants Combustion Containing Activated Carbon From Coconut Shell As A Catalyst

Nur Rachman Supadmana Muda, I.N.G.Wardana I.N.G.Wardana, Nurkholis Hamidi, Lilis Yuliati, Aries Boedi Setiawan


This study investigates the capabilities of thrust, burn time, and total impulse from solid propellant materials. Attempts to increase the three variables are quite difficult because the thrust value is inversely proportional to the value of the burn time, it requires the catalyst as a regulator of the composition to produce an optimal variable value. The activated carbon from the coconut shell is used as a catalyst on a composite solid propellant material containing ammonium perchlorate (AP), hydroxyl terminated polybutadiene (HTPB) and aluminium (Al). The effect of adding coconut shell activated carbon may affect thrust parameters, burn time and total impulse rocket. The method of measuring parameters using rocket thrust test equipment. The mass of the test sample is 250 grams, the diameter of the test chamber is 20 mm, the length of the chamber is 200 mm. After going through the combustion process, it produces a graph and thrust value, total impulse and burning time. The thrust test results show that the test propellant 3 produces the best characteristic composition of 70% AP, 15% HTPB, 10% Al, and 5% activated carbon of 400 mesh with average thrust: 148.67N, total impulse: 637, 5 Ns, burn time: 4,288 s.

Full Text:



Aigbodion. V.S: “Potential of using bagasses ash particle in Metal Matrix Composite, PHD Department of Metallurgical and Materials Engineering, Ahmadu Bello University”, Samaru, Zaria, Nigeria, 2010 Bamgboye A. Isaac and Jekayinfa .S. O: “Energy Consumption Pattern in Coconut Processing Operations”.

Agricultural Engineering International: the CIGR Journal Manuscript EE 05013. Vol. VIII, 2006. Galfetti, L., Severini, F, DeLuca, L.T., Marra, G.L., Meda, L., Braglia, R., “ Ballistics and Combustion Residues of Aluminized Solid Rocket Propellants”. In: Proceedings of the 9-IWCP, Novel Energetic Materials and Applications, vol. 18., 2014 G. Singh, I.P.S.Kapoor, R.Dubey and P.Srivastava, “Preparation Characterization and catalytic behaviour of CdFe2O4 and Cd nanocrystals on AP, HTPB and composite solid propellants”, Thermochimica Acta, Vol.511,No.1,2010,pp.112-118. Hinkelman, Matthew C., dan Stepen D Heister,. Evaluation of Solid Composite Propellants Using a Dicyclopentadiene Binder, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San Diego, 2011,”Thrust Curve Tool”,, Rev. 11/01/2006, v1.06 K. Kishore, “Comprehensive view of the combustion models of composite solid propellants”,AIAA J.,17, 1979, pp. 1216-1224 Kishore, K., & K Sridhara, 1999. Solid Propellant Chemistry, Ministry of Difense, New Delhi.

Martin, et al, 2003. Variable Burn Rate Propellant,US Patent No. 6, 503. 350 B2. O.S.Olaoye,O.A.Abdulhafeez,”Design and Performance Characteristics of Rocket Using Potassium Nitrate and Sucrose as Propellants”, International Journal of Science and Reserach(IJSR), Volume 3 Issue 8, August 2014.

P.B Madakson, D.S.Yawas and A. Apasi.,”Characterization of Coconut Shell Ash for Potential Utilization in Metal Matrix Composites for Automotive Applications”, International Journal of Engineering Science and Technology (IJEST), Vol. 4 No.03 March 2012 R.F.B.Gongalves,J.A.F.F.Rocco and K.lha,”Thermal decomposition kinetics of aged solid propellant based on amonium perchlorate-AP/HTPB binder”,44th AIAA/ASME/SAE/ASEE Joint propulsion Conference and Exhibit,July 2008. Richard Nakka, “Experimental Rocketry Web Site KN-Sucrose Propellant Chemistry and Performance Characteristics”,2001 Rajan T.P.D, Pillai R.M, Pai B.C., Satyanarayana K.G, Rohatgi, P.K : Fabrication and characterization of Al–7Si–0.35Mg/fly ash metal matrix composites processed by different stir casting routes, Composites Science and Technology, 67, 3369–3377, 2007. S. Chaturvedi, P.N. Dave, “Nano metal oxide: potential catalyst on thermal decomposition of ammonium perchlorate “, J. Exp. Nanosci., 2011, pp. 1-27 Sutton, G.P.,Biblarz, O.,”Rocket Propulsion Elements”, Newyork: Wiley-nterscience,2000



  • There are currently no refbacks.