Aircraft engineering / Parametric concept

Design studio

Explore a safe conceptual aircraft mass/power budget and export a draft engineering record. The illustration is a schematic—not calibrated CAD, dynamics or structural analysis.

Configuration parameters

Revision name

Concept airframe

Dry airframe mass (kg)

Battery mass (kg)

Declared MTOM (kg)

Sensor payload mass (kg)

Benign payload category

Nominal payload power (W)

Declared aux power (W)

Mount interface independently verified Mass limit supported by external evidence Auxiliary power budget independently verified

Concept schematic

Illustrative only

Rotate concept: 33°

View elevation: 49°

This illustrative normalized geometry has no real dimensions, imported CAD, mass distribution or motor design. Measured geometry and structural checks are required before design release.

Physical rotor clearance, lift, moment of inertia and CG envelope need actual CAD and measured parameters.

Preliminary engineering review

2.75 kgNeeds evidence

2.75 kg declared total3.40 kg provided limit

Declared mass margin0.65 kg

Declared aux power margin33 W

Declared values pass the two arithmetic comparisons, but fit, propulsion, materials, control and airworthiness are not evaluated.

Mounting and CG still require evidence.
At least one limit lacks declared supporting evidence.
Never convert this result into real-world authorization.