Space Storable Hybrid Rockets for Orbit Insertion or In Situ Resource Utilization Applications

This research effort will pave the way towards a Mars Sample Return (MSR) campaign and potentially, future human exploration of Mars. Hybrid rockets utilize a solid fuel and liquid (or gaseous) oxidizer. A typical flight like configuration is shown in Figure 1. For the MSR application, a hybrid Mars Ascent Vehicle (MAV) would allow the fuel to be transported to Mars as a dense, solid. The oxidizer could be generated from CO2 on the surface, reducing the required landed mass on Mars. Alternatively, a JPL study  has recently identified hybrid propulsion as the lowest mass option of two potential technologies that could enable a single stage to orbit MAV.

Goals:
1. Continue development of a flexible facility capable of small scale hybrid propulsion tests. The facility will be able to adapt to new research objectives as questions arise.
2. Enable the inclusion of hybrid propulsion systems in future mission design studies by determining the empirical constants in the regression rate equation for paraffin-based fuels with in situ oxidizers (a combination of O2, CO and CO2).
3. Determine hybrid rocket packaging constraints by testing at different fuel grain L/D’s to understand how the combustion efficiency and mixing changes with length.