Dornier V/STOL Transport
Dornier GmbH (Germany)
Do 231

Do 31 Variants Lift + Lift/Cruise
While the Do 31 E experimental aircraft were under construction, the proposed operational version of the Do 31 continued to evolve to meet expected requirements. Do 31 operational concept
  • Lift power: 10 RB.162-31 lift engines
  • Cruise Speed: 750 km/h (405 kt)
  • Design Weight: 22.5 metric ton (49,600 lb)
  • longer wing
  • T-tail
A design in mid-1962 had longer wings, fuselage and tail with two BS.100 engines. The BS.100 was a BE.53 engine with an additional fan stage and plenum chamber burning (PCB) intended for the supersonic P.1154. (The BS.100 first ran in 1964 and produced about 30,000 lb with PCB.)
Do 31 design with two BS.100 engines.  Do 31 design with two BS.100 engines.
Do 31 design with 16 RB.162 lift engines. Another design in early-1963 had the BS.100 engines and 16 RB.162 lift engines.
Do 31 design with extendable lift engines. Another design used four groups of three lift engines that could be extended from the four corners of the fuselage. The four cruise engines also tilted up for lift thrust.
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Do 131 Lift + Lift/Cruise
Military V/STOL plane. Design based on the Do 31 . Start of the projekt 1966.
For the Do 131 B the cruise engines were expected to be high bypass engines; the lift engines were also expected to be turbofan engines, instead of turbojets like the RB.162 and all other lift engine that had been built. In the case of the Do 131A or B, the lift engine pods could also be removed for a conventional high speed transport aircraft with increased payload or replaced with fuel for greater range capabilities.
    Do 131 B
  • Lift Power Version A: 14 Rolls-Royce RB.162-81 jet-lift engines: seven in each wing pod.
  • Lift/Cruise Power Version A: Two Rolls-Royce RB.168-25-38 engines
  • Cruise Speed: 850 km/h (460 kt)
  • Wing span: 24.82 m (81.42 ft)
  • Wing area: 88.0 m² (947 ft²)
  • Length: 24.6 m (80.71 ft)
  • Height: 8.0 m (26.21 ft)
  • Maximum STO weight Version A: 41,000 kg (90,400 lb)
  • Design VTO weight Version A: 37,630 kg (83,000 lb)
  • Payload Version A: 4,900 kg (10,800 lb) @ 925km distance; max. 7,250 kg
  • Payload Version B: 7,100 kg (15,700 lb) @ 925km distance;
  • 3-side-view Version A
  • 3-side-view Version B
Do 131B
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Do 231 Lift + Cruise
Submitted in a proposal to the West German Federal Defence Ministry for an 80-100 passenger V/STOL transport projected for service in late 1970s. Design based on the Do 31 .
  • Lift Power: 12 x 58.2 kN (13,084 lb) Rolls-Royce RB.202-25 s.t. jet-lift engines: four in each wing pod, two in nose and two in tail.
  • Cruise Power: Two Rolls-Royce RB.220 engines; 106.4 kN (23,920 lb) thrust each with a 6.5 bypass ratio. Do 231M
  • Maximum Speed: 900 km/h (560 mph, 486 kt) at 25,000 ft
  • Maximum Altitude (2 engines): 11,100 m (36,400)(C), 10,000 m (M)
  • Maximum Altitude (1 engine): 5,250 m (C)
  • Maximum rate of climb: 13 m/s (42.7 ft/s) 18.5 m/s (M)
  • Range: 800 km (500 miles)
  • Maximum VTOL range with half payload: 2,460 km (1,330 nm)
  • Maximum VTOL range with max fuel: 2,790 km (1,500 nm)
  • Wing span: 26.0 m (85.3 ft)
  • Wing Area: 120.0 m²
  • Length: 35.55 m (118.8 ft)
  • Height: 9.55 m (31.3 ft) (C), 10.5 m (M)
  • Maximum STO weight: 66,900 kg (M)
  • Maximum VTO weight: 59,000 kg (130,075 lb)
  • Maximum Take-off weight: 129,000 lb.
  • Maximum Landing weight: 57,000 kg (125,660 lb)
  • Payload: 10,220 kg (22,530 lb) or 100+4 passengers + 22.3 m³ of baggage(C); 10,000 kg (M)
  • 3-side-view Civilian and Military version.
Do 231 with lift engine doors open Do 231 Do 231
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Do P378 Lift + Lift/Cruise
Do P378-3 Civilian V/STOL plane. Design based on the Do 31 . Start and stop of the projekt 1966.
  • Lift Power: 10 Rolls-Royce jet-lift engines: five in each wing pod.
  • Lift/Cruise Power: 4 Rolls-Royce engines
  • Wing span: 24.82 m
  • Length:32.1 m
  • Height:7.3 m
  • 3-side-view
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Do P 407 Rotor
Designed 1966,at the end of the development, the engineers had been studying a fast helicopter for 35 passengers and a cruising speed of 500 km/h (270 kt).
  • Power: two engines
  • Rotor: four-bladed main rotor and the three bladed propeller
  • Capacity: four seats
  • 2-side-view
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Do P 410 Rotor
Designs begins 1964.
  • Power: two Lycoming T53 engines
  • Rotor: The main rotor was 16.40 m (53.8 ft) and the tail rotor 3.50 m (11.5 ft). Four-blade main rotor with a tail rotor capable of swiveling 35° for torque compensation and additional propulsion
  • Cruise Speed: 375 km/h (200 kt)
  • Maximum Speed: 430 km/h (230 kt)
  • Maximum Altitude:
  • Maximum rate of climb:
  • Range: 620 km (335 nm)
  • Wing span: 7.95 m (26 ft)
  • Wing Area:
  • Length: 17.05 m (55.9 ft)
  • Height: 4.30 m (14.1 ft)
  • Empty Weight: 3,805 kg (8,390 lb)
  • Gear: a retractable main landing gear and fixed tail-wheel
  • Maximum VTOL Weight: 5,850 kg (12,900 lb)
  • Maximum Take-off Weight:
  • Capacity: two seats
Dornier P 410 compound helicopter
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    Sources:
  • "World Air News" Air Pictorial. January 1970: 10-11.
  • Luftfahrttechnik, Raumfahrttechnik Band 14 (1968), Band 16 (1970). West Germany.
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