Define thrust, propellant type, and chamber pressure —
your flight-ready engine design is generated
in hours.
© 2026
19'
(Input)
Specify thrust requirements, propellant selection, and chamber pressure. Our AI system processes your input against validated propulsion engineering models and thermal datasets.
(+Generate)
Full 3D-printable geometry is generated — combustion chambers, regenerative cooling channels, nozzle contours, and injector patterns — optimized for metal additive manufacturing.
(=Validate)
Not Months
Hours
Compliant
ITAR
Physics-
Native Design Core
Combustion thermodynamics, Nusselt heat transfer correlations, and nozzle contour equations are encoded directly into the generation engine — not bolted on as post-processing steps.
Hours,
Not Months
Design cycles that traditionally require weeks of manual engineering — chamber sizing, cooling channel layout, injector patterning, nozzle shaping — are resolved computationally in a single session.
Metal
Additive-Native Output
Geometry is generated against the constraints of powder-bed fusion and DED processes. Internal channel resolution, wall thickness, and printability are part of the design specification, not afterthoughts.
ITAR
US-Based & Controlled
Designed and operated within the United States. All technical data is handled in compliance with ITAR export control regulations, built for programs in launch vehicle development and national defense.