Tupolev Tu-244
| Tupolev Tu-244 | |
|---|---|
 Model of the Tupolev Tu-244 |
|
| Type: | Supersonic - airliner |
| Design country: | |
| Manufacturer: | |
| First flight: |
Never happened |
| Commissioning: |
Development ended in 1993 |
| Production time: |
Was never produced |
| Number of pieces: |
0 |
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The Tupolev Tu-244 was planned as the successor to the Tupolev Tu-144 , but did not get beyond this stage. It was about an eight-engine passenger aircraft that should offer a transcontinental range at twice the speed of sound . A double delta design in a low-wing design was planned as the supporting structure, while the elevators and ailerons were to be combined to form so-called elevons .
history
The design work began in 1979, and by the end of the project in 1993, significant progress had been made in the design. In particular, the resistance in the area of Mach 2 was only 50% higher than that of a conventional passenger aircraft at Mach 0.9. The project is currently on hold, but Tupolev sees a market for around 100 machines of this type by 2025.
construction
The almost circular fuselage (3.9 m wide, 4.1 m high) and the structure were to be made largely of titanium composite materials . More powerful modifications of the Samara NK-321 - Turbofan , as they are also used in the Tupolev Tu-160, were planned as engines . The adjustable air inlets should also come from the Tu-160. A total of 311 passengers should be able to be carried.
Fly-by-wire was provided for flight control . All processes should be automated as far as possible, including the landing, whereby blind landings up to CAT IIIa would have been possible. A tilted nose was dispensed with. Cameras should provide the necessary visibility during landing and on the ground.
Technical data (projected)
| Parameter | Data |
|---|---|
| span | 54.47 m |
| length | 88.70 m |
| Wing area | 975 m² |
| Empty weight | 172,000 kg |
| Max. Takeoff weight | 350,000 kg |
| Cruising speed | Mach 2.05 at 19,000 m |
| Range | 9,200 km |
| Engines | 8 × turbofans Samara TW WRD each thrust 323.73 kN |
