Soviet Helicopters

Friday, January 31, 2014

Mil Mi-28 (Havoc)

Mil Mi-28 "Havoc"

The Mil Mi-28 (NATO reporting name 'Havoc') is a Russian all-weather, day-night, military tandem, two-seat anti-armor attack helicopter. It is a dedicated attack helicopter with no intended secondary transport capability, better optimized than the Mil Mi-24 for the role. It carries a single 30mm gun in an undernose barbette, plus external loads carried on pylons beneath stub wings.

In 1972, following completion of the Mil Mi-24, development began on a unique attack helicopter with transport capability. The new design had a reduced transport capability (3 troops instead of 8) and omitted the cabin, to provide better overall performance and higher top speed. Improved performance was important for its intended role fighting against tanks and enemy helicopters and covering helicopter landing operations. Initially, many different designs were considered, including an unconventional project with two main rotors, placed with engines on tips of wings (in perpendicular layout), and with an additional pusher propeller on the tail. In 1977, a preliminary design was chosen, in a classic single-rotor layout. It lost its similarity to the Mi-24, and even the canopies were smaller, with flat surfaces. Design work on the Mi-28 began under Marat Tishchenko in 1980.[3] In 1981, a design and a mock-up were accepted. The prototype (no. 012) was first flown on 10 November 1982. The second prototype (no. 022) was completed in 1983. In 1984, the Mi-28 completed the first stage of state trials, but in October 1984 the Soviet Air Force chose the more advanced Kamov Ka-50 as the new anti-tank helicopter. The Mi-28 development was continued, but given lower priority. In December 1987 Mi-28 production in Rosvertol in Rostov on Don was approved.

In January 1988 the first Mi-28A prototype (no. 032) flew. It was fitted with more powerful engines and an "X" type tail rotor instead of the three-blade version. The Mi-28A debuted at the Paris Air Show in June 1989. In 1991 the second Mi-28A (no. 042) was completed. The Mi-28A program was cancelled in 1993 because it was deemed uncompetitive with the Ka-50, and in particular, it was not all-weather capable.

The Mi-28N was unveiled in 1995, the N designation meaning "night". The prototype (no. 014) first flew on 14 November 1996. The most significant feature is a radar in a round cover above the main rotor, similar to that of the American AH-64D Apache Longbow. Mi-28N also has improved Tor vision and an aiming device under the nose, including a TV camera and FLIR. Due to funding problems, development was interrupted. A second prototype with an improved rotor design was unveiled in March 2004 at Rosvertol. Changes in the military situation after the Cold War made specialized anti-tank helicopters less useful. The advantages of the Mi-28N, like all-weather action ability, lower cost, and similarity to the Mi-24, have become important. In 2003, the head of Russian Air Forces stated that the Mi-28N and Ka-50 attack helicopters will become the standard Russian attack helicopter. The first serial Mi-28N was delivered to the Army in 2006.[5][6] By 2015, 67 Mi-28Ns are planned to be purchased, when the Mi-24 is to be completely replaced.[6][7] Mil also developed an export variant of the Mi-28N, designated Mi-28NE, and a simpler day helicopter variant, the Mi-28D, based on the Mi-28N design, but without radar and FLIR.

General characteristics

Crew: 1 pilot (rear), 1 navigator/weapons operator (front)
Length: 17.01 m (55 ft 10 in)
Rotor diameter: 17.20 m (56 ft 5 in)
Height: 4.70 m (15 ft 5 in)
Disc area: 232.35 m² (2,501 ft²)
Empty weight: 8,600 kg (18,960 lb)
Loaded weight: 10,700 kg (23,590 lb)
Max. takeoff weight: 11,500 kg (25,350 lb)
Powerplant: 2 × Klimov TV3-117VMA turboshaft, 1,636 kW (2,194 shp) each

Performance

Maximum speed: 320 km/h (172 knots, 199 mph)
Cruise speed: 270 km/h (145 knots, 168 mph)
Range: 435 km (234 nmi, 270 mi)
Combat radius: 200 km (108 nmi, 124 mi); with 10 min loiter and 5% reserves
Ferry range: 1,100 km(593 nmi, 683 mi)
Service ceiling: 5,700 m (19,000 ft)
Rate of climb: 13.6 m/s (2,677 ft/min)

Armament

Guns: 1× chin-mounted 30 mm Shipunov 2A42 cannon with 250 rounds (±110° horizontal fire)
Hardpoints: Two pylons under each stub wing to mount bombs, rockets, missiles, and gun pods. Main armament configurations include:
- 16 Ataka-V anti-tank missiles and 40 S-8 rockets, Or
- 16 Ataka-V anti-tank missiles, and 10 S-13 rocket, Or
- 16 Ataka-V anti-tank missiles, and two 23 mm Gsh-23L gun pods with 250 rounds each.
- Other ordnance: 9K118 Sheksna and 9A-2200 anti-tank missiles, 8 Igla-V and Vympel R-73 air-to-air missiles, 2 KMGU-2 mine dispensers

Mil Mi-26 "Halo"

The Mil Mi-26 (NATO reporting name: Halo), given the product code izdeliye 90, is a Soviet/Russian heavy transport helicopter. In service with civilian and military operators, it is the largest and most powerful helicopter ever to have gone into production.

Following the incomplete development of the heavier Mil Mi-12 (prototypes known as Mil V-12) in the early 1970s, work began on a new heavy-lift helicopter, designated Izdeliye 90 ("Project 90") and later allocated designation Mi-26. The new design was required to have an empty weight less than half its maximum takeoff weight. The helicopter was designed by Marat Tishchenko, protégé of Mikhail Mil, founder of the OKB-329 design bureau. The Mi-26 was designed as a heavy-lift helicopter for military and civil use, and was to replace earlier Mi-6 and Mi-12 heavy lift helicopters, with twice the cabin space and payload of the Mi-6, then the world's largest and fastest production helicopter. The primary purpose was to move military equipment like 13 metric ton (29,000 lb) amphibious armored personnel carriers, and mobile ballistic missiles, to remote locations after delivery by military transport planes such as the Antonov An-22 or Ilyushin Il-76. The first Mi-26 flew on 14 December 1977 and the first production aircraft was rolled out on 4 October 1980. Development was completed in 1983, and the Mi-26 was in Soviet military and commercial service by 1985.

The Mi-26 was the first factory-equipped helicopter with a single, eight-blade main lift rotor. It is capable of flight in the event of power loss by one engine (depending on aircraft mission weight) thanks to an engine load sharing system. While it is only slightly heavier than the Mi-6, the Mi-26 can lift up to 20 metric tons (44,000 lb). It is the second largest and heaviest helicopter ever constructed, after the experimental V-12. The tail rotor has about the same rotor diameter and thrust of the four-bladed MD 500 main rotor. The Mi-26's unique main gearbox is relatively light but can absorb 19,725 shp, which was accomplished using a non-planetary, split-torque design. Because Mil's normal gearbox supplier said that such a gearbox could not be designed, the Mil Design Bureau designed the VR-26 transmission itself. As of 2013, the Mi-26 still holds the FAI record of greatest mass lifted to 2,000 metres - it lifted 56,768.8 kg in 1982.

In July 2010 a proposed Russian-Chinese development of a 33-ton heavy-lift helicopter was announced. The Russian helicopter manufacturer, Rostvertol, is in the process of refurbishing and upgrading the entire fleet of Mi-26s serving in the Russian Air Force. The fleet is estimated to number around 20 helicopters. Refurbished and upgraded aircraft will be comparable to an up-to-date variant: Mi-26T. Contract completion is planned for 2015. The same contract covers the manufacture of 22 brand new Mi-26T helicopters. As of January 2012, eight new-production helicopters have been delivered to operational units.

General characteristics

Crew: Five– 2 pilots, 1 navigator, 1 flight engineer, 1 flight technician
Capacity:
- 90 troops or 60 stretchers
- 20,000 kg cargo (44,090 lb)
Length: 40.025 m (131 ft 3¾ in) (rotors turning)
Rotor diameter: 32.00 m (105 ft 0 in)
Height: 8.145 m (26 ft 8¾ in)
Disc area: 804.25 m² (8,656.8 ft²)
Empty weight: 28,200 kg (62,170 lb)
Loaded weight: 49,600 kg (109,350 lb)
Max. takeoff weight: 56,000 kg (123,450 lb)
Powerplant: 2 × Lotarev D-136 turboshafts, 8,500 kW (11,399 shp) each

Performance

Maximum speed: 295 km/h (159 kt, 183 mph)
Cruise speed: 255 km/h (137 kt, 158 mph)
Range: 1,920 km (1,036 nmi, 1,190 mi)(with auxiliary tanks)
Service ceiling: 4,600 m (15,100 ft)

Mil Mi-24 "Hind"

The Mi-24, which has the NATO reporting name 'Hind', was developed during the mid-1960s to provide a multi-role military helicopter-of formidable capability. It appears to be evolved from, the Mil Mi-8/Mi-14 family, but a combination of reduced size and increased power gives this aircraft improved manoeuvrability and performance. While of the same basic configuration as its predecessors, and with a dynamic system based on that of the Mi-8, the Mi-24 has a more slender fuselage suitable for the gunship role, but with sufficient capability to accommodate a crew of four and a maximum of eight armed troops. The tricycle landing gear has retractable main units and a semi-retractable nose unit. Short-span cantilever shoulder wings with considerable anhedral are a distinguishing feature, and each provides mountings for a variety of weapons. Entering service in 1973-74 and deployed initially in East Germany, the Mi-24 has developed during military exercises into variants for armed assault, for anti-armour use, and for use as a helicopter escort, well able to oppose enemy helicopters in air-to-air combat. About 1,500 'Hinds', in production since the early 1970s, are currently in service with CIS forces. The type saw much action in Afghanistan, used as the proving ground for many operational improvements to the 'Hind'. The type was also used in the Iraq/Iran war of the early 1980s. The Mi-24 has been widely exported and a number are in service on most continents, with examples delivered to, or operating in, Afghanistan, Algeria, Angola, Bulgaria, Chad, Cuba, Czechoslovakia, Germany, Hungary, India, Iraq, Libya, Mozambique, Nicaragua, North Korea, Peru, Poland, Sri Lanka, Syria, Vietnam and Yemen. Production continues at a low rate and by 1991 more than 2,300 had been built.

The core of the aircraft was derived from the Mil Mi-8 (NATO reporting name "Hip"): two top-mounted turboshaft engines driving a mid-mounted 17.3 m five-blade main rotor and a three-blade tail rotor. The engine configuration gave the aircraft its distinctive double air intake. Original versions have an angular greenhouse-style cockpit; Model D and later have a characteristic tandem cockpit with a "double bubble" canopy. Other airframe components came from the Mi-14 "Haze". Two mid-mounted stub wings provide weapon hardpoints, each offering three stations, in addition to providing lift. The loadout mix is mission dependent; Mi-24s can be tasked with close air support, anti-tank operations, or aerial combat. The Mi-24 fuselage body is heavily armored and can resist impacts from 12.7 mm (0.50 in) rounds from all angles. The titanium rotor blades are also resistant to 12.7 mm rounds.[citation needed] The cockpit is protected by ballistic-resistant windscreens and a titanium-armored tub.The cockpit and crew compartment are overpressurized to protect the crew in NBC conditions.

In 1972, following completion of the Mi-24, development began on a unique attack helicopter with transport capability. The new design had a reduced transport capability (3 troops instead of 8) and was called the Mi-28, and that of the Ka-50 attack helicopter, which is smaller and more maneuverable and does not have the large cabin for carrying troops. In October 2007, the Russian Air Force announced it would replace its Mi-24 fleet with Mi-28Ns and Ka-52s by 2015. However due to economics the Russian Air Force will upgrade some Mi-24s and keep them in service past 2015, as will the Russian Navy.

General characteristics

Crew: 2–3: pilot, weapons system officer and technician (optional)
Capacity: 8 troops or 4 stretchers or 2400 kg (5,291 lb) cargo on an external sling
Length: 17.5 m (57 ft 4 in)
Rotor diameter: 17.3 m (56 ft 7 in)
Wingspan: 6.5 m (21 ft 3 in)
Height: 6.5 m (21 ft 3 in)
Disc area: 235 m² (2,530 ft²)
Empty weight: 8,500 kg (18,740 lb)
Max. takeoff weight: 12,000 kg (26,500 lb)
Powerplant: 2 × Isotov TV3-117 turbines, 1,600 kW (2,200 hp) each

Performance

Maximum speed: 335 km/h (208 mph)
Range: 450 km (280 miles)
Service ceiling: 4,900 m (16076 ft)

Armament

Internal guns

flexible 12.7 mm Yakushev-Borzov Yak-B Gatling gun on most variants. Maximum of 1,470 rounds of ammunition.
fixed twin-barrel GSh-30K on the Mi-24P. 750 rounds of ammunition.
flexible twin-barrel GSh-23L on the Mi-24VP and Mi-24VM. 450 rounds of ammunition.
PKB passenger compartment window mounted machine guns

External stores

Total payload is 1,500 kg of external stores.
Inner hardpoints can carry at least 500 kg
Outer hardpoints can carry up to 250 kg
Wing-tip pylons can only carry the 9M17 Phalanga (in the Mi-24A-D) or the 9K114 Shturm complex (in the Mi-24V-F).

Bomb-load

Bombs within weight range (presumably ZAB, FAB, RBK, ODAB etc.), Up to 500 kg.
MBD multiple ejector racks (presumably MBD-4 with 4 × FAB-100)
KGMU2V submunition/mine dispenser pods

First-generation armament (standard production Mi-24D)

GUV-8700 gunpod (with a 12.7 mm Yak-B + 2 × 7.62 mm GShG-7.62 mm combination or one 30 mm AGS-17)
UB-32 S-5 rocket launchers
S-24 240 mm rocket
9M17 Phalanga (a pair on each wingtip pylon)

Second-generation armament (Mi-24V, Mi-24P and most upgraded Mi-24D)

UPK-23-250 gunpod carrying the GSh-23L
B-8V20 a lightweight long tubed helicopter version of the S-8 rocket launcher
9K114 Shturm in pairs on the outer and wingtip pylons

Mil Mi-17 "Hip"

The Mi-17 retains the codename 'Hip-H', denoting its derivation from the Mi-8 design. First identified in 1980-81, the Mi-17 is virtually a revision of the Mi-8 design using a combination of the 'Hip' airframe but with the port-side tail rotor, and fitted with the more powerful powerplants of the Mi-14. These result in an overall improvement in performance, particularly the hovering ceiling. The type remains in current production for both civil and military use as a cargo-carrying helicopter, with secondary capability as a passenger transport capable of carrying up to 24 passengers, or 12 stretcher cases when used as an ambulace. The first export examples were delivered to Cuba in 1983, and Mi-17s are now in service in Angola, Hungary, India, North Korea, Nicaragua, Papua New Guinea, Peru and Poland, as well as the CIS.

Developed from the basic Mi-8 airframe, the Mi-17 was fitted with the larger TV3-117MT engines, rotors, and transmission developed for the Mi-14, along with fuselage improvements for heavier loads. Optional engines for 'hot and high' conditions are the 1545 kW (2070 shp) Isotov TV3-117VM. Recent exports to China and Venezuela for use in high mountains have the new VK-2500 version of the engine with FADEC control. The designation Mi-17 is for export; Russian armed forces call it Mi-8MT. The Mi-17 can be recognized because it has the tail rotor on the port side instead of the starboard side, and dust shields in front of the engine intakes. Engine cowls are shorter than on the TV2-powered Mi-8, not extending as far over the cockpit, and an opening for a bleed air valve outlet is present forward of the exhaust.

Actual model numbers vary by builder, engine type, and other options. As an example, the sixteen new Ulan-Ude-built machines delivered to the Czech Air Force in 2005 with –VM model engines were designated as Mi-171Sh, a development of the Mi-8AMTSh. Modifications include a new large door on the right side, improved Czech-built APU, Kevlar armor plates around the cockpit area and engines. Eight have a loading ramp in place of the usual clamshell doors, and will load a vehicle up to the size of an SUV. In May 2008 licensed production of the Mi-17 started in China, with production being led by Mil Moscow Helicopter Plant JSC and the Sichuan Lantian Helicopter Company Limited in Chengdu, Sichuan province. The plant built 20 helicopters in 2008, using Russian Ulan-Ude-supplied kits; production is expected to reach 80 helicopters per year eventually. The variants to be built by Lantian will include Mi-171, Mi-17V5, and Mi-17V7.

General characteristics

Crew: Three – two pilots and one engineer
Capacity: 30 troops or 12 stretchers or 4,000 kg (8,820 lb) cargo internally /5,000 kg (11,023 lb) externally slung.
Length: 18.465 m (60 ft 7 in)
Rotor diameter: 21.25 m (69 ft 10½ in)
Height: 4.76 m (15 ft 7¼ in)
Disc area: 356 m² (3,834 ft²)
Empty weight: 7,489 kg (16,510 lb)
Loaded weight: 11,100 kg (24,470 lb)
Max. takeoff weight: 13,000 kg (28,660 lb)
Powerplant: 2 × Klimov TV3-117VM turboshafts, 1,633 kW (2,190 shp) each

Performance

Maximum speed: 250 km/h (135 knots, 155 mph)
Range: 465 km (251 nmi, 289 mi)(standard fuel)
Service ceiling: 6,000 m (19,690 ft)
Rate of climb: 8 m/s(1,575 ft/min)

Armament

up to 1,500 kg (3,300 lb) of disposable stores on six hardpoints, including bombs, rockets, and gunpods

Mil Mi-14 "Haze"

The Mil Mi-14 ( NATO reporting name: Haze) is a Soviet anti-submarine helicopter which is derived from the earlier Mi-8.
Formal development of an anti-submarine warfare (ASW) version of the Mil Mi-8 transport helicopter was authorised by the Soviet Communist Party Central Committee and Council of Ministers in April 1965, with the objective of replacing the Mil Mi-4 in the short-range, shore based anti-submarine role. The new helicopter was required to have an endurance of 2 hours on station at a radius of 222 kilometres (120 nmi; 138 mi) from base.

The new design (with the internal designation V-14) differed from the Mi-8 in having a boat-like hull similar to the Sea King, allowing it to operate off the water, and a retractable undercarriage, with the mainwheels retracting into large sponsons on the rear of the fuselage. The helicopter was to be powered by two Klimov TV3-117MT turboshaft engines. A watertight weapons bay is fitted to the centreline of the fuselage allowing internal carriage of a single torpedo or eight depth charges, while a radome housing a search radar is fitted beneath the nose.

The first prototype V-14, converted from a Mi-8 and powered by the older and less powerful Klimov TV2-117 engines, flew on 1 August 1967. Development was slowed by problems with the helicopter's avionics and due to reliability problems with the TV3-117 engines, with production at Kazan not starting until 1973, and the helicopter (now designated Mi-14) entering service on 11 May 1976.

General characteristics

Crew: 4
Length: 18.38 m (60 ft 3 in)
Rotor diameter: 21.29 m (69 ft 10 in)
Height: 6.93 m (22 ft 9 in)
Disc area: 356 m² (3,832 ft²)
Empty weight: 11,750 kg (25,900 lb)
Max. takeoff weight: 14,000 kg (30,865 lb)
Powerplant: 2 × Klimov TV3-117MT turboshafts, 1,454 kW (1,950 shp) each

Performance

Maximum speed: 230 km/h (124 kt)
Ferry range: 1,135 km(705 mi)
Service ceiling: 3,500 m (11,500 ft)
Endurance with max fuel: 5 h, 56 min

Armament

torpedoes, bombs and depth charges

Mil Mi-10 "Harke"

The Mil Mi-10 (NATO reporting name Harke), given the product number izdeliye 60, was a Soviet military transport helicopter of flying crane configuration, developed from the Mi-6, entering service in 1963.

The advent of the Mi-6 gave the Soviet Union the very useful ability to move and place large, bulky or heavy loads with precision. Limitations of the Mi-6 in the flying crane role included a weight to payload ratio and the inability of the crew to easily see the load and its intended final position. A Council of Ministers directive of 20 February 1958 tasked OKB-329 (OKB Mil) with the development of a dedicated flying crane helicopter for carrying bulky loads unable to be carried in the hold of a Mi-6. The Mil OKB's response drew heavily on the Mi-6, utilising the dynamic components and 4,100 kW (5,500 hp) Soloviev D-25V turboshaft engines, on a slim fuselage sitting on four tall strut braced undercarriage legs, with a wide track allowing the helicopter to taxi over loads, or for mobile loads to be moved underneath. The fuselage can carry 28 passengers inside the cabin as well as 3 t (3,000 kg; 6,600 lb) of cargo loaded through a side door in the aft fuselage, by an integral boom and winch. Underslung loads can be attached directly to the fuselage by hydraulically operated clamps, or carried on a 8.5 m × 3.6 m (28 ft × 12 ft) pallet lifted by the winch and braced by cables and/or struts to the undercarriage legs. The external sling system, with a capacity of 8 t (8,000 kg; 18,000 lb), of the Mi-6 could also be fitted under the centre fuselage.

The first prototype V-10 emerged with canted main undercarriage legs with single wheels on all four legs, as well as a retractable emergency escape chute extending below the cockpit and external auxiliary fuel tanks either side of the centre fuselage. As development progressed the main undercarriage legs were replaced with vertical units carrying twin wheels, twin nose undercarriage wheels after a period retaining the single wheels, an Auxiliary power unit (APU) installed behind the cockpit on the starboard side and emergency escape slide cables for use when the pallet is carried. The first prototype V-10 was completed in 1959 and was soon allocated the service designation Mi-10. The first flight took place on 15 June 1960 and flight testing continued successfully until in May 1960 the first prototype crashed during a precautionary landing resulting from loss of gearbox oil pressure, only the Navigator/ radio operator surviving. After joining the flight test programme the second prototype began a series of world record breaking altitude/payload flights for turbine powered helicopters. State acceptance trials were passed successfully in 1961, but production did not commence until 5 March 1964 at the Rostov-on-Don factory, with first flight of a production aircraft on 10 September 1964, leading to a total of forty of the long-legged Mi-10 helicopters built, from 1964 to 1969.

The operational service of the Mi-10 was of moderate success, being distributed mainly to units of the VVS (Voyenno-Vozdushnyye Sily - Soviet Air Force) which already operated the Mi-6. Operations with no load were found to be unstable, and the best procedure for take-off was found to be a rolling take-off, which usually also resulted in nose-wheel shimmy when lightly loaded. The main mission of the early Mi-10 virtually evaporated with the improvements in contemporary ballistic missiles; thus the majority of the long-legged variants were converted to Mi-10PP, (or mi-10P), airborne Electronic Counter-Measures helicopters, carrying a large ST-900 Step' (Step' - Steppe) ECM pod under the fuselage mounted on a pallet.[1] Other Mi-10 long legged aircraft were converted to carry out a wide variety of missions but usually only as single prototypes. Of special note was the Mi-10R (R - recordnyy- record) record breaking helicopter, converted from a production machine, with the undercarriage of a Mi-6 fitted with fairings and spats, as well as a tail bumper to reduce the risk of damage to the rear fuselage on landing. Other variants are noted or described below in the variants section.

General characteristics

Crew: 4 or 5 (pilot, copilot, flight engineer, navigator/radio operator and optional technician)
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
Length: 32.86 m (107 ft 10 in) , Mi-10K 32.4 m (106 ft) ignoring rotors
Empty weight: 27,100 kg (59,745 lb) , Mi-10K 25,450 kg (56,100 lb)
Gross weight: 43,550 kg (96,011 lb) , Mi-10K 37,000 kg (82,000 lb)
Max takeoff weight: 43,700 kg (96,342 lb) , Mi-10K 38,000 kg (84,000 lb)Ground clearance under fuselage: 3.75 m (12.3 ft)
Powerplant: 2 × Soloviev D-25V turboshaft, 4,100 kW (5,500 hp) each
Main rotor diameter: 35 m (114 ft 10 in)
Main rotor area: 962 m² (10,350 sq ft)

Performance

Maximum speed: 335 km/h (208 mph; 181 kn) , Mi-10K 350 km/h (220 mph; 190 kn)
Cruising speed: 180 km/h (112 mph; 97 kn) , Mi-10K 228 km/h (142 mph; 123 kn)
Range: 430 km (267 mi; 232 nmi) , Mi-10K 500 km/h (310 mph; 270 kn)
Disk loading: 45.27 kg/m² (9.27 lb/sq ft) , Mi-10K - 38.46 kg/m² (7.87 lb/sqft) at normal AUW
Hovering ceiling out of ground effect: Mi-10 3,000 m (9,800 ft), Mi-10K 1,000 m (3,300 ft)
Hovering ceiling in ground effect: Mi-10K 3,000 m (9,800 ft)
Dynamic ceiling: Mi-10K 4,750 m (15,580 ft)

Mil Mi-8 "Hip"

The Mi-8, appeared in prototype form towards the end of 1961. In broad terms it bears the same relationship to the Mi-4 as the Mi-2 has to the Mi-1, and (initially at least) the rotor hub, rotor blades, rear fuselage boom and certain undercarriage components were similar to those employed in the Mi-4. The original prototype was powered by a single 2700shp Soloviev shaft turbine mounted over the cabin roof, but in the second machine, which flew for the first time on 17 September 1962, this was replaced by two of the smaller Isotov engines of 1500shp each. The latter has been the standard installation on all subsequent aircraft, the only major design change being the substitution of a 5-blade rotor for the original 4-blade one in 1964.

Intended primarily for Aeroflot, the Mi-8 carries a 2- or 3-man crew and has seating accommodation for up to 28 passengers in its standard airline form. Alternative internal arrangements include a de luxe saloon cabin for executive travel or a cargo layout for an internal payload of 4000kg. Emergency conversion of the cargo model to a passenger carrier can be carried out quickly by installing 24 tip-up seats along the cabin sides. Clamshell rear doors are provided for loading large items of cargo or, in the ambulance role, 12 stretchers which can be carried with an accompanying medical attendant. Like the other Mil turbine helicopters, the Mi-8 can also be used as a rescue machine with a winch on the cabin side capable of lifting a 250 kg load, or with an under-fuselage hook for an external sling load of about 2500 kg.

Designed originally in 1960, the V-8 'Hip-A' prototype helicopter was basically a turbine-powered version of the Mi-4, retaining initially its rotor, transmission and a number of other components. Intended powerplant was two Isotov turboshaft engines, but as these were not fully developed when the V-8 was nearing completion, it was powered instead by a single large Soloviev turboshaft derated to the 2013kW limit of the transmission, for its first flight in June 1960. However, the second machine (flown for the first time on 17 September 1962) introduced the Isotov engines, each then rated at 1119kW, and this became the standard installation on early production aircraft, designated Mil Mi-8 (NATO reporting name 'Hip'). The only other major change to be introduced since that time resulted from problems with the main rotor inherited from the Mi-4, replaced in 1964 by a five-bladed rotor of more advanced design in the 'Hip-B' prototype. The availability of so much engine power, by comparison with the 1268kW of the Mi-4, meant the new helicopter had a larger cabin, providing accommodation for a crew of two or three and up to 28 passengers in a standard airline configuration. Since series construction began, a total of 10,000 Mi-8s have been built, for both civil and military use. Some components are built in China. Large numbers of Mi-8s are used by Aeroflot in the transport role, being deployed also for ice reconnaissance, rescue operations and logistic support, but even greater numbers are operated by the Soviet Union's Frontal and Naval Aviation and, in addition, these helicopters have been supplied to the armed forces of about 40 other nations. The military versions are identified usually by their NATO reporting names.

General characteristics

Crew: 3 (pilot, copilot, flight engineer)
Capacity:
- 24 passengers or
- 12 stretchers and seat for 1 medical attendant or
- 3,000 kg (6,600 lb) on internal/external hardpoints
Length: 18.17 m (59 ft 7 in)
Rotor diameter: 21.29 m (69 ft 10 in)
Height: 5.65 m (18 ft 6 in)
Disc area: 356 m² (3,832 ft²)
Empty weight: 7,260 kg (16,007 lb)
Loaded weight: 11,100 kg (24,470 lb)
Max. takeoff weight: 12,000 kg (26,455 lb)
Powerplant: 2 × Klimov TV3-117Mt turboshafts, 1,454 kW (1,950 shp) each
Fuel max total capacity: 3,700 l (977 US gal)

Performance

Maximum speed: 260 km/h (140 kt)
Range: 450 km (280 mi)
Ferry range: 960 km(596 mi)
Service ceiling: 4,500 m (14,765 ft)

Armament

up to 1,500 kg (3,300 lb) of disposable stores on six hardpoints, including 57 mm S-5 rockets, bombs, or 9M17 Phalanga ATGMs.