The ZA-125 is an experimental solid rocket motor designed from first principles. It is sized in OpenMotor, modeled in Fusion, machined in-house and static-fired to compare measured thrust against the simulation.
The nozzle is a two-piece design: a replaceable graphite throat insert in a 6061-T6 aluminum carrier, retained in the case by radial bolts.
Spec sheet · Rev A
Motor type
Solid, BATES grain
Peak thrust (sim)
≈ 168 N
Burn time (sim)
≈ 2.7 s
Peak chamber pressure (sim)
≈ 660 psi
Case design pressure
1,600 psi (2× limit)
Throat / exit diameter
4.00 / 10.71 mm
Expansion ratio
7.169
Nozzle
Graphite throat, 6061-T6 carrier
Simulated values from OpenMotor, nozzle iteration 1.
Section view of the ZA-125: casing, phenolic liner, propellant chamber and two-piece nozzle.
All motor testing is done on a secured static stand, outdoors, at a safe distance, with adult or instructor supervision. The motor case is designed to twice the maximum expected chamber pressure.
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