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MiG-31B (Type 01B 12): Second
production and service variant with improved Zaslon-A radar, ECM and EW equipment and with
upgraded R-33S missiles. Replaced 01/01DZ in production in late 1990. Avionics upgrade includes
A-723 long-range navigation system, compatible with Loran/Omega and Chaika ground stations.
MiG-31BS (Type 01BS): Designation applied to Type 01/01DZ when converted
to MiG-31B standard.
MiG-31E: Export version of basic Type 01 Prototype ("903")
first noted 1997; simplified systems, no active jammer, downgraded IFF, radar and DASS. Offered to China, India and other
countries.
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MiG-31E Technical Data
| Crew requirements | 2 |
| Engine type | 2 x D30F6 |
| Thrust | 15,500 kg. each |
| Maximum takeoff weight | 46.200 kg. | | Internal fuel | 18,500 l. |
| Fuel quantity in fuel drop tanks | 2 x 2,500 l. |
| Maximum airspeed |
| - at altitude | 3,000 km/h. |
| - at S/L | 1,500 km/h. |
| Maximum operational g-load | 5 |
| Service ceiling | 20,600 m. |
| Interception range at | M=2.35, H=18,000 m., 720 km. |
| Interception range at | M=0.8, H=10,000 m., 1,450 km. |
| Interception range with one inflight refueling at | M=0.8, H=10,000 m., 2,250 km. |
| Takeoff run | 1,200 m. |
| Landing roll | 800 m. |
| Runway length required | 2,500 m. |
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MiG-31F: Projected multirole interceptor and fighter-bomber using a range of TV-,
radar- and laser-guided ASMs. MiG-31F, FE and BM will all have improved air-to-air capability,
with a radar upgrade based on technology developed for Zaslon-M of the MiG-31M. This will give
a detection capability against ultra-high-speed targets (M6+), and much longer range, as well
as better resolution and various new synthetic aperture and real-beam mapping modes for the
variants' new air-to-ground role. New versions will also have compatibility with advanced AAMs,
including R-77 (AA-12 "Adder") and long-range R-37. Revised cockpit layout includes new HUD,
pilot's tactical situation display - MFI-68 152 × 203 mm (6 × 8 in) colour LCD MFD - and three
similar MFDs for the navigator. Some sources also suggest upgraded MiG-31s will incorporate
structural modifications to increase service life.
MiG-31BM: Designation applied
to proposed defence suppression variant based on MiG-31F.
Demonstrator (14306 "58"), shown August 1998 with standard R-33S AAMs under fuselage, R-77,
Kh-58 and Kh-31P underwing. Possible replacement for MiG-25BM in Russian Air Forces service.
Designation now applied to single-role interceptor upgrade with K-37M and K-77M AAMs and new
cockpit displays, to be applied to in-service MiG-31B. Two MiG-31BMs built by Sokol, but were
inactive at MiG's test airfield in late 2000, awaiting funding.
MiG-31FE: Export version of MiG-31BM or MiG-31F.
Alternative designation MiG-31MF.
MiG-31LL: Ejection seat testbed (Red "79") used by LII.
MiG-31M (Type 05): Improved interceptor,
under development since 1984; first prototype ('051')
first flew 21 December 1985; first shown publicly February 1992; upgraded engines, with
modified nozzles; one-piece rounded windscreen; small side windows only for rear cockpit
(though dual controls are fitted); wider and deeper dorsal spine, containing 300 litres
(79.3 US gallons; 66.0 Imp gallons) of additional fuel; more rounded wingtips, with flush
dielectric areas at front and rear; taller fins with larger, curved root extensions; modified
and extended wingroot leading-edge extensions; smaller wing upper-surface fences; all systems
upgraded; digital flight controls; multifunction CRT cockpit displays; new multimode Phazotron
Zaslon-M phased-array radar, with 1.40 m (55 in) diameter antenna, in 3º 30' downward-inclined
nose; detection range of 360 km (224 miles); retractable flight refuelling probe transferred to
starboard side of nose; non-retractable pod with collimated IRST and laser ranger.
No gun; number of fuselage weapon stations increased to six, by addition of two centreline
stations with R-37 AAMs in addition to side-mounted R-37s or older R-33s; four new-type
underwing pylons for R-77 (AA-12 "Adder") active radar-guided AAMs. First prototype, produced
by conversion of MiG-31B "503" lost on 9 August 1991; five or six more prototypes (051 to 057),
at least one (057) with cylindrical wingtip ECM/ECCM jammer pods carrying upper and lower
winglets. Maximum T-O weight 52,000 kg (114,640 lb), with increased-thrust D-30F6M engines to
compensate. Internal fuel 16,350 kg (36,045 lb).
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MiG-31M Technical Data
| Crew | 2 |
| Engine | 2 x Turbofan D-30F6M | | Thrust |
16,500 kg. each |
| Length | 22,69 m. |
| Overall height | 6,15 m. |
| Wing Span | 13,46 m. |
| Wing Area | 61,6 m2. |
| Take-off weight | 52,000 kg. |
| Warload | 9,000 km/h. |
| Maximum airspeed |
| - at altitude 17,500 m. | 3,000 km/h. |
| - cruise | 2,500 km/h. |
| Practical ceiling | 20,600 m. |
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MiG-31D (Type 07): Dedicated anti-satellite models (numbered 071 and 072) were produced and
flight-tested in 1986, with ballast instead of radar in nose, a flat fuselage undersurface
without recesses, large winglets above and below wingtips, and underwing Vympel ASAT missiles.
MiG-31S: Commercial small satellite launch variant, with
Fakel OKB Micron missile capable of delivering a 100 kg (220 lb) payload into a 200 km
(124 mile) orbit or a 70 kg (154 lb) payload into a 500 km (311 mile) orbit. The type could
also launch the Aerospace Rally System rocket-powered suborbital glider, for astronaut training upper atmosphere
research or space tourism.
MiG-31EH: Export version for Cannounced at Zhuhai Air Show 6 November 2000.
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