ISRA
Missions

M003

Homi Shatam II

Status
Static testing
Launched
Not yet
Motor
In-house KNSU, E5 target
Short name
HomiS II

What we set out to do

Our own motor, matching the E5 class of the commercial motor Homi Shatam I flew, and a flight computer that ejects the parachute at apogee.

What has happened so far

Metal casings, small nozzles and fast propellant don't mix: T004 and T005 both exploded.

An M-Seal nozzle can't hold chamber pressure. It failed in T004, T006 and T007, even made thicker.

Batch-to-batch repeatability isn't there yet. T003 was meant to repeat T002 and came in lower.

The flight computer runs on the board and passed an indoor stair test on 26 Sept 2026. It isn't flight-ready.

What we changed next

Bring the combustion rate down before going back to metal hardware, and change one variable at a time.

Static fires

9 on record, 3 with a thrust curve we can draw. The others say what went wrong: a rig that didn’t record, nozzles and casings that failed, or data we can’t yet reproduce.

Pick up to four tests to compare. The last one you pick is highlighted.

T014: thrust rose to 10.45 N 0.70 s after ignition; the recording stops at 0.80 s, and the motor exploded at 3.62 s.
Data cut outMotor exploded
Peak thrust
10.45 N
Data cut out
0.80 s after ignition
Motor exploded
3.62 s after ignition

Thrust is weight-corrected as in our analysis script: tared against the first 49 readings, then corrected for propellant burned. We draw only what was measured, not the extrapolation in the team's plot. Raw data: T014.csv.

  1. T00126 Jun 2026

    Changed: First test with the thrust rig.

    Result: The rig didn't record, so there's no thrust data.

  2. T00229 Jun 2026

    Changed: Same motor as T001, on the Electronics team's improved rig.

    Result: Our first full thrust curve.

  3. T0033 Jul 2026

    Changed: A repeat of T002 with a smaller nozzle.

    Result: The rig dropped samples; we filled the gaps. Thrust came in lower than T002.

  4. T0046 Jul 2026

    Changed: A change to the propellant and how it was prepared.

    Result: The nozzle failed and the motor exploded. No data.

  5. T00510 Jul 2026

    Changed: A CNC-machined steel nozzle.

    Result: The casing failed and the motor exploded. No data.

  6. T0069 Aug 2026

    Changed: A new propellant formulation and a cardboard casing.

    Result: The nozzle blew out. No data.

  7. T00713 Aug 2026

    Changed: A thicker nozzle; everything else as T006.

    Result: The nozzle blew out again. No data.

  8. T008Uploading soon
  9. T009Uploading soon

    Changed: Uploading soon.

    Result: A full burn of about 2.1 s.

    Peak 12.16 N, burn 2.10 s, total impulse 7.37 N·s. Figures from the team's analysis plot. The committed data file doesn't reproduce them yet, so we don't draw its curve.

  10. T010Uploading soon
  11. T011Uploading soon
  12. T012Uploading soon
  13. T013Uploading soon
  14. T014Uploading soon

    Changed: Uploading soon.

    Result: The motor exploded 3.62 s after ignition. Data cut out at 0.8 s, just after peak thrust.

Flight computer

  • ESP32-CAM
  • GY-87 (MPU6050 and BMP180)
  • MG90S servo for parachute ejection

The records on GitHub

Footage

T002, 29 Jun 2026: our first static fire with a full thrust curve.
T001, 26 Jun 2026: the motor fires; the rig records nothing.
T004, 6 Jul 2026: the nozzle fails and the motor explodes.

Photos

  • The proposed ejection mechanism for Homi Shatam II, in CAD.