Combustion Characteristics of AP Based Solid Rocket Propellant

There were many studies on ammonium perchlorate (AP) based solid rocket propellant and some data already existed. However, there is no complete data available in Malaysia especially on the information of combustion characteristics of baseline data of AP based SRP. This monograph discusses on the combustion characteristics of AP based SRP including the methods of the propellant selection and fabrication, burning rate test and static thrust test. Thirteen sets of different propellant mixture were prepared with consideration of the mechanical and processability factors. The propellant was a mixture of AP as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as binder/fuel. By varying the AP and Al, the effect of oxidizer-fuel (O/F) ratio on the whole propellant was determined. The propellant strands were manufactured using press-molding method and burned in a strand burner to obtain the initial burning characteristics. This monograph suitable for those who interested to get better understanding in AP based solid propellant.

Autorentext

Amir Aziz, B.Eng. Mechanical (Aeronautics), from Universiti Teknologi Malaysia, Malaysia (2008).MSc Mechanical specialized in solid propellant (2011) from Universiti Tekonologi Malaysia, Malaysia. lecturer at the Faculty of Mechanical Engineering, Universiti Malaysia Pahang (UMP) in 2011. His research interest is in Rocket Propulsion Technology.