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Latest from eMotres

Test results, milestones and announcements from the AeroStator Core™ programme.

6 kW/kg continuous — the CIANO14 40_12 runs 30 minutes straight

We ran the CIANO14 40_12 on a propeller test stand for 30 minutes straight — roughly double the sustained power of any 3115-class motor on the market. Here’s what the stand logged at minute 29 (125 g motor):

Thrust
3,455 g
Shaft power
770 W (6.16 kW/kg)
Electrical input
1,038 W
Efficiency
74.2 %
Current
43.85 A @ 23.7 V
Max temp
150 °C (stabilized)

A standard 3115 tops out at 300–350 W continuous before hitting thermal limits. Same form factor — twice the sustained power. The winding stays within its 200 °C insulation limit throughout.

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An inrunner that beats the class-leading outrunner

First bench tests of the CIANO14 40_12, built on AeroStator Core™, challenge a basic assumption in this class. Conventional wisdom says outrunners own drone propulsion on efficiency and thrust density — our first data says otherwise.

Benchmarked on the same propeller and the same 24 V against the class-leading T-Motor V3115 outrunner:

Electrical efficiency
+12–13 pp at high thrust
Peak efficiency
76.9 % (75–77 % plateau)
T-Motor V3115 at max
~64 %

And these are trapezoidal BLDC results — we haven’t switched to FOC yet, so there’s clear room to grow. Next: a controller integrated directly into the motor, 0.15 mm laminations, and foil (flat) coils.

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First test results — the 150_30 reaches 50 kg continuous thrust

First test results — the 150_30 reaches 50 kg continuous thrust

The first drone-propulsion motor built on AeroStator Core™ completed its initial bench tests on a thrust stand. At 50 kg continuous thrust (56″ propeller, BLDC controller):

Continuous thrust
50 kg
Shaft power
~7,800 W
Torque
~32 N·m (10.7 N·m/kg)
Specific power
2,600 W/kg
Motor efficiency
91 %
Operating temp
115 °C (air-cooled)

The AeroStator Core™ architecture turns the stator yoke into an active cooling structure — enabling tangential polarization with standard F45SH magnets at performance levels that usually demand much heavier or more expensive cooling. The roadmap: 60 kg continuous thrust at the same 3 kg, via FOC integration, 28- vs 42-pole analysis, and 63″ propeller tests.

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