Comparing Dry T50 with F-22

October 29 2010 1

In response to the request of journalists to compare the PAK FA fighter with the American F-22 Raptor, created ten years ago, the chief designer of the aircraft, Alexander Davydenko, said: "The main functions remained the same, but we tried to make them better."

Davydenko said that during the development of the Sukhoi Design Bureau, the T-50 air combat with the F-22 was simulated.

“I think we will have competitive prices. As for the cost / efficiency criterion, our aircraft is much better, ”the designer added.

The head of the OKB, Mikhail Pogosyan, demonstrated to Putin the work of a special stand, which simulates the operation of an electric hydraulic drive of the aircraft in conjunction with the operation of a combat vehicle control system.

According to Pogosyan, the aircraft's drive system is very reliable and even if one or another equipment fails, it can shift the machine control function to other controls. The aircraft itself is completely without mechanical control - all the work for the pilots is done by a “smart” integrated control system, ITAR-TASS reports.

At the same time, Pogosyan noted, due to new technologies, the weight of the system is reduced by 30 percent compared to previous samples.

Pogosyan introduced to Putin the honored test-pilot of Russia Sergey Bogdan, who was the first to fly a fifth-generation plane into the air. Putin congratulated the pilot and asked him about the sensations during the flight. The tester said that he had already raised the combat vehicle three times in the air, and the results obtained during the testing at the Sukhoi design bureau's stand made it possible to avoid surprises during real flights.

The Prime Minister was also shown personnel working out various aircraft systems, including an engine, as well as flights of a promising front-line aviation complex aviation. Poghosyan emphasized that already during the first flights the heeling angles were checked and the angle of attack of 27 degrees was reached. When testing the Su-27 aircraft, such results could be achieved only a few months after the machine first flew into the air.

In stat. the hall, where 50-0 stands, drove only GDP and a pair of camera cameras + a regular camera Sukhovsky (but his photos, which got 50-0, are not yet given, like "No way", although RTR and NTV have already seen all the stills) .

1. 50-2 waiting closer to the end of the year. 3 and 4 - in 2011.
2. The radar on 1 and 2 was naturally not planned (MAP was very angry with fools-journalists who made far-reaching conclusions based on this). We are waiting for her on board in 2011. Behind and do not wait, because "we don't need it"
3. The engine of the second stage is not waiting for the year to 2020 th. "The engine of the first stage satisfies all the TTT, including cruising supersonic," with him go serial in 2015-2016. Again, I was very angry with the journalist who consider the first stage engine to be "old" (because the brand new FADEC, new turbine, thrust "+ 2500 kgf", weight and expense less, etc., etc.).
4. ESR. It was said this way: for the 4 generation (“Su-27 type aircraft”) - about 12 meters, for F-22 - about 0,3 ... 0,4. And we will have "no worse than the F-22 or so"

Analysis T-50-1

Side view of 31.9 sq.m
Top view 129.3 sqm
Front view 10.13 sq.m
Airframe 34.73 cubic meters
Area bearing 90 sq.m

The size of the air intake corresponds to an engine compressor with a diameter of 1.14 m. For reference, "117 ed." - 0.932 meter. It is likely that the engine of the "second stage" known as "ed.127" will have a afterburner thrust in the region of 17500 kgf and maximum - 11000 kgf.

Maximum take-off weight 35080 kg
Weight is normal, 63% kg 26510 fuel
Weight is normal, 100% kg 30610 fuel
Empty weight 17500 kg
Weight of fuel 11100 kg (100%) / 7000 kg (63%)
1310 kg load weight kg - 10000 kg
External load nodes - 6 pieces, internal - 8 pieces.
Total volume of compartments - 7 cubic meters
Relative Volume - 20%
The weight of a universal intra-ejection ejecting unit UVKU-50L is taken as 100 kg, weight UVKU-50U is 200 kg.

Calculation of take-off weight:

Normal weight No. 1 (63% fuel)
17500 (empty) + 100 (pilot) + 7000 kg (fuel) + 1140 kg (6 UR SD) + 600 kg (AKU) + 170 kg (2 UR SD) = 26510 kg,
wing load 295 kg / sq.m, thrust-weight 1.13 kgf / kg

Normal weight No. 2 (100% fuel)
17500 (empty) + 100 (pilot) + 11100 kg (fuel) + 1140 kg (6 UR SD) + 600 kg (AKU) + 170 kg (2 UR SD) = 30610 kg
wing load 340 kg / sq.m, thrust-weight 0.98 kgf / kg

Maximum weight with internal suspension (63% fuel)
17500 (empty) + 100 (pilot) + 7000 kg (fuel) + 4000 kg (8 AB-500) + 800 kg (4 DB) + 380 kg (2 SD SD) + 200 kg (2 AKU) = 29980 kg

Maximum weight with internal suspension (100% fuel)
17500 (empty) + 100 (pilot) + 11100 kg (fuel) + 4000 kg (8 AB-500) + 800 kg (4 DB) + 380 kg (2 SD SD) + 200 kg (2 AKU) = 34080 kg

Weight of fuel 11100 kg (full), 7000 kg (normal)
2 PTB-2000, 2 x 1570 kg = 3140 kg of fuel, total weight 11100 kg + 3140 kg = 14240 kg
Kilometer fuel consumption 2.59 kg / km

Range:

with "normal" refueling 2700 km
with "maximum" refueling 4300 km
with PTB-2000 5500 km
on supersonic 2000 km
Maximum speed 2200 - 2500 km / h
Speed without running 1850 - 2100 km / h
The plane uses a hydraulic system with a working pressure 350 kg / sq. Cm