Ability Test of Solid Composite Propellant Burning Rate Based on Composition of Fuel-Binder Ratio Using LAPAN’s HTPB

One of the most important parameters for designing the rocket motor is the burning rate of the propellant used, therefore it is important to know the effect of changes in raw material composition comprising propellant oxidizer, fuel-binders and additive metal on the burning rate. Fuel-binder used is polyurethane which is the reaction product of HTPB and TDI. HTPB used herein are local material that is the synthesis of HTPB in LAPAN’s laboratory. Before it can be declared fit for use as a propellant binder, it must do some validation. One of validation that has been done is to test the value of the burning rate of propellant produced with local HTPB binder. In this study has been testing the propellant burn rate at three different compositions using the method of Crawford Strand Burner. The composition is made by changing the oxidator and aluminum content, and the content of binder used while maintaining at ratio of HTPB / TDI, 7 : 1. The test results showed the composition II has the lowest burning rate value, while the composition III has the highest burning rate. With this burn rate measurability, then this self HTPB fit for use as a binder for the manufacture of the solid composites propellant