TU-160, Máy bay ném bom chiến lược của Nga

TU-160, Máy bay ném bom chiến lược của Nga

TU-160 BLACKJACK STRATEGIC BOMBER, RUSSIA
The Tu-160 supersonic strategic bomber was manufactured by the Tupolev Aircraft Research and Engineering Complex Joint Stock Company in Moscow and the Kazan based Gorbunov Aircraft Production Association in Tatarstan from 1980 to 1992. Production has since been restarted and a Tu-160 was delivered to the Russian Air Force in May 2000. 15 aircraft are now in service with Russia. The Ukraine destroyed the last of its fleet in February 2001.

The purpose of the aircraft is the delivery of nuclear and conventional weapons deep in continental theatres of operation. The aircraft has all-weather, day-and-night capability and can operate at all geographical latitudes.

The performance of the Russian Tu-160 is often compared to the US B-1B. The aircraft has an operational range of 14,000km and a service ceiling of 16,000m. The maximum flight speed is 2,000kph at high altitude and 1,030kph at low altitude.

DESIGN

The bomber's airframe has a distinctive appearance, with the wing and fuselage gradually integrated into a single-piece configuration. The airframe structure is based on a titanium beam, all-welded torsion box. Throughout the entire airframe, all the main airframe members are secured to the titanium beam.

The variable geometry outer tapered wings sweep back from 20 to 65 degrees in order to provide high-performance flight characteristics at both supersonic and subsonic speeds. The tail surfaces, both horizontal and vertical, are one piece and all-moving.

The aircraft uses fly-by-wire controls.

The aircraft is equipped with three-strut landing gear, a tail wheel and a brake parachute. For take-off, the aircraft requires a concrete runway of 3,050m.

****PIT

The crew of the Tu-160 comprises a pilot and copilot, a navigator, and an operator. The four crew are equipped with zero/zero ejection seats, which provide the crew with the option of ejecting safely throughout the entire range of altitudes and air speeds, including when the aircraft is parked.

In the ****pit and cabins, all the data is presented on conventional electro-mechanical indicators and monitors, and not head-up displays or cathode ray tube displays. The Tu-160 has a control stick for flight control as used in a fighter aircraft - rather than control wheels or yokes, which are usually used in large transporter or bomber aircraft.

WEAPONS

The Tu-160 can carry nuclear and conventional weapons including long-range nuclear missiles. The missiles are accommodated on multi-station launchers in each of the two weapons bays.

The Tu-16 is capable of carrying the strategic cruise missile Kh-55MS, which is known in the West by the NATO designation and codename AS-15 Kent. Up to twelve Kh-55MS missiles can be carried, six in each bay. The Kh-55MS is propelled by a turbofan engine. The maximum range is 3,000km, and it is armed with a 200-kiloton nuclear warhead.

The weapons bays are also fitted with launchers for the Kh-15P, which has the NATO designation and codename AS-16 Kickback. The Kh-15P Kickback has solid rocket fuel propulsion, which gives a range up to 200km. The Kickback can be fitted with a conventional 250kg warhead or a nuclear warhead. The aircraft is also capable of carrying a range of aerial bombs with a total weight up to 40 tons.

AVIONICS

The aircraft is highly computerised, and the avionics systems include an integrated aiming, navigation and flight control system, with a navigation and attack radar, an electronic countermeasures system, and automatic controls.

ENGINES

The aircraft propulsion system consists of four NK-32 augmented turbofan engines, which each provide a maximum thrust of 25,000kg. The engines are installed in two pods under the shoulders of the wing. The air intake incorporates an adjustable vertical wedge. The bomber has an in-flight refuelling system. In the inoperative position, the refuelling probe is retracted into the nose of the fuselage in front of the pilot's cabin. The aircraft fuel capacity is 160,000kg.


Tu-160 in-flight refuelling.


Maximum flight speed at high altitude for the Tu-160 is 2,000kph.


Operational flight range with maximum combat mode is 10,500km.


The engines are installed in two pods under the shoulders of the wing. The air intake incorporates an adjustable vertical wedge.


The Tu-160 Blackjack will be upgraded to improve Russia's long-range bomber fleet.


The Tu-160 launching a Kh-55SM Cruise missile. This missile is currently undergoing a modernisation programme.

AVIATSIONNY NAUCHNO-TEKHNISHESKY KOMPLEKS IMENI A N TUPOLEVA OAO (Aviation Scientific-Technical Complex named for A N Tupolev JSC)
TUPOLEV Tu-160
NATO reporting name: Blackjack
TYPE: Four-engined variable geometry long-range strategic bomber.
PROGRAMME: Designed as Aircraft 70 under leadership of V I Bliznuk; first of two prototypes observed by satellite at Zhukovsky flight test centre 26 November 1981 (photograph in 1982-83 Jane's), first flew 19 December 1981; first exceeded M1.0 February 1985; second production aircraft lost 1987; US Defense Secretary Frank Carlucci invited to inspect 12th aircraft built, at Kubinka airbase, near Moscow, 2 August 1988; deliveries to 184th Guards Heavy Bomber Aviation Regiment, Priluki airbase, Ukraine, began May 1987; equipment of 1096th HBAR at Engels began 16 February 1992, but only six received before production at Kazan airframe plant terminated 1992; of 100 aircraft due to be built, at least 32 (including prototypes) accounted for; unconfirmed reports suggest total of 39, flying, plus one uncompleted at Kazan.
CURRENT VERSIONS: Tu-160 (`Blackjack'): Strategic bomber.
Tu-160SK: Launch vehicle for proposed Burlak-Diana two-stage space vehicle; described separately.
CUSTOMERS: Ukraine government seized 19 at Priluki on achieving independence, pre-empting planned transfer to Engels; purchase of these by Russia was subject to protracted negotiations, and aircraft deteriorated in storage; March 1996 agreement on transfer of 10 best airframes was not implemented; attempts to purchase eight failed in March 1998 and Russia then abandoned hopes of expanding Tu-160 fleet. Will now be scrapped with US assistance. Russia maintains force of six (declared as ALCM carriers under START) at Engels (where 1096th HBAR was redesignated 121st Guards HBAR in 1994), plus flying testbed at Zhukovsky; at least four more were derelict at Zhukovsky by 1995. However, latest US estimates of Russian combat forces report total holding of nominally serviceable aircraft as 25, though this would not seem to be possible.
On 3 March 1999 the Russian Commonwealth Aerospace Technology Consortium (RCATC) was authorised by the Ukrainian government to sell three demilitarised Ukrainian Air Force Tu-160s, plus spares, to Platforms International Corporation of the USA, with which it has finalised a strategic partnership. The US$20 million deal includes a 20 per cent interest in Orbital Network Services Corporation, which plans to use the aircraft as re-usable communications satellite launchers in its HAAL-2000 High-Altitude Air Launch programme. The Tu-160s will continue to be based at Priluki, maintained and flown by Ukrainian crews, but flown to customer countries for individual space launch missions.
DESIGN FEATURES: Intended for high-altitude standoff role carrying ALCMs and for defence suppression, using short-range attack missiles similar to US Air Force SRAMs, along path of bomber making low-altitude penetration to attack primary targets with free-fall nuclear bombs or missiles; this implies capability of subsonic cruise/supersonic dash at almost M2 at 18,300 m (60,000 ft) and transonic flight at low altitude. About 20 per cent longer than USAF B-1B, with greater unrefuelled combat radius and much higher maximum speed; low-mounted variable geometry wings, with very long and sharply swept fixed root panel; small diameter circular fuselage; horizontal tail surfaces mounted high on fin, upper portion of which is pivoted one-piece all-moving surface; large dorsal fin; engines mounted as widely separated pairs in underwing ducts, each with central horizontal V wedge intakes and jetpipes extending well beyond wing centre-section trailing-edge; manually selected outer wing sweepback 20º, 35º and 65º; when wings fully swept, inboard portion of each trailing-edge flap hinges upward and extends above wing as large fence; unswept tailfin; sweptback horizontal surfaces, with conical fairing for brake-chute aft of intersection.
FLYING CONTROLS: Fly-by-wire. Full-span leading-edge flaps, long-span double-slotted trailing-edge flap and inset drooping aileron on each wing; five-section spoilers forward of flaps; all-moving vertical and horizontal one-piece tail surfaces.
STRUCTURE: Slim and shallow fuselage blended with wing-roots and shaped for maximum hostile radar signal deflection; 20 per cent titanium, including leading-edges and wing centre-section spar box.
LANDING GEAR: Twin nosewheels retract rearward; main gear comprises two bogies, each with three pairs of wheels; retraction very like that on Tu-154 airliner; as each leg pivots rearward, bogie rotates through 90º around axis of centre pair of wheels, to lie parallel with retracted leg; gear retracts into thickest part of wing, between fuselage and inboard engine on each side; so track relatively small. Nosewheel tyres size 1,080 ?- 400 mm; mainwheel tyres size 1,260 ?- 425 mm.
POWER PLANT: Four Samara NK-321 turbofans, each 137.3 kN (30,865 lb st) dry, 245 kN (55,115 lb st) with afterburning. In-flight refuelling probe retracts into top of nose. Fuel in centre-section spar box and in outer wings.
ACCOMMODATION: Four crew members in pairs, on individual Zvezda K-36LM zero/zero ejection seats, in pressurised compartment; one window each side of flight deck can be moved inward and rearward for ventilation on ground; flying controls use fighter-type sticks rather than yokes or wheels; crew enter via extending ladder in nosewheel bay. Cooking facilities and toilet.
AVIONICS: Systems utilise around 100 digital processors and eight digital nav computers.
Radar: Nav/attack radar in slightly upturned dielectric nosecone claimed to provide terrain-following capability.
Flight: Astro-inertial nav with map display.
Instrumentation: No HUD or CRTs.
Mission: Strike sight fairing with flat glazed front panel, under forward fuselage, for video camera to provide visual assistance for weapon aiming.
Self-defence: Active ECM jamming system; RWR.
ARMAMENT: No guns. Internal stowage for free-fall bombs, mines, short-range attack missiles or ALCMs; two 12.80 m (42 ft) long weapon bays; rotary launcher for six Kh-55MS (AS-15 `Kent') or RKV-500B (AS-15B `Kent-B') ALCMs or 12 Kh-15P (AS-16 `Kickback') SRAMs in each bay. Current plans envisage carriage of non-nuclear Kh-101 ALCMs, when available.
DIMENSIONS, EXTERNAL:
Wing span: fully spread (20º) 55.70 m (182 ft 9 in)
35º sweep 50.70 m (166 ft 4 in)
fully swept (65º) 35.60 m (116 ft 9?ắ in)
Wing aspect ratio: fully spread 8.6
Length overall 54.10 m (177 ft 6 in)
Height overall 13.10 m (43 ft 0 in)
Tailplane span 13.25 m (43 ft 5?ắ in)
Wheel track 5.40 m (17 ft 8?ẵ in)
Wheelbase 17.88 m (58 ft 8 in)
DIMENSIONS, INTERNAL:
Weapons bay (each): Volume 43.0 m3 (1,518 cu ft)
AREAS:
Wings, gross: fully swept 360.00 m2 (3,875.0 sq ft)
fully spread approx 400.00 m2 (4,305.6 sq ft)
moving areas, fully swept (total) approx 180.00 m2 (1,937.5 sq ft)
WEIGHTS AND LOADINGS:
Weight empty 110,000 kg (242,505 lb)
Weight empty, equipped 117,000 kg (257,940 lb)
Max fuel 171,000 kg (376,990 lb)
Max weapon load 40,000 kg (88,185 lb)
Normal T-O weight 267,600 kg (589,950 lb)
Max T-O weight 275,000 kg (606,260 lb)
Max landing weight 155,000 kg (341,710 lb)
Max power loading 280 kg/kN (2.75 lb/lb st)
PERFORMANCE:
Max level speed at 12,200 m (40,000 ft)
M2.05 (1,200 kt; 2,220 km/h; 1,380 mph)
Cruising speed at 13,700 m (45,000 ft) M0.9 (518 kt; 960 km/h; 596 mph)
Max rate of climb at S/L 4,200 m (13,780 ft)/min
Service ceiling 15,000 m (49,200 ft)
T-O run at max AUW 2,200 m (7,220 ft)
Landing run at max landing weight 1,600 m (5,250 ft)
Radius of action at M1.5 1,080 n miles (2,000 km; 1,240 miles)
Max unrefuelled range 6,640 n miles (12,300 km; 7,640 miles)
g limit +2

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