PROPULSION + BATTERY

Find the useful tradeoff.

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Assumptions Adjust the aircraft

Battery chemistry Availability Propulsion evidence

Airframe + electronics mass

Includes enclosure, tilt mechanism, ESCs and wiring. 500 g is an optimistic redesign assumption, not the current CAD mass.

Pack hardware mass

Interconnects, protection, connector and swap cassette, in addition to cells.

Electronics power

Coaxial thrust loss

Drag area · CᴅA

0.040 m² corresponds to a 20 × 20 cm frontal area if Cᴅ = 1. Speed estimates use this assumption.

Battery & operating assumptions

Minimum WhMaximum Wh

Pack hardware · €Packs in pool

JGNE landed assumption · €/cell

Delivered-energy factor

Lifetime scenario multiplier

100% uses the cited test-cycle benchmark as a scenario. It does not verify exact 10–90% flight life. Wear uses an additional 90% mean-capacity factor.

Static thrust margin

Minimum test-bench maximum thrust / hover thrust. This is not a continuous-duty or controllability certification.

Power targets

Hover · WMovement · W

Only show the hover target pass

Movement watts set the selected point’s calculated speed; a speed is not a verified operating limit.

Payload 750 gCharge window 10–90%Duty 16 h/day · 365 daysCharging 1C planning rate

Purchase cost × flight time

Compare combinations

Frontier only

Motor / propeller / battery

Sources, calculations & limits What the graph does and does not establish