Mikoyan Project 1.44

https://en.wikipedia.org/wiki/Mikoyan_Project_1.44

The Mikoyan Project 1.44/1.42 (NATO reporting name: Flatpack) was a technology
demonstrator developed by the Mikoyan design bureau. It was the Soviet Union's
answer to the U.S.'s Advanced Tactical Fighter (ATF), incorporating many
fifth-generation jet fighter aspects such as advanced avionics, stealth
technology, supermaneuverability, and supercruise. The design's development was
a protracted one, characterised by repeated and lengthy postponements due to a
chronic lack of funds; the MiG 1.44 made its maiden flight in February 2000,
nine years behind schedule, and was cancelled later that year.

Preliminary design

The MiG 1.44 had its origins in the early 1980s, when the U.S. Air Force began
developing a fighter under the Advanced Tactical Fighter (ATF) project, which
would result in the supermanueverable and stealthy, albeit costly, Lockheed
Martin F-22 Raptor. Consequently, the Soviet government tasked its fighter
design bureaux the job of developing a fighter with which to counter the
American threat, and replace the Sukhoi Su-27. Mikoyan occupied itself with two
concurrent projects, one of which focused on a heavy multi-role design
designated MFI (Mnogofunksionalni Frontovoy Istrebitel, "Multifunctional
Frontline Fighter"), the other a light tactical fighter named LFI (Lyogkiy
Frontovoy Istrebitel, "Light Frontline Fighter"). To minimise costs, both
designs were to share as many components as possible.

However, as the research and development phase for the two projects progressed,
costs escalated due to the complexity normally associated with advanced aircraft
projects. As a result, the Soviet government created the Combined Task Programme
in 1983 with the aim of maximising efficiency and developing technologies to be
used for all classes of aircraft. Mikoyan became the primary contractor for the
programme, the importance of which was illustrated with its inclusion into the
Soviet five-year economic plan. The design bureau soon formulated initial
specifications for the new fighters.

Mikoyan proceeded with the preliminary design of both the MFI and LFI with
participation from numerous institutions, which assisted in the progressive
definition of the designs. TsAGI (Tsentralniy Aerogidrodinamicheskiy Institut,
"Central Aero- and Hydrodynamic Institute") was responsible for collecting wind
tunnel test results, which, along with theoretical studies, were vital during
this phase of development. The institution recommended that Mikoyan include
canards for the MFI, since it offers great agility and lift, the latter
important as the MFI was a statically unstable design. The delta wings then had
a wing leading edge sweep of 40–45°. During this period, engineers undertook
unprecedented wind tunnel testing to refine the MFI's aerodynamics and verify
its radar cross-section (RCS).

The MFI would have a variable engine intake ramp located under the front
fuselage, reminiscent of the Eurofighter Typhoon; this was particularly
important with the nature of the aircraft, since it allows for sustained air
flow into the engine during sudden manoeuvres. As for the engine themselves,
research was conducted on thrust vectoring, allowing for markedly improved
manoeuvrability and short take-off and landing performance. Besides the
mechanical and aerodynamic aspects of the design, engineers investigated
hundreds of issues to refine the layout and specifications. In 1987, Mikoyan and
the associated institutions submitted the MFI and LFI proposals for review.

Design

The MiG MFI was a delta wing, twin-tailed, fifth-generation air
superiority/strike fighter design that incorporated advanced technology to
theoretically give the aircraft excellent stealth and fighting attributes. It
featured a close-coupled canard layout which, when working with the vectorable
engines, gave the aircraft remarkable maneuverability. The aircraft had a
tricycle landing gear system, with a single, dual-wheel landing gear in the
front, and two single wheels in the rear. The MFI had relaxed stability and was
controlled by a fly-by-wire flight control system. Mikoyan made use of
weight-saving materials in the construction of the aircraft, with
aluminium-lithium alloys making up 35% of the empty weight, steel and titanium
alloys (30%), composites (30%) and others (5%).

The MiG MFI was unconventional in its layout, in an effort to improve in-flight
efficiency and stealth characteristics. Efforts were made to minimise
surface-area, possibly to reduce drag. The wings were of delta planform, with
leading-edge sweep at 52°. At the tips were dielectric fairings which housed
electronic countermeasures/electronic support measures. The wings had full-span
leading-edge flaps. The canards, meanwhile, had a leading-edge sweep of 58°, and
had prominent dogtooth which improved airflow over the wings at high alpha
(angles of attack). Russian aviation experts claim that the unorthodox design,
use of radar-absorbent materials (RAM), and internally mounted weapons, gave an
radar cross-section (RCS) of less than 0.3 m2 (3.2 sq ft), comparable to that of
the F-22 Raptor. The RCS falls to 0.001 m2 (0.011 sq ft) with the use of a
plasma shield.

The fighter is equipped with a glass cockpit and features a Pulse-Doppler radar.
The N014 radar, with a range of 420 km (260 mi) and target detection from 250 km
(160 mi) to one metre (3.3 ft), was able to track up to 40 targets and shoot
against 20. The radar system has a passive electronically scanned array antenna
and is linked to a fire-control system. The 1.42/1.44 fighter is believed to
have evolved into the Mikoyan LMFS fifth-generation light fighter project.

Some Russian military analysts believe that the Chinese fifth generation J-20
drew heavy inspiration from or was fundamentally based on the MiG 1.44, citing
similarities in its canards, tail section, and "duck like" aerodynamic design.

Specifications (Project 1.42/44)

General characteristics
Crew: 1
Length: 19 m (62 ft 4 in)
Wingspan: 15 m (49 ft 3 in)
Height: 4.5 m (14 ft 9 in)
Empty weight: 18,000 kg (39,683 lb)
Gross weight: 28,000 kg (61,729 lb)
Max takeoff weight: 35,000 kg (77,162 lb)
Powerplant: 2 × Lyulka AL-41F afterburning turbofan engines, 176 kN (40,000 lbf)
with afterburner

Performance
Maximum speed: 2,760 km/h (1,710 mph, 1,490 kn)
Maximum speed: Mach 2.24
Range: 4,000 km (2,500 mi, 2,200 nmi)
Service ceiling: 17,000 m (56,000 ft)
Thrust/weight: 1.09

Armament

Guns: 1 × 30 mm Gryazev-Shipunov GSh-30-1 autocannon with 250 rounds
Missiles:
R-77 air-to-air missiles
R-73 AAMs
R-37 AAMs



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