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  • Armstrong Whitworth AW.55 Apollo

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    Description

    The Armstrong Whitworth AW.55 Apollo was a 1940s British four-engine turboprop airliner built by Armstrong Whitworth at Baginton.

    General Information

    The aircraft was in competition with the Vickers Viscount but was beset with engine problems and only two were built.

     

    The requirement resulted from the Brabazon Committee's Type II design, calling for a small, medium-range pressurized aircraft to fly its less-travelled routes which became Air Ministry Specification C.16/46 for an aircraft able to carry 24-30 passengers over 1,000 mi (1,610 km) at a cruising speed of 300 mph (480 km/h).

     

    The resulting design was the AW.55 Apollo, a low-wing cantilever monoplane with retractable tricycle landing gear. Due to the narrowness of the engines, there was no room in the nacelles for the main wheels which instead folded up into the wings. It had a conventional tail unit with a mid-placed cantilever horizontal tailplane. It had a pressurised fuselage with seating for 26-31 passengers. It was designed to use the Armstrong Siddeley Mamba ASM.2 which was expected to produce 1,270 shp (950 kW) plus 307 lbf (1.37 kN) static thrust for the production aircraft. When the prototype Apollo was ready to fly the engine could only produce 800 shp (600 kW). Two prototypes - one to be completely fitted out - and a static test fuselage were ordered by the Ministry of Supply and construction started in 1948. The prototype (serial VX220) first flew from the grass field at Baginton, Coventry on 10 April 1949 for a thirty-minute test flight.

     

    The aircraft was unstable and underpowered, and after just nine hours of test flying, it was grounded to try to solve some of the problems. Test flying resumed in August 1949 but the aircraft had further engine problems. Changes were made to the design of the tail unit including fitting a dorsal fin and increasing the fin area to improve the flying qualities.[2] In October 1950, a limited category Certificate of Airworthiness was granted to allow the aircraft to carry non-fare paying passengers. One proving flight - between Baginton and Paris taking 1 hr 26 min - was carried out on 12 March 1951.

     

    Further engine problems stopped the trial and test flights. The company started a selling campaign to European airlines, but the problems with performance and continual engine difficulties caused the decision in June 1952 to abandon development of the aircraft. The competing Brabazon IIB design the Vickers Viscount powered by the Rolls-Royce Dart became a best-selling turboprop in the 1950s and 60s.

     

    The second prototype was expected to use the Mamba 3 to give it a maximum weight of 45,000 lb.

     

     

    A-W apollo-1.jpg

    A-W apollo-2.jpg

    A-W apollo-6.jpg

    A-W apollo-14.jpg

    Specifications

    Seats:
    Crew: 3 Capacity: 26–31 passengers
    Length:
    71 ft 6 in (21.79 m)
    Wingspan:
    92 ft 0 in (28.04 m)
    Height:
    26 ft 0 in (7.92 m)
    Wing Area:
    986 sq ft (91.6 sq m)
    Empty Weight:
    30,800 lb (13,971 kg)
    MTOW:
    Gross weight: 45,000–47,000 lb (20,412–21,319 kg)
    Fuel Capacity:
    970 imp gal (1,160 US gal; 4,400 L)
    Powerplant:
    4 × Armstrong Siddeley Mamba AS.1 axial-flow turboprops[6], 1,010 shp (750 kW) each
    Vne:
    Maximum speed: 330 mph (530 km/h, 290 kn)
    Cruise Speed:
    276 mph (444 km/h, 240 kn)
    Range:
    940 mi (1,510 km, 820 nmi)
    Rate of Climb:
    1,500 ft/min (7.6 m/s) at sea level
    Service Ceiling:
    28,000 ft (8,500 m)

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