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Mikoyan Project 1.44

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Mikoyan Project 1.44/1.42
Company typeTechnology demonstrator project
IndustryAerospace, Defense
Founded1983
FounderMikoyan design bureau
Defunct2000
FateCancelled; superseded by PAK FA program
SuccessorSukhoi Su-57 (via PAK FA program)
Headquarters
Moscow (assumed, as Mikoyan is based there)
,
Russia (formerly Soviet Union)
Area served
Military aviation
Key people
Gheogiy A. Sedov (Chief Project Engineer), Anatoliy Belosvet (Deputy General Designer), Vladimir Gorboonov (Test Pilot)
ProductsMultirole fighter technology demonstrator aircraft
OwnerMikoyan design bureau / Russian government
ParentMikoyan design bureau


The Mikoyan Project 1.44/1.42[N 1] (Russian: Микоян МиГ-1.44; NATO reporting name: Flatpack)[1] represents a multirole fighter technology demonstrator engineered by the Mikoyan design bureau. The designation 1.42 corresponds to the intended production model, whereas 1.44 identifies the technology demonstrator itself. This aircraft was developed under the Soviet Union’s MFI (Mnogofunksionalni Frontovoy Istrebitel, meaning "Multifunctional Frontline Fighter") initiative, part of the I-90 ("1990s fighter") program conceived as a response to the U.S.'s Advanced Tactical Fighter (ATF) project. The MFI aimed to integrate numerous fifth-generation jet fighter characteristics, including supermaneuverability, supercruise capability, sophisticated avionics, and some level of radar signature reduction through stealth technology.

The development process experienced significant delays and setbacks, largely due to chronic funding shortages following the Dissolution of the Soviet Union. Consequently, the MiG 1.44 completed its first flight in February 2000—approximately nine years later than initially planned—and was subsequently cancelled within the same year. The MFI initiative was ultimately superseded by the more cost-effective and modern PAK FA program, which culminated in the creation of the Sukhoi Su-57.

Development

Main article: Post-PFI Soviet/Russian aircraft projects

Initial design phase

File:Mig 1.44 (2).png
Conceptual illustration of MiG 1.44 in flight

The origins of the MiG 1.44 trace back to the early 1980s when the U.S. Air Force embarked on developing a successor to the F-15 Eagle through its Advanced Tactical Fighter (ATF) program, which eventually produced the highly maneuverable and stealth-capable yet expensive F-22 Raptor, first flown in 1997. In reaction, the Soviet government commissioned its fighter design bureaus to create a countermeasure capable of replacing the Sukhoi Su-27. The project received formal approval in 1983 under the name I-90 (Russian: И-90, an abbreviation for short for: Истребитель 1990-х годов, lit. '"Fighter of the 1990s"'). At this stage, criteria for next-generation fighters were not universally established; while U.S. efforts concentrated on an air superiority platform emphasizing stealth and kinematic performance, Soviet priorities leaned toward "multifunctionality"—a multirole fighter with strong air-to-ground capabilities combined with advanced maneuverability at high angles of attack and extended supersonic endurance.[2][3][4][5] Mikoyan simultaneously pursued two projects: a heavy multirole fighter designated MFI and a lightweight tactical fighter named LFI (Lyogkiy Frontovoy Istrebitel, "Light Frontline Fighter"). To reduce expenses, both designs were planned to share numerous components.[6]

As research and development advanced, escalating costs—typical for sophisticated aircraft programs—prompted the Soviet government to establish in 1983 the Combined Task Programme aimed at enhancing efficiency and fostering technologies applicable across various aircraft types.[6] Mikoyan was appointed lead contractor for this initiative, underscored by its integration into a Soviet five-year economic plan. Subsequently, initial requirements for these fighters were drafted.[6]

Mikoyan moved forward with preliminary designs for both MFI and LFI projects with support from multiple institutions that contributed to refining specifications. The Central Aero- and Hydrodynamic Institute (TsAGI) conducted wind tunnel testing integral to this phase and recommended incorporating canard surfaces into the MFI design due to their benefits in agility and lift—particularly crucial given that the MFI was designed with relaxed static stability.[6] The delta wing featured a leading-edge sweep between 40° and 45°.[6] During this period, aerodynamic assessments and radar cross-section evaluations were carried out via wind tunnel experiments.[6]

The MFI’s design included a variable engine intake ramp beneath the forward fuselage—similar in concept to that found on the Eurofighter Typhoon—to maintain consistent airflow during abrupt maneuvers.[6] Engine research also explored thrust vectoring technology intended to significantly enhance maneuverability as well as short takeoff and landing (STOL) capabilities.[7] Beyond mechanical and aerodynamic considerations, extensive efforts addressed numerous other factors to optimize layout and performance parameters.[7] In 1987, Mikoyan submitted proposals for both MFI and LFI designs for official evaluation.[7]

The production variant designated as 1.42 was planned to incorporate an internal weapons bay aimed at reducing radar visibility; however, this feature was omitted from the technology demonstrator version 1.44.[8]

Full-scale development

File:Mig 1-44-2.png
An artist's impression of the MiG 1.44 technology demonstrator

Although both the MFI and LFI concepts successfully passed critical evaluations, Mikoyan decided to suspend the LFI project due to financial limitations, reallocating resources toward the MFI, which had been renamed Izdeliye (product) 1.42.[7] Under Chief Project Engineer Gheogiy A. Sedov’s guidance and coordination, Mikoyan initiated an extensive design phase. With the LFI discontinued, the 1.42 adopted a multi-role mission profile, tasked with excelling in both air-to-air and air-to-ground operations.[9] The Central Aerohydrodynamic Institute (TsAGI) remained involved by testing radio-controlled scale models to study stability and handling qualities, especially at elevated angles of attack. Subsequent findings confirmed that the 1.42 maintained controllability at angles reaching 60°.[9]

By this stage, specifications were becoming more concrete. Engineers from multiple institutions had agreed on a finalized design after refining flight-control algorithms, validating wind tunnel data, and assessing critical systems through test rigs and modified aircraft.[10] In 1988, Mikoyan received a formal operational requirement for the 1.42. Three years afterward, the design cleared the Soviet Air Force's rigorous review process. This approval enabled construction of a flyable technology demonstrator, prompting Mikoyan to issue detailed specifications to specialized manufacturing plants.[11]

The demonstrator, designated 1.44, aimed to validate the aerodynamic configuration and flight control system. Construction was midway through when the Soviet Union's collapse caused funding to be withdrawn. Consequently, the planned maiden flight of the nearly completed aircraft was indefinitely deferred.[11] Despite this setback, full-scale mock-ups and structural components of the 1.44 were fabricated for static testing while factories prepared for prototype assembly.[11] Mikoyan petitioned authorities to declassify the project to permit public exhibition at air shows. In June 1995, Deputy General Designer Anatoliy Belosvet announced intentions to showcase the prototype at that year’s MAKS Airshow, but government approval was denied.[12] Another attempt in 1997 also failed.[13]

Testing and cancellation

In early 1994, the incomplete aircraft was relocated to Zhukovsky Airfield for flight testing preparations. Ground trials commenced later that year and culminated in high-speed taxi runs piloted by Mikoyan’s Chief Test Pilot Roman Taskayev.[11] As testing intensified, progress was halted due to insufficient funds preventing procurement of remaining components necessary to complete the demonstrator.[11] This funding shortfall was the primary cause behind the program's indefinite suspension over subsequent years. In 1997, production was officially cancelled by the Russian government citing excessive per-unit costs.[14] Financial instability within Mikoyan led to management changes before 2000, which opened access to alternative funding sources.[15] A potential deal with the Indian Air Force collapsed after Mikoyan demanded a prohibitive royalty fee of USD 5 billion for local production rights.[16]

The company’s leadership overhaul also brought significant developments. The Russian government acknowledged the existence of the project publicly in late 1998. On December 24 that year, Nezavisimaya Gazeta featured a brief article about the fighter accompanied by several photographs.[17] Throughout 1999 final preparations for flight were conducted as assembly was completed. Ground tests included high-speed taxi trials during which the aircraft performed rotations.[18][19] The official rollout occurred on January 12, 1999 in front of senior Russian military officials, government representatives, international media, and other dignitaries.[20][21] Prior to this event, details about the 1.44 had remained largely classified; however, Aviation Week & Space Technology published a photo taken from atop the hangar housing the demonstrator just one day earlier.[22]

On February 29, 2000, Vladimir Gorboonov piloted its inaugural flight lasting approximately eighteen minutes. During this sortie, it achieved an altitude near 1,000 m (3,300 ft) and speeds up to 600 km/h (370 mph) before safely landing at 11:43 am Moscow Time under tight security measures. Gorboonov later characterized the aircraft as responsive and manageable.[5][19][23] After a twenty-two minute second flight on April 27, no further flights were reported—likely indicating technical issues discovered by engineers.[19] The program was subsequently terminated; its sole prototype is preserved at Gromov Flight Research Institute where it underwent restoration and was exhibited at MAKS in 2015.

Following cancellation of the MFI initiative, development shifted toward the PAK FA (Perspektivnyi Aviatsionnyi Kompleks Frontovoi Aviatsyi – Prospective Air Complex for Tactical Air Forces) program aimed at creating an advanced air superiority fighter as a successor to Projects 1.42/1.44. In 2001 India entered into an agreement with Russia to jointly develop and produce this platform. Both Mikoyan and Sukhoi presented proposals based on their respective designs for PAK FA; MiG submitted an updated iteration derived from their MFI concept. Ultimately, Russia’s Defense Ministry selected Sukhoi as lead contractor for PAK FA development resulting in what became known as the Su-57.[24]

Design

Note: Due to the MiG 1.44 not undergoing extensive flight testing, many anticipated performance characteristics remain unverified. Consequently, this section discusses the design under the designation MiG MFI.

The MiG MFI was a fifth-generation air superiority and strike fighter featuring a delta wing and twin vertical stabilizers, integrating cutting-edge technologies intended to provide superior stealth and combat capabilities. Its design incorporated a close-coupled canard configuration which, combined with thrust vectoring engine nozzles, delivered exceptional agility. The aircraft employed a tricycle landing gear arrangement, consisting of a single dual-wheel nose gear and two single-wheel main gears at the rear. Featuring relaxed stability, the MFI was managed through a fly-by-wire flight control system. Mikoyan utilized lightweight materials extensively in its construction: aluminum-lithium alloys accounted for 35% of the empty weight, steel and titanium alloys made up 30%, composites comprised another 30%, with remaining materials constituting 5%.

The layout of the MiG MFI was unconventional, aiming to enhance aerodynamic efficiency and reduce radar detectability. The wings adopted a delta shape with a leading-edge sweep angle of 52°, while dielectric fairings at the wing tips housed electronic countermeasure and support equipment. Full-span leading-edge flaps were incorporated on the wings. The canards featured a sharper 58° leading-edge sweep and included pronounced dogtooth notches that improved airflow over the wings during high angles of attack. According to Russian aviation specialists, the aircraft’s unusual configuration, use of radar-absorbent materials (RAM), and internally stowed weaponry contributed to a radar cross-section (RCS) below 0.3 square meters—comparable to Russian assessments of the F-22 Raptor’s stealth profile. When equipped with a plasma shield, this RCS could be further reduced to approximately 0.001 square meters.

Powered by two Lyul'ka Saturn AL-41F afterburning turbofan engines generating 177 kN of thrust each, the MFI could reach speeds up to Mach 2.35. These variable-cycle engines enhanced dry supersonic thrust and enabled sustained supercruise at Mach 1.5. The axisymmetric nozzles were capable of thrust vectoring in both pitch and yaw axes. To minimize infrared signature, ceramic tiles lined the inner petals of the nozzles. Engine air intakes were fed through double ramps with splitter plates beneath the forward fuselage, connected via serpentine ducts coated in RAM to reduce radar visibility. Additionally, external hardpoints under the wings could carry weapons or fuel drop tanks.

The cockpit was equipped with advanced glass displays and integrated a Pulse-Doppler radar system—designated N014—with an operational range of approximately 420 kilometers and capable of detecting targets from as close as one meter up to 250 kilometers away. This radar could simultaneously track up to 40 targets and engage 20 concurrently, featuring a passive electronically scanned array antenna linked to an advanced fire-control system. Technologies developed for the MiG 1.42/1.44 program are believed to have influenced the smaller Mikoyan LMFS fifth-generation light fighter initiative.

Several Russian defense analysts suggest that China’s Chengdu J-20 stealth fighter drew significant design inspiration from the MiG 1.44, pointing to similarities in its canard arrangement, tail structure, and overall “duck-like” aerodynamic form.

Variants

  • MiG 1.42: The main production model intended to surpass the performance of the 1.44 variant. NATO designated this version as "Foxglove".
  • MiG 1.44: A prototype demonstrator featuring unsuccessful upgrade attempts; only one unit was constructed. NATO referred to it as "Flatpack".
  • MiG 1.42R: A conceptual reconnaissance model equipped with surveillance systems housed within the weapons bay.
  • MiG 1.42K: A proposed carrier-based version incorporating folding wings, an arrestor hook, reinforced landing gear, and improved corrosion resistance.
  • MiG 1.42 trainer: A suggested two-seat trainer configuration designed for pilot instruction.

Specifications (Project 1.42/44)

File:Mig-144.png
Three-dimensional representation
File:MiG-1.44-crossection.png
Four-view schematic

Note: Since neither the 1.44 nor the 1.42 advanced beyond the pre-production phase, most specifications remain approximate.

Template:Aircraft specs

Gallery

Russian Air Force, 144, MiG-1.44 Flatpack (49580576543) MiG-1.44 front view MAKS 2015 exhibition image

See also

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References

Notes
  1. ↑ Also referred to as "Object/Article 1.44/1.42". The fighter is additionally known by the designation "MiG-MFI". Although the MFI was once informally called the "MiG-35", this label is currently assigned by Mikoyan to an advanced variant of the Mikoyan MiG-29.
Citations
  1. ↑ Lua error in Module:Citation/CS1/Configuration at line 2123: attempt to index field '?' (a nil value).
  2. ↑ Gordon 2021, p. 7
  3. ↑ Gordon 2001, pp. 6, 12.
  4. ↑ Barrie 1996, p. 24.
  5. ↑ 5.0 5.1 Lua error in Module:Citation/CS1/Configuration at line 2123: attempt to index field '?' (a nil value).
  6. ↑ 6.0 6.1 6.2 6.3 6.4 6.5 6.6 Gordon 2001, p. 12.
  7. ↑ 7.0 7.1 7.2 7.3 Gordon 2001, p. 13.
  8. ↑ Gordon, Yefim and Komissarov. Sukhoi Su-57: Famous Russian Aircraft. Crécy Publishing Ltd, 2021.ISBN 1-9108-0993-4.
  9. ↑ 9.0 9.1 Gordon 2001, pp. 13–14.
  10. ↑ Gordon 2001, pp. 15–22.
  11. ↑ 11.0 11.1 11.2 11.3 11.4 Gordon 2001, p. 22.
  12. ↑ Barrie 1995, p. 4.
  13. ↑ Gordon 2001, p. 23.
  14. ↑ Lua error in Module:Citation/CS1/Configuration at line 2123: attempt to index field '?' (a nil value).
  15. ↑ Gordon 2001, p. 27.
  16. ↑ Lua error in Module:Citation/CS1/Configuration at line 2123: attempt to index field '?' (a nil value).
  17. ↑ Gordon 2001, p. 29.
  18. ↑ Velovich 2000, p. 32.
  19. ↑ 19.0 19.1 19.2 Gordon 2001, p. 37.
  20. ↑ Flight International 1999, p. 9.
  21. ↑ Gordon 2001, pp. 29–30.
  22. ↑ Gordon 2001, p. 30.
  23. ↑ Flight International 2000, p. 20.
  24. ↑ Butowski (2021), pp. 22-25
Bibliography
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  • Lua error in Module:Citation/CS1/Configuration at line 2123: attempt to index field '?' (a nil value).
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External links

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