Ka-62 helicopter has a single-rotor system with multiblade antitorque rotor in the annular channel of the vertical tail. Blades of rotors and glider are made of polymeric composites by 60 per cent. The glider is distinguished by excellent aerodynamic outlines, spacious transport passenger cabin and three-stand landing gear with tail crutch. The powerplant includes new-generation engines with module construction designed by Rybinsk Motorbuilding Design Bureau. Civilian modification has borrowed the following characteristics from the basic military one: high cruise speed, fuel efficiency and haul capacity as well as wide transport cabin apertures along the both fuselage sideways.
Ka-62 helicopter is designed in compliance with international requirements of flight safety. Flight and landing with one operating engine is ensured. In case of heavy landing injury prevention for pilot and passengers is guaranteed through a complex of measures, including energy absorbing construction of landing gear and seats. Antitorque rotor in tail is protected from accidental damage. The vehicle is equipped with effective antiicing and fire-prevention systems.
The helicopter can be used for passenger carriage with proper comfort, freight hauling aboard and on external sling, ambulance operations, salvage and rescue operations, ice reconnaissance and patrol operations of different kinds, controlling the water and trade zones boundaries, maintenance of offshore gas and oil pipelines etc.
Ka-62 can be supplied with the standard equipment of basic transport variant for flying in visual conditions. It can also have rotorcraft instrument piloting complex for any weather conditions with the use of satellite navigation equipment. Should the customer wish so, the export variant of the helicopter can be supplied with engines and avionics produced by foreign companies.
| Takeoff weight | 6500 kg |
|---|---|
| Flight-deck workload | 2770 kg |
| External sling load | 2750 kg |
| Cruise speed | 270 km/h |
| Practical flight range | 770 km |
| Flight endurance | 4,3 h |
| Hovering ceiling | 2600 m |
| Length (including rotors) | 13,46 m |
| Diameter of the main rotor | 13,8 m |
| Height | 4,8 m |
| Crew | 1-2 persons |
| Passengers | 14 persons |
| Type of engine | two RD-600V turboshafts |
| Takeoff output | 2х1300 h.p. |