Abstract
The high density polyethylene, as hybrid rocket fuel, has been chosen to be studied. Thermogravimetric analysis allowed to determine an Arrhenius type equation for its regression rate. A flash pyrolysis coupled to GC/MS/FID has been used to observe influence of oxidative environment on pyrolysis byproducts quantity. With a test bench, the regression rate of the solid fuel under various conditions (pressure, oxidizer mass flow rate, oxygen mass fraction) has been evaluated at an average value of 0.2 mm.s -1 . The Marxman law is completed with other studies conducted at higher oxidizer mass flow rates, between 0.6 and 20 g.s -1 .cm -2 . Finally, the first hybrid rocket combustor simulation is presented along its governing equations. Preliminary comparison gives a numerical regression rate 10% above the value found during experimental firing despite assumptions on the gas phase model.
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