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SPRINT Hot Fire Test - September 13th and 14th, 2025

Attempt Sequence

September 13 included an unsuccessful igniter attempt that produced a cold flow, followed later that day by a successful firing identified in the archive as SPRINT Hotfire 2. The successful run produced a reported peak thrust near 190 lbf, or approximately 845 N, but the SCADA fault prevented the other channels from being recorded.

Two additional hot fires were completed on September 14. The first again lost data to the SCADA fault. The final run recorded the full pressure, thrust and tank-mass set. It was shortened because insufficient nitrous oxide remained in the tank.

Final Run Measurements

The September 14 telemetry reached 839.1 N peak thrust and 184.1 psi peak chamber pressure. Contemporary analysis reported approximately 2.4 kN·s total impulse. The graph offsets the propellant-mass channel so its minimum plotted reading is 0 kg; pressure and thrust values are unchanged. After unchanged duplicate samples were removed without smoothing, usable new-value rates were 19.4 Hz for tank pressure, 16.0 Hz for chamber pressure, 13.6 Hz for thrust and 10.6 Hz for propellant mass.

Test Videos

September 13 SPRINT Hotfire 2.
One of the two September 14 firings.

Test Data

Burn Telemetry

SPRINT burn telemetry for September 14th, 2025 with propellant mass normalized to a minimum of zero kilograms
Unsmoothed telemetry from the final September 14 firing; propellant mass is normalized to a minimum of 0 kg.

Team Photo

SPRINT team at the September 13th and 14th, 2025 hot-fire campaign
SPRINT team members at the hot fire test on September 13th and 14th, 2025.