An attack & armoured personnal carrier
This heavily armed attack helicopter is an armored
troop carrier Mi-24 and a powerful, heavy and tough helicopter. max
speed:310 km/h; standard range:7500 km; climb rate:750 m/min.
VARIANTS: --- from Janes
(`Hind-A, B and C'): These early versions had a pilot and
co-pilot/gunner in tandem under continuous glazing; large flight deck;
about 250 were built, including Mi-24U unarmed dual-control trainers
(first flight 1972);---- 1989-90 Jane's.
Mi-24D (Type 24-6; `Hind-D'): Interim gunship version; design in 1971; produced
at the Arsenyev and Rostov plants 1973; about 350 built 1973-77.
Basically a `Hind-A' with TV3-117 engines and port-side tail rotor,
entire front fuselage redesigned above floor forward of engine air
intakes; separate armored cockpits for weapon operator and pilot in
tandem; flight mechanic optional, in main cabin; transport capability
retained; USUP-24 gun system, with rangefinding; undernose JakB-12.7
four-barrel 12.7 mm machine gun in turret, slaved to adjacent KPS-53A
electro-optical sighting pod, for air-to-air and air-to-surface use;
Falanga P (Phalanx) anti-tank missile system; nosewheel leg extended to
increase ground clearance of sensor pods; nosewheels semi-exposed when
retracted. Mi-24DU dual-control training version has no gun
(Types 20-1and 24-2; `Hind-E'): As Mi-24D, with modified wingtip
launchers and four underwing pylons; weapons include up to eight 9M114
(AT-6 `Spiral') radio guided tube-launched anti-tank missiles in pairs
in Shturm V (Attack) missile system; ASP-17V enlarged undernose
automatic missile guidance pod on port side, with fixed searchlight to
rear; R-60 (K-60; AA-8 `Aphid') air-to-air missiles optional on
underwing pylons; pilot's HUD replaces former reflector gunsight.
Deliveries to Soviet Air Force began 29 March 1976; about 1,000 built at
Arsenyev and Rostov 1976-86. (See also Mi-35.)
Proposed upgraded Mi-24V first shown in model form at Moscow Air Show
'95. Mi-28 main and tail rotors and nose turret for twin 23 mm cannon;
large IR suppressors scabbed to fuselage sides.
Variant of Mi-24V with twin-barrel 23 mm gun, with 450
rounds, in place of four-barrel 12.7 mm gun in nose; photographed 1992;
small production from Rostov.
Mi-24P (Type 24-3; `Hind-F'): built 1974; about 620 built 1981-90; P of
designation refers to pushka = cannon; as Mi-24V, but nose gun turret
replaced by GSh-30-2 twin-barrel 30 mm gun (with 750 rounds) in
semi-cylindrical pack on starboard side of nose; bottom of nose smoothly
faired above and forward of sensors.
(Type 46-2; `Hind-G1'): Identified at Chernobyl after April 1986
accident at nuclear power station; no undernose electro-optical and RF
missile guidance pods; instead of wingtip weapon mounts, has `clutching
hand' mechanisms on lengthened pylons, to obtain six soil samples per
sortie, for NBC (nuclear/biological/chemical) warfare analysis; air
samples sucked in via pipe on port side, aft of doors; datalink to pass
findings to ground; lozenge shape housing with exhaust pipe of air
filtering system under port side of cabin; bubble window on starboard
side of main cabin; small rearward-firing marker flare pack on tailskid;
crew of four wear NBC suits; deployed six per helicopter regiment
throughout CIS ground forces. Designation (also appearing as Mi-24RCh)
indicates Razvedchik: reconnaissance/chemical. About 150 built 1983-89.
(korrektirovchik: corrector) (`Hind-G2'): As Mi-24R, but with large
camera in cabin, f8/1,300 mm lens on starboard side; six per helicopter
regiment for reconnaissance and artillery fire correction; gun and
B-8V-20 rocket pods retained. No target designator pod under nose;
upward hinging cover for IR sensor. About 150 built 1983-1989.
A few modified 1973 for minesweeping.
Special version for Russian Ministry of Internal Affairs; prototype
displayed at Moscow Air Show '95. Equipment includes undernose FLIR
ball; searchlight pod outboard of this on port side, loudspeaker pack on
starboard side; hoist; climbdown ropes; stations for radio operators.
Ecological Survey Version: Modification by Polyot industrial research
organisation, to assess oil pollution on water and seasonal changes of
water level. First seen 1991 with large flat sensor `tongue' projecting
from nose in place of gun turret; large rectangular sensor pod on outer
starboard underwing pylon; unidentified modification replaces rear cabin
window on starboard side.
Export Mi-24D, including those for Afghanistan,
Cuba and India.
Export Mi-24V. Unarmed, dual control
trainer version also produced for India.
Upgraded night-capable version of Mi-24/35 designed to meet the latest
air mobility requirements of the Russian Army. Features include Mi-28
main and tail rotors and transmission; 1,636 kW (2,194 shp) Klimov
TV3-117VMA engines; new avionics; a reduced empty weight resulting from
new titanium main rotor head, composites rotor blades, shortened
stub-wings and non-retractable landing gear; a 23 mm GSh-23-2
twin-barrel gun in nose turret, with 470 rounds; up to 16 radio-guided
9M114 (AT-6 `Spiral'), or laser-guided 9M-120 anti-tank, 9M-120F blast
fragmentation or 9A-220 air-to-air versions of Ataka (AT-12) missile; or
a range of armament options including GUV gun/grenade pods; UPK-23-250
gun pods; B-8V-20 and B-13L rocket pods; S-24B rockets; and KMGU pods of
anti-armor and anti-personnel mines. Night Operation Capable Avionics
System (NOCAS) by Sextant Avionique and Thomson-TTD Optronic integrates
Chlio FLIR ball with a TMM-1410 display, providing night vision for
target acquisition and identification, missile guidance and gun aiming.
Other equipment includes a VH-100 HUD, NVGs, liquid-crystal MFD, Nadir
10 mission management and navigation system, laser-gyro INS and GPS. The
FLIR ball is mounted outboard of the standard missile guidance pod.
Ability to carry Igla V air-to-air missiles is optional. Non-flying
demonstrator first displayed at 1995 Paris Air Show.
gunship configuration, with stepped tandem seating for two crew and
heavy weapon load on stub-wings; fuselage unusually wide for role, due
to requirement for carrying eight troops; dynamic components and power
plant originally as Mi-8, but soon upgraded to Mi-17-type power plant
and port-side tail rotor. Main rotor blade section NACA 230,
thickness/chord ratio 11 to 12 per cent; tail rotor blade section NACA
230M; stub-wing anhedral 12°, incidence 19°; wings contribute
approximately 25 per cent of lift in cruising flight; fin offset 3°.
main rotor; forged and machined steel head, with conventional flapping,
drag and pitch change articulation; each blade has aluminum alloy spar,
skin and honeycomb core; spars nitrogen pressurized for crack detection;
hydraulic lead/lag dampers; balance tab on each blade; aluminum alloy
three-blade tail rotor; main rotor brake; all-metal semi-monocoque
fuselage pod and boom; 5 mm hardened steel integral side armor on front
fuselage; all-metal shoulder wings with no movable surfaces; swept
fin/tail rotor mounting; variable incidence horizontal stabilizer.
rearward-retracting steerable twin-wheel nose unit; single-wheel main
units with oleo-pneumatic shock-absorbers and low-pressure tires, size
720 x 320 mm on mainwheels, 480 x 200 mm on nosewheels. Main units
retract rearward and inward into aft end of fuselage pod, turning
through 90° to stow almost vertically, discwise to longitudinal axis of
fuselage, under prominent blister fairings. Tubular tripod skid
assembly, with shock-strut, protects tail rotor in tail-down take-off or
Two Klimov TV3-117MT
turboshafts, each with T-O rating of 1,434 kW (1,923 shp), side by side
above cabin, with output shafts driving rearward to main rotor shaft
through combining gearbox. There is 5 mm hardened steel armor protection
for engines. Main fuel tank in fuselage to rear of cabin, with bag tanks
behind main gearbox. Internal fuel capacity 1,500 kg (3,307 lb); can be
supplemented by 1,000 kg (2,205 lb) auxiliary tank in cabin (Mi-24D);
provision for carrying (instead of auxiliary tank) up to four external
tanks, each 500 liters (132 US gallons; 110 Imp gallons), on two inner
pylons under each wing. Optional deflectors and separators for foreign
objects and dust in air intakes; and infra-red suppression exhaust mixer
boxes over exhaust ducts.
Pilot (at the rear) and
weapon operator on armored seats in tandem cockpits under individual
canopies; dual flying controls, with retractable pedals in front
cockpit; if required, flight mechanic on jump-seat in cabin, with narrow
passage between flight deck and cabin. Front canopy hinged to open
sideways to starboard; footstep under starboard side of fuselage for
access to pilot's rearward-hinged door; rear seat raised to give pilot
unobstructed forward view; anti-fragment shield between cockpits. Main
cabin can accommodate eight persons on folding seats, or four
stretchers; at front of cabin on each side is a door, divided
horizontally into two sections hinged to open upward and downward
respectively, with integral step on lower portion. Optically flat
bulletproof glass windscreen, with wiper, for each crew member.
Cockpits and cabin are
heated and ventilated. Has a dual electrical system, with three
generators, giving 36, 115 and 208 V AC at 400 Hz, and 27 V DC.
Retractable landing/taxiing light under the nose; navigation lights;
anti-collision light above tailboom. Stability augmentation system.
Electrothermal de-icing system for main and tail rotor blades. AI-9 V
APU mounted transversely inside fairing aft of rotor head for engine
starting and ground services.
Comms: Include VHF and
ARK-15M radio compass, ARK-U2 radio compass, RV-5 radio altimeter.
Blind-flying instrumentation, and ADF navigation system with Doppler-fed
mechanical map display. Air data sensor boom forward of top starboard
corner of bulletproof windscreen at extreme nose.
Mission: Undernose pods
for electro-optics (starboard) and Raduga-F semi-automatic missile
guidance (port). Many small antennae and blisters, including SRO-2 Khrom
(`Odd Rods') IFF transponder.
radar warning antennae on each side of front fuselage and on
trailing-edge of tail rotor pylon. Infra-red jammer (L-166V-11E Jspanka
microwave pulse lamp: `Hot Brick') in `flower pot' container above
forward end of tailboom. ASO-2V flare dispensers under tailboom forward
of tailskid assembly initially; later triple racks (total of 192 flares)
on sides of center-fuselage.
Gun camera on port
wingtip. Color-coded identification flare system.
Afghanistan, Bangladesh, Belarus, Bosnia and Herzegovina, Bulgaria,
Bhutan, Czech republic, Egypt, Etiopia, Finland, Croatia, India, Iraq,
Yemen, Armenia, Yugoslavia, Kampuchia, Kazahstan, China, Congo, Cuba,
Laos, Libya, Lithuania, Madagscar, Hungary, Macedonia, Mali, Moldova,
Mongolia, Mozambique, Germany, Nicaragua, Pakistan, Peru, Poland,
Republika Srpska, Romania, Russia, North Korea, Sierra Leone, Syria,
Slovakia, Sudan, Sri Lanka, Tajikistan, Turkmenistan, Turkey, Ukraine,
Uzbekistan, Venecuela, Vietnam, Zambia