Light Fighter S-56

Promising light fighter S-56 on the assertions of Mikhail Pogosyan had to take off next after the Su-33KUB.

Details of the project C-56 with "intermediate" engine: AL-31F or P-79M.

... H ormalnaya takeoff weight C-56 (with two missiles of "air - air" medium-range and two SD melee) was 12 tonnes - little more than the latest versions of the MiG-21 (8 - 9 m). Aerodynamic design S-54/55/56 close linking of Su-33: all-moving front and rear empennage, a trapezoidal wing relatively high aspect ratio, smoothly mates with the fuselage, vertical tail dvuhkilevoe ... 
But there are significant differences. By comparison with the last car of the family, "twenty-seventh," Su-ZZKUB aerodynamics of the new light fighter is much improved. The wing was adaptive, which considerably increased aerodynamic efficiency. To improve the maneuverability characteristics keels and ventral crests tselnopovorotnym made ​​and installed on the same axis.
C-56 will Without exaggeration, the most compact fighter in the world. The designers set out to "fit" the cross section of an airplane in a "folded" in the form of a square with sides of 3x3 m. This was achieved through the use of double-folding wing, which "breaks" in the axis units attachment to the fuselage, as well as in the middle of the console (with one half of the covers on top the other). Another original solution - "curtsying" chassis. Front support is removed by turning the front and the main pillars - turning back . poluubrannom position in aircraft landing gear "sits "in a sort of" split ", which limits its high parking meters by three .

At the two-seater C-55 made ​​a cross-location pilots seat (like the Su-24, Su-27IB and Su-ZZKUB), which facilitates the interaction of the crew in flight and easier training of pilots.However, despite its small size aircraft, managed to keep the distance between the seats, no less than the Su-24 bombers. 
C-54 is equipped with one engine type AL-31 with "three dimensional" thrust vector control system. At normal takeoff weight of takeoff thrust provided significantly greater than unity. In the future, equipping cars with engines of new generation can be achieved and supersonic cruising speed. In internal tanks C-54 may be placed 4500 kg of fuel (for comparison, twice as heavy American fighter F-15C "Eagle" can take on only 6100 kg of kerosene). This, as well as advanced aerodynamics, made ​​it possible to achieve a practical range equal to 4000 km (the F-15 without external fuel tanks, it is only 2,000 km). Aircraft of C-54 to be equipped with modern avionics. Diameter fairing radiotransparent radar in the forward fuselage fairing diameter equal plane Su-27 (about 1 m). This enables you to install a powerful light fighter radar with a phased antenna array, which provides detection range of aerial targets, much higher than that of aircraft such as F-16C, or JSF. The radar will be complemented by a new optical-electronic complex, comprising low level night system and able to work both on air and on ground (surface) targets.

Information-control field holds the cab on the new principles, using multi-colored indicators that are the size of the diagonal equal to 14 ... 15 inches. 
In the cockpit you plan to install an improved ejection seat, which is a further development of the chair of K-36. Will use a new G-suit and oxygen system pilot, providing an opportunity of conducting.

length 5.17 m

span 7.11 m

height 5.1 m

wing area 49.2 sq ft (40 m)

Weight:

        Max 15,000 kg

        11 250 kg of normal

        Empty 8000 kg

        4500 kg of fuel

        load 3000 kg

speed max. 2100 km / h

Cruising speed. 1400 km / h (AL-41F1)

range of 4000 km

engine  

                     AL-31F 12 500 kg.

                     AL-41F1 15 500 kg.

Aircraft, in particular for storing in a standard container

Authors: Antonov, VI, Ivanov, Y., Klyagin AS, Maksimov AL, Marbashev KH, Merkulov VI, Tkachenko, PG, Chernov, LG

Plane (two versions), characterized by:

- Composition of the compositional elements: a fuselage with a cabin, forward-swept wings, connected to the fuselage at the root of the wing and deflected with socks in front of the wing, front and tail horizontal stabilizer, tail boom, which is located on the sides of the fuselage at the rear, dvuhkilevoe vertical stabilizers, air intake ;

- Location of the vertical stabilizer on the tail boom;

wherein:

- Using the tail boom, extended to the cockpit as a side stekatelya forming the root of the wing flow;

- On the side and front wing stekatele horizontal tail;

--Wing, front and tail horizontal tail in different planes in height;

- The presence of slotted slat located on the wings between their toes and roots;

- Using the tail horizontal tail on the reverse sweep and the leading edges that are parallel to trailing edge;

- Using the front face of the inlet, tapered from the rear of the fuselage;

- Location of air intakes under the fuselage from the bottom of cab to rear end;

-Option 1 is characterized by a solid performance wing;

-Option 2 is characterized by the implementation of the wing consists of a group developing between the parts.

Patent:

http://www1.fips.ru/fips_servl/fips_servlet?DB=RUDE&rn=3980&DocNumber=53136&QID=21E83CBA-8B34-4889-9B06-A2268D18CFA8&TypeFile=html

Length 11.8 m

span 8.4 m

height 3.3 m

wing area 15 sq. m

side view of 15.62 sq.m

view from above 29.44 m

Front View of 4 sq.m

volume of 12.25 cubic meters

Weight:

Max 12,000 kg

normal 10000 - 11000 kg

Empty 5800 kg

3100 kg of fuel

load 2000 kg

service 100 kg

Engine type RD-33 RD-133, VC-10 VC-12

afterburning power 1 x 9000 - 11500 kgs

maximum thrust of 1 x 5200 - 7500 kg

Maximum speed 1600 - 2100 km / h

ferry range 2500 km

The radar "Wasp" and "Lance"

antenna diameter of 500 mm

The normal combat load:

4 P-73 (440 kg) + 4 AAP-62 (200 kg) = 640 kg

Gun NH-301