Optionally piloted and unmanned aircraft system with solar cells
- Overview
- Specifications
Extremely low noise level
Less than 50 dB noise level (German LTF-UL 2020) – moderate rainfall noise. Operation in noise protected areas possible.
Operational costs
45 EUR/h (OPS version), aircraft depreciation cost, electricity and battery, maintenance, insurance.
Redundancy
Dual redundant propulsion system. Each of two subsystems is composed of motor, motor controller, battery. Dual redundant power supply for avionics and autopilot. In case of failure of motor, motor controller, battery or all of them in one subsystem, the aircraft is able to climb with at least 1.5 m/s.
In case of OPS, double redundant electronic flight instruments.
In case of UAS, triple redundant autopilot system composed of flight control computer (FCC), navigation sensors, air data system. Double redundant actuators.
Solar system
The solar system serves as a range extender. It is composed of solar generator and solar converter (maximum power point tracker). The solar system is connected to the batteries and propulsion unit so that the solar energy can be used for the motor directly, for charging batteries or for both in parallel.
Optionally piloted system (OPS)
Elektra One Solar OPS is equipped with autopilot system. The pilot can switch to the autopilot mode and can fly a mission completely autonomously including take-off and landing. The flight mission can be defined by means of a special software before the flight and changed or adapted during the flight from the cockpit or from the ground control station. Elektra One Solar OPS can be delivered for operation without pilot in the cockpit.
Unmanned aerial system (UAS)
Elektra One Solar UAS is equipped with a triple redundant autopilot system. By removing the instrument panel, flight controls, canopy, seat and seat belts, the empty weight of the aircraft is reduced by 20 kg, allowing an increase in payload or battery capacity.
| Category | Parameter | Technical Specification（OPS） | Technical Specification（UAS） |
|---|---|---|---|
| Flight Performance | Cruise speed | 90 km/h | 90 km/h |
| Stall speed VS0 (flaps extended) | 70 km/h | 70 km/h | |
| Stall speed VS1 (flaps retracted) | 75 km/h | 75 km/h | |
| Max. operating speed | 150 km/h | 150 km/h | |
| VNE (never exceed speed) | 160 km/h | 160 km/h | |
| Max. climb speed | 3 m/s | 3 m/s | |
| Takeoff & Landing Performance | Take-off distance | < 100 m | < 100 m |
| Landing distance | 300 m | 300 m | |
| Range & Endurance | Max. flight duration (with solar) | 3.5 hours | 6.5 hours |
| Max. flight duration (w/o solar) | 2.5 hours | 5 hours | |
| Max. flight range (with solar) | 300 km | 560 km | |
| Max. flight range (w/o solar) | 220 km | 440 km | |
| Power Plant | E-motor | HPD 32D | HPD 32D |
| Max. peak power | 32 kW | 32 kW | |
| Max. continuous power (MCP) | 20 kW | 20 kW | |
| Cruise power | 5 kW | 5 kW | |
| Max. battery capacity | 21 kWh | 42 kWh | |
| Solar surface | 7.5 m² | 7.5 m² | |
| Max. solar power | 1.65 kW | 1.65 kW | |
| Weights | Max. take-off weight (MTOW) | 410 kg | 410 kg |
| Max. battery weight | 90 kg | 180 kg | |
| Max. payload weight | 50 kg | 110 kg | |
| Max. pilot weight | 110 kg | – | |
| Empty weight (w/o battery) | 180 kg | 180 kg | |
| Fuselage Specifications | Wingspan | 14 m | 14 m |
| Wing aspect ratio | 18 | 18 | |
| Core Capabilities | Noise level | < 50 dB | < 50 dB |
| Certification | LTF-UL-2020 | Country-specific |
