The solid rocket propellant [Name TBD], previously called "Propellant X" in development, was developed after the COVID-19 pandemic with initial mixing and testing in April 2023 and finalized in September 2023.
History and Purpose
After the successful manufacturing and launch of Phoenix in January 2023, the team created goals for the next Spaceshot rocket, Project Medusa. One of the Medusa goals are to get halfway to space (~185,000 feet). Therefore, it was clear that a new propellant was necessary to fit the project's goals. Initial propellant formulas were developed in spring 2023, and characterization tests occurred throughout summer 2023. Lack of AP access slowed down the process in late summer-early fall 2023.Due to a lack of mixing space access as a result of the pandemic, the development of the propellant did not begin until November 2021, concluding with the final characterization fire in February 2022. First used in flight on the Phoenix Test Launch in May 2022.
Goals for this formula:
- Experiment with increased aluminum levels using 5-micron aluminum instead of 30-micron
- Make a propellant that is easy to handle when mixing and handling to increase density
- trimodal AP
- Experiment with burn rate modifiersBecome a platform for future propellant formulas to be used on a space shot attempt eventually
Changes from previous propellant (Cherry Limeade):
- Experiment with trimodal AP
- Experiment with burn rate modifiers
- Removed Castor Oil and Triton X100, since the propellant was already viscous
- Changed from 200-micron AP to 400-micron AP as the large particle in packing to increase pourability
- Replaced HTPB with an added a new bonding agent to separate combine HTPB and Tepanol bonding agentAdded magnesium to reduce excessive slag and raise the combustion temperature due to high Al content
Formula
Mixings
| Date | Designation | Motor(s) | Site | Result |
|---|---|---|---|---|
| 4/17/23 | Baja Blast | Characterization Motors | RT Lab | Resulted in too low pressures |
| 7/23/23 | Blue Voltage | Characterization Motors | RT Lab | |
...
| Date | Propellant | Result |
|---|---|---|
| 7/1/23 | Baja Blast | 5 test motors integrated: 2 successful fires, 1 failure (igniter lodged itself inside the small nozzle opening), 1 didn't ignite (igniter was well at the bottom but the motor, 1 not attempted (nozzle was smaller than the failed motor, so even higher risk of repeating failure). Unfortunately, we couldn't use this data due to our pressure numbers for static fire being lower than expected (to the point that it's an issue). Likely issue was due to our load cell because hydrosttic test was successful (so no leaks). |
| 7/15/23 | Baja Blast | Static fire cancelled due to thunderstorms all day |
| 7/29 | Baja Blast | Two successful fires, but both motors had leaks, leading to substantial pressure loss. Location of leaks weren't clear until deintegrationde-integration: the braces pushed the nozzle away from the carrier by a few thousandths, destroying the RTV seal. Decisions after this static fire: create new formulation for next characterization fire, and remove converging section of nozzle (make it a graphite puck). |
| 8/29 | Blue Voltage | 5 test motors prepared, all successfully fired. Pressures are within good operating range (Nozzle A - 1779 psi, Nozzle E - 1249 psi, Nozzle I - 1283 psi, Nozzle, N - 808 psi, Nozzle S - 684 psi Interesting observations about all motors:
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