Engineering:Mil Mi-60 MAI

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Short description: Unbuilt 2000s Russian helicopter project
Mi-60 MAI
Role Light utility helicopter
National origin Russia
Manufacturer Mil
Designer Marat Nikolayevich Tishchenko[1][2]
Status Unrealised project

The Mil Mi-60 MAI (Cyrillic: Миль Ми-60 МАИ) was a joint project between Mil and the Moscow Aviation Institute to develop a light utility helicopter.[3] A mockup was displayed at the MAKS 2001 air show,[2][3][4] where Russian aerospace journal Aviatsiya i Kosmonavtika (Авиация и космонавтика; "Aviation and Space") described it as a "little brother" to the Mil Mi-34.[5]

The Mi-60 MAI was intended to fulfil a range of general aviation activities, including pilot training, agricultural work, police and firefighting duties, resource monitoring, aerial photography, and tourism.[2] Domestic demand in Russia for such an aircraft was estimated at around 400–600 units.[2] No Russian manufacturer was producing a lightweight helicopter such as this, and foreign aircraft were unsuitable for Russian conditions.[6]

The design was further presented at the 1997 International Aviation Forum in Moscow, and the World Salon of Inventions in Brussels the same year.[7] It won a gold medal at the latter event.[7]

Design

The Mi-60 MAI was a conventional design for a light helicopter, with a pod-and-boom fuselage, a three-bladed main rotor, two-bladed tail rotor, and a skid undercarriage with rear wheels on each skid.[3][4][2] The pilot and a single passenger were to sit side-by-side in an extensively-glazed, enclosed cabin with dual controls.[1]

At different stages of development, a variety of powerplants were proposed, including:

  • one 120-kilowatt (160 hp) Lycoming O-320-B2C piston engine[1][4]
  • one 150-kilowatt (200 hp) Aviadvigatel D-150 wankel engine[1][4]
  • one 145-kilowatt (194 hp) Textron Lycoming HIO-360-F1AD piston engine[3]
  • one 177-kilowatt (237 hp) VAZ-426 wankel engine[3]
  • two 84.6-kilowatt (113.5 hp) Rotax 914F piston engines.[3][4]
  • two 103-kilowatt (138 hp) LOM M332A piston engines[3]

These were to be located inside the fuselage, behind the cabin, with power transmitted to the rotor through V-belts.[1] In the twin-engine versions, the engines were to be located side-by-side.[1][4] One criterion for engine selection was favouring engines that could run on automotive-grade petrol.[2][6] This would allow the aircraft to operate in regions with less well-developed infrastructure.[8] The twin-engine variants were expected to be able to continue to fly on only one engine.[7]

Construction was to make extensive use of composite materials.[6]

Development

Initial funding for the project came from the Russian Ministry of Education.[3] Development started in 1993 and technical work was finished the following year.[3] In 1997, the Russian Army became a sponsor, hoping to use the Mi-60 MAI as a helicopter trainer.[3]

Construction of a mockup commenced at the Kazan helicopter factory in 2000.[3] It was displayed the following year at the MAKS air show, and production was planned to start the same year.[3] Production would have taken place at the Rostvertol factory in Rostov-on-Don[4] As of 1998, an estimated $30 million was still required to put the aircraft into production.[7]

Development work on the program ended in 2001,[2] although it was still included in the Russian federal aviation plan for 2002–10.[3] As of 2013, no examples had been constructed.[4]

Specifications (as designed, with VAZ engine)

Data from Jackson 2007, p.497, except as noted.

General characteristics

  • Crew: one pilot
  • Capacity: 1 passenger
  • Length: 7.370 m (24 ft 2 in) (fuselage, including tail rotor)[8]
  • Height: 2.286 m (7 ft 6 in) [8]
  • Max takeoff weight: 1,300 kg (2,866 lb)
  • Powerplant: 1 × VAZ-426 piston engine, 177 kW (237 hp)
  • Main rotor diameter: 10.00 m (32 ft 10 in)

Performance

  • Maximum speed: 225 km/h (140 mph, 121 kn)
  • Cruise speed: 185 km/h (115 mph, 100 kn)
  • Range: 400 km (250 mi, 220 nmi)
  • Service ceiling: 5,500 m (18,000 ft)
  • Rate of climb: 142 m/s (28,000 ft/min)

Notes

References

  1. ↑ 1.0 1.1 1.2 1.3 1.4 1.5 Mikheev 1998, p.268
  2. ↑ 2.0 2.1 2.2 2.3 2.4 2.5 2.6 Mikheev 2007, p.318
  3. ↑ 3.00 3.01 3.02 3.03 3.04 3.05 3.06 3.07 3.08 3.09 3.10 3.11 3.12 Jackson 2007, p.497
  4. ↑ 4.0 4.1 4.2 4.3 4.4 4.5 4.6 4.7 Gordon & Komissarov 2013, p.606
  5. ↑ Nikolskiy 2001, p.9
  6. ↑ 6.0 6.1 6.2 MAI+Mil new ultralight, p.16
  7. ↑ 7.0 7.1 7.2 7.3 MAI+Mil new ultralight, p.19
  8. ↑ 8.0 8.1 8.2 MAI+Mil new ultralight, p.17

Bibliography

  • "МАИ+Миль новый сверхлегкий". Вертолёт (Kazan: Omega Research Centre) (2): 16–19. 1998. 
  • Mikheev, Vadim Rostislavovich (1998). МВЗ им. М. Л. Миля 50 лет. Moscow: Lyubimaya. 
  • Mikheev, Vadim Rostislavovich (2007). МВЗ имени М. Л. Миля. Moscow: Polygon. 
  • Nikolskiy, Mikhail (2001). "Первый российский авиасалон XXI бека". Авиация и космонавтика (Moscow: Techinform) (9): 1–10. 
  • Gordon, Yefim; Komissarov, Sergey (2013). Unflown Wings: Soviet and Russian Unrealised Aircraft Projects 1925-2010. Manchester: Créey Publishing. 
  • Jackson, Paul, ed (2007). Jane's All the World's Aircraft 2007-08 (98th ed.). London: Jane's Publishing Group. 

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