Motives for Decreasing the Curing Time of HTPB-AP Composite Propellants

Authors

  • Nagmeldin Elamin Defence Industries System, Advanced Industries Group, Sudan
  • Ahemed.M. Bashir Defence Industries System, Advanced Industries Group, Sudan

DOI:

https://doi.org/10.54388/jkues.v1i2.64

Keywords:

Composite propellant, Curing time, Curing temperature, Burning rate

Abstract

One of the standard conditions for solidifying composite propellants consist of hydroxyl terminated poly-butadiene as a binder and ammonium perchlorate as oxidizer, is the curing process for certain time in a certain temperature. On this paper, the motives and reasons for the decreasing of this curing time were studied and discussed. The study and discussion include the productivity, cost, delivery, manpower, and maintenance points of view. By experiments and questionnaire work, it was seen that, all the previous points of view were affected positively. Generally, the productivity of the propellant was increased by 100%, the cost of curing process was decreased by 25% of the previous cost, the man power needed for the process of waiting and recording the readings was decreased by 50%, customer delivery process was fasted by 50% of the previous delivery time, and finally the maintenance processes due to equipment depreciation were improved by 50% from the previous. From the whole point of view, it was seen that, the decreasing of the curing time is very useful for the production of the propellant. Finally, it is observed that the decreasing of the curing time to the half time brought the same properties of the standard curing time, and then it is concluded that the deceasing of the curing time can be applied safely and usefully in the casting production line.

References

{1} Nagmeldin M. Elamin and M.H.M Abuuznien "Effect of the decreasing of curing time on the performance and mechanical properties of HTPB-AP composite propellants". 12th international conference of aerospace sciences and aviation technology in military technical college {Cairo - Egypt}, 2007.

{2} Francis,G. et al.,"Structural Assessment of Solid Propellant Grains", Advisory Group for Aerospace Research and Development {AGARD, AR-350}, England, 1997.

{3} Lewis,R.C., "Solid Propellants Selection and Characerization", National Aeronautics and Space Administration {NASA SP8064}, USA, 1971.

{4} Urbanski, T., "Chemistry and Technology of Explosives", vol. 4, Pergamon Press, Oxford, New York, 1984.

{5} Alain, D., "Solid Rocket Propulsion Technology", Pergamon Press, Oxford New York, 1993.

{6} Lewis,R.C., "Solid Propellants Processing Factors in Rocket Motor Design", NASA SP8075, Oct, 1971.

{7} Sutton, G. P., "Rocket Propulsion Elements", An Introduction to the Engineering of Rockets, New York, Fourth Printing, May 1967.

{8} Viger,Y,et al.,"Solid Propellant Chemistry, Combustion and Interior Motor Ballistics", Progress in Astronautics and Aeronautics, AIAA, Vol 185, USA, April 2000.

{9} Luigi, D.L., Edward W. P. and Summerfield,M.,"Nonsteady Burning and Combustion Stability of Solid Propellants", Progress in Astronautics and Aeronautics, Volume 143, May 1992.

Downloads

Published

2021-12-21

How to Cite

Elamin, N., & Bashir, A. . (2021). Motives for Decreasing the Curing Time of HTPB-AP Composite Propellants. Journal of Karary University for Engineering and Science, 1(2). https://doi.org/10.54388/jkues.v1i2.64