Main Menu

Pipistrel PEM 60MVLC


The E-811 is the first electric engine certified for use in General Aviation by the European Union Aviation Safety Agency (EASA).
The E-811 engine combines a liquid-cooled electric motor and a liquid-cooled power controller. Offering 57.6 kW (77 hp) of peak power, and 49.2 kW (66 hp) of maximum continuous power, the E-811 is a powerplant for powered sailplanes, UL, LSA and VLA aircraft, where a Type Certified Engine is required.
The propulsion motor is an axial flux synchronous permanent magnet electric motor. Lighter and more compact, these motors are also more powerful than radial flux motors, making them ideal aviation. The propeller is mounted directly on its rotor.
The associated controller converts direct current (DC) from the batteries to alternating current (AC) for the motor. The controller receives torque command via CAN bus and adjusts the motor current input accordingly through the engine’s high voltage AC bus. The motor reacts instantaneously and without hesitation. The controller also requires a 12-volts power supply.
The motor’s rotation direction is not factory selected and can be easily adapted to any given application as part of the installation. The motor can turn clockwise or counter-clockwise as the default direction of rotation.
The E-811 supports a wide range of propellers. Fixed, ground-adjustable and electric variable-pitch propellers can be mounted on the engine, as long as they are compatible with the flange geometry and screw pattern (6xM8 on 75 mm diameter). Hydraulic governors are not supported. The propeller should have a maximum moment of inertia of 3245 kg-cm2 (7.7 lb-ft2) and weigh less than 5.5 kg. Maximum engine speed is 2500 rpm.
The engine is entirely liquid-cooled through a single cooling circuit with a mixture of 50% water and 50% glycol (automotive grade G12+). The coolant inlet is located on the power controller, it then proceeds to the motor via an intermediate coolant hose. The coolant outlet is located on the motor.
The cooling system is part of the installation and can be provided by Pipistrel. It comprises a coolant pump; a radiator; an expansion tank; an overflow bottle; inlet, outlet and intermediate hoses; and the coolant itself. The circuit shall ensure a coolant temperature at either component of less than 60°C.
In order to control the engine power output, an auxiliary control system should be provided. This can be ensured either by a power lever or a flight control computer, while cockpit indication such as an RPM indicator shall be provided as well.
The engine requires high-voltage DC power to be supplied for propulsive force. Depending on the chosen architecture, the engine will accept DC power from the energy source, which may be batteries connected via a battery management system (BMS), or a generator, or a fuel cell, or combinations thereof. A low-voltage (12 VDC) power connection is also needed.
Installation of the additional equipment depends on the aircraft configuration.
The EASA Type Certificate (No. EASA.E.234) follows the CS-22, Subpart H, Amdt. 2 standard, and the SC E-1 special condition for Electrical Engine for powered sailplanes, LSA or VLA.
Pipistrel’s Electric propulsion system is a true Plug & Play solution for electric aircraft. You receive everything you need: the motor, power controller, battery system complete with BMS and a lightweight airborne charger, complete with an advanced color display cockpit instrument, which provides you with full control. The system also supports propeller positioning and automatic retraction for self-launching glider applications.
Cockpit instrument is an ESYS-MAN V2 high-resolution 3-inch sunlight readable color display and control interface. Displays all system temperatures, controls RPM/Power with automatic over-temperature protection, charge indicator, charge status overview, battery health overview, visual warnings, system enable/disable and support for propeller positioning and automatic retraction (self-launch gliders).
Pipistrel offers several chargers for the Taurus Electro conversion kit, a portable 2 kW world unit, supporting both 110V/60 HZ and 250 V/50 Hz networks. It has a 5 inch display and an intuitive interface, providing information about charge status, battery health overview and system configuration. It supplies 2 kW charge power in a 3 kg package.
For faster charging we have an 8kW charger weighing just 25 kg.
Pipistrel 2kW Charger
Pipistrel 8kW Charger
The cockpit battery, which supports the avionics, power controller and motor extension/retraction, is charged together with the main power battery. This provides an extra layer of safety and allows gliding even with the main battery depleted. The cockpit battery is also charged in flight by the solar panels attached to the aircraft
The propeller is a composite lightweight 2-blade propeller, diameter 165 cm, specially optimized specially to take advantage of the electric motor characteristics.
Pipistrel E-811-268MVLC
Type: axial flux synchronous permanent magnet
Diameter: 268 mm (10.55 in)
Width: 91 mm (3.58 in)
Dry weight: 22.7 kg (50 lb)
Maximum take-off power (MTOP) up to 90 sec: 57.6 kW (77 hp) at 2500 rpm
Maximum continuous power (MCP): 49.2 kW (66 hp) at 2350 rpm
Outside air temperature range: -20°C, +40°C (-4°F, 104°F)
Max motor temperature: 110°C (230°F)
Speed limits: 2350 rpm (MCP), 2500 rpm (MTOP)
Torque limits: 200 Nm (MCP), 220 Nm (MTOP)
Coolant flow: > 5.5 l/min
Coolant temperature: < 60°C (140°F)
Pressure drop (over the entire system): < 1 bar
Max propeller moment of inertia: 3245 kg-cm2 (7.7 lb-ft2)
Max propeller mass: 5.5 kg (12.1 lb)
Max propeller speed: 2500 rpm
Controller – H300C
Dimensions: 245 x 126 x 230 mm (9.65 x 4.96 x 9.05 in)
Dry weight: 8.1 kg (17.8 lb) including cables
Max controller temperature: 70°C (158°F)
Input voltage range: 250 – 400 VDC
Max controller current: 311 A
Max continuous current: 226 A
Battery capacity 20 Ah: 4.75 kWh
Battery capacity 30 Ah: 7.10 kWh
Battery capacity 40 Ah: 9.7 kWh
Battery Management System (BMS): Integrated, with datalogging & failure prediction.
Airborne Charger: Supports 110 VAC and 240 VAC, 2 kW, typical charge time 3 h
Battery voltage: 190 V -270 V Voltage per battery pack: nominal 17×3.7 V = 63 V
Maximum operating temperature: 70° C – max battery temperature 60° C
Minimum operating temperature: 5° C
Electric motor power: High efficiency outrunner, synchronous 3-phase PEM 40 kW (1 min), 30 kW cont. Air cooled
Max RPM: 2200 RPM
System weights:
20 Ah unit = 59 kg
30 Ah unit = 75 kg
40 Ah unit = 91 kg

Copyright © 2022 all-aero. All Rights Reserved.
Joomla! is Free Software released under the GNU General Public License.