The GAS418A is a four-cylinder, 1.8-liter, four-stroke Otto-cycle engine developed for unmanned aerial vehicles requiring reliable power in Medium-Altitude Long-Endurance (MALE) operations. It delivers up to 100 kW (135 hp) at 5,800 RPM at sea level and provides a power-to-weight ratio of 1.8 hp/kg, with a dry weight of 75 kg in the horizontal configuration and 80 kg in the vertical configuration. Two installation orientations are available, enabling integration flexibility depending on airframe layout requirements.
The engine features electronic fuel injection managed by an EFI Technology Euro 2 ECU, with CAN bus 2.0B communication. A version combining EFI with carburetors is also available on request to provide fuel system redundancy. Double spark electronic ignition is ECU controlled, and throttle control is mechanical (with electronic throttle available on request). A mechanical reduction gearbox with three ratio options (2.18:1, 2.20:1, 2.33:1) allows propeller matching. The engine operates on 98-octane automotive gasoline and includes a 14 V DC, 32 A alternator as standard, with provision for a supplementary alternator installation.
Specifications:
| Engine type: | 4-stroke, Otto cycle, 4-cylinder boxer layout |
| Displacement: | 1.8 liters |
| Bore / Stroke: | 92 mm / 68 mm |
| Maximum power: | 100 kW (135 hp) @ 5,800 RPM (sea level) |
| Maximum continuous power: | 84 kW (115 hp) @ 5,200 RPM |
| Maximum torque: | 150 Nm @ 5,000 RPM (sea level) |
| Dry weight: | 75 kg (horizontal version) / 80 kg (vertical version) |
| Alternator: | 14 V DC, 32 A (secondary alternator installation provision) |
