Firebiter

On Nov 13th 2022, Firebiter, an 6-inch diameter, 64-inch long P-class solid rocket motor, was successfully fired, becoming the team’s first successful static fire since Spring 2019. The motor delivered a total impulse of 15,674 lbf-s, producing a maximum thrust of 1632 lbs. Firebiter was fired in a carbon-epoxy motorcase with a carbon-phenolic nozzle, all of which were designed and fabricated by USC students. 



Mission: Firebiter

Fired: 11/13/2022

Performance:

Total Impulse: 15,674 lbf-s

Max Thrust: 1,632 lbf

Burn Time: 9.19 sec


 

The purpose of this static fire was to certify a motor for use on Fireball, our upcoming 6” high-performance flight vehicle. The design of Firebiter began in September 2022, we started by designing the overall grain geometry and nozzle geometry by utilizing our proprietary motor simulation. After the design was completed the engineering leads compiled a comprehensive design review detailing both the design and planned manufacturing process. This design review was presented to both current members and lab alumni, and after considering all aspects of the design the team agreed to move forward with manufacturing.


The first component to be produced was the carbon-fiber filament wound case which is essential to containing the extreme internal pressure of the burning solid propellant. The design of the case was determined by our analysis team, using in-house developed scripts to analytically calculate the optimal wind angles and overall laminate design. After handing this design off to the composites team the winding could begin!


Filament Winding

After hours of meticulous winding the case was placed in an oven in order to cure the epoxy. After curing overnight, the case was ready to be removed from the oven and taken off its mandrel, and the composites team were eager to inspect this first case of the year. Unfortunately, during inspection of the inside of the case a flaw was found, the part of the case responsible for sealing against the bulkheads had chipped. The cause of the defect was quickly determined to be a minor manufacturing oversight, and we were confident a new case wouldn’t have this same issue. However, a new case layup would be a formidable task, it takes nearly two full days to complete the entire process, and the composites team has to constantly supervise in order to ensure the layup is proceeding without error. So following the discovery of this defect a discussion was organized to talk about possible solutions/repairs to the chipping. Although, after careful consideration of possible solutions we came to the conclusion that any solution at this point would introduce unquantifiable risk of the seals failing, which would certainly result in the destruction of the case and the failure of the static fire. So we concluded that doing a whole new case layup would be the best course of action.

A few weeks later the new case layup began and with cautious optimism we hoped this case would turnout well. The winding began and we patiently watched as layer by layer the case began to take shape. Once the winding was complete, once again the case was placed in the oven and cured overnight. This time when the case was removed, we took it off it’s mandrel and we saw that the sealing surface was pristine, and the case looked amazing (pictured below).

Completed Motor Case

The nozzle was the next component to be completed. The process began with our machining team creating the mold onto which the nozzle would be formed. The composites team then intricately wrapped layers of carbon phenolic in order to form the nozzle. After the wrapping was complete the nozzle was cured. Pictured below is the nozzle after it was finished curing and ready to be removed from its mold. Once the nozzle was demolded, it was handed to the machining team for final machining and completion.


Cured Nozzle

Completed Nozzle


The propellent grains were the next to be produced. RPL sets itself apart from other collegiate organizations in the fact that we cast our own solid propellant. To cast the grains the propulsion team has to travel out to a specialized off-site facility where we ultimately mix, cast, cure and then finally integrate said grains into the motor case.

For Firebiter the casting trips didn’t come without some difficulties, during one casting session an unforeseen lightning storm appeared in the skies, this presented a danger to the mixing operations and therefore was halted for the day and all personnel went home. Regrettably this meant all the propellent mixed that day was scraped. Despite this unfortunate complication the propulsion team bounced back and resumed production and before long all the grains were cast and ready to be integrated into the motor. Most excitingly the propulsion team had worked out a new process and formulation which allowed for the propellant to be easily pourable, a feat which had been in the works for the past few years but had been elusive till now. This pourable quality enabled the propellant to be packed more efficiently, and thus the propellant density was significantly increased.


When all parts were ready for final assembly, we drove out to the Reaction Research Society’s Mojave Test Area (MTA). Once at MTA we unpacked our trailer, and began our integration process.

Ready to Fire!

Once the motor was fully-integrated on the pad and we got the all-clear from the on-site pyro-technician to proceed with the static fire. We retreated to the bunker with nervous anticipation. Standing in the bunker the Earthshaker static fire series loomed heavy in all our minds, the three consecutives failures of ESI, ESII, and ESIII gave discouraging prospects for this static fire but we all hoped Firebiter would break the streak. Once all respective leads had given the ‘GO’ for firing we readied ourselves.

The countdown began.…Three…Two…One…IGNITION

The motor erupted into a fury of fire and smoke. Everyone was captivated as the motor burned, and we watched with baited breath for whether it would end in a fiery explosion or successfully complete the burn.

Before long the raging exhaust yielded and the smoke cleared.

IT WORKED!

The bunker erupted into a frenzy of cheers and excitement. The success of this static fire was the culmination of months of hard work, and marked the end of a discouraging chain of failures.

Armed with this success we are moving forward with Fireball, our upcoming 6” flight vehicle. Look out for more information on Fireball in the upcoming months as we hope to launch in the coming spring.

SUCCESS!

 

Jawbone Launch

USCRPL successfully launched and recovered Jawbone on Saturday April 23rd, 2022. The vehicle reached an apogee of 41,300 ft AGL, a max speed of Mach 1.717, and a peak acceleration of 7.266 Gs. Jawbone saw multiple new systems in avionics and recovery. First, the avionics unit on Jawbone received a number of upgrades. First flown on CTRL+V, USCRPL's custom pancake-style PCB stack conforms around the nosecone deployment CO2 canister, allowing more space in the nosecone. The system featured a new custom battery charging and management PCB to prolong pad standby time. Additionally, this was our first flight of the Lightspeed Rangefinder, an in-house designed and built tracking unit that used four ground stations positioned around the launch site to triangulate the position of Jawbone following its flight.

We lost communications with the main avionics unit a few seconds into flight due to a ground side antenna issue. Lightspeed Rangefinder ground stations continued to track the rocket and collect positional data, which proved valuable during the recovery effort of the vehicle. The avionics unit itself performed nominally, collecting GPS, inertial, and barometric data which we analyzed after recovery to determine the vehicles performance.

The Jawbone recovery system featured a next-generation design with improvements from the CTRL+V dual deployment recovery system. Using a connector and extension wire running along the forward shock cord segment, USCRPL's custom avionics unit attempted to control the active deployment of the main parachute when the vehicle reached a decent altitude of approximately 5,000ft. Unfortunately, the recovery system experienced a partial failure resulting in the main parachute failing to open. The drogue parachute still successfully deployed, so the vehicle was recovered intact. The main parachute, which was constrained using a Tender Descender, never deployed due to unexpected loads during nosecone deployment disconnecting the cable attached to the Tender Descender. Additionally, main deployment was never commanded by the avionics unit due to differences between the simulated and actual performance of the vehicle causing touchdown to occur sooner than expected.

Earthshakiier Anomaly Update

Last month, USCRPL fired Earthshakiier (ESII), the space-shot motor designed for Domepiercer, which failed 0.552 seconds into the test. Following the anomaly, USCRPL immediately began the first step of our all-hands anomaly investigation by documenting the condition and location of all debris around the site. We then spent four weeks combing through the data, including strain gauge and load cell measurements. After data review and discussion, we have concluded that this failure was different from Earthshaker (ESI), which failed due to a forward end burn-through in Fall 2020. The most likely cause of the failure is the carbon fiber motorcase, which attempted to balance complex axial and hoop deformation to reduce the mass of the motorcase.

All personnel were in the Reaction Research Society’s bunker at the time of the explosion, and USCRPL conducted the firing with experienced pyro ops overseeing operations. The test was conducted with all necessary safety precautions for experimental motors and as such, posed no risk to observers and resulted in no injuries.

 

We first attempted to see if ESII’s failure shared any resemblance to the ESI failure in 2020. ESI suffered a forward-end burn-through, which was visible in the video recording of the test and supported by post-hardware inspection. ESI’s burn through was determined to be caused by deformation of the case creating a leak path at the forward end for hot combustion gasses to recirculate next to the case, eventually causing its failure. We also realized that the ESI motor’s integration procedure deviated from the intended design, exacerbating this failure mode. This was rectified before ESII.

ESI static fire with burn through visible at the forward end.

An inspection of the forward bulkhead and retention mechanism, as well as a review of the thermal video, indicate ESII did not suffer a burn-through. ESII’s forward bulkhead shows soot build-up on the aft side of the aft-most o-ring groove, while everything forward of that is clean, the expected result if combustion gasses stagnated at a sealing surface. There is also no evidence of high-velocity combustion gasses carving channels into the bulkhead. This implies that the o-rings successfully sealed the motor and that the failure differs from ESI

ESII forward bulkhead with clean line visible in first o-ring groove.

Thermal camera courtesy of FLIR.

A clean and straight seam is visible down the entire remaining length of the case. This is a tell-tale sign of a failure due to hoop stress. Additionally, data from the load cell at the forward end of the motor, as well as pressure backed out from strain gauge data, indicates that the motor’s chamber pressure was at the higher end of expected. This would be the second time we have observed motor overperformance with this propellant formula, with the first being on the flight of CTRL+V.

ESII’s case as it was found with the clean cut visible.

ESII’s moment of failure as captured by the overhead GoPro camera.

Before our next static fire, Earthshakiiiest (ESIII), we will incorporate what we learned into our analysis models and use them to properly envelope the environment the case experiences during firing. Additionally, we will be conducting a propellant characterization campaign in the coming months to make improvements to our propellant and record better data than we have for our current formula. In addition to the media featured in this update, we have also released the uncut pad footage here. Thank you to everyone for your support and encouragement following ESII, we can’t wait to see everyone at the test site again soon!

Previous Student and Amateur Rocketry Successes

Although Traveler IV was the first entirely student designed and built rocket to fly to space, USCRPL doesn’t exist in a vacuum (so to speak). The global community of rocketeers serves as a fantastic support network, and any accomplishment like Traveler IV builds off of previous successes by the amateur and student communities. Two other amateur or student-affiliated groups have been confirmed to reach space before: CSXT and the US Air Force Academy.  Additionally, the global competition between rocketry teams for altitude with fully student designed and built rockets saw intense competition from two teams in particular, HyEnD at the University of Stuttgart and DARE at Delft University of Technology.  Hopefully this post can highlight a few teams who have done great work in the field of rocketry.