The Mil Mi-34 (NATO reporting name: Hermit) is a light helicopter designed by the Mil Moscow Helicopter Plant in either a two or four seat configuration for utility and training. It was first flown on 17 November 1986 and introduced at the Paris Air Show in 1987. The Mi-34 entered production in 1993, and is capable of performing aerobatic manoeuvres, including rolls and loops.
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A new domestic engine version, Mil Mi-34M1 made its first hovering flight in October 2024. It uses the Russian made VK-650V turboshaft engine instead of the previous Radial engine.[1]
- Mi-34S[note 1] – four seat production model powered by a 239 kW (325 hp) Vedeneyev (VOKBM) M-14V-26V nine-cylinder, air-cooled, radial engine mounted sideways in the fuselage, and equipped with modern avionics. A few aircraft were purchased by the Moscow police.
- Mi-34S2 "Sapsan" – turbine version of the Mi-34. It will be able to accommodate up to 4 passengers and the first deliveries are planned by the end of 2011. It will be powered by Turbomeca Arrius-2F[2]
- Mi-34L – proposed version powered by a 261 kW (350 hp) Textron Lycoming TIO-540J piston engine. None built.
- Mi-34P Patrulnyi (English: patrol) – Police patrol version for Moscow Mayor Office.
- Mi-34A – Luxury version, intended to be powered by an Allison 250-C20R turboshaft engine. None built.
- Mi-34M1 – New prototype, powered by Russian made VK-650V turboshaft engine.[1]
- Mi-34UT – trainer with dual control.
- Mi-34V or Mi-34VAZ or Mi-234 – proposed version powered by two VAZ-4265 rotary piston engines.
- Mi-44 – proposed development with TV-O-100 engine and refined aerodynamics. A mockup was built in 1987.
Data from Jane's All The World's Aircraft 2000–2001 [6]
General characteristics
- Crew: 1 or 2
- Capacity: 2 pax
- Length: 11.415 m (37 ft 5 in) overall
- 8.71 m (29 ft) fuselage
- Height: 2.75 m (9 ft 0 in)
- Empty weight: 950 kg (2,094 lb)
- Gross weight: 1,280 kg (2,822 lb) normal
- 1,100 kg (2,425 lb) aerobatic
- Max takeoff weight: 1,450 kg (3,197 lb)
- Fuel capacity: 176 L (46 US gal; 39 imp gal) / 128 kg (282 lb)
- Powerplant: 1 × Vedeneyev M-14V-26V 9-cylinder air-cooled radial piston engine, 239 kW (321 hp) or 1 × VK-650V Turboshaft engine, 485 kW (650 hp) for Mi-34M1
- Main rotor diameter: 10 m (32 ft 10 in)
- Main rotor area: 78.7 m2 (847 sq ft)
Performance
- Maximum speed: 210 km/h (130 mph, 110 kn)
- Cruise speed: 170 km/h (110 mph, 92 kn)
- Best climb speed: 90 km/h (56 mph; 49 kn)
- Range: 356 km (221 mi, 192 nmi) with maxfuel at 500 m (1,600 ft) and 5% reserve
- Service ceiling: 4,000 m (13,000 ft) *Hover ceiling OGE: 900 m (3,000 ft)
- g limits: +3
- Disk loading: 18.4 kg/m2 (3.8 lb/sq ft)
- Power/mass: 0.165 kW/kg (0.100 hp/lb)
Aircraft of comparable role, configuration, and era
Jane's (2004–05) indicates that the Mi-34S is the base design and that prior to 1999, all marketing literature referred to the Mi-34 using the Mi-34C designation. The S or C suffixes were used to indicate the aircraft's certification by the Interstate Aviation Committee. The Russian word for certified (Russian: Сертифицированные) begins with the Cyrillic C, which is romanized as the letter S.
Jackson, Paul, ed. (2000). Jane's all the World's Aircraft 2000–01 (91st ed.). Coulsdon, Surrey, United Kingdom: Jane's Information Group. pp. 429–431. ISBN 978-0710620118.
- Jackson, Mark. Jane's All The World's Aircraft 2003–2004. Coulsdon, UK: Jane's Information Group, 2003. ISBN 0-7106-2537-5.
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