Dornier P 410
The Dornier P 410 was a project draft by the German manufacturer Dornier and was the predecessor of the Eurocopter Tiger helicopter used today .
history
In 1968 the Federal Ministry of Defense asked three companies ( Bölkow , Dornier and Merckle) to develop a helicopter for anti-tank defense . Dornier was commissioned to design an anti-tank and escort helicopter and to work out a design evaluation process with the other two companies . The aim was to come up with a joint design and joint implementation / production.
The draft of the P 410 supported by the three companies was the first work on the anti-tank helicopter in Germany, which first led to the interim solution PAH 1 based on Bo 105 and ultimately to the Eurocopter Tiger . Merkle and Dornier gave up helicopter development in early 1970, only Bölkow / MBB continued helicopter development in Germany.
technology
At Dornier, a version with a hot gas rotor like the Do 132 , a mechanically driven version with a high load on the rotor surface, a mechanically driven version with a low load on the rotor surface, and a mechanically driven version without propulsion relief were examined in more detail. The mechanically driven version with a low rotor area load was selected for further processing and cooperation within the three companies and was given the designation P 410.
It was a narrow silhouette helicopter with seats in tandem, with clear wings of 8 m wingspan, downward-pointing vertical tail and a rearward-pointing tail rotor as a pusher propeller. The main rotor head was semi-rigid with lamellar swivel joints and, as Bölkow's contribution, had four rotor blades in the Bo-105 design. Main and rear gearboxes were conventional light metal housings and planetary gear sets. An Emerson rotating turret for MiniGun TAT-103 was provided under the fuselage, as well as holding points for machine guns and rockets or other drop weapons under the wings . The fuselage was conventionally designed in a frame / stringer / shell light metal construction.
Like a main rotor , the pusher propeller had cyclical control , was able to align the thrust vector left-right and thus compensate for the counter-torque or execute the yaw control while hovering. With increasing speed, the vertical stabilizer took over these tasks and the tail rotor only worked as a push propeller to increase the forward speed. The wings generated additional lift and thus relieved the main rotor, so that speeds of up to 450 km / h should be achieved. The elevator was used for pitch control in high-speed flight as well as for trimming.
To reduce air resistance and increase speed, a skid landing gear was dispensed with and the helicopter was provided with a main landing gear made by Hawker-Siddeley that could be retracted towards the fuselage and was specially designed by this company for this application. The tail landing gear could be turned to attach a tow bar.
Two Lycoming T53 shaft turbines , each with 1420 WPS (1044 kW), as well as armoring of important parts and redundancies against machine gun fire from 100 m away were planned.
Disassembled into a few components, the helicopter should be transportable in a wagon 11.4 m long in the rail transit profile and then quickly reassembled and made ready for operation.
Project data
| Parameter | Data |
|---|---|
| length | 17.05 m |
| Rotor diameter | 16.4 m, 4 rotor blades |
| Tail rotor diameter | 3.5 m |
| height | 4.3 m |
| Entry height front cockpit | 2 m |
| Trunk width | 105 to 165 cm |
| span | 8 m |
| drive | 2 × T53-L-13 , 2 × 1400 SHP |
| Cruising speed | 443 km / h |
| Normal range | 620 km with 0.5 h reserve |
| crew | 2 pilots in tandem |
| Total mass | 6800 kg |
| payload | 3000 kg |