MAD TORQ M40C30 50KV v2.1 Brushless Motor for Paramotor, 24S, IP35, 2789 g, 70 kg Max Thrust

MAD

$1,498.50 USD

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Overview

MAD TORQ M40C30 V2.1 50KV is a brushless motor for paramotor setups, designed for high-thrust electric propulsion on up to 24S power systems.

Sustained thrust	20~28 kg
Max thrust	70 kg
Support voltage	24S
Weight	2789 g

Key Features

Motor model: MAD M40C30 IPE V2.1
50 KV
Degree of protection: IP35
Centrifugal heat dissipation: YES
Extended enameled wires: 150 mm cable length
Balance specs: rotor balance ≤20 mg; motor balance ≤30 mg

Description

TORQ Paramotor Series M40C30 V2.1 50KV brushless motor (light version). Testing feedback referenced in the source description includes operation with a 450A ESC on 18S LiPo and a 125 cm propeller, reporting 59 kg thrust in that configuration, plus multiple 15-minute flights with efficient and cool running.

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Specifications

Motor Data

Motor model	MAD M40C30 IPE V2.1
Number of pole pairs	15
Stator	Anticorrosive
Varnished wire degree	220°C
Motor size	D:152 × 65 mm
Magnet degree	180°C
Degree of protection	IP35
Cable length	150 mm (extended enameled wires)
Centrifugal heat dissipation	YES
Rotor balance	≤20 mg
Motor balance	≤30 mg
Propeller mounting holes	D:50 M6×6; D:38 M4×4
Shaft diameter	IN: 15 mm
Motor mounting holes	D:50 M6×6
Bearing	HR30202J / 3202A-2RZTN
Disruptive test	500 V

Test Sheet Specifications

RPM/V	50 KV
Nominal voltage	24S LiPo battery
No load current	2.3 A/30 V
Internal resistance	20.3 mΩ
Motor weight	2789 g
Product boxed weight	4008 g (260 × 210 × 120 mm)
Maximum current	197.2 A
Maximum power	19089 W
Maximum thrust	70 kg
Maximum torque	47.1 Nm
Recommended ESC	MAD AMPX 200A (12-24S)
Recommended propellers	47×13
Max temperature (test sheet header)	120°C
UAV take-off weight (24S-47")	100 kg (Quadcopter); 150 kg (Hexacopter); 200 kg (Octocopter)
Single rotor take-off weight	20 kg ~ 30 kg

Performance Data (Test Sheet Table)

Throttle (%)	Voltage (V)	Current (A)	Input Power (W)	Output Power (W)	Torque (N·m)	RPM	Thrust (gf)	Efficiency (%)	Efficiency (gf/W)
30	98.47	7.11	700.1	443.7	3.252	1303	7464	63.38	10.7
35	98.44	10.8	1063.2	711.0	4.518	1503	10198	66.88	9.6
40	98.49	14.97	1474.4	1048.0	5.759	1738	13440	71.08	9.1
45	98.43	21.67	2133.0	1580.1	7.815	1931	16680	74.08	7.8
50	98.52	27.96	2754.6	2090.5	9.457	2111	20309	75.89	7.4
55	98.45	34.32	3378.8	2610.8	10.794	2310	24824	77.27	7.3
60	98.36	43.68	4296.4	3342.1	12.706	2512	28645	77.79	6.7
65	98.53	61.02	6012.3	4750.3	16.752	2708	33541	79.01	5.6
70	98.52	74.44	7333.8	5831.1	19.222	2897	37973	79.51	5.2
75	98.59	84.08	8289.4	6591.8	20.499	3071	42967	79.52	5.2
80	98.57	101.78	10032.5	7960.8	23.559	3227	48624	79.35	4.8
85	98.47	122.18	12031.1	9500.9	26.734	3394	55141	78.97	4.6
90	96.66	148.62	14365.6	11277.0	30.354	3548	56628	78.50	3.9
95	97.35	168.64	16417.1	12797.1	32.879	3717	62113	77.95	3.8
100	96.8	197.2	19089.0	14793.9	36.488	3872	70078	77.50	3.7

Drawing & Mount Hole Data

Main dimensions shown: 152 mm diameter; 65 mm length; 58 mm section diameter; 4.5 mm feature shown on drawing
Propeller mounting holes shown: Ø50-M6×6; Ø38-M4×4
Additional drawing callouts shown: Ø50-Ø6.2×6; Ø50-Ø6.1×6; Ø90; Ø24.9; Ø89.8; 52; 38; 6.6; 4

Applications

Electric paramotor propulsion systems (24S capable)
Single-rotor lift applications (20 kg ~ 30 kg take-off weight reference from test sheet)
Multi-rotor platforms (take-off weight references provided in test sheet)

Test Notes

Analytical graph labels: I = Current, P = Input Power, η = Electrical Efficiency, T = Thrust, N = Rotational Speed.
Test sheet notes: data measured with input voltage of 100 V at 25°C and sea level; rotational speed adjusted by the throttle.
Table note: values are theoretical at input voltage 98 V for reference. At 25°C without additional cooling, current over 197 A is a non-working zone; 61–197 A is a short-term (about 10–30 s) working zone; below 61 A is a sustainable working zone. Control running time according to environment temperature and heat dissipation.