OPTIMASI KINERJA PROPELAN KOMPOSIT PADAT BERBASIS BITUMEN (ASPAL BUTON) MELALUI VARIASI JENIS OKSIDATOR, DENSITAS, DAN RASIO NOSEL

• Main Authors: , Fauzan Affandi,S.Si, , Dr. Ir. Bardi Murachman, SU., DEA.
• Format: Theses and Dissertations NonPeerReviewed
• Published: [Yogyakarta] : Universitas Gadjah Mada 2011
• Subjects: ETD
• Online Access: https://repository.ugm.ac.id/89621/; http://etd.ugm.ac.id/index.php?mod=penelitian_detail&sub=PenelitianDetail&act=view&typ=html&buku_id=51708
• Institution: Universitas Gadjah Mada

This research aims to make a composite solid propellant which is cheap and competitive from bitumen as the main raw material (buton asphalt) that was found in Indonesia and also to study the influence of oxidizing types, the density of propellant and nozzle diameter ratio on the performance of propellant (specific impulse). Propellant is a mixture of fuel, oxidant and metal additive materials. Propellant manufacturing process in this study using the dissolution method. Bitumen was dissolved first with hexane before mixed with an oxidant and metal additive materials. Static test was carried out to determined performance of the propellant. From the static test will be obtained several important parameters which indicate the performance of propellant that is the average thrust (F), and the results of counting specific impulse (Isp). Both of these value are quite important physical parameters for the design of the rocket. To optimize the performance of propellant, some variations should be done, which are included: the type of oxidant, the density of propellant and nozzle diameter ratio. The results of this research showed that the optimum operating conditions for composite solid propellant-based bitumen is: with an oxidant mixture propellant KClO4 and KNO3 (1:1 ratio), density 1.900 gram/cm3 and use the nozzle expansion ratio Ae/A * 3.33. This propellant has a value of average thrust 14.082 N and spesific impulse value 277.0689 seconds. Based on the results of previous research, the composite solid propellant should have a range of specific impulse values between 200-300 seconds. It can be concluded that the propellant as the result of this study can be used as fuel that could make the rocket fly.