Kaman K-MAX
Kaman K-MAX.

Kaman K-MAX


Kaman K-MAX is a civil American helicopter ("flying crane"), which is designed specifically for the transport of goods (weighing up to 2720 kg) on ​​an external sling. The prototype was produced by KamanAircraft in 1991, in 2007 small-scale production continues. It is built according to the synchropter scheme traditional for Kaman, namely with two crossed rotors.


Kaman K-MAX photo

Kaman K-MAX. Photo.

In the 1980s, Kaman, which traditionally occupied a narrow niche as a supplier of anti-submarine helicopters and was not able to compete on equal terms with large aircraft manufacturers, tried to gain a foothold in niche, narrow markets for aircraft. In the last decade of Kaman Charles' practical work, the target has been the flying crane market. Building a flying crane practically from scratch, and not on an existing platform, would make it possible to increase the efficiency of the machine. The prototype KMAX took off shortly after leaving Kaman's management position in 1991, the first production KMAX in January 1994.


Kaman K-MAX. Photo 2.

Kaman K-MAX. Photo 2.

Helicopter of a criss-cross, twin-rotor, with a tricycle landing gear and one gas turbine engine. Controlled horizontal and vertical tail, like an aircraft. A single-seater helicopter, there is no passenger cabin, and even for the second pilot. The narrow fuselage gives the pilot an excellent view, especially in the rearward direction of the cargo, which is suspended at the end of the cable.


Kaman K-MAX. Photo booths.

Kaman K-MAX. Photo of the cabin.


Features helicopter Kaman K-MAX:


  • Crew: 1

  • Capacity: 2721kg 

  • Length: 15,85m 

  • Width: 15,67m 

  • Fuselage length: 12,73m 

  • Main rotor diameter: 14,73 m

  • Height: 4,14m 

  • The area swept rotor: 340,9kv.m

  • The base chassis 4,27m 

  • Track chassis 3,68m 

  • Curb weight: 2334kg 

  • The highest take-off weight: 2948kg 

  • with suspension: 5443kg 

  • Volume of fuel tanks: 865l (+ 238,5l additional tank in the cargo hold) 

  • Fuel weight in internal tanks: 705kg 

  • Powerplant: 1 × turboshaft HoneywellT5317A1 

  • Take-off engine power: 1 × 1350л.с. (1 × 1007kW) 

  • Speed ​​limit: 185km / h 

  • with suspension: 148km / h 

  • Practical range: 494km 

  • with suspension: 369km 

  • Flight duration: 2 × X41min 

  • with optional tank: 3 × X41min 

  • Ceiling: 4572m 

  • Static ceiling:

  • using ground effect: 8020 

  • no ground effect: 8875 

  • Rate of climb: 12,7m / s 

  • The load on the drive: 17,2kg / sq.m

  • Thrust-to-weight ratio: 171,5Vt / kg 



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