Trực thăng-Phần 2

Mil Mi-12M
1967 - project.

Mi-12M project with two D-30V high-power turboshafts and six-blade rotors.

Mil Mi-14
1967.

Very little is known as yet of the Mil Mi-14, a derivative of the Mi-8, which is now in service with the shore-based units of the Soviet Naval Air Force and in Libya. It appears to have been tested in the Soviet Union at the beginning of 1974, entering service in 1975, and is now in full-scale production. It differs from the Mi-8 in that it has a watertight hull with sponsons and marine-type rudders on either side of the aft portion, into which the rear landing gear units retract. A fairing for the search radar is fitted underthe nose, and a dipping sonar or magnetic anomaly detector beneath the root of the tail boom. In all probability, the Mi-14 can be used for over-the-horizon target designation, guidance of surface-to-surface missiles and for search and rescue. It probably has a bomb bay for antisubmarine torpedoes, depth charges and other weapons.

The Mi-14, allocated the NATO reporting name ''Haze'', is an amphibious version of the Mi-8 intended to replace the Mi-4 in the ASW and mine counter-measure roles with the Soviet navy. The prototype, designated V-14, was first flown in September 1969 with a redesign watertight hull and sponsons containing fuel and a retractable undercarriage to confer water stability. Using the twin powerplants and rotor system of the Mi-17, the ''Haze'' went into service in 1977 and has become the basic shore-based helicopter with the Soviet navy for use in three distinct roles. Although amphibious, the Mi-14 is, like its Sea King counterpart, only intended for occasional operations from water. By 1991, about 230 had been delivered, with exports to Bulgaria, Cuba, East Germany, North Korea, Libya, Poland, Romania, Syria and Yugoslavia.
VARIANTS
M-14PL''Haze-A'': basic ASW version equipped with dunking sonar and search radar
Mi-14PW: Polish designation of ''Haze-A''
Mi-14BT''Haze-B'': mine countermeasures version
Mi-14PS ''Haze-C: search and rescue version fitted with two searchlights in nose, a sliding double door on the port side alongside a retractable hoist capable of lifting three persons in a basket

Technical data for Mi-14
Engine: 2 x Klimov TV3-117MT turboshaft, rated at 1400kW, main rotor diameter: 21.29m, fuselage length: 18.38m, height: 6.93m, take-off weight: 14000kg, empty weight: 11750kg, max speed: 230km/h, cruising speed: 215km/h, service ceiling: 3500m, range with max fuel: 1135km

Mil Mi-24
1969.

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. FAI records set by the A-1O experimental variant of the ''Hind'' gave some indication of the type''s capabilities, as when on 2 September 1978 over a 15/25km course it achieved a speed of 368.4km/h.
VARIANTS
Mi-24 ''Hind'': early production version, reported in 1972 but not seen until 1973; introduced into Soviet service in 1973/74
Mi-24 ''Hind-A'': second production model, with tail rotor moved from the starboard to port side of the tailfin; used as armed assault helicopter, carrying eight troops and three crew members
Mi-24''Hind-B'': initial production model with tail rotor on starboard side, wings without anhedral, no wingtip stations and only four underwing hardpoints; test use only
Mi-24 ''Hind-C: dedicated training helicopter similar to ''Hind-A'', but without nose-gun installation and wingtip stations
Mi-24D ''Hind-D'': initial dedicated gunship variant; first reported around 1977, Mi-24D is basically a late production ''Hind-A'' with revised forward fuselage containing separate ****pits for pilot and gunner, the latter controlling a single 12.7mm turret-mounted machine-gun and pylon-mounted AT-2 ''Swatter'' wire-guided ATMs; some versions had 23mm cannon in turret
Mi-24W ''Hind-E'': improved version of ''Hind-D'' gunship first reported in early 1980s; equipped with 12 AT-6 ''Spiral'' radio-guided ATMs mounted on stub wings together with AA-8 ''Aphid'' air-to-air missiles for self-defence
Mi-24P ''Hind-F'': Mi-24P (P for pushka, cannon) version of gunship, appeared in 1982 fitted with 30-mm GSh-30-2 cannon in starboard uderfuselage nose pack which includes 750 rounds of ammunition
Mi-24R ''Hind-G 1'': fitted with wingtip ''grapplers'' or ''clutching hands'' apparently used in connection with NBC technology, the Mi-24R was first reported in 1986 after the Chernobyl disaster
Mi-24K ''Hind-G 2'': similar to Mi-24R but with large camera installed in cabin with lens on starboard side
Mi-25: export version of ''Hind-D''
Mi-35: export version of ''Hind-E''
Mi-35P: export version of ''Hind-F''

In the middle of the 60s, while the western countries were looking the helicopter primary as a transport and rescue machine, the soviet army think at them as the air counterpart of the battle tanks. Heavy armed versions of the Mi-8 "Hip" were in service in that years when the Mil bureau start working in a new prototype called A-10. This new helicopter, designed primary as an anti tank weapon begun tests in 1970 and was first saw by the NATO in East-Germany in 1972. The A-10 reach a speed record of 368km/h. The first versions used a standard helo ****pit but in 1975 appears the Hind-D with the now tra***ional attack ****pit in a tandem configuration The later versions, as the Hind-E, used the more sophisticated AT-6 "Spiral" missiles instead of the AT-2 "Swatter" and a 23mm cannon replacing the 12.7mm machine gun in the turret. In their better moment, more than 1000 Hinds were in service in the Red Army and they were extensively used in Afghanistan forming teams with the attack aircraft Sukhoi Su-25.

Mil Mi-26
1977.

The Mi-26, which was seen in public for the first time at the 1981 Paris Air Show, is the result of a specification issued at the beginning of the seventies for a transport helicopter whose empty weight, without fuel, was not to exceed half the maximum take-off weight. It first flew on 14 December 1977 and has two very powerful turbine engines driving a big eight-blade rotor, and a large cargo hold 3.20m wide, 3.15m high and 15m deep with two winches on overhead rails, each capable of lifting 2.5 tonnes. Access to the hold is through a hydraulically-actuated rear loading ramp. The maximum payload is 5000kg or 70-100 passengers. The helicopter has a crew of four, with room for an ad***ional handler, and has a full range of navigational electronics and an automatic hover system.

Except for the V-12 prototypes that preceded it, the Mil Mi-26 ''Halo'' is the heaviest helicopter to have flown to date. Designed to provide Aeroflot with a heavylift helicopter to assist in the exploitation of undeveloped regions, this aircraft began life in the early 1970s, as soon as it became clear that the V-12 was not going to fulfil this role. It required the costly and time-consuming design and development of a completely new rotor and transmission system, which was precisely why the Mil bureau had arrived at the configuration of the V-12. As a result the design, development and testing of a suitable dynamic system, plus the need to meet an official requirement that the aircraft''s empty weight should be only half that of its maximum take-off weight, meant that it was not until 14 December 1977 that the V-26 prototype achieved its first hovering flight. Of similar overall configuration to the Mil Mi-6 heavylift helicopter, and with a fuselage of similar dimensions, the Mi-26 has a smaller-diameter (but eight-bladed) main rotor and powerplant of almost double the output, enabling it to carry 66% more payload than the Mi-6. This was demonstrated effectively on 3 February 1982 when, as just one of a string of new records established by the Mi-26, this new helicopter lifted a total mass (helicopter plus pay-load) of 56768.8kg to a height of 2000m.
Development of the ''Halo'' was completed in 1983 and the type was in civil and military service by 1985, since when about 70 have been built. The production model carries a crew of five, and up to 85 combat-equipped troops, or two airborne infantry combat vehicles. A new version is reported to be under development to replace the ''Hook'' in the command support role, with uprated engines, composite rotor blades and maximum payload increased to 22000kg.


Technical data for Mi-26T
Crew: 4, passengers: 70, engine: 2 x Progress D-126 turboshaft, rated at 7355kW, main rotor diameter: 32.0m, length with rotors turning: 40.03m, width: 8.15m, take-off weight: 56000kg, empty weight: 28200kg, fuel: 12000kg, max speed: 295km/h, cruising speed: 255km/h, service ceiling: 4600m, hovering ceiling, OGE: 1800m, range with 18000kg payload: 670km, payload: 20000kg

Mil Mi-18
1979.

Mi-17 with 0.9m fuselage extension, retractable undercarriage and modified cabin doors. Prototype only.


Technical data for Mi-18
Crew: 3, passengers: 30, engine: 2 x TV3-117MT turboshaft, rated at 1425kW, main rotor diameter: 21.3m, take-off weight: 11500-13000kg, empty weight: 7550kg, max speed: 270km/h, cruising speed: 240km/h, hovering ceiling, IGE: 3200m, service ceiling: 5550m, range: 580km, payload: 3000-5000kg

Mil Mi-17
1981.

Modified Mi-8 (initially Mi-8M) with Mi-14 dynamic systems, tail rotor on starboard side and two TV3-117MT turboshafts. Designed for export customers. Prot. FF 1976.

Technical data for Mi-17
Engine: 2 x Klimov TV3-117MT turboshaft, rated at 1400kW, main rotor diameter: 21.29m, length: 25.35m, height: 4.76m, take-off weight: 13000kg, max speed: 250km/h, cruising speed: 240km/h, service ceiling: 5000m, hovering ceiling, OGE: 1760m, range: 465km, payload: 3000-5000kg
Được Freesky sửa chữa / chuyển vào 01:09 ngày 28/09/2006

AS 332

BRANTLY B2

CH 19E

HA S6