MPC 75

MPC 75 was an aircraft project of the company "MPC Aircraft GmbH" a subsidiary of "Deutsche Airbus". Work on the project was done mainly between 1988 and 1992 in Hamburg, Germany. Predevelopment work was finished, however the project never got the "go ahead" and never made it into full development.

Development

In October 1985, a memorandum of understanding (MoU) was signed by between Messerschmitt-Bölkow-Blohm (MBB) of West Germany and the China National Aero-Technology Import & Export Corporation (CATIC) to study the feasibility of an aircraft designated the MPC 75.[1] MPC 75 development was started by MBB in 1988 in Hamburg, West Germany. The name "MPC" was formed from "MBB" and "People's Republic of China" because the project was a German - Chinese joint venture. In the wake of restructuring German aerospace companies in 1989, MBB was taken over and the MPC 75 project came under "Deutsche Airbus GmbH". "Deutsche Airbus GmbH" was representing the independent German part of the Airbus consortium. For the development of MPC 75 restructuring did not make a difference since the same engineers continued the design work.[2]

On 07.01.1989 "MPC Aircraft Gesellschaft mit beschränkter Haftung" (HRB41092) - abbreviated to "MPC Aircraft GmbH" - was founded with head office in Hamburg. Eventually it became a 100% subsidiary of "Deutsche Airbus GmbH". "MPC Aircraft GmbH" formally took over the MPC 75 project. On 13.12.1994 the company was renamed to "MPCA Multi Purpose Commuter Aircraft GmbH" reflecting the end of the German - Chinese cooperation. Abbreviated the company name remained "MPC Aircraft GmbH".[3]

The first design of the MPC 75 was a 75-seat (4 abreast) regional jet, with an open rotor propfan and a T-tail. In the later development, the design changed to an 89-seat (5 abreast) regional jet, with conventional turbofan engines and a conventional empennage (MPC 75-100). A stretched version with a capacity of 115 seats was also planned (MPC 75-200).[4]

The fly-by-wire (FBW) flight control technology accumulated in the project was later fed into a research aircraft called Advanced Technology Demonstrator ATD. The ATD was a revived VFW 614.[2]

Design

The MPC 75 was designed with a high amount of composite materials to save structural weight. Flight control was based on fly-by-wire with sides-sticks and CRT displays. The jet had two high bypass ratio engines. The new technologies would have led to low operational costs per trip and seat compared to other aircraft at that time.[4]

Specifications

Airplane Characteristics[4]:M75.A.0005.C, M75.A.0006.C, M75.A.0008.F
VariantMPC 75-100MPC 75-200
Maximum take-off weight (MTOW) 39,950 kg (88,100 lb)45,100 kg (99,400 lb)
Maximum landing weight (MLW) 37,950 kg (83,700 lb)42,850 kg (94,450 lb)
Maximum zero-fuel weight (MZFW) 35,350 kg (77,950 lb)41,000 kg (90,400 lb)
Operating empty weight (OEW) 24,500 kg (54,000 lb)27,000 kg (59,500 lb)
Maximum structural payload 10,850 kg (23,950 lb)14,000 kg (30,900 lb)
Maximum fuel capacity (outboard tanks) 10,450 L (2,760 US gal)
Maximum fuel capacity (center section tanks) 5,000 L (1,320 US gal)
Seats (typical two-class) 82107
Seats (single class) 89115
Cabin width (armrest level) 3.23 m (10 ft 7 in)
Stowage volume (overhead) 6.54 m3 (231 cu ft)8.75 m3 (309 cu ft)
Stowage volume (underfloor) 18.15 m3 (641 cu ft)27.55 m3 (973 cu ft)
Wing area 92 m2 (990 sq ft)
Wing span 29.7 m (97 ft 6 in)
Height 10.2 m (33 ft 4 in)
Length 28.5 m (93 ft 7 in)33.6 m (110 ft 3 in)
Engine thrust (sea-level static) 62.3 kN (14,000 lbf; 6,350 kgf)73.4 kN (16,500 lbf; 7,480 kgf)
Range (standard) 1,600 nmi (3,000 km; 1,800 mi)1,400 nmi (2,600 km; 1,600 mi)
Range (with center wing fuel tank) 2,600 nmi (4,800 km; 3,000 mi)

References

Citations

Bibliography

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