RS.aero The RS.500 is projected as a larger aircraft with an MTOM of about 5,000 kg

GENERAL DESIGN FEATURES

The plane comes in low wing high aspect ratio and T-tail configuration. There is a clean separation between the pressurized cabin and the payload bay below the cabin floor, covered by sealed hatches for reconfigurable payload installations. It offers payload/sensor flexibility without expensive and time consuming large major change efforts for wide range of mission tasks.

The large cabin size meets the equipment and manpower requirements on board during longer missions. Allows two crews with rest area for manned missions over long distances and long periods of time. For full day missions the plane will be equipped with a flight control system for unmanned operation over 25 hours.

This design allows use in parallel with surveillance for the growing need for rapid express delivery of sensitive medical and industrial goods. Cargo volume 10m3. The new types of ICE engines with JET-A1 fuel or SAF allow for cost efficient multi-step tours as well as for far-distant tasks.

AVIONICS

Customized.

STRUCTURE

Full carbon airframe structure. Wing with central segment including engines and landing gear, and outer wing segments. Hard points for external payload or fuel tanks for extreme range and endurance on center wing with standard connections. Cabin pressurized up to 18,000 ft.

FLIGHT CONTROL SYSTEM

Mechanical flight control system for standard manual operation, actuators for autopilot and Remotely Piloted Aircraft System RPAS (UAV mode). FCS allows Optional
Piloted Operation (OPV) as well as UAV mode.

LANDING GEAR

Retractable tricycle gear. Main wheels retract rearwards the rear part of the engine nacells. Nose wheel retracts rearwards. Use of a reknowned rugged system capable for unpaved landing strips.

SYSTEM

Primary 28V DC electrical system. Air conditioning and pressurizing system. Electrical power supply for payload according customer requirements. FIKI deicing system.

POWER PLANT

The platform is powered by two engines with 1100 hp take-off power in total. The engines are latest design of internal combustion type, certified by EASA and FAA.They offer a distinct advantage for mission requirements that involve both loitering and getting to the target area quickly. All this at very low fuel burn over the full range of operation with 40–50 % reduction to common turbines, offering new performances in endurance and range as well as a contribution to climate and severe cost reduction (SAF being a climate-neutral fuel). The standard engines allow 30,000 ft operation altitude; a special version allows up to 50,000 ft, offering long-endurance high-altitude UAV missions at low cost.