Beech (Raytheon) King Air


AH of the US Army’s Guardrail-configured RC-12s, like this RC-12N, are festooned with antennas for their communications intercept and Jamming role.



he Beech Super King Air family of six – to 10-seat.

twin-turboprop business aircraft evolved from the King Air 90 and King Air 100 to the Model 200 Super King Air, which first flew on 27 October 1972 (the ‘Super’ title was drooped from all King Airs in 1996), The Model 200 was an enlarged, more powerful derivative, with a T-tail, increased wing span, extra fuel and improved pressurisation.

The Model 200 was rapidly adopted by all US armed services, primarily as utility aircraft/light transports, under The designation C-12 Variants include the C-12A (Model A200 for the US Army, USAF and Greece); UC-12B (Model A200C with cargo door for USMC and USN; TC-12B (USN crew trainers converted from C-12B); C-12C (with uprated PT6A-41 engines for US Army, later US Customs Service); C-12D (Model A200CT for US Army, USAh), C-12E (USAF C-12As refitted with PT6A-42s); C-12F (Operational Support Aircraft similar to B200C for USAF, US Army and National Guard); UC-12F (USN equivalent of РТбА-42-powerod C-12F); UC-12M (C-12F equivalent for USN); C-12R (B200C for US Army). The designation C-12J has been applied to a version of the Beech Model 1900 operated by the USAF and Army, while the C-12S is a Model 350 operated by the US Army.

Other military operators of the (Super) King Air include Argentina, Bolivia. Canada, Chile, Colombia Ecuador, Egypt, Greece, Guatemala, Guyana, Indonesia, Ireland, Israel, Ivory Coast, Jamaica,

Japan (Model 350, local designation LR-2), Mexico, Morocco, Pakistan, Spain, Sri l. anka, Sweden (local designation Tp 101), Thailand. Turkey and Venezuela. A radar-equipped maritime B200T patrol version serves with Algeria, Peru and Uruguay.

The US Army operates battlefield signals intelli­gence (Sigint) RC-12s, urder the Guardrail programme. Current versions include the RC-12D Improved Guardrail V (Model A200CT, fitted with AN/USD-9 remote-controlled communications inter­cept system, associated antenna and wingtip pods); RC-12G (increased weight version based on RC-12D); RC-12H Guardrail Common Sensor (System -3), increased weight version based on RC 12D: RC-12K Guardrail Commons Sensor (System 4), developed from RC-12F1, also delivered to Israel: RC-12N Guardrail Commons Sensor (System 1), developed from RC-12K with new mission fit; RC-12P Guardrail Commons Sensor (System 2), developed from RC-12N RC-12Q Direct Satellite Relay (relay platform for RC-12P).The US Navy also operates two RC-12M RANSAC range patrol aircraft.

Beech (Raytheon) King Air

Dassault Mirage F1


Подпись: Specification: Dassault Mirage F1C Powerplant: one 70.21-kN (15,785-lb) SNECMA Afar 9K-5Q terboje: Dimensions: wing span 9.32 m (30 ft 6/ in) with winglip AAMs; lengti 15.33 m (Ь0 ft 2/ in|; height 4 53 m (14 ft 9 ini1 Weights: empty 74C0 kg 116,314 lb); maximum take-off 16200 kg (35,715 Ibl Performance: maximum level speed 2338 kmh (1,453 mphj; service ceiling 23000 n (85.615 ft), combat radius 425 kin (264 mlEs) on a hi-lo-hi attack mission with 14 250-kg |551-lb) bombs Armament: two internal DEFA 553 30-mm cannon with 13b rpg. maximum ordnance load of 6300 kg (13,889 lb)


espite its suffix, the Mirage F1C was the initial production version of Dassault’s successor to its highly successful Mirage ІП/5 delta. It was deve ooed to meet ап Агтёе de ҐAir fAA) require merit for an all-weather interceptor. Forsaking the Mirage Ill’s delta configuration *’or a high-mounted wing and conventional tail surfaces, the prototype first flew on 23 December 1966, Mirage F1C production deliveries to the AA began in May 1973. The initial 83 aircraft were followed by 79 Mirage F1C-20Qs with fixed refuelling probes (necessitating a small fuselage plug), The AA also received 20 Mirage F1B tandem-seat trainers which retained their Tull combat capability.

Dassault converted 64 F1C-200S to serve as dedicated tactical reconnaissance platforms. These Mirage F1CR-200s arc equipped with an infra-red linescan unit, undernose cameras and centreline pods for SLAR, LOROP or Elint equipment. They also have a modernised cockpit with a Martin-Baker Mk 10 ejection seat, new RWR and two additional underwing hardpoints for chaff/flare dispensers. The F1CR fleet is now being equipped with the PRESTO stand-off reconnaissance pod, replacing the interim DFSIRF system.

The Mirage F1CT (T-Tactique) was a logical product of the shortfall in French ground attack capability and a surplus of air defence fighters following Mirage 2000C deliveries. From 1991, 55 Mirage FICs were converted to F1CT standard

France’s dual-role Mirage FICRs are tasked with reconnaissance and attack missions, and had their combat dehut in 1991, during Desert Storm.

have peer given expanded tactical capability with a laser rangefinoer. improved RWR and chaff/f:are dispensers. FlCTs are most often deployed with the French units still based in Africa. The last remaining AA F1C squadron is also based in Africa, with IEC4/33 in Djibouti,

The Mirage F1 has been widely exported. F1Cs were sold to Soutn Africa (F1CZ. now withdrawn), Morocco (F1CH), Jordan (F1CJ), Kuwait (F1CK, F1CK2. now withdrawn), Greece (F1CG) and Spain (F1CEK The Mirage F1A was a simplified version for day visual attack missions, equipped with the Aida II ranging radar in a reprofiled nose. It was sold to Libya (FIADi and South Africa (F1AZ fitted with a laser-ranger, now withdrawn).

The Mirage FlE (and corresponding Mirage FID trainer) was an upgraded multi-role fighter/attack version for export, fitted with an INS. central nav/attack computer and HUD. F1Es were exported to Ecuador (F1JA/E), Iraq (F1EQi. Jordan (F1EJ), Libya (FlED), Morocco (FlEH and FlEH-200), Qatar (FIEDA and F1DDA) and Spain (F1EE-200)

Between 1999 and 2001 Spain’s 52 Mirage F1s received a cockpit upgrade adding new communications, self – defence and navigation systems

Подпись: Dassault Mirage 2000C, 2000-5 Airdefence/multi-role fighter The Mirage 2000-5F is the Armee de I'Air’s version of the freshly upgraded multi-role fighter. It can carry the Mica missile - with four fitted on this aircraft.

For the third Mirage generation, Dassault returned to the delta configuration, using negative longitu­dinal stability and a fly by-wire flight control system to eliminate many of the shortcomings of a conven­tional delta – As such, the Mirage 2000 has its predecessor’s large internal volume ano low wave drag, but has improved agility, slow-speed handling and lower landing speed. The first of five prototypes was initially flown on 10 March 1978. The first of 37 production Mirage 2000Cs made its maiden flight on 20 November 1982 and deliveries began in April 1983, with IOC in July 1984. All eariy production 2000C-S2. – S3 aircraft had SNECMA M53-5 engines, and introduced successive improvements to the Thomson-CSF RDM radar. The Mirage 2000C-S4 and – S5 introduced the uprated M53-P2 powerplant and the superior RDI radar optimised for look- down/shoot-down intercepts with two MATRA Super 530D missiles. With RDM radar, Mirage 2000Cs carried Super 530F and Magic 1 missiles.

Export versions of the RDM-equipped, M53-P2- powered variant have been delivered to Abu Dhabi (Mirage 2000EAD, 22 aircraft), Egypt (Mirage 2000EM, 16), Greece (Mirage 2000EG, 36), India (Mirage 2000HS Vajra, 46) and Peru (Mirage 2000P 10).

The Mirage 2000B tandem two-seat trainer first flew in August 1983. It loses some internal fuel and both cannon in order to accommodate the second cockpit. Abu Dhabi’s two-seat trainers are known as Mirage 200QDADs, India’s are Mirage 2000THs and Peru’s are Mirage 2000DPs. The reconnais­sance-configured Mirage 2000R has a radar nose and carries podded sensors: multi-camera, side­looking airborne radar, and long-range optical. Abu Dhabi has acquired eight Mirage 2000RADs

The upgraded Mirage 2000-5 introduces an advanced five-screen cockpit display. Mica AAMs, RDY multi-mode radar, and advanced self-protec­tion suite and additional avionics. The 2000-5 is aimed largely at the export market, and significantly improves the basic aircraft’s combat capability. The French air force is also acquiring the Mirage 2000-5F through the conversion of 37 of its existing 2000Cs. The first converted prototype flew on 26 February

1996. The first export customer for the -5 came in 1992 when Taiwan ordered 60 Mirage 2000-5Els (including 12 2000-5DI trainers). Deliveries began in

1997. Other orders have come from Qatar (12 Mirage 2000-5EDA/DDAs). Abu Dhabi (UAE) and Greece are acquiring a further improved version the Mirage 2000-5 Mk II. also referred to as the Mirage 2000-9

Подпись: Qatar’s two-seat Mirage 2000-5s are known as Mirage 2000-5DDAs. These aircraft are quipped with the RDY radar, but are not combat capable. Specification: Dassault Mirage 2000-5 Powerplant: ore 95.12-kN (21,384-lb) SNECMA M53-P2 turbofan Dimensions: wing span 9,13 m (29 ft 112 in); length 14.36 nr. (47 ft 1И in): height 5 20 m (17 ft/in)

Weights: empty /500 kg (16,534 lb), maximum take-off 17000 kg (37.478 lb)

Performance: maximum level speed more than 2338 kmh (1.453 mph); maximum rate of climb at sea level 17060 m (55,971 ft) par minute: service ceiling 18900 m (59.055 ft); combat range over 1480 km (920 miles) with four 250-kg bombs

Armament: two 30 mm 0EFA 554 cannon with 125 rpg: 6300-kg (13,890-lb) ordnance

Lockheed S-3 Viking Carrier-based ASW and ASuV aircraft


Each US Carrier Air Wing embarks a single S-3B squadron for battle group ASW protection, but the Vikings have many other useful functions.


Подпись: Specification: Lockheed S-3B Viking Powerplam: two 41,26-kN (9,275-lb) General flectrfc TF34-GE-2 turbarans Dimensions: wing span 20.93 m (68 ft 3 rn); length overall 1 S.26 m (53 ft 4 in) height overall 6.93 m (22 ft 9 in) Weights: empty '2038 kg (26,660 lb); (42.5Ю lb); maximum take-off 23832 kg (52,540 lb) Performance: max speed at sea level 814 kmh: (506 mph); maximum rate of climb at sea level 1280 m (4,200 It) per minute; service ceiling 10670 m 136.000 ft]; combat radius over 1751 km (1,088 miles) Armament: maximum ordnance 3175 kg (7.000 lb) with 1814 kg (4.000 lb) carried internally


eveloped to counter the new generation of Soviet navy quiet, deep-diving nuclear-powered submarines, the Lockheed S-3 Viking is the US Navy’s standard carrier-based, fixed-wing ASW aircraft. It is a conventional high-wing, twn-turbofan aircraft with four crew (pilot co-pilot, tactical co­ordinator and acoustic sensor operator) The first of eight service-test YS-3As made its maiden flight on 21 January 1972, and was followed by 179 production S-3A Vikings equipped with an AN/APS-116 search radar and OR-89 FUR. The heart of the ASW suite is an AN/ASQ-81 WAD sensor housed in a retractable Tailboom. The S-3A carried 60 sonobuoys in its aft fuselage and has a ventral bomb bay and wing hardpoints for bonnbs, mines torpedoes or depth charges. The S-3A entered fleet service in July 1974. Lockheed produced four US-ЗА COD aircraft which have now been retired, and a single KS-3A tanker demonstrator.

The current in-service S-3B Viking variant is the result of a 1981 upgrade programme, which added the APS-137 Inverse Synthetic Aperture Radar, the ALR-76 ESM system and the ALE-39 chaff/flare dispenser. The Viking’s anti surface warfare capability was greatly improved througn the integration of the Harpoon and Maverick missiles. About 160 S-3 As

For the future the US Navy is looking to its Common Support Aircraft requirement to replace the S-3 Viking, E-2 Hawkeye and C-2 Greyhound.

were upgraded to S-3B standard. In recent years the Viking fleet has placed less emphasis on the ASW role as the Russian naval threat receded. Vikings instead took on an increased attack and special missions role, while also acting as the de facto tanking aircraft for carrier air wings. Specialist S-3B programmes include the Outlaw Viking (over-the-horizon targeting! Beartrap Viking (ASW development), Orca Viking (ASW development) and the Grey Wolf (overland reconnaissance, com­mand and control with a podded SAR radar)

The ES-3A Shadow was a carrier-based Elint aircraft modified from the S-3A with extensive sur­veillance equipment. The co-pilot’s position was replaced by a third sensor station and the bomb bays were modified to accommodate avionics. The ES-3A had a new radome, direction-finding antenna, and other equipment in a dorsal ‘shoulder’ on the fuselage, an array of seven receiving antennas on its underfuselage, an omnidirectional Elint antenna on each side of the rear fuselage, and wingtip AN/ALR 76 ESM antennas. Two squadrons operated the ES-3A from 1995 to 2000 when it was retired in favour of land-based Elint aircraft. Studies for an S-3 replacement are now being conducted under the US Navy’s Common Support Aircraft programme.



arly variants of the Lockheed U-2 had successful (if clandestine) careers as high-altitude recon­naissance platforms. However, these models were limited by the size and weight of sensors which they could carry, and so Lockheed developed the improved U-2R which first flew in August 1967. It was larger overall, offering greatly improved range/ payload, endurance and handling characteristics Twelve early-production U-2Rs served with the USAF (in Vietnam) and with the CIA.

In 1979 the production line re-opened to provide the USAF with 37 new airframes for the TR-1A tactical reconnaissance programme, using the U-2R as a platform for the ASARS-2 synthetic aperture battlefield surveillance radar, the PLSS radar location system, and all-new Sigint-gathering equipment. The batch also nc:uded two two-seat TR-1B (later TU-2R and TU-2S) trainers and one U-2RT All three two-seat trainers are identical. Finally, two ‘civilianised’ U-2Rs were built for NASA as ER-2 earth resources monitoring aircraft. In 1991 the USAF abandoned the TR-1 designation and renamed all its aircraft as U-2Rs.

All U-2R and U-2R i aircraft were re-engined with the General Electric FI01 (later redesignated F118- 101) replacing the original J75 engine, to become the U-2S and the U-2ST, respectively. The new engine had a dramatic effect on performance and operating costs. Flight tests began in 1991 and the aircraft were redelivered between 1994 and 1998.

The chief identifying feature of the U-2R/U-2S are the ‘super pods’fitted to the inboard wing. These large pods carry a range ofSigint systems

The U-2S most resembles a large powerea g ider. The retractable main bicycle undercarriage is aided by plug in detachable ‘pogo’ outriggers. The wingtips incorporate skids, above which are RWR$, Sensors are carried in the nose, a large ‘Q-bay‘ for cameras (behind the cockpit), smaller bays along the lower fuselage ano in two removeabie wing ‘super pods’. Sensors include Comint and Elint recorders, imaging radars, radar locators and high resolution cameras. A common mission fit combines a nose – mounted ASARS-2 radar and the Senior Glass Elint system with its substantial ‘farm’ of Sigint antennas on the rear fuselage and in the ‘super pods’. Recorded intelligence can be transmitted via datalink ю ground stations, and some aircraft can carry the Senior Span/Spur satcom antenna in a large rear-mounted teardrop radome. The U-2S has also been re-equipped with the SYERS (Senior Year Electro-optical Relay System) camera, which uses imaging technology developed for US reconna s- sance satellites. The electro-optical camera at the heart of SYERS is carried in the aircraft’s nose.

ine senior spur satellite communications antenna allows the U-2S to relay ASARS-2 imagery back to base from the other side of the world.



Specification; Lockheed U-2S Powerplant: une 81.4-kN (18,300-lb) General Electric F118-101 non-afterburning lurbo’an Dimensions: wing span 31.39 m (103 ft in); lergth 19 13m {Б2 ft 9 in); height 4.88 in (16 ft) Weights: operating empty about 6441 kg (14,199 lb); maximum take-off 18733 kg (41.300 lb)

Performance: maximum cruising speed at 21335 m (70,000 Ilf over 692 kmh (430 mpb). operational ceiling approximately 25450 m (83,500 ft), maximum range over 12500 km (7767 miles); mission endurance over 12 hours


Saab 37 Viggen


High performance strike fighter



aab’s System 37, tne Viggen (thunderbolt) was developed as a relatively low-cost Масо 2 fighter capable of deployed short-field operations. The design pioreerec the use of flap-equipped canards with a stabie delta-wing configuration. The selected RM8A turbofan was based on the commercial P&W JT8D-22 and equipped with a thrust reverser and Swedish afterburner.

The initia AJ 37 Viggen all-weather attack variant featured sophisticated nav/attack and landing sys­tems and the PS-37 multi-role radar. The first of seven Viggen prototypes initially flew on 8 February 1967 and deliveries of the first of 109 AJ 37s began in 1971. The primary armament comprised Saab Rb 04E anti-ship missiles (replaced by the far more capable long-range Rbs 15) and licence-built AGM-65 Maverick ASMs.

Several AJ 37-based variants were developed. The SF 37 was tasked with all-weather day and night overland reconnaissance. It is equipped with various optical and IR cameras, and carries podded sensors. The SH 37 was modified for all-weather sea surveillance and patrol with a secondary maritime strike role. It has a modified radar, ventral night reconnaissance and long-range camera pods. A tandem two-seat SK 37 trainer was also developed with a stepped rear cockpit fitted with a bulged canopy and twin periscopes.

The next-generation JA 37 Jakt Viggen (fighter Viggen) was developed as a dedicated interceptor.

The Viggen’s operational career is being cut short by budget cuts and the arrival of the next generation Gripen. The last JA 37s will be withdrawn in 2003.

It introduced a new pu se Doppler look-down/shoot – down PS-47 radar, new avionics, an uprated and modified RM8B engine and a ventral 30 mm cannon. A modified AJ 37 was flown as the JA 37 prototype on 27 September 1974. Overall production of this variant was increased to 149, tak­ing total Viggen procurement to 330. JA 37s entered service in 1978. A number of aircraft have now undergone the JA 37 Mod D upgrade, giving them AIM-120 AMRAAM capability.

Force cuts during the 1990s brought about the retirement of many AJ 37s as squadrons were dis­established and aircraft were scrapped. The advent of the JAS 39 Gripen brought about a rationalisation of the Viggen fleet. The attack/recce Viggens were upgraded to a new ‘multi-role’ standard, allowing them to familiarise pilots with Gripen weapons and procedures. Under this upgrade AJ 37s became AJS 37s, SF 37s became AJSF 37s and SF!37s became AJSH 37s. A number of two-seat SK 37s have also been radically modified to serve as SK 37E EW/SEAD aircraft.

Sweden’s fighter Viggens wear a mix of overall grey and green/brown splinter camouflage. The splinter scheme was applied to all attack/recce Viggens.

image200Specification: Saab JA 37 Viggen Powerplani: one 125 04-kN (28,11 C-lb) Volvo Flygmotor RMI33 turbofar with Swedish anerhi. rner and thrust reverser Dimensions: wing span 10.30 m (34 ft 0/1 ini, length 16.40 m (53 ft 9/1 in) including probe; heigh 5.90 m (19 ft 4И in)

Weights: normal take-off 15000 <g (33,069 lb); тзхіпшпі take-oil 17C00 kg (37.478 lb) Performance: maximum level speed 2126 kmh [1,321 mph); combat radius more than 1000 km (622 miles) on hi-lo-hi profile Armament: one ventral 30-mm Oerlikon KCA cannon with 150 rounds; maximum ordnance 13,000 lb (5897 kg)

Bell Model 205, 212 and 412


This Turkish army UH-1H is typical of the huge number of UH-1Hs that are still in miiitaiy service around the world.



erived from the Bell Model 204/UH-1 Iroquois, the improved Model 205 was first flown In August 1961. Retaining the existing T53 turboshaft, it introduced a larger-diameter main rotor, additional fuel capacity and a lengthened fuselage. Over 2,000 UH-IDs were built for the US Army, followed by the similar UH-1H, which introduced the uprated T53-L-13 engine. A total of 2,008 UH-1Ds and 3,573 UH-lHs were built for the US Army alone, and the type was exported to over 50 countries, With several thousand Model 205/UH-1Hs still in service, a number of companies offer modernisation and upgrade programmes. Bell Helicopter has developed the Huey II upgrade, which adds the uprated T53-703 engine and a new transmission system. The Huey II has been ordered by Colombia and more sales in South America are likely. Other UH-1 conversions include the Global Helicopter Huey 800. which completely replaces the T53 with an LHTEC T800-800 engine and UNC Helicopter’s UH-1/T700, which adds the GE T700 engine.

The Model 212 ‘Twin Huey’ is a twin-turbine UH-1 H, fitted with two PT6T-3 turboshafts driving a single shaft. Announced in May 1968, the 212 was launched with a Canadian order for 50 CH-135 aircraft. The USAF, USN and USMC acquired it as the UH-1N
and the Marines are now upgrading their aircraft to UH-1Y standard (in parallel with the AH-1Z Cobra upgrade). The UH-1Y will be fitted with an all-new four-bladed composite rotor system and new cock­pit systems. Italy’s Agusta has built the Bell 212 under licence as the AB 212, and also developed a range of special missions versions. The most important of these is the shore-/ship-based anti­submarine variant, the AB 212ASW.

In 1978 Bell introduced the Model 412, Essentially similar to the Model 212 it featured an entirely new four-bladed main rotor system. The Model 412 has been built by Agusta as the AB 412 and by Indonesia’s IPTN as the NB 412. Developed versions include the Model 412SP (Special Performance) with extra fuel and increased maxi­mum take-off weight; Model 412HP, with uprated transmission; and the Model 412EP (Enhanced Performance) powered by a refined PT6T-3D engine and fitted with a three-axis digital flight con­trol system. This is now the standard production model. In 1992 Canada ordered 100 aircraft, based on the Model 412EP, as the CH-148 Griffon

Since 1986 all Bell helicopter production has been undertaken in Mirabel, Quebec, by Bell Helicopter Textron Canada.

Подпись: In British service the Model 412 is known os the Griffin HT.Mk 1. The type serves with the tri-service Defence Helicopter Flying School. SPECIFICATION: Bell 412EP Powerplant: two 1342-kW (1,BG0-hp) Pro il & Whitney Canada РГ6Т-30 Turbo Twin-Pac turboshafts

Dimensions: таіп rotor diameter 14.02 m (46 ft); height, tail rotor turning 4.57 m (15 ft); length, rotors turning 17.12 m (56 ft 2 in)

Weights: empty, standard 3079 kg (6,769 lb): maximum take-off 5397 kg 111.900 lb); maximum external hook load 2041 kg (4,500 lb) Performance: max cruising speed, at sea level 226 kmh(KOnnph); hovering ceiling, in ground effect 311C m (10,200 ft) and 1585 m (5.200 ft) out of ground effect, maximum range, with no reserves 745 km (463 mrles|



rench requirements for a Mirage IVP replace­ment to carry the ASMP stand-off nuclear missile resulted in Dassault receiving a contract in 1979 for two Mirage 2000P (Penetration) prototypes (later designated Mirage 2000IM (Nucleaire)). Based on the 2D00B two-scat trainer, the 2000IM has a strengthened airframe for low-leve! flight and considerable differences in avionics, including twin INSs. and Antilope 5 radar optimised for terrain following, ground mapping and navigation. It provides automatic terrain following down to 91 m (300 ft) at speeds up to 1112 kmh (691 mph). Both pilot and WSO have moving map displays. ASMP delivers a 150- or 300-kT warhead up to 80 km (50 miles) from a low-altitude launch point. Outboard, the Mirage 2000N carries a pair of large, 2000-litre (440-lmp gall drop tanks and two self- defence MATRA Magic AAMs. Further protection is provided by the Serval RWR, Sabre electronic jammers and a Spirale chaff/flare system.

The prototype Mirage 2000N was flown on 3 March 1986. The first 30 production aircraft were built to Mirage 2000IM-K1 standard, without the Spirals countermeasures equipment. The – Kl was a dedicated nuclear strike variant, and was armed with two AM.52 free-fall bombs before the ASMP missile was ready for service The second batch of 44 deliveries were Mirage 2000IM-K2S, which had a dual nuclear/conventional capability, and full ASMP compatibility. France’s Mirage 2000N deliveries
were completed in 1993. The 2000N-K1 aircraft have since been upgraded to acquire a limited conventional attack capability.

While the Mirage 200QN is largely dedicated to nuclear strike, Dassault has also developed a similar version for conventional long-range precision attack missions. This is the Mirage 2000D, which out­wardly looks almost identical to the 2000N According to Dassault the D suffix stands for ‘Diversifie’ (diversified). The prototype Mirage 2000D first flew on 19 February 1991 (in fact, this aircraft was modified from the 200QN prototype). France has ordered a total of 86 Mirage 2000Ds and the final aircraft was delivered in 2001.

As with previous Mirages increasing levels of capability have been introduced during the aircraft’s life. The initial production Mirage 2000IM-R1 aircraft d;d not have the full weapons capability of the late production standard Mirage 2000IM-R2s. The -R2 aircraft introduced the Apache and Scalp stand-off missiles, the Samir self-protection fit, and the Atlis II laser-designation system.

Подпись: The Mirage 2000D looks very similar to the 2000N, but does not have a nuclear role. This aircraft is carrying a single Apache stand-off missile. Specification: Dassault Mirage 2000D Powerplant: one 95.12-kN (21,384-Eb) SWECMA M53-P2 turbofan Dimensions: wing span 9,13 m (29 ft 112 in); length 14.55 n |47 ft 9 in); height 5.15 m (16 ft Ш in)

Weights: empty 7600 kg (16,755 lb): maximum take-off 17000 kg (37.478 lb)

Performance: maximum level speed more than 2338 kmh (1.453 mph); maximum rate of Climb a! sea level 17060 m (55.971 ft) per minute: service ceiling 18000 m (59.055 ft): combat range over 1480 km (920 miles) with four 25Q-kg bombs

Armament two 30 mm DEFA 554 cannon with 125 rpg, 6300-kg (13,830-fb) ordnance

Lockheed Martin C-13D Hercules



he C-130 Hercules is the world’s most widely used and most versatile military transport, serving with 64 countries, The YC-130 first flew in August 1954. and was followed by the production C-130A in April 1955. An entire alphabet of specialised versions followed, but the basic transport aircraft had a straightforward evolution. In 1958 the C-130B introcuced more powerful T56-A-7A engines with four-bladed props and increased "uel tankage in the wings. In 1961 the C-130E arrivec, with yet more fuel and higher operating weights. The C-130H followed, initially as an export aircraft, but it became the definitive first-generation Hercu es variant, Powered by uprated T56-A-15 engines, the C-130H first flew in November 1964. The airframe featured a strengthened wing box, improved brakes and new avionics, The first production aircraft went to the RNZAF in 1965, and the USAF received its first С-1 ЗОН in April 1975.

The RAF’s C-130K (Hercules C. Mk 1) – based on the C-130H – has British avionics and equipment. Thirty were ‘stretched’ by 4.5 m (15 ft) to become C. Mk 3s, increasing capacity from 92 to 128 troops. With the addition of refuelling probes these aircraft became C. Mk iP/C. Mk 3Ps. Several nations are upgrading their older C-130s. Belgium

The most obvious difference between the C-130J and earlier models is the new aircraft’s AE2100 engines and their six-biaded ail-composite propellers.

This Royal Air Force of Oman С – 130H is typical of the many Hercules aircraft in every-day service all around the world today.

has fitted a ‘glass’ cockpit and new weather radar to its C-130Hs and Marshall’s of Cambridge have oeen doing similar work to South Africa’s C-13QBs. Many other operators have fitted missile warning equipment, chaff/flare dispensers and cockpit armour to their aircraft. Production of 2,156 first-generation C-130s ended rn 1998 with the delivery of з C-130H то Japan. By this time Lockheed (now Lockheed Martin) had developed its successor, the C-130J The C-130J began as a Lockheed private venture in 1991, as The ’Hercules ІГ. It modernised the С-1 ЗОН with new-technology engines and s:x-bladed proas, an advanced digital cockpit for two crew with HUDs as primary flight controls, a cigital engine management and diagnostic system. In 1994 the RAF became the launch customer, ordering 10 stretched C-130J-30S (Hercules C. Mk 4! and 15 C-130JS (Hercules C. Mk 5). Other customers include Australia, Italy, Denmark and the USA (including EC-130J, KC-130J and WC-130J variants), The first C-130J flew on 5 April 1996 but several unexpected problems slowed the flight test programme considerably. The first aircraft was not de ivered to the UK until August 1998 and further decays prevented the C-130J from entering service with the RAF until November 2000.


Specification: Lockheed C-13CJ Hercules Powerplant: four 3424-kW (4,531-hp) Ralls Payee (Al. isan) AE 21 (3033 turboprops Dimensions: wing spas 43.41 m (132 It 7 in); lengtn 2979 m (97 fi 9 in); height 11.66 n (38 ft 3 in)

Weights: operating empty equipped 34274 kg 175,562 lb); maximum oaylnad 18955 <g 141,790 lb): maximum taka-off 70,305 kg 1155.000 lb)

Performance: maximum cruising speed et 9′ 4b m (30,000 n) 595 kmh (379 mph); maximum rate af climb зі $еэ eve-l 640 m (2,100 ft) per minute; service ceiling 93" 5 m (30,650 ft); maximum range with a 18’44-ky (40,0Ш-ІЬ) payioad 5253 km km (3.262 miles)


Saab JAS 39 Gripen


Advanced multi-role combat aircraft


The heavyweight Rbs 15F anti-ship missile gives the Gripen an unparalleled maritime attack capability. This JAS 39A is carrying two Rbs 15s and AGM-65s.



ollowing the cancellation of the Saab B3LA light – attack/advanced trainer project in 1979, Saab began development of the JAS 39 Gripen (gryphon) as an advanced lightweight multi-role successor to the Viggen. The JAS designation (Jekt Attack Spaning – fighter, attack, reconnaissance) underlined the fact that one aircraft (and one pilot) would be able to undertake all the combat tasks of the mission-specific Viggen family. The Gripen was designed to carry the advanced Ericsson PS-05/A multi-mode radar, ntegrated with the D80 mission computer. The cockpit featured the Ericsson EP-17 display system with three monochrome screens and a wide-angled HUD. The Gripen uses a highly – developed version of Sweden’s tactical airborne datalink system that allows rapid real-time exchange of complex mission data between aircraft and ground stations. Power was supplied by the Volvo RM12 turbofan, an improved licence – built version of the General Electric F404. Above all the Gripen was designed to be rapidly deployable and easily maintainab e. It was intended to use Sweden’s Bas 90 system of disoersed 800-m (2,624-ft) long roadstrips, and to be re-armed, refuelled and maintained in the field by a team of just five ground personnel.

The two-seat JAS 39B was drawn up as a trainer, but it wiil be fielded as a fuily-opera tionai mission – specific aircraft, perhaps with a dedicatedSEAD

Five JAS 39A prototypes were built, with the first flying on 9 December 1988. The first production JAS 39A Gripen flew on 16 December 1992 The development programme was slowed by the loss of two aircraft in 1989 and 1993. These incidents led to a redesign of the Gripen’s pioneering digital fly-by-wire system.

The Gripen was declared fully operational with the lead Swedish unit, F7 Wing, on 1 Movember 1997. A second squadron at F7 followed on 30 December 1998. Deliveries to the second Gripen wing, F10, are now underway. The Swedish air force will acquire a total of 204 Gripens, including 28 two-seat combat-capable JAS 39Bs. Sweden’s Gripens are being delivered in three batches, each with improving levels of capability.

The ultimate Batch Three evolution (designated JAS 39C and JAS 39D) will be delivered from 2003 to 2007. These 64 aircraft will have the EP22 full colour cockpit with enlarged displays, air-to-air refuelling capability, upgraded D96 computer systems. Future Gripen upgrade options include a re-engining plan and conformal fuel tanks to extend range. In 1998 South Africa ordered 25 Gripens which wiil be equivalent to Sweden’s Batch Three aircraft, tor delivery beginning in 2007.


Specification: SAAB JAS 39A Gripen Powerplant: cne 8C,5-kN (18,100-lb) Volvo Aero RM12 turbofan

Dimensions: wine span 840 fit (27 ft 6’& in), ever missile rails; length 14.1 Dm (46 ft 3 ini including probe; heiyht 1.50 m (I4 ft 0 in) Weight’s: operating empty 6522 kg (14600 lb); maxiirum :аке-сТ 13000 kg I28.600 lb) Performance: supersonic all all altitudes; landing anc take-off distance less than 8DQ m (2,525 ftj; combat radius approx mately 830 krr (497 miles)

Armament: one 27-:nm Mauser В К 27 cannon, plus six external hardpoints. and wingtip missile launchers; maximum erdnar. ee approximately 4500 kg 19,920 lb)



Подпись: SEPECAT JaguarGround attack and reconnaissance aircraft


Unlike their French counterparts British single-seat Jaguars have a chisel nose housing a laser range­finder and marked target seeker.



esigned to meet в 1965 joint Anglo-French specification for an advanced trainer, the SEPECAT Jaguar was transformed into a potent iow-levei all-weather fighter-bomber The first proto­type flew on 8 September 1968. The RAF received 200 Jaguars, comprising 165 single-seat GR. Mk 1s {Jaguar S) with Ferranti LRMTS in a re-profiled nose and a tai – mounted RWR and 35 T. Mk 2 trainers (Jaguar B), all fitted with a sophisticated NAVWASS nav/attack system. They equipped a three-squadron Wing at Coitishall, operating in the conventional attack and reconnaissance roles, and with an out-of-area, rapid reinforcement commitment. The Jaguar also equipped a four-squadron Wing at RAF Bruggen in Germany {with a further recce unit at RAF Laarbruch) until 1988, with an additional nuclear strike commitment.

The RAF’s Jaguars received more powerful Adour Mk 104 engines from 1978-84, while the GR. Mk 1A/T. Mk 2A upgrade added a FIN1064 I NAS to 75 single-seaters, and 14 trainers. The aircraft also received AIM-9G Sidewinders, AN/ALE-40 flare dispensers, Phimat chaff/flare dispensers and AN/ALQ-101 jamming pods. For Operation Granby in 1991, the RAF’s Jaguars received defensive sys­tems improvements, overwing AlM-9Ls, CRV-7 rockets and CBU-87 cluster bomDS. Since 1994, the surviving Jaguars been upgraded (to GR. Mk ЗА standards} adding GPS, TERPROM, the TIALD laser designator, an advanced NVG-compstible cockp t,
helmet mounted sight and a sophisticated new mission planner. They are due to serve unti 2008- 2009, and perhaps even longer.

The French Armee de Г Air received 160 single – seat Jaguar As and 40 Jaguar E trainers with more austere avionics. Some had an undernose TAV-38 laser rangefinder, and all had an OMERA 40 vertical camera. The French Jaguars equipped EC.7 (operating in the attack and, until 1991, strike roles), EC.11 (with out-of-area and defence suppression commit­ments) and one escadron of EC.3. The surviving French Jaguars, still powered by the original Adour 102, will be withdrawn by 2004. The aircraft now use ATLIS laser designator pods, AS30 missiles and various LGBs. French Jaguars have seen action in Mauritania, Chad, the Gulf and the Balkans.

The Jaguar International (based on the RAF variants) vvas sold to Ecuador, India, Nigeria and Oman. India also builds the type under licence, (93 so far. with production continumg). India’s Jaguars include some Jaguar IM maritime attack aircraft, with Agave radar and BAe Sea Eagle missiles.

Подпись: The British Jaguar T.Mk 2A and (as seen here) the French Jaguar Є trainers have a stepped tandem cockpit configuration in an elongated nose. Specification: SEPECAT Jaguar A Powerplant: two 32.49-kN (7,305-lb! Rolls – RoyceAurbomcca Acour Vlk 102 furbcfan Dimensions: wing span 8.59 m!28 ft 6 in); length 17.53 nr. (57 ft Б’/. in) including probe; height 4.89 m (16 ft Kin)

Weights: empty equipped 70Г.0 kg (15,432 lb); maximum take-off 15700 kg I34.G12 lb) Performance: maximum level speed at 10975 m 135,000 :t) ІБ99 kmh (1.056 mph); combat radius 852 km 1530 miles) on e li – c-hi attack mission with internal fuel Armament: two DEFA 553 ЗП-mm cannon with 150 yog; maximum load of 4536 kg Г 0,006 Ih) on lour underwing and one centreline hartfpoinrs


The J-8 II was a radical re-design of the original J-8. The F-8 IIM is a further improved export version equipped with Russian-supplied radar and missiles.



hina’s J-8 (NATO code name ‘Finback’! originated from a 1964 PLA requirement for an indigenous fighter with performance superior to that of the MiG-21. Shenyang’s twin-engined design incorporated a scaled up configuration of the MiG-21’s ‘tailed delta’, with a ranging radar in the intake centre – body, similar to MiG’s own Ye-150. The first of two prototypes flew on 5 July 1969. These undertook a protracted flight test programme (lasting 10 years), which was interrupted and delayed by political upheaval. The resulting J 8 was armed with a single 30-mm cannon and up to four PL-2 AAMs.

The improved J-8 I ‘Finback-A’ was designed as an ail-weather fighter, and featured a new Sichuan SR-4 radar in an enlarged intake centrebody, some aerodynamic refinements and a two-piece canopy with a fixed windscreen. It introduced a twin-barrelled 23-mm 23-III cannon, and provision for four rocket pods as an alternative to the AAMs. A prototype flew on 24 April 1981. J-8 and J-8 I production totalled about 100 aircraft, and some J-8 Is have been converted to serve in the reconnaissance roie, with an undernose sensor package..

Development of the further improved J-8 II ‘Finback-B’ began in May 1981, leading to first flight of a prototype on 12 June 1984. The J-8 II

The original J-8’s MiG-21 heritage is clear to see in this line-up of‘Finback-As’. Despite its limited capability the J-8 A is still in PLAAF service.

introduced a nose-mounted rada’, and relocated new lateral air intakes for its 69-kN (15,430 lb) WP-138 turbojets and a ventral folding fin. An export F-8 IIM version has been offered, with a pulse-Doppler look-down radar and digital avionics, including a HUD and two HDDs, but this has not yet won any orders.

On 5 August 1987 Grumman received a contract to design, develop and test the Peace Pearl avionics upgrade for the J-8 II. This introduced a modified AN/APG-66 radar, giving compatibility with BVR SARH missiles like the AIM-7. The aircraft would also have received a modem HUD, з US ejection seat and an INS, and a bubble canopy and frame­less wrap-around windscreen. However, the Tienanmen Square massacre led to an immediate halt on work on the project,

J-SIIs of the PLA Air Force and PLA Navy Air Force are being upgraded with new RWRs (intro­duced in the second production block), and some are fitted with fixed inflight refuelling probes as J-8 IVs (also referred to as the J-8DI They are also being equipped with the PL-8 ДАМ (a copy of the Israeli Python III). The J-8 hit the headlines in April 2001 when one was lost after a collision with a US Navy EP-3E over the South China Sea,

image206Specification: Shenyang J-8 II ‘Finback-B‘ Powerplant: two 65.90-kN (I4,815-lb| Liyartg (LMC) Wapen-ІЗЛ II afterburning turbojets Dimensions: wing span 9.34 m (30 ft 8 in); length 21.59 m (/0 ft’ 0 in) including probe: height 5,41 m (17 ft 9 in)

Weights: empty 3820 kg 121.649 lb): maximum take-off 17800 kg (39,24? lb) Performance: maximum level speed 2338 kmh (1,453 mph); maximum rate of climb at sea level 12000 rn (39,370 ft) per minute, service ceiling 20200 m (65,275 ft), ferry range 2200 km (1,367 miles); combat radius 800 km (497 miles) Armament one ventral Type 23-3 twin – barrelled 23 mm cannon with 200 rounds; ordnance Pt-28, PL-8 and PL-10 missiles


Itelly’s Agusta-built AS-61 Rs differ from the basic S-61/SH-3 design with their high-raised taitbooms, rear ramps and water-right hulls.



ikorsky developed the S-61 Sea King to replace its previous S-58 design, combining dual ASW hunter/killer roles in a single airframe, The prototype YHSS-2 first ‘lew or 11 March 1959 and was followed by 245 production SH-3As for the USN. The primary sensors were an AQS-10 dipping sonar and an APN-130 search radar; in the ‘killer’ role the SH-3A carried two torpedoes or depth charges.

The 74 SH-3Ds that followed introduced uprated T58-GE-10 engines. AOS-13A sonar and APN-182 radar The SH-3G conversion modified 105 SH-3A/Ds to set as general-purpose rescue platforms and transports, Some 116 SH-3A, SH-3D, SH-3Gs were later converted to perform the inner-zone anti-submarine mission as SH-3Hs with AQS-13B dipping sonar, LN66HP search radar, chaff dispensers and an ASQ-81 towed MAD bird. ESM equipment end the radar were later replaced by a modern tactical navigation suite and improved sonobuoy and sonar processing capability.

By 2001 only a handful of SH-3Hs remained in US Navy service, strippeo of their ASW equipment and used for utility and SAR duties by second line units, along with small numbers of UH-3A and VH-3A utility transports. The VIP-dedicated VH-3D is also still m service, used as a Presidential transport by Marine Corps squadron HMX-1.

Of the military S-6lRs, which featured rear-load­ing ramps and a more conventional, non-boat-hulled fuselage, the USAF’s CH-3C. CH-3E, and probe-
equipped HH-3E ‘Jolly Green Giants’ have all been retired, as have the US Coast Guard’s similar HH-3F Pelicans. Two are still flown in Argentina, however, and about 33 Agusta-built AS-61 R Pelicans remain operational in the SAR role in Italy. Some of these aircraft have been armed and upgraded with FURS for the combat SAR role.

The basic Sikorsky-built S-61/SH-3 Sea King was exported to a number of countries, and remains operational in Argentina. Brazil, Denmark, Namibia and Spain. Licence manufacture was under-taken by Canada, Italy and Japan. Canada’s surviving CH-124As have been updated for continued ASW service, but are now overdue for replacement. About 48 of the Japan Maritime Self Defence Force’s 100 Mitsubishi-built HSS-2, HSS-2A and HSS-2B helicopters are still operated on ASW, utility and SAR tasks, Agusta-built ASH-3D and ASH-3H ASW, logistic, and VIP transport derivatives for a number of customers, and they remain operational in Argentina, Brazil, Egypt, Iran, Iraq, Italy, Libya, Malaysia, Peru, and Venezuela.

Only smalt numbers of H-3 Sea Kings remain in US Navy service today, serving largely as base SAR and utility transport aircraft

Specification: Sikorsky S-61 (SH-3H ) Powerplant:two 1O44-kW(I.4O0-hp|

image208General Electric T58-GE-10 turboshafts Dimensions: main rotor diameter 18 90 in {62 ft m|, length overall, rotors turning 22.15 m (72 ft 8 in), fuselage 16.69 m(54 ft Я ir. J; height overall 5.13 m (16“ft10in|

Weights: empty 5601 kg 112.350 lb); maximum take-off 9526 kg (21.000 lb) Performance: maximum level speed 267 kmh (166 mph); economical cruising speed 219 kmh (136 mph); maximum rate of climb at sea level 670 m (2,200 ft) per minute; service ceiling 4480 m (14,700 ft); hovering ceiling 3200 m (10.500 ft! IG£ and 2500 m (8,200 ft) OGC; range 1005 km (625 miles)


Подпись: Specification: Sikorsky CH-53E Powerplant three 2756-kW (3,696-hp) General Electric 764-GE-41S turboshafts Dimensions: main rotor diameter 24.08 m (79 ft); iength overall, rotors turning 30.19 m (99 ft A in), fuselage 22.35 m (73 ft 4 in); height overall, rotors turning 8.97 m (29 ft 5 in) Weights: empty 15072 kg (33.338 lb); maximum take-off 33340 kg (73.500 lb), maximum payload 16330 kg (36,000 Ibj Performance: maximum level speed 315 kmh (196 mph); maximum rate of climb at sea level with 11340-kg (25.000-lb) payload 762 m (2,500 ft) per minute; service ceiling 5640 m (18,500 ft); operational radius 925 km (575 miles) with 9072-kg (20,000-lb) external payload

The Sikorsky CH-53 (Model S-65) heavy-lift helicopter first flew in prototype form on 14 October 1964 and, as the CH-53A Sea Stallion, it became the USMC’s principal heavy-iift helicopter in Vietnam, entering service in 1965. The CH-53D introduced uprated engines and a revised interior for increased troop accommodation. In the air assault role, it carried 55 troops or 3630 kg (8,000 lb) of cargo internally. Four USMC units (all in Hawaii) operate the surviving 45-50 CH-53Ds today. S-65s were exported to Austria (two S-65C-2 or S-650 aircraft, later sold to Israel), West Germany (112 CH-53Gs) and Israel (about 40 S-65C-3s and ex – USMC CH-53As). 30 of 38 surviving Israeli CH-53s are undergoing the Yasur-2000 upgrade, which adds new EW and cockpit systems.

The RH-53D was a US Navy mine sweeping variant, able to tow a mine countermeasures ‘sled’, and introduced uprated engines and an optional IFR probe and sponson tanks. Now withdrawn by the US Navy, two remain operational in Iran.

The first-generation H-53 remains active with the USAF. The service has retired its early HH-53B/53C SAR platforms and CH-53C transports have gone, but the type remains active in the CSAR role. The HH-53H Pave Low til introduced APQ-158 terrain-

The Pave Low t/ is a special-forces dedicated infittration/exfiitration helicopter, which has take over the combat search and rescue rote for the USAF.

The three-engined CH-53E Super Stallion is the US Marines’ primary heavylift helicopter. It can carry 55 equipped troops or 14545 kg (32,000 lb) of cargo

following radar. LLLTV, a FLIR turret, and other improvements, and led to the current MH-53J Pave Low III Enhanced This has uprated engines, TER, FLIR, NVG, RWRs, IR jammers, chaff/flare dispensers, GPS, IFR probe, external tanks, titanium armour and provision for three door/rear ramp – mounted 7.62-mm Miniguns. The fleet are now being upgraded further to Pave Low IV standards, with EFIS cockpits and improved defensive aids. A handful of earlier variants are used for training.

The improved, three-engined CH-53E Super Stallion (S-80) variant flew in prototype form on 1 March 1974, and introduced a seven-bladed main rotor, a lengthened airframe and fuselage sponsons as well as the third engine,. IOC was achieved in 1981 and the type now forms a vital part of USMC amphibious operations. The VIP-configured VH-53E serves with HMX-1. In 2000 Turkey ordered eight S-80E (CH-53E) transports.

The current CH-53E-based MH-53E Sea Dragon features enlarged fuselage sponsons with increased fuel capacity and modernised mine countermeasures systems. A total of 46 was delivered to the US Navy to replace the RH-53D, equipping two squadrons. The JMSDF operates 11 similar S-80M-1S.

Подпись: The External Stores Support System (ESSS) was built into late-model UHdOA/Ls. It can carry fuel and weapons toads of up to 2268 kg (5,000 lb).

Sikorsky’s S-70 design was developed to meet the US Army’s 1972 requirement (or a utility/ tactical transport helicopter to replace the UH-1, offering far better performance, crashworthiness and all round survivability, The YUH-60A prototype first flew on 17 October 1974 and featured a broad, squat cabin for one crew chief/door gunner and 11 troops A production UH-60A Black Hawk first flew in 1978, and the type entered service in June 1979. The cheaper UH-60L (delivered from 1989) has uprated engines and other improvements.

Other US Army models include the EH-60C Quick Fix battlefield jamming system variant, which has two tailboom dipole antennas. A UH-60C com­mand post is under development. The Army has a number of dedicated medevac UH-60Q Dustoff Hawks, and converted MH-60A and MH-60L ‘Velcro Hawks’ with FLIR, extra nav/comms, auxil­iary fuel tanks and Miniguns for special operations support, and rocket-armed AH-60L ‘Direct Action Penetrators’ The definitive, new-production Special Operations MH-60K has TFR, FUR, pintle – mounted 0.50-in machine-guns, ESSS wings for fuel tanks, IFR probe, HIRSS, comprehensive comms/nav equip-ment, and defensive warning receivers and countermeasures. The US Army hopes to procure at least 1,400 UH-60A/L models, and is upgrading many to Enhanced Black Hawk standards. The USMC use nine VH-60IM White Hawks in the VIP transport role

Export models (sometimes designated as S-70As) are in widespread service worldwide, including Argentina, Australia, Bahrain, Brazil, Brunei, Chile, China, Colombia, Egypt, Hong Kong, Israel, Jordan, Malaysia, Mexico, Morocco, the Philippines, Saudi Arabia, Taiwan and Turkey. Licence-production is undertaken in South Korea 1UH-6OP1 and Japan (UH-60J)

The USAF also uses the type for SAR and CSAR. The planned HH-60D/E Night Hawk was cancelled, and instead the USAF pursued a three-phase procurement process, the Phase One UH-60A Credible Hawk has an IFR probe, provision for additional fuel and door guns. The Phase Two MH-60G Pave Hawk added new avionics (radar, GPS, INS, secure comms equipment and full coun­termeasures) and Phase Three added a HUD and FLIR. Sixteen special operations MH-60G support helicopters (with 0.50-in machine-guns) retained the MH – designation prefix, but aircraft with Phase Two avionics and lower calibre door weapons were re-designated as HH-60Gs.

Подпись: Specification: Sikorsky UH-60A Po werplant two 1151 -kW (1,560-hp) General Electric T700-GE-700 turboshafts Dimensions: main rotor diameter 16.36 m (53 ft 8 in): length overall, rotors turning 19 76 m |64 ft 10 in), fuselage 15.26 m 150 (t % in): height overall 5.13 rn|16 ft 10 in) Weights: empty 5118kg(11.284 lb); maximum take-off 9185 kg (20.250 lb); maximum internal payload 1197 kg (2.640 lb) and 3629 kg (8,000 lb] carried externally Performance: maximum level speed 296 kmh [184 mph); maximum vertical rate of climb at 1220 m (4.000 ft) 125 m (411 ft) per minute, service ceiling 5790 m (19,000 ft); range 592 km (368 miles) with standard fuel

Turkey is an important Black Hawk customer with over 100 S-70A (UH-60A) aircraft in service with the army and para-military police units.

Подпись: The evolved CH-60S has a combination of Black Hawk and Seahawk design features, and will provide the US Navy with a new multi-role transport.
Sikorsky’s navalisod S-70B was developed to meet toe U$N’s LAMPS III requirement. This called for a he icopter capable of providing an over – the-horizon search ano strike capability for ASW frigates and destroyers, using radar, MAD, sonobuoys and ESM to detect its targets. A prototype YSH-60B f ew on 12 December 1979, followed by the first production SH-60B Seahawk in 1983. Retaining 83 per cent commonality with the UH-60A, it introduced airframe anti-corrosion treatment, T700-GE-4-01 engines, a folding tailboom. modified undercarriage and HAST (recovery assist secure and traverse) gear. Mission equipment comprises APS-124 ventral search radar, a 25-tube sonobuoy launcher, ASQ-81(V)2 towed MAD, and ALQ-142 ESM. with an armament of two Mk 46 torpedoes It has a hoist for the secondary SAR role. S-7GBs have been exported to Australia (with MEL Super Searcher radar), Japan, Spain, Thailand and Turkey.

The SH-60F Ocean Hawk variant performs the CVW (carrier-based) inner zone ASW mission. Initially deployed in 1991, it lacked radar and RAST but instead had AQS-13F dipping sonar, FLIR and ESM and was armed with three Mk 50 torpedoes Greece received a hybrid version with SH-60B type radar, but with provision for dipping sonar and with

This Royal Australian Navy S-70B-2 wore a special scheme to mark the 50th anniversary of its squadron, the NAS Nowra-based HS 816.

SH-60F ESM. Taiwan bought 21 similar S-70CIMI-1 and S-70C(M)-2 Thunderhawks. The SH-60F – oaseo HH-60H Rescue Hawk is the USIVs strike rescue platform, and entered service in 1989. It has a secondary covert SEAL team infil/exfil roie,

Some 273 of the Navy’s SH-60Bs, SH-60Fs and HH-60Hs are being re-manufactured to a common SH-60R standard, optimised for littoral operations with new passive and active detection and ECM systems, including a new AN/APS-147 ISAR radar, and new sonar equipment. The MAD is deleted, and computer and navigation systems are replaced The prototype flew on 22 December 1999.

The CH-60S is a new-buiid multi-role VERTREP, SAR and CSAR derivative of the Seahawk, intended to replace the HH-60H, CH-46 and HH-3. It combines a UH-60L fuselage with the dynamics system, folding rotors and tailboom and other features of the SH-60B. The aircraft will aiso have a glass cockpit (also being adopted for the SFI-60R) and flew in prototype form on 6 October 1997.

The USCG’s SAR HH-60J Jayhawk replaced the Sikorsky HH-3F in the SAR, patrol and smuggling interdiction roles, and featured a search/weathei radar, a searchlight, an NVG-compatible cockpit and an optional fuel tank.

Saab JAS 39 Gripen


Specification: Sikorsky SH-60B Seahawk Powerplant: two l417-kVV(1,90D*hp) General Electric T700-GE-401C turboshafts Dimensions: main rotor diameter 15.36 iri 153 ft В in); length overall, rotors tuning 19.75 m |64 ft 10 in!, fuselage 15.26 n {50 ft 04 ini; height overall, rotor turning 5,18 m (17 111 Weights: empty 61Э1 kg {13,648 lb) for the ASW mission, maximum take-о" 99?6 kg |71,&84 lb) far the utility mission: maximum payload 3629 kg (8.000 lb)

Performance: dash sceed 234 krnh (145 mph); operational radius 278 km (173 miles) for a one-hour loiter

Armament: AGM-119B Mod 7 Penguin ASM, and pintle-mounted 0.50-in machine-guns


Soviet Union (Russia) Tacticaf strike/attack aircraft


This Russian air force ‘Fitter-К’ represents the most modern version of the Su-17/Su-22 family, which has gained a reputation for rugged dependability.



o improve the payload/range and STOL capability of the Su-7, Sukhoi built an improved derivative with a variable-geometry (‘swing’) wing. The result was the Sukhoi S-22I (Su-7IG Titter-ЁГ) prototype flew on 2 August 1966. The production Su-17M Fitter-C’ introduced the 109.83-kN (24,690-lb) AL-21F-3 engine and a new nav/attack system. A handful of ‘Fitter-Cs’ were built for reconnaissance duties, with provision for multi-sensor reconnais­sance pods as Su-17Rs. All ‘Fitter-Cs’ have been retired from use in Russia, and Poland, and similar export aircraft (designated Su-20) delivered to Afghanistan, Algeria. Angola, Egypt, Iraq, North Korea, Syria and probably Vietnam are all also believed to have been retired.

The Su-17M-2D ‘Fitter-D’ introduced a length­ened, drooping nose and revised avionics. The ranging radar was replaced by a laser ranger and Doppler was added below the nose, A sanitised, less-sophisticated version, the Su-17M-2K ‘Fitter-F’, was built for export to Angola, Libya and Peru. These aircraft were powered"by Tumanskii R-29BS – 300 engines. A handful remain active in Peru, upgraded with new avionics and refuelling probes.

The Su-17UM-2D ‘Fitter-E’ was a two-seat trainer based on the Su-17M-2D airframe, but with no port cannon. Export Su-17UM-2Ks used the R-29BS-300 engines and aircraft were delivered to Afghanistan, Algeria, Angola, Iraq, Libya, Peru, Vietnam and North and South Yemen.

The Su-17M-3 ’Fitter-H’ for Frontal Aviation had a deepened forwaro fuselage, a tall tailfin and a removable ventral fin, like tne trainer, but with two wingroot cannon and a single cockpit. A dedicated AAM launch rail was added beneath each inner wing. It was supplied to Frontal Aviation and Afghanistan only. The similar Su-22M-3K ‘Fitter-J’ (with the Tumanskii R-29BS engine) was exported to Iran, Iraq, Libya, Peru, Syria, Vietnam and both Yemens, and remains in service with most of these operators. The Su-22UM-3K was a trainer based on the tall-tailed Su-17M-3 airframe, produced with Lyuf’ka and Tumanskii engines.

The final production variant, the Su-22M-4 ‘Fitter-K’ introduced new avionics and compatibility with an even wider range of weapons, and was distinguished by a small intake at the base of the tailfin. The type is in limited service with a number of former Soviet states, and in Angola, the Czech and Slovak Republics, and Poland. The Su-22M-4 was also exported to Afghanistan, and the former East Germany.

Подпись:Specification: Sukhoi Su-17M-4 ‘Finer-K’ Powerplant: cne 110.32-kN (24.B0?-!b) NPO Saturn ILyul’ka) AL-21F-3 afterburning turbojet Dimensions: wing span I3.80 m (45 ft 3 in) spread and 10 m (32 ft 10 in); length 18.75 m 161 ft 5» in): height 50 m (16 ft 5 in)

Weights: normal take-off 16400 kg (36,155 lb), maximum take-off 19500 kg |42,989 lb) Performance: maximum level speed 1400 kmb (870 mphj; service ceiling 152D0 m (49,870 ft), combat radius 1150 km (715 miles) on a hi-lo-hi attack mission with a 2000-kg (4,409-lb) wariaad Armament: two wingroot-moonted NR-30 30-mm cannon with 80 rpg; maximum practical ordnance load 1000 kg (2,205 lb) plus drop tanks


Bomber, EW, reconnaissance aircraft


The Su-24MR ‘Fencer-Є’ is a tactical reconnaissance version equipped with a sideways-looking airborne radar, IF line-scan and cameras.



he Su-24 (NATO code-name ‘Fencer’) was intended as an all-weather low-level supersonic □omber able to attack fixed and mobile targets with pinpoint accuracy and with a secondary photo­graphic reconnaissance role. It was developed from the unsuccessful T-6-1 delta-winged VTOL bomber prototype, which had separate cruise and lift engines’ The heavy lift jets were removed to leave space for fuel or weapons and a variable-geometry wing was added to produce the T-6-2IG prototype, which made its maiden flight during May 1970.

The production Su-24 ‘Fencer-A’ was powered by a pair of Perm/Soloviev AL-21F-3 turbofans. The Su-24 ‘Fencer-B’ had an extended-chord tailfin giving a distinctive ‘kinked’ tailfin, and introduced a heat exchanger above the fuselage. Late-model ‘Fencer-Bs’ had a refined rear fuselage {more closely following the jet pipes), and a brake chute fairing below the rudder. The Su-24 ‘Fencer-C’ had trian­gular RWR fairings on the sides of the fin-tip and on the engine intakes,

The improved Su-24M ‘Fencer-D’ attack variant entered service in 1986 and introduced a retractable IFR probe above the nose, an upgraded avionics suite and provision for a UPAZ-A buddy refuelling pod. Its shortened, reshaped redome

The Su-24M ‘Fencer-D’ is the second-generation strike/attack version of the Su-24. It has a new naviattack fit and a laser/TV targeting system.

houses Orion-A forward-looking attack radar and Relief TFR. The Keira 24 laser and TV sighting system gives compatibility with the newest Soviet TV – and laser-guided ASMs.

Soviet Su-24 bombers could carry free-fall TN – 1000 and TN-1200 nuclear bombs, and a variety of conventional free-fall bombs and guided ASMs. ‘Fencer-Bs’, ‘-Cs’ and ‘-Ds’ remain in widespread front-line use witn Russia, and with a number of former Soviet states. Belarus is reported to have sold eight aircraft to UNITA in Angola. Downgraded, non-nuclear capable export Su-24MKs have been delivered to Algeria, Iran, Iraq, Libya and Syria. The 24 Iraqi aircraft That fled to Iran during the 1991 Gulf War, were absorbed by the IIAF.

The Su-24IVIR ‘Fencer-E* tactical reconnaissance aircraft uses internal and podded sensors of various types, and is able to transmit data from some sen­sors to a ground station in real time. The Su-24MP ‘Fencer-F’ is believed to have a primary Elint – gathering role and is similar in appearance to the Su-24MR. It can be distinguished from the earlier aircraft by a prominent undernose fairing below the nose and swept-back intake-mounted ‘hockey stick’ antennas. The Russian air force is now examining a range of Su-24 upgrade options.


Specification: Sukhoi Su-24 Fencer-C’ Powerplant: two 110 32-kN (24,302-lb) NPO Saturn (Lyui’ka) AL-21F-3A turbofans Dimensions: winy span 17.63 m {57 It 10 ini spread and 10.36 m (34 ft) swept length 24.53 m (BO It 5M in) including probe; height 4.97 rr <16 ft З^їп)

Weights: empty equipped 19000 <g j41,887 lb); normal take-off 36DOO kg (79,365 lb|; maximum take-off 39730 kg (87,522 lb)

Performance: maximum levt speed 232C krnh 11,441 mph); service ceiling 1750(1 m (57,415 ft); combat radius 1050 km IS50 miles) on a hi-lo-hi attack mission

Armament: ere GSh-6-23M 23-mm cannon; maximum ordnance 8000 kg (17,637 lb|



The first export customer for the Su-25K was Czechoslovakia. Its Su-25s were later split between the independent Czech and Slovakian air forces.



he Su-25 was developed during the late 1960s, as a jet shturmovik, using the tried and trusted weapons system of the Su-17M-2. A prototype flew on 22 February 1975 with RD-9 engines and a depressing GSh-23 cannon under the nose. Further prototypes introduced the R-95Sh turbojet (a non – afterburning version of the MiG-21 ‘s R-13-300), a twin-barrelled AO-17 30-mm cannon and the upgraded weapons system of the Su-17M3.

The production Su-25 ‘Frogfoot-A’ introduced enlarged engine intakes and increased armour around cockpit and critical components, and was evaluated under combat conditions in Afghanistan led to the addition of bolt-on chaff/flare dispensers, and an exhaust IR suppressor. From 1987 the R-195 engine was introduced, as fitted to all two – seaters, and to 50 Su-25BM dual-role attack/target – towing aircraft. Single-seat Su-25 production ended in 1989, after 330 aircraft had been delivered, including export Su-25Ks ю Angola, Ви garia, Czechoslovakia, Iraq and North Korea, and, according to some reports, Afghanistan. Peru has recently taken delivery of a number of probabiy second-hand Su-25s, while Iran obtained ex-Iraqi aircraft curing the Gulf War.

The Su-25UB ‘Frogfoot-B’ trainer featured a lengthened fuselage with stepped tandem cockpits, and a taller tailfin. Similar Su-25UBKs were provided to export customers. The Su-25UT (later Su-28) had all armament and weapons systems removed
and was intended for the pilot training role with the VVS and DOSAAF. The Su-25UTG was a carrier trainer with strengthened undercarriage and hook.

ne Su-25T and Su-25TM (briefly the Su-34> are extensively modernised Su-25 derivatives – single – seaters based on the Su-25UB airframe, using the rear cockpit to house avionics and fuel. To give true night capaoility, the aircraft have new avionics, sen­sors and systems, including provision for podded radars or LLLTV/FLIR systems. Eight Su-25Ts were reportedly built for Frontal Aviation, plus a handful completed as Su-25TMs. The Russian air forces reportedly have an outstand ng requirement for 24 Su-25TMs to meet regional reinforcement and out-of-area requirements, while Georgia has a requirement for 50 aircraft. The export Su-25TK or Su-39 Strike Shield has also been offered to Abu Dhabi and Bulgaria.

In April 2001 Israel’s Elbit and Georgia’s TAM unveiled the Su-25 Scorpion upgrade, maturing a modernised cockpit with two MFDs, HUD and a new weapons delivery and navigation system.

Подпись: The Su-25 ‘Frogfoot-A’ has remained largely unchanged throughout its front-line career, and proved its combat worth in Afghanistan. Specification: Sukhoi Su-25K Trogfoot-A’ Powerplant: two 44.13-kN |9,921-lbj MNPK ’Soyuz’ ITunianskii] R 195 turbojets Dimensions: wing span 14.30 n (47 f11.4 in); length 15.53 m [50 ft 1VA in); height 4.80 m (15 ft 9 in)

Weights: empty equipped 9500 kg (20,944 lb); maximum take-off 17Б0С kg (33,ВСІ Ibl Performance: maximum level speed ‘clear’ at sea level 975 kmh (BOB mph); service ceiling /GDI] m |22.9Bb ft); combat radius 550 km |34? miles) nn hi-ln-hi attack mission with a 4000 kg (3.818-lb) warload and two drop tanks Armament: one 30-mm A0-17A cannon with 250 rounds; maximum ordnance 440C кц (9,700 lb)


Air superiority fighter, long-range interceptor


The Su-27 shocked Western air forces, because it combined long-range and a heavy warload, with dramatic manoeuvrability.



ukhoi began work on a new long range heavy fighter for Frontal Aviation in 1969. This was to be a highly manoeuvrable aircraft, with long range, heavy armament and modern sensors, capab e of intercepting low-flying or high-level bombers, and of out-fighting the F-15. The requirement was re-drafted to cover two separate but complementary Designs, one heavy and with a long range, and the other a cheaper, lower cost tactical fighter.

Sukhoi was awarded a contract to develop the heavy aircraft, as the T10, The T10-1 ‘Flanker-A’ prototype flew on 20 May 1977, but testing revealed serious problems and the type underwent a total redesign. Four TIQs (TIQ-I to -4) were built in the OKB’s own workshops, and five more (T10-5, -6. -9. -10 and -11) at Komsomolsk. The planned seventh prototype (T10-7) was completed as the T10S-1 ‘Flanker-B’ with a redesigned wing, under­carriage and fuselage, and a spine-mounted airbrake, and flew on 20 April 1981. An early T10S was stripped and lightened and fitted with uprated engines. As the P-42 this aircraft set a series of time-to-height records between 1986 and 1988. The new configuration formed the basis of the production Su-27 ‘Flanker-B’, which entered service in 1985, and was officially ‘accepted’ in 1990.

The ‘Flanker-B’ has an advanced pulse-Doppler radar, backed up oy a sophisticated EQ complex with an IRST system and a laser rangefinder. This allows the Su-27 to detect, track and engage a target without using radar. The Su-27 is also com­patible with a helmet-mounted target designation system. The prototype Su-27UB ‘Flanker-C’ trainer featured a lengthened fuselage with stepped tandem cockpits under a single canopy and increased height/area tailfins and airbrake and flew on 7 March 1985.

About 600 Su-27s have been built, and 567 were estimated to be in service by the end of 1999. About 395 of these were in service with the Russian air forces, serving with Frontal Aviation and The PVO atr defence force. Most of the remainder served in small numbers with former Soviet republics, including Armenia, Azerbaijan, Belarus, Georgia, Ukraine, Uzbekistan. Some of these aircraft have been sold on, to Angola, and Ethiopia. Fifty new-build export Su-27SKs and two-seat Su-27UBKs have been delivered to the People’s Republic of China, where 200 more are to be built under licence by Shenyang as the J-11. The first Chinese-built Su-27 flew in December 1998. Some 12 aircraft have also been delivered to Vietnam.

Подпись: The Su-27 ‘Flanker-B’ can carry up to 10 modern and effective air-to-air missiles, a load that gives it immense combat persistence. Specification: Sukhoi Su-27 ‘Flanker-B1 Powerplant: two 122.58-kN (27,557-lb) NP0 Saturn (Lyul’ka) AL-31F turbafans Diin elisions: wing span 14.70 nn (48 ft 2 ‘A in): length 21.935 m (71 It 11 /fin) Excluding probe; height 5.932 m (19 ft 5)? in)

Weights: empty 17700 <g {39.021 lb}: maximum take-off 30000 kg 165,138 lb) Performance: maximum ‘eveI speed 2500 kmli (1.553 mph); maximum rate of climb at sea level 183ІЮ m (60,039 ft) per minute; service ceiling 18000 m (59,055 ft): combat radius 1500 km (932 miles) with four AAMs Armament: one 30-mm GSh-30-1 cannon in starboard wingroot with 150 rounds: maximum ordnance 6000 kg (13,228 lb) no


Advanced strike fighter


The sectored-thrust Su-ЗОМК! strike/attack aircraft, now under development for the Indian Air Force, is fitted with canards and AL-37FP engines,



he Su-27PU (later Su-30) was designed to fulfil a long-standing requirement for a long-range fighter-interceptor to replace the Tu-128 in defending Russia’s northern frontiers. The basic Su-27’s long range was further Improved through the use of inflight refuelling, (the aircraft being fitted with a retractable AAR prone), long range navigation equipment was provided and systems were tested and proved for long endurance use. The IA-PVO received about five Su-27PUs before production was halted by funding constraints, and the type was marketed to export customers as the Su-30K Sukhoi also designed and built a single-seat Su-27P with the same systems as the Su-27PU, but its single cockpit made it difficult to exploit the aircraft’s long endurance potential operationally, and none were delivered to frontline customers. At least one example was built to become the Su-30KI demonstrator, in anticipation of an Indonesian order. Two more long-endurance were delivered as aerobatic demonstration aircraft, as the Su-27PD

Sukhoi added limited air-to-ground capabilities to the two-seat Su-30 to produce the Su-ЗОМ <M for multi-role) marketing the aircraft to export customers as the SU-30MK Although a succession of aircraft appeared at international airshows in colourful ground attack camouflage colour schemes, festooned with dummy weapons, most of these were standard Su-27UB trainers, and it
took some time for the Su-30MK’s mult’-role avionics to catch up with the marketeers’ promises. Thus, when India took delivery (late) of eight Su-30MKIs in 1997 the aircraft were little more than probe- equipped Su-27UBs, and it will be some time before ground-attack capable aircraft are delivered.

China has ordered 60 of the baseline aircraft as the Su-ЗОМКК, and Chinese ‘Flanker’ production will switch to this version after the 80th Su-27SK. Vietnam has also ordered the type, under the simple designation Su-30K.

India’s full-standard Su-30MKIs are planned to be much more capable aircraft, with canard fore­planes, thrust-vectoring engines and advanced air-to-ground precision weapon capability. Sukhoi is now flying aircraft to this standard, but production deliveries are not yet imminent. Some sources expect this two-seat configuration (sometimes referred to as the Su-35UB or Su-37UB) to replace the vectored-thrust Su-37 single-seater as the Russian air forces’ next-generation ‘Super Flanker’ of choice.

Small numbers of the baseline Su-30 long-range interceptor have entered service with Russian units, such as the 54 ZAP operational training regiment.



Specification: Sukhoi Su-30 Powerplant: two 122.58 kN 127.557 lb) NPO Saturn IlyulTal AL-31F afterburning turbofans Dimensions: wing span 1 4 70 m (48 ft ТА in); length 21.335 n 171 ft 11 JAn) excluding probe: height 6.30 гіібО ft 10k in)

Weights: empty 17700 kg (39,02′ lb): maximum take off 33,500 kg (73,850 lb) Performance: maximum level speec 2500 kmh (1.550 mph). service ceiling 17500 m (57,420 ft) combat radius 1500 km (932 miles) on a hi-hi-hi interception mission with (our AAMs

Armament: опеЗО-mm GSh-30-1 cannon in starboard wingroot with 150 rounds; maximum ordnance 6000 kg (13,228 lb)





Sukhoi has developed several versions of the original two-seat Su-27!В which are all largely identical. These include the Su-32FN and the Su-34.



ith its long range and heavy load-carrying capa­bility the Su-27 offered considerable potential as a tactica strike/attack aircraft, and as a replace­ment for the Su-24.The Su-27IB fighter bomoer began life as a carrier-based trainer aircraft for Su-27K pilots, initially Designated Su-27KU or Su-27KM-2. By the time the prototype was rolled out, the slimmed down carrier programme had removed the need for a dedicated trainer, and the aircraft was redesigned as a fighter-bomber under the new designation Su-27IB. lt first flew on 13 April 1990. The aircraft combined canard toreplanes with a new forward fuselage accommodating a side-by-side two-seat cockpit, with a titanium armoured cockpit, armoured glass, and three large CRT displays. The broad, flat, ‘duck-nose’ led to the Su-27lB’s unofficial ‘Platypus’ nickname, and accommodated a new Leninetz B-004 multi-function radar with з fixed phased array antenna, The intakes were redesigned *or higher low-ievel speeds

The prototype was followed by four aircraft built to the plannee production standard, with twin – wheel main undercarriage bogies, and a raised, thickened tailsting housing a rearward-looking tail warning radar. The first of these productionised Su~27!Bs (designated Su-34s by the OKB) flew on
18 December 1993, l or long range missions the aircraft had a lavatory and a galley, with room for the crew to stand upright or tie prone between the seats, A retractable IFR probe was also provided, together with ejection seats incorporating a ’back massage’ function.

Development of the Su-27IB has been slow, due to funding and technical problems, and the planned in-service date of 1998 slipped by virtually unnoticed. There is still an aspiration for the Su-27IB to replace all Russian air forces’ Su-24s (although not by 2005 as once announced). The programme is progressing slowly, and has not been cancelled. Production Su-27IBs are expected to use more powerful 175-kN (39.240-lb) Saturn AL-41F engines.

The aircraft was marketed as a dedicated maritime attack aircraft under the designation Su-32FIM (using the th’rd pre-production Su-27IB as a demonstrator), and as a multi-role export aircraft as the Su-32MF

The basic side-by-side Su-27IB airframe now forms the basis of the Su-33UB (or Su-27KUB) carrier trainer, an Su-30-2 long range interceptor, and as yet undesignated recce and EW variants. The prototype Su-27KUB trainer made its maiden flight on 29 April 1999.

Подпись: The Sukhoi Su-32FN is a long-range maritime attack aircraft developed from the original Su-27IB. It exists only as a single demonstrator aircraft. Specification: Sukhoi Su-271B Powerplant: Two 130.43-kN (29.320-lb) Lyul’ka AL-31FM (AL-35F) turbcfais Dimensions: wing span ‘4.70 m (48 ft 2У – in); length 23.335 m 176 ft 6’A in) excluding probe; height 6,5 m (71 ft 4 in)

Weights: maximum take-off 451 DO kg 93/28 lb)

Performance: maximum level speed clean’ at 11000 m (36.090 ft) 1.900 kmh (1.180 mph) and at sea level 1,400 kmh 1870 mph]; service ceiling 19800 m 165.000 ft), combat radios 1,113 km (691 miles) on a hi-hi-tn mission Armament: One 30-mm GSb-30-1 cannon, maximum ordnance 8000 kg (17,636 lb)


The key to the Su-37’s performance is its thrust – vecloring AL-37FU engines, that give it a truly unique combat manoeuvring capability



he Su-27M ‘Flanker’ was designed to meet the same Frontal Aviation requirement that spawned the MiG-29M, for a multi-role tactical fighter to rep ace existing first-generatior MiG-29s. Based on the existing Su-27 airframe, the Su-2/М had a higher proportion of carbon fibre composites and aluminium-lithium alloys in its airframe and had minor airframe improvements, including a re­profiled forward fuselage and (on most aircraft) twin nosewheels and taller, square-topped tailfins with integral fuel tanks.

More obviously, the aircraft had canard fore­planes and a new quadruplex digital FBW control system (though the early prototypes retained the original analogue system). Canards were first used on the proof-of-concept T-10-24 (first flown during 1982) and on the navalised. carrierborne Su-27K (later re-designated Su-33). The carrierborne ‘Flanker’ also featured folding wings and tailplanes, strengthened undercarriage and an arrester hook, but retained the original F8W control system and weapons system of the basic Su-27, The new Su-27M, by contrast, had new multi-role avionics, an advanced glass cockpit, new defensive systems and an N011 Zhuk radar. Ths first of six prototypes made its maiden flight on 28 June 1988.

The aircraft was re-designated as the Su-35 by the Design Bureau in the early 1990s. Although the type was once expected to enter service from 1995. Despite marketing it to a number of potential
customers Sukhoi has received no orders for the Su-35. Attention has now largely switched to Su-27 upgrades, and to the thrust-vectoring Su-37

The first Su-37 was the penultimate aircraft of six planned pre-production Su-27Ms, modified before delivery with a pair of thrust-vectoring Saturn/Lyulka AL-31FU engines, and a revised flight control system, with a sidestick controller and new throttle/nozxle control lever. It first flew (with nozzles locked) on 2 April 1996, and was joined by a second aircraft in mid-1998.

The decision was soon taken to abandon the non-thrust vectoring Su-35 and to concentrate on the Su-37, whose planned production version may have used the designation Su-37MR The new variant was to feature further improved avionics, including a new N011M radar with a fixed ohased array antenna. The Su-37MR was expected to enter service with the two-dimensional thrust-vectoring, AL-37FP engine, or the AL-37FU. A three-dimensional thrust-vectoring AL-37PP engine is reportedly under development.

This is one of Sukhoi’s Su-35 demonstrator aircraft, produced in the early 1990s. The Su-35 has since been overtaken by the even more advanced Su-37.



Specification: Sukhoi Su-37

Powerplant two 142.2-kll (31,970-lb) thrust – vectoring SuLurn/Lyulka AL-37FU turbofans Dimensions: wing soan 15.16 m (49 ft 9 in); length 22.185 m (72 ft 97 in) excluding probe; height 6.36 m (20 ft 10K in!

Weights: empty 1200D kg 137,479 lb); maximum take-off 34000 kg (74.957 lb) Performance: maximum level speed cean’ at sea levei 1400 kmh (870 miles); maximum rate of climb at sea level 13800 m (45.27b ft) per minute: service ceiling 18800 nn (61,683 ft): range 3300 km (2.050 miles! on a hi-hi hi intercepbcn mission with four AAMs Armament GSh-30-1 cannon with 150 rounds; maximum ordnance 8.200 kg (18,077 lb)


Bell OH-58D Kiowa (Model 406)


These Kiowa Warriors are operated by the US Army’s 1-7 CA V, based at Ft Hood, where they operate as advance scouts for the 1st Cavalry Division.



n March 1968 Be I s Model 206A JetRanger five – seat light helicopter was ordered into production for The US Army as the OH-58A Kiowa for the light observation role. Deliveries began on 23 May 1969, and over five years a total of 2,200 was procured. Export customers comprised Australia (56 licence built Kalkadoons), Austria (12 OH-58Bs) and Canada (74 C0H-58As).From 1978, 585 OH-S8As were converted to improved OH-58C standard with a flat glass canopy, an uprated engine with infra-red suppression and improved avionics.

In 1981, the Bell Model 406 proposal was selected as the winner of the US Army Helicopter Improvement Program (AHIP) competition. This new version, known as the OH-58D, introduced a mast-mounted sight (housing a TV and IR sensor with a laser designator/rangefinder), a four-bladed main rotor, defensive systems (including an IR jam­mer and laser-warning system) specialised mission avionics and new cockpit displays.

Initial plans to upgrade 592 US Army OH-58As to OH-58D standard have been revised several times and the current total stands at 424. The first OH-68D conversions began in 1983. In 1987, 15 specially – armed OH-58Ds were upgraded for Operation Prime Chance. Based aboard US Navy vessels in the Persian Gulf, they were used on clandestine missions against Iranian fast-patrol boats, that were harassing international oil tanker traffic. The deci­sion was taken to add a permanent weapons fit to
all US OH-58Ds, becoming known as OH-58DII) Kiowa Warriors. All of the US Army’s OH-58Ds are now Kiowa Warrior’s, and feature with integrated weapons pylon, uprated engine and transmission, increased gross weight, RWR, IR jammer, aser warning receiver, integrated avionics and a lighter structure. Typical weapons include Hellfire missiles, 70-mm rockets and 0.50-in gun pods. Beginning in May 1991, 192 new-build Kiowa warriors were delivered to the US Army, and 25 Kiowa Warriors have also been acquired by the Taiwanese army.

All US Kiowa Warriors have been further modified modified to Multi-Purpose Light Helicopter iMPLH) standard, with squatting landing gear and quick-folding rotor blades, fins and tails for rapid redeployment by air

The Model 406CS Combat Scout is a lighter and simplified export derivative of the OH-58D, retaining the main rotor, tail rotor and transmission and a similar powerplant. Fifteen TOW-capable OH-58s were delivered from June 1990 onwards to Saudi Arabia as MH-58Ds.

Подпись: This Kiowa Warrior is armed with a versatile mix of weapons, including an air-to-air Stinger missile (starboard) and a Hellfire anti-tank missile (port). Specification: OH-MD(I) Kiowa Warrior Powerplant: one 435-kW (650-hp) Allison 250-C30R/3IT703-AD-7D0) turboshaft Dimensions: main rotor diameter 10.67 re (35 ft 0 ;n|; length overall, rotors turning 12.58 m (42 ft 72 in) ard fuselage 10.48 m (34 ft 4Kin); height overall 3.93 m (12 ft Ш in)

Weights: empty 1492 kg (3,289 lb); maximum take-off 2495 kg (5,500 lb)

Performance: maximum leve speed 232 kmh (144 mph); hovering ceiling more than 3660 m (12,000 ft) in ground effect and 3415 m (11,200 ft) out of ground effect; range 436 km (308 miles) Armament: 0.50-in gun pods. 70-mm rocket pods, plus provision Tor Stinger AAMs and hellfire anti-armour missiles



assault’s Avion de Combat Experimentale

(ACX), evolved s$ an early 1980s technology demonstrator for a national combat aircraft programme even before France’s withdrawal from the~EFA (Eurofighter) project in August 1985. The Rafale A ACX testbed was first flown on 4 July 1986. It established and proved the basic design, configuration ard performance of the defirr – tive’Rafale, or ACT (Avion de Combat Tactique: as well as Its fly-by-wire cont’ol system and mainly composite structure. Rafale is powered by a pair of SNECMA M88-2 turbofans, with the more powerful M88-3 now under development. Rafale’s RBE2 mum-mode electronically-scanned radar is one of the first phased-array fighter radars to be developed in the west, and will be fully-integrated with the OSF IRST/FLIR sensor package above the nose. Ra’ale will also be fitted with tne Spectra RF/laser/ IR self-protect:on system.

The Armee de I’Air’s generic "Rafale D’ (discret, ‘stealth’) family is four per cent smaller than the prototype Rafale A. and uses ‘low-observable’ (stealthy) elements in its airframe. In addition to these design techniques, Dassault may also have developed a classifieo ‘active stealth’ system to further reduce the aircraft’s radar-cross section.

The Rafale C is the Armee de I’Air’s production – standard single-seat multi-role combat version, and a prototype first flew on 19 May 1991. Rafale M is the Aeronavale’s single-seat carrierborne hghter, modified for carr’er operations w’th an arrester hook, a ‘jumo strut’ nosewheel eg and no forward centreline pylon. The prototype Rafale M flew on 12 December 1991. The Rafale В was originally planned as a straightforward dual-contro trainer, but :s now neinc developed into a fully operational version. The first prototype flew on 30 April 1993.

Rafale’s deve opment and acquisition plans have been very badly hampered by budget restrictions. The first aircraft to enter service wi I be the Aeronavale’s 60 Rafale Ms – the first production – standard example flew on 6 July 1999. Rafale M wili be fully operational in 2002, The two-seat Rafale BM will enter service in 2007. The initial Rafale M-F1 si’ defence a’rcrsft will be reolacec oy the mult-role Rafale IVI-F2 in 2004/05. Deliver’es of the full-standard Rafale M-F3 will begin in 2007, and all 60 Rafale Ms will oe in service by 2012

The Armee de ҐAir Is acquiring a total of 212 Rafales, with the first to be de ivered in 2003. The air force is splitting its Rafales 60:40 between the fully combat-capable Ra’ale В and Rafale C aircraft,

Подпись: The Fiench navy’s Rafale Ms will initially be dedicated to air defence. Here the M01 prototype is seen firing a Mica EM active radar-guided AAM. Specification: Dassault Rafale C Powerplant: two 86.Э8 kM (19,555-le) SNECMA M88-2 turbofans Dimensions: wing span 10 fi m (35 ft 9/ in) with tip-mounted AAMs: ength 15.30 n (5C ft I/. in!: height’ 5.34 m (17 ft 6 A ir) Weights: empty, equipped 9060 kg (19.973 lb); maximum ta<e off 21530 kg (47,399 !b) Performance: maximum level speed ’dean’ 2125 krli {1,321 mph), combat radius 1055 km (655 m les) or an air-to-air miss on with eight Mica ‘Missiles and lour IjuI tanks Armament: one 30-mn GIATCITA 791В cannon in port engine intake trunking; 14 stores stations Icr maximum о: 8C0C kg (17,637 lb) af ordnance