TITLE:

SUKHOI Su-17

SUKHOI Su-20

SUKHOI Su-22

NATO reporting names: 'Fitter-C, -D, -E, -F, -G, -H, -J and -K'

TYPE:

Single-seat variable geometry ground attack fighter, reconnaissance aircraft and two-seat combat trainer.

PROGRAMME:

Prototype S-22I or Su-7IG (Izmenyaemaya Geometriya; variable geometry) was minimal conversion of fixed-wing Su-7 (NATO `Fitter-A'); only 4.2 m (13 ft 9 in) of each wing pivoted, outboard of large fence and deepened inboard glove panel; first flew 2 August 1966; shown at Aviation Day display July 1967; given NATO reporting name `Fitter-B'; two squadrons of Su-17 `improved Fitter-Bs' in Soviet air forces 1972; AL-21F-3 engine then replaced AL-7 in major Soviet air force production versions, beginning with `Fitter-C'. Production ended 1991.

VARIANTS:

Su-17M (S-32M, `Fitter-C'): Single-seat attack aircraft; AL-21F-3 engine; eight stores pylons; additional wing fence on each glove panel; curved dorsal fin; operational with CIS air forces and Naval Aviation since 1971 in relatively small numbers. Detailed description applies to basic Su-17, except where indicated otherwise.

Su-17R: Reconnaissance version of Su-17M.

Su-17M2/M2D (S-32M2, `Fitter-D'): Generally as Su-17M, but forward fuselage lengthened by 0.38 m (15 in) and drooped 3° to improve pilot's view while keeping intake face vertical; added undernose Doppler navigation radar pod; Klen laser rangefinder in intake centrebody.

Su-17UM3 (`Fitter-G'): Two-seat trainer version of Su-17M-3 with combat capability; drooped forward fuselage and deepened spine like Su-17UM-2D; taller vertical tail surfaces; removable ventral fin; starboard wingroot gun only; laser rangefinder in intake centrebody.

Su-17M3 (S-52, `Fitter-H'): Improved single-seater; same deepened spine and tail modifications as Su-17UM-3; Doppler navigation radar internally in deepened undersurface of nose; gun in each wingroot; launcher for R-60 (AA-8 `Aphid') air-to-air missile between each pair of underwing pylons; approximately 165 `Fitter-H/Ks' equipped for tactical reconnaissance carry, typically, centreline sensor pod, active ECM pod under port wing glove, two underwing fuel tanks.

Su-17M4 (S-54, `Fitter-K'): Single-seat version, identified 1984; cooling air intake at front of dorsal fin; otherwise as Su-17M-3. Maximum weapon load 4,250 kg (9,370 lb), including nuclear weapons, bombs, rocket pods, S-25 tube-launched rockets with 325 mm head, 23 mm SPPU-22 gun pods, two R-3 or R-13M (AA-2 `Atoll'), R-60 (AA-8 `Aphid') or R-73A (AA-11 `Archer') air-to-air missiles, Kh-23 (AS-7 `Kerry') or Kh-25ML (AS-10 `Karen') air-to-surface missiles, or a reconnaissance pod. When four SPPU-22 gun pods are fitted, with downward attack capability, the two underfuselage pods can be arranged to fire rearward. Chaff/flare and decoy dispensers standard.

Su-20 (S-32MK, `Fitter-C'): Export version of Su-17M.

Su-20R: Reconnaissance version of Su-20.

All Su-17s and Su-20s have AL-21F-3 engines; some Su-22 export aircraft have Tumansky R-29BS-300 (112.8 kN; 25,350 lb st with afterburning) in more bulged rear fuselage, with rearranged small external air intakes on rear fuselage and shorter plain metal shroud terminating fuselage, as follows:

Su-22U (`Fitter-E'): Tandem two-seat trainer developed from Su-17M2, with Tumansky engine; no Doppler pod; deepened dorsal spine fairing for additional fuel tankage; port wingroot gun deleted.

Su-22 (`Fitter-F'): Export Su-17M2; modified undernose electronics pod, R-29 engine; gun in each wingroot; weapons include R-3 (AA-2 `Atoll') air-to-air missiles; aircraft supplied to Peru had Sirena-2 limited coverage radar warning system and virtually no navigation aids; some basic US supplied avionics retrofitted.

Su-22UM3K (`Fitter-G'): Export Su-17UM3; AL-21F-3 or R-29B engine.

Su-22M3 (`Fitter-J'): As Su-17M3 but R-29 engine; internal fuel tankage 6,270 litres (1,656 US gallons; 1,379 Imp gallons); more angular dorsal fin; AA-2 (`Atoll') air-to-air missiles.

Su-22M4 (`Fitter-K'): As Su-17M4; AL-21F-3 engine.

Su-22M5: Franco-Russian upgrade proposal. See following entry.

MODERNISATION:

Sukhoi: Su-22 (`Fitter-F'). See Versions.

Sukhoi/Sextant Avionique Su-22M5. See following entry.

OPERATORS:

Versions of the Su-17/20/22 are in service with the armed forces of the following countries: Afghanistan (50), Algeria (32), Angola (15), Bulgaria (21), Czech Republic (41), Hungary (12), Iraq, Libya (90), Peru (35), Poland (90), Russia, Slovakia (20), Syria (60), Ukraine (40), Vietnam (40) and Yemen (50).

DESCRIPTION:

Description applies to basic Su-17, except where indicated.

DESIGN FEATURES:

Modest amount of variable geometry added to original fixed-wing Su-7 permitted doubled external load from strips little more than half as long, and 30 per cent greater combat radius; progressive refinements led to very effective final versions. Conventional mid-wing all-swept monoplane, except for variable geometry outer wings with manually selected positions of 28°, 45°, 63°; wide span fixed centre-section glove panels; basically circular fuselage with dorsal spine; ram intake with variable shock-cone centrebody; pitot on port side of nose, transducer to provide pitch and yaw data for fire control computer starboard; anti-flutter bodies near tailplane tips.

FLYING CONTROLS:

Slotted ailerons operable at all times; slotted trailing-edge flap on each variable geometry wing panel operable only when wings spread; area-increasing flap on each centre-section glove panel; full-span leading-edge slats on variable geometry wing panels; top and bottom door type airbrakes each side of rear fuselage, forward of tailplane; all-moving horizontal tail surfaces; conventional rudder; no tabs.

STRUCTURE:

All-metal; semi-monocoque fuselage; large main wing fence on each side, at junction of fixed and movable panels, square-cut at front, with attachment for external store; shorter fence above glove panel each side.

LANDING GEAR:

Retractable tricycle type, with single wheel on each unit. Nosewheel retracts forward, requiring blistered door to enclose it. Main units retract inward into centre-section. Container for single cruciform brake-chute between base of rudder and tailpipe.

POWER PLANT:

One Saturn/Lyulka AL-21F-3 turbojet, rated at 76.5 kN (17,200 lb st) dry and 110 kN (24,700 lb st) with afterburning. Fuel capacity increased to 4,550 litres (1,202 US gallons; 1,000 Imp gallons) by added tankage in dorsal spine fairing. Provision for carrying up to four 800 litre (211 US gallon; 176 Imp gallon) drop tanks on outboard wing pylons and under fuselage. When underfuselage tanks are carried only the two inboard wing pylons may be used for ordnance, to a total weight of 1,000 kg (2,204 lb). Two solid propellant rocket units can be attached to rear fuselage to shorten T-O run.

ACCOMMODATION:

Pilot only, on ejection seat, under rearward hinged transparent canopy. Rearview mirror above canopy.

AVIONICS:

SRD-5M (NATO `High Fix') I-band ranging radar in intake centrebody; ASP-5ND fire control system; HUD standard; Sirena-3 radar warning system providing 360° coverage, with antennae in slim cylindrical housing above brake-chute container and in each centre-section leading-edge, between fences; SRO-2M IFF; SOD-57M ATC/SIF, with transponder housing beneath brake-chute container; SP-50 ILS, RSB-70 HF and RSIU-5/R-831 UHF/VHF.

ARMAMENT:

Two 30 mm NR-30 guns, each with 80 rounds, in wingroot leading-edges. Total of nine weapon pylons (one on centreline, two tandem pairs under fuselage, one under each centre-section leading-edge, one under each main wing fence) for more than 3,175 kg (7,000 lb) of bombs, including nuclear weapons, rocket pods, 23 mm gun pods and guided missiles such as the air-to-surface AS-7 (NATO `Kerry'), AS-9 (`Kyle') and AS-10 (`Karen').

LENGTH (m) : 18.75

HEIGHT (m) : 5.00

WING SPAN (m) : 13.80

MAX T-O WEIGHT (kg) : 19500

MAX WING LOAD (kg/m{2}) : 487.50

MAX LEVEL SPEED (knots) : 1379

MAX RANGE (nm) : 1240

SERVICE CEILING (m) : 15200

T-O RUN (m) : 900

LANDING RUN (m) : 950