MiG-1.44 fighter (Russian: изделиемиг 1.44, English: mikoyan MIG-1. The aircraft adopts unconventional delta wing, double vertical tail canard aerodynamic layout and adjustable S-shaped inlet. The fuselage adopts a large number of composite materials and technologies that can reduce infrared characteristics, and the fuselage surface and inlet also adopt wave-absorbing coatings.
MiG-1.44 fighter was developed by Russia to compete with the United States for the fifth generation fighter. The design began in 1983 (design code 1.42), and the first aircraft assembly began in 1989 (engineering code 1.44). After the disintegration of the Soviet Union, 19 1, the MGO Design Bureau was due to (In 2006, mikoyan, Su Huoyi, Ilyushin, Ilkut and tupolev merged to form "United Aviation Manufacturing Company"), which made its first flight on February 29th, 2000, with only 1 technical verification machine.
Weapon performance: Name: MIG-1.44 fighter; R&D unit: MGO Design Bureau; Aerodynamic layout: swept wing; Number of engines: double engines; Flight speed: subsonic; Occupant:1; Captain:19m; Span:15m; Machine height: 4.5m; Empty weight:18000 kg; Engine: 2 а L-4 1f turbofan engines (with vector propulsion function); Maximum takeoff weight: 35,000 kg; Maximum flight speed: 3185 km/h; Maximum range: 4000 kilometers.
Development and Evolution-Research Background: In the middle and late 1970s, the United States first launched the advanced tactical fighter "ATF" pre-research project, and the final engineering model of this project was the F/A-22 Raptor heavy stealth fighter. In the 1980s, the former Soviet Union drew up a secret decision to develop the fifth-generation fighter for American projects, and instructed the Ministry of Aviation Industry and the Air Force to jointly accomplish this secret task.
Design and production: 1983, the design scheme of MFI multi-function fighter was submitted to the Russian Air Force by the Russian Mikoyan Design Bureau (design code 1.42). MIG Design Bureau has also carried out the research and development of double-engine medium-sized multi-role fighter "MFI" and single-engine light tactical fighter "LFI". Thereafter, MFI was classified as item 5. 12, while LFI was named as item 4 12 or item 4. 12. The previous research results have been transformed into a new generation of verification machine MIG-1.44. In the pre-research stage, the Central Institute of Fluid and Aerodynamics of the former Soviet Union suggested that mikoyan should apply the full-motion canard layout to a new generation of combat aircraft, so as to relax the static stability, improve the structural strength and improve the lift coefficient.
1988, MIG design bureau received the task of producing the first MFI prototype. 1989, MGM Design Bureau completed the design of a complete set of MFI drawings and started the production of the first MFI. 199 1 year MFI design passed the review, and MIG Design Bureau Experimental Equipment Factory and Air Force Industry Department 2 1 Aircraft Factory were responsible for the prototype manufacturing. Due to the disintegration of the Soviet Union in 199 1, after 1992, all the funds of MFI project began to be borne by MIG Design Bureau. At the beginning of 1994, the MFI fighter plane was assembled and shipped to zhukovsky. 1994 65438+In February, the MiG-1.44 fighter made its first high-speed taxiing test on the ground. Romanov Taskayev, a test pilot of the Russian MIG-Moscow aircraft production joint venture, piloted the aircraft to complete the rapid taxiing on the runway of Zhukovsky gromov Flight Test Center. 1at the beginning of 998, Moscow MIG Aviation Industry Joint Company restarted the research and development of this aircraft after raising a small amount of funds.
199965438+1October 12, a joint venture between MIG Russia and Moscow Aircraft Production presented the fifth-generation MFI multi-role fighter to Russian First Deputy Prime Minister Yuli Masryukov and former Defense Minister Igli sergeyev, as well as the air force litigation of some embassies in Russia and domestic and foreign journalists at the zhukovsky gromov Flight Test Base on the outskirts of Moscow.
On February 23rd, 2000, MIG-1.44 fighter entered the first flight stage, and made its first flight on February 29th1.25/8 minutes. After the first flight, the MIG-1.44 fighter did not carry out high-density test flight, but gradually faded out of public view.
Design features-aerodynamic design: MiG 1.44 fighter adopts the aerodynamic design of tightly coupled canard, tailless delta wing, multi-wave system adjustable inlet in the belly and double engines and vertical tails; The leading edge of the main wing is swept back 52 degrees, the leading edge is maneuvered, the trailing edge is straight, and there are flaps and ailerons; The leading edge of the canard is swept back 58 and the trailing edge is swept back 23, and the root of the leading edge of the canard is designed with serrations; The double vertical tail with vertical stabilizer is 15, which is installed on the tail strut extending backward from the main wing; The tail end and ventral fin have movable deflection wings.
The widely separated double vertical tails are inclined outward, which is not only beneficial to stealth, but also beneficial to avoid eddy currents caused by canards and strakes. Pay attention to the horizontal control surface between the vertical tail and the engine nozzle, which can be used to maintain roll control at particularly high angles of attack. The vertical tail above and the ventral fin below can "trap" the airflow and strengthen the functions of these two control surfaces.
The second half of the ventral fin is a movable control surface, which is also used to control yaw at particularly high angles of attack.
Stealth design: the fuselage adopts a large number of composite materials and integrated infrared characteristic control technology, and the exposed air inlet of the belly adopts unique design and absorbing coating. Because its tail adopts V-shaped vertical tail, the camber angle of vertical tail is large and the area is small, which improves the efficiency and stealth performance of vertical tail. In addition, all its airborne weapons can be hung in the belly bomb bay, reducing the echo area. The cockpit cover of MIG-1.44 fighter is slightly dark yellow, and the surface is plated with metal to block radar waves from entering the cockpit.
Power design: MIG-/KOOC-0/.44 fighter adopts Al-4/KOOC-0/F engine developed by Ryuka-Saturn Company of the former Soviet Union on the basis of Al-3/KOOC-0/F and AL-37 engines. This engine can ensure that MIG-1.44 fighter can fly at supersonic speed without afterburner for a long time. The thrust-to-weight ratio of the whole engine is as high as 1 1, the maximum afterburning thrust is 175 kN, and the outlet temperature of the combustion chamber reaches 19 10K. Moreover, the launch control system integrates the thrust vector control system and adopts the pitch deflection amplitude. Its maximum cruising speed at high altitude is Mach 2.6 (2500 km/h), its supersonic range is 2000 km, and its subsonic range is over 4000 km.
Armed design: KS- 172 hypersonic ultra-long-range anti-early warning aircraft missile with a range of 400 kilometers, and R-77M medium-range interceptor missile with a range of 80 kilometers. When the engine room is full of weapons, the aircraft also keeps a 30mm machine gun and an external point of 12 ~ 14, which can increase the combat load when necessary and undertake the tasks of air interception and ground attack. The aircraft is equipped with a rear-view self-defense radar, which can be used in conjunction with the R-73 rear-launched air-to-air missile to carry out missile attacks on enemy aircraft in the rear. At the same time, it is equipped with TACAN satellite navigation system and new N-0 14 multifunctional phased array radar, with a search distance of 250-400 kilometers. It can track more than 20 targets at the same time and ensure over-the-horizon attacks on more than 6 targets. Therefore, MIG-1.44 fighter can act as air combat commander, indicating targets for other fighters and guiding the missiles they launch.
Disadvantages: Pneumatic complexity.
MiG-1.44 fighter is a typical prototype with complex aerodynamics and simple flight control. There are as many as 18 movable wings, especially the ventral fin and tail strut are designed with adjustable rudder surfaces, which limits the ability of vector propulsion heading control and vector propulsion pitch control. It shows that the main wing of MIG-1.44 fighter has insufficient pitch control ability and limited vertical tail course control ability, especially when maneuvering at high angle of attack, it is necessary to rely on ventral fins for course control. The distance between the two engines in the rear fuselage is narrow, the nozzles are close to each other, and the outside of the nozzles is close to the tailstock, which leads to the failure of the three-dimensional vector propulsion of the engines in the yaw direction.
Sawtooth on canard is also a backward aerodynamic means, which is mainly used to improve the nonlinear characteristics of canard vortex and reduce the difficulty of writing flight control law.
Limited stealth capability: The radar cabin, cockpit and air intake are the keys to stealth design.
MiG-1.44 fighter, as a verification prototype, did not design a radar cabin, which could not meet the stealth design requirements of the fifth generation aircraft. The cockpit stealth is covered with film; The inlet is a multi-wave adjustable inlet with adjustable lip, which is equivalent to the design level of the fourth generation aircraft and has almost no stealth effect.
The radar echo design of the whole aircraft does not adopt parallelism, such as the leading edge and trailing edge of canard, the leading edge and trailing edge of wing and the leading edge and trailing edge of vertical tail, and no angle is parallel to each other. In addition, the whole machine has more than a dozen lobes, and the radar echo area is the same as that of the third generation machine.
The head-on RCS (radar cross section) of MIG-1.44 is about 2m2-5m2 (the head-on RCS of F/A-22 is 0.00 1m2), and the circumferential RCS is the same as that of the third generation fighter without mounting.