Session
Weekday Session 9: Propulsion
Location
Utah State University, Logan, UT
Abstract
The Space Dynamics Lab is developing a prototype "green" hybrid prototype propulsion system for SmallSats. The system is based on Utah State's patented High Performance Green Hybrid Propulsion (HPGHP) technology. HPGHP leverages unique dielectric breakdown properties of 3D-printed acrylonitrile butadiene styrene (ABS), allowing re-start, stop, and re-ignition. HPGHP works most reliably using gaseous oxygen (GOX) as the oxidizer, but has experienced ignition reliability and latency issues when replaced by high test hydrogen peroxide (HTP). This deficiency results from HTP's high decomposition energy barrier. Tests show that noble metal catalysts like platinum on alumina are effective at decomposing 90% HTP in monopropellant form, but the decomposition releases insufficient energy to reliably ignite a hybrid rocket. This study reports on a non-catalytic, thermal-ignition method for hybrid rockets. Combustion is initiated using a gaseous oxygen pre-lead, with HTP being introduced to the hot combustion chamber once full GOX-ignition occurs. Residual energy from the GOX/ABS combustion thermally decomposes the HTP flow, with the freed-oxygen allowing full HTP-hybrid combustion. Design options and test results are presented for prototype systems at 0.5, 1.0, and 5 N thrust levels using 90% HTP with acrylonitrile butadiene styrene (ABS) and polymethylmethacrylate (PMMA) as fuels.
A Miniaturized Hydrogen Peroxide/ABS Based Hybrid Propulsion Systems for CubeSats
Utah State University, Logan, UT
The Space Dynamics Lab is developing a prototype "green" hybrid prototype propulsion system for SmallSats. The system is based on Utah State's patented High Performance Green Hybrid Propulsion (HPGHP) technology. HPGHP leverages unique dielectric breakdown properties of 3D-printed acrylonitrile butadiene styrene (ABS), allowing re-start, stop, and re-ignition. HPGHP works most reliably using gaseous oxygen (GOX) as the oxidizer, but has experienced ignition reliability and latency issues when replaced by high test hydrogen peroxide (HTP). This deficiency results from HTP's high decomposition energy barrier. Tests show that noble metal catalysts like platinum on alumina are effective at decomposing 90% HTP in monopropellant form, but the decomposition releases insufficient energy to reliably ignite a hybrid rocket. This study reports on a non-catalytic, thermal-ignition method for hybrid rockets. Combustion is initiated using a gaseous oxygen pre-lead, with HTP being introduced to the hot combustion chamber once full GOX-ignition occurs. Residual energy from the GOX/ABS combustion thermally decomposes the HTP flow, with the freed-oxygen allowing full HTP-hybrid combustion. Design options and test results are presented for prototype systems at 0.5, 1.0, and 5 N thrust levels using 90% HTP with acrylonitrile butadiene styrene (ABS) and polymethylmethacrylate (PMMA) as fuels.
