Mirage 2000, Dassault-Breguet


Mirage 2000

The Mirage 2000 reverted to the familiar delta wing shape of the Mirage III, in a new, sophisticated form with slats and small canards. As light air-superiority fighter, it achieved some succes, despite the competition of the F-16 and F-18. The Mirage 2000C is the fighter version; the Mirage 2000N is a two-seat nuclear-armed strike aircraft, and the 2000D a conventional attack aircraft.

Type: Mirage 2000C
Function: fighter
Year: 1983
Crew: 1
Engines: 1 * 95.0kN SNECMA M53-P2
Wing Span: 9.13 m
Length: 14.36 m
Height: 5.20 m
Wing Area: 41 m2
Empty Weight: 7500 kg
Max.Weight: 17000 kg
Speed: Mack 2.35
Ceiling: 17060 m
Range: 3335 km
Armament: 2*g 30 mm 6300 kg payload
Unit cost: 23 million USD


Mirage 2000N

Wing: span 9.29 m ( 30 ft 4.5 in); aspect ratio 2.03 Fuselage and tail: length 14.55 m (47 ft 9 in); height 5.15 rn (16 ft 10.75 in): wheel track 3.40 m (11 ft 1.75 in); wheel base 5.00 m (16 ft 4.75 in) Powerplant: one SNECMA M53-P2 rated at 64.33kN (14,462 lb st) dry and 95.12 kN (21,384 1 b st) with afterburning Weights: empty 7500 kg (16,534 lb): normal take-off 10680 kg,(23,545 lb); maximum take-off 17000 kg (37,478 lb) Fuel and load: internal fuel 3160 kg ; external fuel up to 3720 kg ( 8,201 lb) in one 1300-liter (343-US gal) and two 1700-liter drop tanks; maximum ordnance 16300 kg (13,890 lb) Speed: maximum level s.peed 'clean' at 11000 rn (36,090ft) 2338 km/h (1,262 kt, 1,453 mph); penetration speed at6o m (197 ft) 1112 km/h (600 kt; 691 mph) Range: ferry range 3335 knn J1,800 nm; 2072 miles) with droptanks; combatrange more than 1480 km with four 250 kg bombs, or morethan 1850 km with two drop tanks Performance: maximum rate of climb at sea level 17060 rn (55,971 ft) per minute; service ceiling 18000 m (59,055 ft); climb to 15000m (49,215 ft) 4 minutes; time to intercept a Mach 3 target at 24400 rn (80,050 ft) from brakes off less than 5 minutes; take-off run about 450 rn (1,476 ft) at normal take-off weight g limits: +9 normal and +13.5 ultimate

TYPE:
Multi-role fighter.

PROGRAMME:
Selected as main French Air Force combat aircraft 18 December 1975; first developed as interceptor with SNECMA M53 and Thomson-CSF RDM multi-mode pulse Doppler radar; M53-5 in early production aircraft succeeded by M53-P2; fitted with RDI radar from 38th French Air Force 2000C onwards; first flight of production 2000C 20 November 1982; first flight of production two-seat 2000B, 7 October 1983; first unit, EC 1/2 'Cigognes', formed at Dijon 2 July 1984.

DESIGN FEATURES:
Low-set thin delta wing with cambered section, 58 degrees leading-edge sweep and moderately blended root; area ruled carrying four air-to-air missiles.

STRUCTURE:
Multi-spar metal wing; elevons have carbonfibre skins with AG5 light alloy honeycomb cores; carbonfibre/light alloy honeycomb panel covers avionics bay; most of fin and all rudder skinned with boron/epoxy/carbon; rudder has light alloy honeycomb core.

LANDING GEAR:
Retractable tricycle type by Messier-Bugatti, with twin nosewheels; single wheel on each main unit. Hydraulic retraction, nosewheels rearward, main units inward. Oleo-pneumatic shock absorbers. Electrohydraulic nosewheel steering (+/-45 degrees). Manual disconnect permits nosewheel unit to castor through 360 degrees for ground towing.

POWER PLANT:
One SNECMA M53-P2 turbofan, rated at 64.3 kN (14,462 lb st) dry and 95.1 kN (21,385 lb st) with afterburning or (available 1995) M53-P20 rated at 98.06 kN (22,046 lb st). Movable half-cone centrebody in each air intake. Internal wing fuel tank capacity 1480 litres (391 US gallons; 326 Imp gallons); fuselage tank capacity 2498 litres (660 US gallons; 549 Imp gallons) in single-seat aircraft, 2424 litres (640 US gallons; 533 Imp gallons) in two-seat aircraft. Total internal fuel capacity 3978 litres (1050 US gallons; 875 Imp gallons) in 2000C and E, 3904 litres (1030 US gallons; 859 Imp gallons) in 2000B, N, D and S. Provision for one jettisonable 1300 litre (343 US gallon; 286 Imp gallon) RPL-522 96 kg (212 lb) fuel tank under centre of fuselage, and a 1700 litre (449 US gallon; 374 Imp gallon) RPL-501/502 210 kg (463 lb) drop tank under each wing. Total internal/external fuel capacity 8678 litres (2291 US gallons; 1909 Imp gallons) in 2000C and E, 8604 litres (2271 US gallons; 1892 Imp gallons) in 2000B.

ACCOMMODATION:
Pilot only in 2000C, on Hispano-Suiza licence-built Martin-Baker F10Q zero/zero ejection seat, in air-conditioned and pressurised cockpit. Pilot-initiated automatic ejection in two-seat aircraft; 500 ms delay between departures. Canopy hinged at rear to open upward and, on Mirage 2000D, covered in gold film to reduce radar signature.

AVIONICS:
Thomson-CSF RDM multi-mode radar or Dassault Electronique/Thomson-CSF RDI pulse Doppler radar, each with operating range of 54 nm (100 km; 62 miles). (Mirage 2000N/D have Dassault Electronique/Thomson-CSF Antilope terrain-following radar for automatic flight down to 61 m (200 ft) at speeds not exceeding 600 knots (1112 km/h; 691 mph); Antilope 5 in 2000N includes altitude-contrast updating of navigation system; Antilope 50 in 2000D has full terrain-reference navigation facility.) SAGEM Uliss 52 inertial platform (52E in 2000C and B; 52D for export; and two 52P in 2000N/D, plus integrated GPS in 2000D), Dassault Electronique Type 2084 central digital computer and Digibus digital databus (2084 XR in 2000D), Sextant TMV-980 data display system (VE-130 head-up and VMC-180 head-down) (two head-down in 2000N/D), SFENA 605 autopilot (606 in 2000N, 607 in 2000D, 608 in 2000-5), LMT Deltac Tacan, LMT NRAI-7A IFF transponder, SOCRAT 8900 solid-state VOR/ILS and IO-300-A marker beacon receiver, TRT radio altimeter (AHV-6 in 2000B and C, AHV-9 in export aircraft, two AHV-12 in 2000N and AHV-17 in 2000-5), TRT ERA 7000 V/UHF com transceiver, TRT ERA 7200 UHF or EAS secure voice com, Sextant Avionique Type 90 air data computer, and Thomson-CSF Atlis laser designator and marked target seeker (in pod on forward starboard underfuselage station).

ARMAMENT:
Two 30 mm DEFA 554 guns in 2000C and 2000E (not fitted in B, D, N or S), with 125 rds/gun. Nine attachments for external stores, five under fuselage and two under each wing. Fuselage centreline and inboard wing stations each stressed for 1800 kg (3968 lb) loads; other four fuselage points for 400 kg (882 lb) each, and outboard wing points for 300 kg (661 lb) each. Typical interception weapons comprise two 275 kg (606 lb) Matra Super 530D or (if RDM radar not modified with target illuminator) 250 kg (551 lb) 530F missiles (inboard) and two 90 kg (198 lb) Matra 550 Magic or Magic 2 missiles (outboard) under wings.

DIMENSIONS: EXTERNAL:
Wingspan: 9.13 m (29 ft 11 1/2 in) Wing aspect ratio: 2.03 Length overall: 2000C, E: 14.36 m (47 ft 1 1/4 in) Height overall: 2000C, E: 5.20 m (17 ft 0 3/4 in)

WEIGHTS AND LOADINGS:
Weight empty: 2000C, E: 7500 kg (16,534 lb) Max internal fuel: 2000C: 3160 kg (6967 lb) Max external fuel: 2000B, C, E: 3720 kg (8201 lb) Max external stores load: 6300 kg (13,890 lb) Max T-O weight: 17,000 kg (37,480 lb) Max wing loading: 414.63 kg/m/2 (84.97 lb/sq ft)

LENGTH (m): 14.36 HEIGHT (m): 5.20 WINGSPAN (m): 9.13 MAX T-O WEIGHT (kg): 17,000 MAX WING LOAD (kg/m/2): 414.63 MAX LEVEL SPEED (knots): 688 MAX RANGE (nm): 1000 MAX RATE CLIMB (m/min): 17,060 SERVICE CEILING (m): 16,460

Data from FAS, Jane's All the World's Aircraft, and Aerospace/Defense Companies.


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