(Bristol) 188 @·AIRCRAFTUBE

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    Bristol Type 188
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    Bristol T.188
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    Farnborough - 1962
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    Bristol T.188
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Bristol 188

The Bristol 188 was a British supersonic research aircraft built by the Bristol Aeroplane Company in the 1950s. Its length, slender cross-section and intended purpose led to its being nicknamed the "Flaming Pencil".

Design and development

The aircraft had its genesis in Operational Requirement 330 for a high speed (Mach 3) reconnaissance aircraft, which eventually developed into the Avro 730. As the 730 was expected to operate at high speeds for extended periods of time, more data was needed on high speed operations, leading to Operational Requirement ER.134T for a testbed capable of speeds greater than Mach 2. The aircraft was expected to run at these speeds for extended periods of time, allowing it to study kinetic heating effects on such an aircraft. The aircraft was expected to spend a considerable amount of time with a skin temperature around 300 Celsius.

Several firms took interest in this very advanced specification and the eventual contract (6/Acft/10144) was awarded to Bristol Aircraft in February 1953.

Bristol gave the project the type number 188, of which three aircraft were to be built, one a pure test bed and the other two (constructor numbers 13518 and 13519) for flight testing. Under contract number KC/2M/04/CB.42(b) serial numbers XF923 and XF926 were given on 4 January 1954 to the two that would fly. To support the development of the Avro 730 Mach 3 reconnaissance bomber, another three aircraft were ordered (Serial Numbers XK429, XK434 and XK436). The follow-up order was cancelled when the Avro 730 programme was cancelled in 1957 as part of that year's review of defence spending. The 188 project was continued as a high speed research aircraft.

The advanced nature of the aircraft meant that new construction methods had to be developed. Several materials were considered for construction and two specialist grades of steel were selected: a titanium-stabilized 18-8 austenitic steel and a 12%-Cr steel used in gas turbines (Firth-Vickers Rex 448). These had to be manufactured to better tolerances in sufficient quantities for construction to start. The 12% chromium stainless steel with a honeycomb centre was used for the construction of the outer skin, to which no paint was applied. Riveting was a potential method for construction but the new arc welding technique using an Argon gas shield known as puddle welding was used. There were long delays with the method, which was less than satisfactory. The W. G. Armstrong Whitworth company, provided substantial technical help and support to Bristol during this period; they produced major sections of the airframe as a subcontractor.

A fused-quartz windscreen and canopy and cockpit refrigeration system were designed and fitted but were never tested in the environment for which they had been designed.

The engine installations had to allow development of variable-geometry intake systems. These would permit maximum efficiency across a range of supersonic speeds. This had also led to the engines' position on the wings rather than within the fuselage. Rolls-Royce engines were initially selected to power the 188, but five engine combinations were subsequently evaluated: two with Rolls-Royce Avon 200s, two with the de Havilland Gyron Junior and one with an AJ.65, the last disintegrating on test. Finally, in 1957, the choice for the 188 was two 10,000 lbf (44 kN) thrust Gyron Junior DGJ10Rs, developing 14,000 lbf (62 kN) of thrust on reheat at sea level and 20,000 lbf (89 kN) at Mach 2 at 36,000 ft (11,000 m).

The Gyron Junior was then under development for the Saunders-Roe SR.177 supersonic interceptor and incorporated a fully variable reheat, from idle to full power, the first such application used in an aircraft. Unfortunately this choice of powerplant resulted in the 188 having a typical endurance of only 25 minutes, which was too little time for any serious high-speed research. Chief Test Pilot Godfrey L. Auty reported that while the 188 transitioned smoothly from subsonic to supersonic flight, the Gyron Junior engines were prone to surging beyond that speed, causing the aircraft to pitch and yaw.

In order to solve the aerodynamic and flutter problems, a large number of scale models were employed. Mounted on converted rocket boosters, a number of models were launched from RAE Aberporth, for free-flight investigation.

Operational history

In May 1960, the first airframe was delivered to the Royal Aircraft Establishment at Farnborough for structural tests – loading tests both heated and unheated – before moving on to RAE Bedford. XF923 undertook the first taxiing trials on 26 April 1961, although due to problems encountered, the first flight was not until 14 April 1962. XF923 was intended to remain with Bristol for its initial flights and evaluation before turning it over to the MoA. XF926 had its first flight, using XF923s engines, on 26 April 1963. XF926 was given over to RAE Bedford for its flying programme. Over 51 flights, it managed a top speed of Mach 1.88 (1,440 mph : 2,300 km/h) at 36,000 ft (11,000 m). The longest subsonic Bristol 188 flight was only 48 minutes in length, requiring 70% of the fuel load to be expended to attain its operational altitude.

The first prototype made its first public appearance in September 1962 when it was displayed on the ground and in the air at that years Farnborough Airshow.

Measurements collected during testing were recorded onboard and transmitted to the ground station for recording. The flight information transmitted meant that a "ground pilot" could advise the pilot.

The project suffered a number of problems, the main being that the fuel consumption of the engines did not allow the aircraft to fly at high speeds long enough to evaluate the "thermal soaking" of the airframe, which was one of the main research areas it was built to investigate. Combined with fuel leaks, the inability to reach its design speed of Mach 2 and a takeoff speed at nearly 300 mph (480 km/h), the test phase was severely compromised. Nonetheless, although the 188 programme was eventually abandoned, the knowledge and technical information gained was put to some use for the future Concorde program. The inconclusive nature of the research into the use of stainless steel led to Concorde being constructed from conventional aluminium alloys with a Mach limit of 2.2. Experience gained with the Gyron Junior engine, which was the first British gas turbine designed for sustained supersonic operation, additionally later assisted with the development of the Bristol (later Rolls Royce) Olympus 593 powerplant which was used on both Concorde and the BAC TSR-2.

Various proposals to further develop the 188 were considered including incorporating ramjets and rocket engines as well as considering fighter and reconnaissance variants. One serious proposal involved the fitting of "wedge" type intakes.

The announcement that all development was terminated was made in 1964, the last flight of XF926 taking place on 12 January 1964. In total the project cost £20 million. By the end of the programme, considered the most expensive to date for a research aircraft in Great Britain, each aircraft had to be "cannibalised" in order to keep the designated airframe ready for flight.

Survivors

In April 1966, both 188 fuselages were transported to the Proof and Experimental Establishment at Shoeburyness, Essex to act as targets for gunnery trials, but during 1972, XF926 was dismantled and moved to RAF Cosford (without its engines) to act as instructional airframe 8368M, and is preserved at the Royal Air Force Museum Cosford near Wolverhampton. XF923 was subsequently scrapped at Foulness.

Operators

United Kingdom : Royal Aircraft Establishment

Notable appearances in media

The Bristol 188 (XF923) was prominently featured in Some People (1962), a feature film primarily shot in Bristol.

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This text is available under the Creative Commons Attribution-ShareAlike License
Source : Article Bristol 188 of Wikipedia ( authors )

Specifications (Bristol 188)

  • Crew : 1.
  • Length : 77 ft 8 in (23.67 m).
  • Height : 12 ft (3.65 m).
  • Wingspan : 35 ft 1 in (10.69 m).
  • Airfoil : biconvex section, 4 per cent t/c ratio.
  • Operational weight : 37,527 lbs (17,022 kg).
  • Max.speed : record at 1,242 kts (2,300 km/h).
  • Powerplant : Two de Havilland Gyron Junior DGJ10Rs turbojet with reheat.
  • Dry thrust : 10,000 lbf (44 kN) each.
  • Thrust with afterburner : with reheat 14,000lbf at sea level, 20,000lbf at 36,000ft (62 kN at sea level, 88 kN at 36,000ft) each.

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This text is available under the Creative Commons Attribution-ShareAlike License
Source : Article Bristol 188 of Wikipedia ( authors )
Bristol 188 : Your comments on this subject
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