Credit
Unknown author Unknown author · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
Mi-10 · fuselage only
Single sourceMi-10 · overall length, rotors turning
Single sourceConfiguration
| Specification | Mil Mi-10 | Mitsubishi RP-1 |
|---|---|---|
| Type | Aerial crane[source] | Experimental twin-engined helicopter[source] |
| National origin | Russia[source] | Japan[source] |
| Manufacturer | Mil Moscow Helicopter Plant[source] | Mitsubishi Heavy Industries[source] |
| Status | Active as of 2014 (Mi-10K)[source] | — |
32.86 m (107 ft 10 in) (fuselage only), 41.89 m (137 ft 5 in) (overall length, rotors turning)[source]
Length
Single source15.00 m (49 ft 2.5 in)[source]
Mi-10 · Main rotor diameter
Single source35.00 m (114 ft 10 in)[source]
Empty; Mi-10 · Empty weight
Single sourceEmpty; Mi-10 · Mi-10K
Single sourceGross; Mi-10 · Gross weight
Single sourceGross; Mi-10 · Mi-10K
Single sourceMaximum take-off; Mi-10 · Max takeoff weight
Single sourceMaximum take-off; Mi-10 · Mi-10K
Single source27,100 kg (59,745 lb) , Mi-10K 25,450 kg (56,110 lb)[source]
43,550 kg (96,011 lb) , Mi-10K 37,000 kg (82,000 lb)[source]
43,700 kg (96,342 lb) , Mi-10K 38,000 kg (84,000 lb)[source]
Mi-10 · pilot, copilot and flight engineer, navigator/radio operator and optional technician
Single source3 (pilot, copilot and flight engineer, navigator/radio operator and optional technician)[source]
Mi-10 · Range
Single source430 km (270 mi, 230 nmi)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Number built |
|---|
55[source] |
| Manufactured | 1964–69[source] | — |
|---|
| Introduction date | 1963[source] | — |
|---|
| First flight | 15 June 1960[source] | 14 September 1994[source] |
|---|
| Developed from | Mil Mi-6[source] | Sikorsky S-76[source] |
|---|
| Capacity | 28 passengers or 3 t (3,000 kg; 6,600 lb) internally up to 15 t (15,000 kg; 33,000 lb) payload on platform or 8 t (8,000 kg; 18,000 lb) max slung payload[source] | — |
|---|
| Ground clearance under fuselage | 3.75 m (12 ft 4 in)[source] | — |
|---|
| Main rotor area | 962 m 2 (10,350 sq ft)[source] | — |
|---|
| Hovering ceiling out of ground effect | 3,000 m (9,840 ft)[source] | — |
|---|
| Service ceiling | 3000 м[source] | — |
|---|
| Developed into | — | Mitsubishi MH2000[source] |
|---|