de Havilland DH 106 Comet / Nimrod

Comet 4C

The Comet resulted from the wartime Brabazon Committee’s recommendations for the Type IV North Atlantic turbojet mail plane, which led to numerous studies including a 20-passenger aircraft with three rear-mounted Goblin engines.
The final design emerged as an orthodox low-wing monoplane with 20 degree leading-edge sweep-back and four 19.8kN de Havilland Ghost centrifugal-flow turbojets buried in the wing roots. Initial accommodation was for 36 passengers in two cabins, pressurised to provide internal pressure equivalent to 2,438m when flying at 12,192m. Cruising speed was about 788km/h.

DH 106 Comet Article

The prototype Comet made its first flight on 27 July 1949.

The first two BOAC Comet 4C delivered to London Airport from Hadfield, 30 September 1958

BOAC received a fleet of ten Comet Is and on 2 May 1952 inaugurated the first passenger services to be operated by turbojet aircraft – on the London-Johannesburg route, covering the 10,821km in 23 hr 34 min. Comets were subsequently introduced on a number of routes, bringing drastic cuts in journey time: such as the reduction from 86 to 33 1/4 hours between London and Tokyo. Air France and UAT soon began Comet services and there were a number of airline orders for Comet 1s when one broke up near Calcutta exactly a year after its introduction; in January and April 1954 two more suffered inflight structural failure, resulting in the type being withdrawn.
In October 1952, a Comet broke up in flight near Calcutta. Modifications were made, but when, on April 8, 1954, the fifth Comet accident occurred, all Comets were withdrawn from service and production was halted.

Salvage and careful investigations showed that fatigue failure of the cabin was the cause of the crashes, and the fuselage was redesigned. Painstaking detective work by scientists and engineers had established that the Comet ls had suffered metal fatigue, causing explosive decompression of the pressurized fuselage.

DH COMET SITUATION – Flight 7 May 1954


A great deal of structural knowledge was gained through the accidents of four of the original nine Comet I models. This knowledge was later tested on the model 3 and applied to the model 4.
The Avon-powered Comet 2s on order for BOAC were strengthened and some delivered to the RAF.

No.216 squadron of RAF Transport Command was equipped with Comet 2 from 1956 in order to operate a courier service between Britain and the Long-range Weapons Establishment at Woomera, Australia. Operated with full C of A, they were modified and powered by Rolls-Royce Avon 117/118 turbojets.

A longer-fuselage long-range Comet 3 had been developed and in the light of the inquiry into the Comet 1s disasters it was redesigned, first flying on 19 July 1954. It did not go into production but made a round-the-world flight and served as a test vehicle.

Comet 3B

Most of the flight tests for the Comet 4 were conducted on the one and only Comet 3 built by Hawker.

In 1957 it was decided that Comets would be reinstated and BOAC ordered 19 Comet 4s. These were powered by 46.71kN Rolls-Royce Avon 524, had longer fuselages than the Comet 1 and could carry 60-81 passengers. The first Comet 4 flew on 27 April 1958 and on 4 October BOAC Comets inaugurated North Atlantic jet services over the London-New York route when Comet 4s of BOAC (G APDB and G APDC) made simultaneous crossings in opposite directions. BOAC bought 19 larger, more powerful Comet 4s, and successfully operated the first London/New York jet service from 1958. On 1 April 1959 Comets were put back on the London-Tokyo route.

First BOAC Comet 4

It was a long range version of the basic Comet design and was recognized by the projection of the two-pod fuel tanks on the leading edge of each wing. Following the model 4, the Comet 4B was produced for intermediate-range flights carrying a high-density passenger load.
The model C-2 was a military cargo airplane and was structurally far superior to the original Comet 1.

Comet C4

Transport Command’s Comet 4 took 76 passengers, the C2 44 and the Comet T2s, which were often pressed into service could carry 36.

From that time Comets took over much of BOAC’s network. Other Comet 4s were used by Aerolineas Argentinas, East African Airways and the RAF. From this version were developed the Comet 4B and 4C which first flew on 27 June and 31 October 1959 respectively. The Comet 4B had a 1.98m increase in fuselage length, a 2.13m reduction in span and was intended for high-speed operation over shorter stages. It could carry up to 101 passengers and was not fitted with wing-mounted external fuel tanks. The main operators of Comet 4B were British European Airways and Olympic Airways.

Characteristics of the Comet 4B used by BEA were the longer fuselage and the shorter wing, without the external nacelle fuel tanks, when compared with the BOAC Comet 4. Olympic Airways also started operating the Comet 4B during 1960.

Comet 4B

The Comet 4C combined the long fuselage of the Comet 4B with the standard Comet 4 wing. This version was ordered by several airlines and went into service in 1960. A total of 112 Comets were built including 74 Series 4 aircraft; and the type was subsequently developed into the RAF Nimrod.

The DH Comet was designed and built all 113 of them over 15 years at Hatfield.

The HS.801 Nimrod was originally designed by Hawker-Siddeley, but was also a product of BAE Systems. First flying on 23 May 1967, the Nimrod serves the RAF in two variants: the R1 variant in a reconnaissance and electronic intelligence gathering capacity (ELINT), and the MR2 variant in the Maritime Reconnaissance role.

Test Flying the Nimrod


Ordered by the RAF to replace the Shackleton MR.Mk.3s, the Nimrod is said to have begun in June 1964 when Hawker Siddeley at Woodford began work on the HS.801. Its true origin is in the de Havilland Comet, two Nimrod prototypes were made from unsold Comet Mk.4C airframes, with many changes involved in producing a maritime reconnaissance version. The second prototype (XV148) was converted to HS.801 standard, four Rolls-Royce RB.168 turbofans replacing the Comet’s original four R-R Avons. Its maiden flight was on 23 May 1967, with the second, Avon-powered, aircraft flying two months later.

In mid-1965 a contract to build 38 Nimrod MR.Mk.Is was placed, and the first flew at Woodford on 28 June 1968. All were built as new airframes and delivered by September 1972, although a further eight were completed three years later. In service with RAF Strike Command since late 1969, the Nimrod MR.1 is based on the airframe of the Comet 4C Main difference are a power plant of four Spey turbofan. In addition of an unpressurised pannier beneath the pressurised main fuselage to house the operational equipment and weapons; and modified tail design incorporating an ECM pod and MAD stinger.

Nimrod MR.1

DH Nimrod Article October 1967

Subsequent plans were to upgrade 35 aircraft to Mk.II standard (by the installation of new communication systems and advanced tactical sensors), with 11 for the new AEW Mk.3 programme, and the last of the Mk.IIs was completed in 1985. The conversion added some 6000 lbs to the empty weight, and external signs of change were a reduction in cabin windows, new intakes and ducts around the rear fuselage. Other MR.2 modifications include the provision of in-flight refuelling probes, Harpoon anti-shipping missiles, and AIM-9 Sidewinder AAMs for self-defence. Loral early-warning support measures pods (EWSM) are mounted on the wing tips, and minor airframe changes have been made, comprising the introduction of larger finlets to the tailplanes and a new ventral fin. The Nimrod R.1 is a specialised Elint variant.

Nimrod MR.2

The AEW.3 conversion programme was scrapped in 1986 after the con¬version of eleven Nimrods at a cost of around NZ$2,700 million.
The UK Ministry of Defence decided drop the Nimrod AEW.3 project in favour of Boeing E-3A Sentry purchase. The planned Nimrod AEW.3 was a conversion of an MR.1 airframe to accept an AEW mission system comprising radar, IFF, ESM, and datalink.
Nimrod R Mk2 – The RAF has three of these specially-equipped versions of the MR Nimrod to fulfil its requirement for long-range electronic reconnaissance missions.
The next changes came in 1982 with the Falklands War, when the Nimrods were required to operate up to 6440 km from their advance base at Ascension Island and carry the Marconi Stingray torpedo, 1000 lb bombs and the AGM-84A Harpoon anti-ship missile. Even air-to-air armament was added in the form of AIM-9G Sidewinders. Another large installation was an inflight refuelling probe to extend its endurance up to 19 hours, which saw large hoses laid over the floor inside the cabin. Placed under the floor when the conflict ended, this gave the Nimrod Mk.IIP code. At the same time GPS was installed in RAF aircraft. The AEW version was plagued with problems and never entered service, being placed in outside storage.

Models offered up four additional hardpoints externally to field even more potent air-to-surface missiles and
mine dispensing munitions. Crew accommodations vary per model. The MRA.Mk 4 (or “Nimrod 2000”) can house a base flight crew of two personnel along with 7 specialists in designated roles. Additionally, up to 13 relief crew members can be carried aboard for extended flights. The Nimrod MRA.4 can operate a 15 hours of endurance time.

Gallery

Comet 1
Engines: 4 x Ghost 50 turbojets, 4,450 lb. (2,020 kg.) thrust.
Range loaded with res: 2,030 sm.
Capacity payload: 14,000 lb.
Fuel cap: 7,050 Imp.G.
Max range with res: 2,610 sm.
Length 93 ft. (28.35 m.)
Wing span 115 ft. (35 m.)
Weight 105,000 lb. (45,540 kg.)
Pax cap: 36 44.
Max cruise speed: 490 m.p.h. (790 km.p.h.).
Cruise alt: 35,000 ft. (11,000 km.) fully loaded.
Range: 1,750 miles (2,800 km.).

De Havilland DH 106 Comet 1 A
Engines: 4 x DeHavilland Ghost 50 Mk 2, 22249 N / 2268 kp
Length: 93.012 ft / 28.35 m
Wingspan: 114.993 ft / 35.05 m
Max take off weight: 115021.6 lb / 52164.0 kg
Max. speed: 459 kts / 850 km/h
Range: 1728 nm / 3200 km
Crew: 3
Payload: 44 pax

Comet 2
Engines: 4 x Avon turbojets.
Range loaded with res: 2,610 sm.
Capacity payload: 14,000 lb.
Fuel cap: 7,050 Imp.G.
Max range with res: 3,700 sm.
Block speed: 444 mph.

Comet 4
Engines: 4 x RR Avon RA.29, 10,500 lb.
Wing span: 115 ft 0 in (35 m).
Length: 111 ft 6 in (33.99 m).
Height: 28 ft 4.5 in (8.65 m).
Max TO wt: 152,500 lb (69,235 kg).
Max level speed: 500 mph ( 800 kph).
Cruise speed 489 mph

Engines: 4 x Rolls-Royce Avon 525B, 46.7kN
Max take-off weight: 73482 kg / 162001 lb
Empty weight: 36430 kg / 80315 lb
Wingspan: 35.0 m / 114 ft 10 in
Length: 36.0 m / 118 ft 1 in
Height: 9.0 m / 29 ft 6 in
Wing area: 197.0 sq.m / 2120.49 sq ft
Cruise speed: 865 km/h / 538 mph
Ceiling: 10000 m / 32800 ft
Range w/max.fuel: 6700 km / 4163 miles
Range w/max.payload: 5350 km / 3324 miles
Crew: 4
Passengers: 72-102

Nimrod MR.1
Engines: Four 11,500 lb (5 217 kg) st Rolls Royce RB.168 Spey turbofan. ¬
Wingspan: 114 ft 10 in (35.0m).
Length: 126 ft 9 in (38.63m).
Wing area: 2121 sq.ft (197.0 sq.m).
Height: 29 ft 8.5 in (9.01 m).
Max TO wt: 192,000 lb (87090 kg).
Max cruising speed: over 500 mph (805 kph).
Max endurance: 12-14 hr.
Crew: 12.
Max level speed: 575 mph (926 kph).

Nimrod MR.2
Engine: 4 x R-R Spey 250 turbofan.
Installed thrust: 216 kN.
Span: 35 m.
Length: 38.6 m.
Wing area: 197 sq.m.
Empty wt: 39,000 kg.
MTOW: 80,500 kg.
Warload: 6100 kg.
Max speed: 930 kph.
Ceiling: 13,000 m.
T/O run: 1460 m.
Ldg run: 1620 m.
Fuel internal: 48,780 lt (+8590 lt).
Endurance: 12+ hr.
Air refuel: Yes.
Armament: Stingray torpedo or AGM-84 Harpoon.

Nimrod Mk.IIP
Engines: 4 x Rolls-Royce RB.168-20 Spey Mk.250 turbofans, 12,140 lb.
Span: 114 ft 10 in (35 m).
Length: 129 ft (39.31 m).
Empty wt: 86,000 lbs (39,009 kg).
MTOW: 192,000 lbs (87,090 kg).
Max speed: 500 kt.
Service ceiling: 42,000 ft.
Max Op alt: 37,000 ft.
Normal transit speed: 425 kts.
Ferry range: 9254 miles.
Endurance: 12 hr.
Crew: 13.

BAe / Hawker Siddeley Nimrod MRA.4
Engines: 4 x Rolls-Royce BR710 Mk 101 turbofan, 15,500lbs / 66218 N / 6750 kp thrust
Length: 126.74ft (38.63m)
Wingspan: 127.00ft (38.71m)
Wing loading: 91.23 lb/sq.ft / 445.00 kg/sq.m
Height: 31.00ft (9.45m)
Wing area: 2538.151 sqft / 235.8 sq.m
Empty Weight: 102,515lbs (46,500kg)
Max take off weight: 231271.4 lb / 104885.0 kg
Fuel capacity: 2959 gal / 11200 lt
Maximum Speed: 575mph (926kmh; 500kts)
Maximum Range: 6,903miles (11,110km)
Service Ceiling: 42,000 ft (12,802m)
Endurance: 15 h
Accommodation: 9 + 13
Hardpoints: 4
Payload: max 5500kg

Nimrod
DH-106 Comet

de Havilland DH 104 Dove / Devon

In 1944 R E Bishop and his team envisaged the DH104 as a successor to the Dtagon, Express and Rapide, and incorporated new construction techniques such as Redux bonding in the airframe and a tricycle undercarriage. A new low-wing monoplane which, with the exception of fabric-covered elevators and rudder, was of all-metal construction, and powered by two de Havilland Gipsy Queen engines, with constant-speed, fully-feathering, and reversible-pitch propellers. Standard accommodation as a transport was for 8 to 11 passengers.

DH 104 Devon / Dove Article

The prototype flew on 25 September1945, initially with an angular dorsal fin before it was replaced by a new dorsal fin and, much later of a redesigned elevator, and of a domed roof to give a little more headroom on the flight deck. Production aircraft were generally similar to the original prototype.

The 15th production DH.104 Dove, CF-DJH, was the only Dove to be flown with twin float undercarriage.

CF-DJH at Toronto, Canada, 1947

The Dove production variants resulted from differing Gipsy Queen powerplants, these including the 246kW Gipsy Queens 71 and 70-3 powering the prototype and the Dove 1/2 respectively; 254kW Gipsy Queen 70-4 in the Dove 1B/2B; 283kW Gipsy Queen 70-2 in the Dove 5/6, and 298kW Gipsy Queen 70-3 in the Dove 7/8.

The Dove 1B powered by 305 hp DH Gipsy Queen 70 was the most prolific model, followed by 128 Dove 4/5, built as the Devon/Sea Devon. The Mk.4 was a military variant of the Dove, with two crew and 8 passengers.

Up to 30 were in Service with the RNZAF during 1946-80.

RNZAF DH 104

In the course of its long life, the type underwent significant improvements with the final production version, the Dove 7/8 having an enlarged cockpit, Heron-style canopy and 400HP Gipsy Queen Mk 3 engines.

Doves in the United States were marketed as the Custom 800.

DH 104 production ran to 542 aircraft before production ended in 1968, mak¬ing it Britain’s best selling commercial air¬liner.

Just over 100 were supplied under the name Devon to many air forces, including the RAF, and a small number went to the Royal Navy with the name Sea Devon.

A number of Dove conversions carried out subsequently by Riley Aircraft in the USA as the Riley Turbo Executive 400 introduced 298kW Avco Lycoming IO-720-A1A flat-eight piston engines.

Riley Turbo-Exec 400 N880JG (04491)

Carstedt went even further with the Carstedt CJ-600A Jet Liner with a fuselage stretch by 7 ft 5 in (2.21 m) to seat up to 18 passengers and two 575 SHP / 451kW Garrett TPE-331 turboprops. The type was supplied primarily to Apache Airlines.
Another version of the Dove was produced by Texas Airplane Manufacturing Co. that employed 705-eshp turboprops and a stretched fuselage.

Gallery

DH104 Mk.1
Engines 2 x D.H. Gipsy Queen 70-2, 330 hp
Length 39 ft 2 in (11.96 m.)
Wing span 57 ft. (17.37 m.)
Weight empty 6,325 lb. (2,870 kg).
Max wt: 8800 lb (3992kg).
Seats 2 crew and up to 11 passengers
Maximum speed: 230 mph (370 kph)
Cruise speed 200 mph (320 kph)
Ceiling 21,700 ft. (6,600 m) full loaded
Maximum range: 880 miles (1415 km)

DH104 Mk.1B
Engines: 2 x DH Gipsy Queen 70-3, 345 hp.

Dove 7
Engines: 2 x Gipsy Queen Mk 3.

Dove 7
Engine: 2 x Havilland Gipsy Queen 70-3 inline, 298kW, 400 hp
Max take-off weight: 4060 kg / 8951 lb
Empty weight: 2985 kg / 6581 lb
Wingspan: 17.37 m / 56 ft 12 in
Length: 11.99 m / 39 ft 4 in
Height: 4.06 m / 13 ft 4 in
Wing area: 31.12 sq.m / 334.97 sq ft
Max. speed: 378 km/h / 235 mph
Cruise speed: 261 km/h / 162 mph
Service Ceiling: 6615 m / 21700 ft
Range: 1891 km / 1175 miles
Crew: 2
Payload: 11 pax

Dove 8
Engines: 2 x Gipsy Queen Mk 3, 400 hp.

Riley Dove
Engines: 2 x Lycoming IO-720, 400 hp.

Carstedt CJ-600A
Engines: two x Garrett TPE-33 1 turboprops, 575 shp

de Havilland DH 103 Hornet

Sea Hornet F.Mk.20

The de Havil¬land Hornet was a private-venture new design as a response to the need for a long-range single-seat escort fighter for service in the Pacific to Specification F.12/43. Development began in 1942, the prototype making its maiden flight on 28 July 1944, but the Hornet suffered heavily through post VJ-Day cancellations.
It entered production at the end of 1944 and deliveries were made to the RAF from February 1945. Four versions were produced for the RAF as: the Hornet F.1 medium-range single-seat fighter with four 20mm cannon and provision for carrying two 450kg bombs or two 455 litre drop tanks; Hornet PR.2 long-range unarmed photographic reconnaissance aircraft; Hornet F.3 long-range single-seat fighter with the increased fuel tankage of the PR.2; and Hornet FR.4 with a vertically mounted camera. More than 200 were built.
The Hornet entered service as a front line fighter in August 1946 until April 1951. The Hornet was the fastest twin piston-engined operational combat aircraft in the world while in service. Operated in Malaya in the early 1950s, the type was finally withdrawn from service in 1955.

DH 103 Sea Hornet

Hornets equipped four UK Air Defence Squadrons, 19, 41, 64 and 65. Flying training was carried out by 226 Operational Conversion Unit (OCU) and by the Hornet Conversion Flight, the latter being based at Linton on Ouse.

Consideration of the possibility of acquiring a carrier-based variant resulted in the testing of three Hornet FMk 1 aircraft in 1944-5, the third of these being fully navalized. It was fitted with folding wings and had provision for deck arrester and RATO gear. Air-draulic shock-absorber legs replaced the rubber-in-compression legs to eliminate bounce in carrier landings. Such was the success of these trials that a production order for 79 Sea Hornet F.Mk 20 fighters soon followed, deliveries getting under way to No. 801 Squadron in June 1947 and joined HMS Implacable in 1949. A carrier-based medium-range single-seat fighter/reconnaissance/strike aircraft, capable of carrying eight 27kg rockets, bombs, mines and drop-tanks. Armament was basically similar to that of the RAF Hornet, and this model remained in service until 1951 in a front-line capacity. The next version was the Sea Hornet NF.Mk 21 night-fighter, whose development began in 1946 although it was not until January 1949 that this attained operational status with the Fleet Air Arm fitted with an A.I. radar scanner in a thimble radome in the nose, equipping No. 809 Squadron at Culdrose until 1954, when it finally gave way to jet-powered equipment in the shape of the de Havilland Sea Venom. Subsequently, the Sea Hornet NF. Mk 21 was reassigned to the training of night-fighter radar operators, a task it performed until 1956 when the handful of remaining aircraft were scrapped. Production of the Sea Hornet was completed with the Sea Hornet PR.Mk 22 for photographic reconnaissance, about two dozen examples being completed, all of which employed a pair of F52 cameras for use by day and a single K19B camera for night work. In order to undertake the reconnaissance mission, the cannon armament was deleted, its place being filled by cameras.

In all, a total of 391 aircraft were produced of which 180 were for the Royal Navy and the production run comprised: two prototypes, sixty F.Mk 1, five PRMk 2, 132 Mk 3, twelve FMk 4, 79 FMk 20 (RN), 78 NMk 21 (RN) and 23 PRMk 22 (RN).

DH Hornet 64 Sqn RAF

Gallery

Hornet F. Mk 3
Engines: 2 x Rolls-Royce Merlin 130/131, 1544kW
Take-off weight: 9480 kg / 20900 lb
Empty weight: 5840 kg / 12875 lb
Wingspan: 13.72 m / 45 ft 0 in
Length: 11.18 m / 36 ft 8 in
Height: 4.32 m / 14 ft 2 in
Wing area: 33.54 sq.m / 361.02 sq ft
Max. speed: 760 km/h / 472 mph
Ceiling: 10670 m / 35000 ft
Range: 4820 km / 2995 miles
Armament: 4 x 20mm cannons, 900kg of weapons
Crew: 1

DH 103 Sea Hornet
Engines: 2 x RR Merlin 133/134, 2030 hp
Wingspan: 45 ft / 13.71 m
Length: 37 ft / 11.28 m
Max speed: 462 mph / 744 kph
Crew: 1-2
Armament: 2 x 20 mm cannon

Sea Hornet F.Mk 20
Engines: two 2,030-hp (15 14-kW) Rolls-Royce Merlin 133/134 inline piston.
Maximum speed 748 km/h (465 mph) at 6705 m (22,000 ft)
Service ceiling 10,670 m (35,000 ft)
Range 2414 km (1,500 miles) with auxiliary fuel.
Empty weight 6033 kg (13,300 lb)
Maximum take-off 8405 kg (18,530 lb)
Wingspan 13.72 m (45 ft 0 in)
Wing area: 361.025 sq.ft / 33.54 sq.m
Length 11.18 m(36 ft 8 in)
Height 4.32 m (14 ft 2 in)
Wing area 33.54 sq.m (361 sq ft).
Armament: four 20-mm cannon, eight 27-kg (60-lb) rockets or two 454-kg (1,000-lb) bombs.

de Havilland DH 100 Vampire / Sea Vampire / Sud-Est SE 530 / 535 Mistral

Vampire FB.6

The design began in 1941, to satisfy Air Ministry Specification E.6/41 for an interceptor fighter to be powered by the then-developing Halford-designed de Havilland H-1 Goblin turbojet of 2,700 lb St (1 226 kgp), the twin-boom configuration of this aircraft was virtually dictated by the chosen power plant. This was because a single turbojet was to provide the total thrust; as this was very limited in early engines, it was necessary to ensure that power loss from the jet tailpipe was restricted to an absolute minimum by keeping the tailpipe as short as possible.

DH 100 Vampire Article

The first flight of the prototype, made by Geoffrey de Havilland jr, took place at Hatfield in Hertfordshire on 20 September 1943 powered by a 12kN de Havilland Goblin turbojet, just 16 months after the start of design the aircraft (LZ548/G) featuring pointed fins. Two further prototypes (LZ551/G and MP838/G) quickly joined the flight programme, the latter car¬rying the planned armament of four 20 mm Hispano cannon under the nose which, like the Mosquito, was of plywood and balsa construction, the remainder of the aircraft being metal. Like the Mosquito’s fuselage, this was built in two half-shells which were joined top and bottom. The monoplane wing was an all-metal structure, incorporating the engine air intakes in the wing roots, split trailing-edge flaps, air brakes and ailerons. The pilot, was seated well forward in the central nacelle beneath a three-piece canopy (replaced later by a bubble canopy).

The name was changed from Spider Crab to Vam¬pire when on 13 May 1944 a contract for 120 production examples of the Vam¬pire F.Mk 1 (later increased to 300) was placed for manufacture by the English Electric Company, Preston. The first production aircraft (TG274/G), with square cut fins and Goblin turbojet (as the Halford engine was named) was flown at Samlesbury on 20 April 1945, becoming the first British fighter with a speed of over 805 km/h (500 mph). Pre service and handling trials occu¬pied the remainder of 1945, however, and the Vampire saw no operational service during the war.

The first production F.1 Vampire was powered by the same engine as the prototype, as were the next 39 aircraft. Subsequent F.1 had 3,100 lb / 13.8kN Goblin Gn.2 engines and a pressurised cockpit, the first 50 production Vampires lacking this feature. Entering service too late to make a contribution to World War II, the first squadron to operate the Vampire was 247 Squadron at Chilbolton in Hampshire, taking delivery of their first aircraft in March 1946 and becoming operational in April.

Production of the Vampire F Mk I, with 3,100 lb St (1407 kgp) Goblin II, was undertaken by English Electric, which built a total of 174 for the RAF and 70 for Sweden’s Flygvapen, delivered from 1946; Switzerland’s Flugwaffe acquired four Vampire Is for evaluation in 1946 and El Cuerpo de Aviaçion Militar of Dominica acquired 25 from Flygvapnet in 1952. One supplied to RCAF.

In 1948 John Cunningham established an altitude record in the Ghost-Vampire at 59,492 feet.

The Vampire 6 was specially evolved to meet Swiss requirements. This variant had clipped wings and powered by a Goblin 3 of 3300 lb thrust. It was designed for combined fighter and ground attack roles.

Based on the positive test results achieved with the DH-100 Mk 1, the decision for a new combat aircraft foe the Swiss Air Force was at the end of 1948 and a series of 75 DH-100 MK6s were ordered. In May 1949, the first aircraft were taken over and replaced obsolete Me109 E-1/3 and Morane D-3800/01. All airplanes were flown to Switzerland from Hatfield, England to Emmen without any incidents. The 75 aircraft (J-1005 to J-1079) were delivered in the years 1949 and 1950.

A year later licence production of a second series of 100 aircraft by FFA began. The 100 licence built DH-100 Mk 6 Vampire (J-1101 to J-1200) were in service from 1951 onwards. Until 1960, all vampires were still in operation without Martin Baker’s seats. Against the heat in the summer, due to the insufficient air conditioning, a light flightsuit and white helmets were introduced. At the beginning of the 1960s, the vampires were equipped with a Martin Baker sling seat, an emergency package, a new joystick and a new cabin roof with single glazing.

The DH-100 Mk 6 Vampire were operational from 1949 to 1973, but most aircraft were retired during 1968/1969. In Switzerland, they were in use from 1949 to 1990. On 12th June 1990, the last Vampire at the Emmen airfield were taken out of the pilot school. A respectable number was written off in 1974, but liquidations were still carried out until 1988. From 1953, two-seater (DH-115) were also used.

The Vampire F Mk 3 was similar to the Mk I but carried 100-imp gal (454-l) drop tanks and had a revised tail unit with lower tailplane, rounded rudders and a tailplane/fin acorn fairing. Production by EEC totalled 117 for the RAF and 85 for the RCAF. The RNoAF evaluated four Mk 3s and the Fuerza Aérea Mexicana acquired 15 from the RCAF in 1961. To adapt the Vampire for ground attack duties, de Havilland introduced a strengthened and clipped wing (first flown on a Mk I airframe on 29 June 1948) to produce the FB Mk 5. With the basic airframe of the F Mk 3 and a 3,100 lb st (1 407 kgp) Goblin 2 or 4,400 lb st (1 998 kgp) Goblin 2/2 turbojet, the Vampire FB Mk 5 had a longer-stroke undercarriage and in addition to the four 20-mm British Hispano cannon could carry, on wing strong points inboard and outboard of the booms, eight 60-lb (27-kg) RPs and two 500-lb (227-kg) or two 1,000-lb (454-kg) bombs, or two 200 Imp gal (9091) drop tanks. The first of 888 FB Mk 5s for the RAF flew on 23 June 1948; some of these were diverted either new or secondhand to the RNZAF, SAAF, Armée de lAir, Aeronautica Militare Italiana and the Lebanon Air Force. Specific export versions similar to the FB Mk Shad the 3,350 lb st (1 521 kgp) Goblin 3 and improved performance; these included the FB Mk 50 for Sweden’s Flygvapnet and the FB Mk 52 built for Egypt, Finland, Iraq, India, New Zealand, Norway and Venezuela.

In New Zealand it became the RNZAF’s first jet fighter, with 58 examples serving between 1951 and 1972 before their replacement by the Strikemasters and Skyhawks.

In the early 1950s, De Havilland produced a two-seat night-fighter version, the NF10, and these aircraft formed the backbone of the RAF’s night-fighter force until the arrival of the Meteor NF11. A total of 95 two-seat NF.10 Vampire night-fighters also served in an interim capacity with the RAF from 1951, pending the introduction of Meteor and Venom night fighters.

The T11 trainer version was a development of the NF10 and the type continued in service until well into the 1980s.

The last major variant was the Vampire T.11 two- seat trainer, over 800 of which were built.

The Royal Navy had a small number of F.20 Sea Vampires, generally similar to the RAF’s FB.5, and 74 T.22 two-seat trainers derived from the T.11.

Sea Vampire F.20 1948

Earlier Sea Vampire were hooked Mk.1, and although the F.20 is virtually a hooked Mk.3, the wings have been clipped, and the aircraft modified to full Naval standard.

Foreign licence production comprised 100 FB Mk 6 by FFA in Switzerland; 80 FB Mk 52A by Macchi and Fiat in Italy; 183 by SNCASE in France in addition to 67 assembled from British components and 281 by HAL in India including 34 from imported components.

Production of single-seat Vampires for the RAF ended with 381 FB Mk 9s, essentially a FB.Mk.5 with cockpit air conditioning for Far East service and 3350 lb thrust. Seventeen ex-Swedish FB Mk 50s were transferred to Dominica in 1956, and ex-RAF Mk 9s went to Rhodesia (5), Jordan and Ceylon.

Three Vampire Is were fitted with 4,500 lb St (2043 kgp) Rolls-Royce Nene 1 engines to Specification F. 11/4S for evaluation but no production of the proposed F Mk II to this standard was undertaken in the UK. After further modification by Boulton Paul to enlarge the wing-root air intakes, one of the three Nene-engined aircraft was shipped to Australia to become the pattern aircraft for 57 Vampire F Mk 30s built by de Havilland for the RAAF. With a 5,000 lb st (2270 kgp) Nene 2-VH assembled in Australia by CAC, the first Vampire 30 flew on 29 June 1948, this and subsequent aircraft having the same tail unit as the British Mk 3 and “elephant ear” intakes above the rear fuselage. Twenty-three FB Mk 31s had a similar airframe to that of the RAF’s FB Mk 5, and 28 Mk 30s were converted to the same standard. Two examples in 1951 became F Mk 32s with cockpit air conditioning, as in the British Mk 9, and ejection seats. The Mk T.35 Vampire was licence built at Bankstown during the 1950s for the Royal Australian Air Force and is outwardly identical to the de Havilland T.11 Vampire. One major difference is that the T.35 has hydraulic “maxaret” anti skid brakes compared to the T.11 s pneumatic system, and the engine is slightly different, being a Mk.5 Goblin compared to the Mk.11 engine. The Mk.T.35 was equipped with Martin Baker Mk.IB ejection seats.

On 14 July 1948 six Vampire 3s of No.54 Squadron became the first ever jet aircraft to fly across the Atlantic under their own power.

Vampire FB.5 VV454 was fitted with an extended jet pipe to test a reheat (afterburner) system for the Goblin 2, with extended tail bumpers to stop the jet pipe touching the ground.

FB.5 VV454 testing reheat

Only the F. 1, and the Nene powered F.2 (not adopted by the RAF, but later Nene powered aircraft were built under licence in Australia and France, the latter being named Mistral) had the original, squared off style tail. The F.3 had a smaller, more rounded type of a shape that was almost a De Havilland trademark. As for the two seaters: these initially had a tail similar to the F.3, etc, but with taller rudders, latter the acorn fairing was deleted and the fin area increased so it extended forward in a gentle curve. Up to the F.3 the wingtips were rounded, but on the FB.5 fighter-bomber the rounded portion was deleted, the result being a “clipped” wing of slightly reduced span.

After assembling 67 Vampire FB Mk 5 single-seat fighters from British-supplied components and licence-building a further 120 aircraft in their entirety, the Societe Nationale de Constructions Aeronautiques de Sud-Est (SNCASE) began production of a more powerful version of the basic aircraft. Assigned the designation Vampire Mk 53 by the parent company and given the appellation of SE 530 by Sud-Est, this was developed for the Armee de l’Air. It utilised the basic Mk 5 airframe mated with the 2270kg Hispano-built Nene 102, the wing root intakes being enlarged and the split-trunk intake of the Hawker P.1040 being adapted to provide the extra air demanded for the rear face of the Nene’s double-sided impeller. Fuel tankage was increased, cabin pressurisation introduced and the pilot was provided with an SNCASO ejection seat. A pre-series of four aircraft was built, the first of these flying on 1 April 1951. Baptised Mistral, the type entered series production in SE 532 form, the first flying in December 1951 and 97 being built. These were followed by 150 examples of the SE 535, the last of which was delivered on 25 March 1954. The SE 535 was powered by the Nene 104 with similar rating to the Nene 102B of the SE 532, and, in addition to its four 20mm HS 404 cannon, could carry eight T-10 or HVAR rockets, or two 450kg bombs. The Mistral internal fuel tanks in the fuselage and wings can be supplemented by two large underwing tanks. The Mistral entered Armee dl’Air service in 1952 and was finally withdrawn in 1961.

Deck-landing trials with one of the prototype D.H. 100 Vampire fighters began aboard HMS Ocean as early as 3 December 1945, these being the first-ever carrier operations by a pure jet aircraft. Successful trials with two fully-navalised Vampire I conversions led to an order for 30 Sea Vampire F Mk 20s, the first of which flew in October 1948. Armed with four 20-mm cannon and with the basic airframe of the Vampire FB Mk 5, they served primarily in a training role to give Fleet Air Arm pilots jet experience. Six RAE Vampire F Mk 3s were converted to Sea Vampire 21s, with reinforced undersides and armament removed, for use in flexible deck landing trials at RAE Farnborough and on HMS Warrior in 1947-55.
The total built include 804 in UK, fifty in India and 109 in Australia.
The Sea Vampire T.22 land-based pilot trainer was ordered in 1952 by the RAAF. Thirteen were delivered, the first in June 1954 and the last in August 1959.
A total of 85 Vampires were delivered to the RCAF between 1948 and 1950. They were built for the RCAF in a contract dated June 13, 1946, the first aircraft flying on June 3, 1947. Construction of the entire batch was carried out by English Electric at their Preston, Lancashire, plant with test flying undertaken at Samlesbury. They received RCAF numbers 17001 to 17042 and 17044 to 17086. After their retirement, 27 were sold to Fliteways Inc at West Bend, Wisconsin, possibly in early 1958.
The President of Fliteways Ine, Merle C Zuelilke, wanted to introduce these former military jets onto the private market as fast hacks or executive aircraft some had already been sold to private owners. However, the American Federal Aviation Administration (FAA) was not keen on the idea of Cessna/Piper Cub pilots zipping about in jets, and so introduced a number of restrictions. New Vampire F.3 owners suddenly found that they could only register them in the experimental/exhibition category as was the case with N6877D (formerly 17069, constructor’s number EEP 42387) which meant that every flight had to be authorised ahead of time, be made under Visual Flight Rules conditions, and be registered on a flight plan. Intended destinations, be they airports or runways, also had to be approved by an FAA safety agent before a flight could take place. Not surprisingly the FAA killed the market stone dead in the US, leaving Fliteways with a number of Vampires it could not sell.
At about the same time (1960) the Mexican Air Force was looking for a fighter aircraft.
The aircraft were flown to Mexico in groups initially by Minnesota Air National Guard pilots, but this idea was abandoned after the local ANG Commanding Officer suffered an engine blow out in FAM 4 (N6875D, formerly RCAF 17019). This was later repaired at a cost of $9,000 for a new wing, nose landing gear, new engine, electrical system and hydraulic system. It is reported that Mr Leo Geib of West Bend ferried most of the aircraft in Mexico and helped to check out the Mexican pilots. One group of FAM Vampires (FAM 13, FAM 6 and FAM 1) were photographed during their stopover at Love Field, Dallas, Texas in February 1961, as they made their way to Mexico.
It was reported in the Mexican Air Force magazine Anuahuac, that by February 14, 1961, 12 of the 15 Vampires had been delivered to BAM 1 (Base Aerea Militar Military Air Base No 1) at Santa Lucia, outside Mexico City. Eventually all 15 were delivered, but it appears that one was damaged en route at Acapulco, Gueffero repairs to FAM 6 cost $2,000 and required, among other things, new landing gear. Only 14 Vampires were flown operationally, the 15th aircraft was possibly used as a spares source. The number FAM-15 was later allocated to one of the two Mk 11 trainers. The Escuadron Aireo 200 was chosen to receive the Vampires.
One thing that the Escuadron Aireo Jet de Pelea 200 lacked was a suitable training aircraft to convert pilots to the Vampires. By 1962 the Mexican Air Force had acquired two de Havilland Vampire T.11 two seat trainers, one being WZ414 which was the first production Mk 11 to enter service in the RAF in 1952. It had been built by de Havilland at Christchurch and spent some time at the Aeroplane & Armament Experimental Establishment at Boscombe Down and with the Empire Test Pilot School. It was declared a non effective airframe on January 29, 1960 and sold to Shackleton Aviation on January 5, 1962. The other was XD439 (built by de Havilland at Chester) which was delivered to the RAF in 1954, and had once served at the Central Navigation and Control School at Shawbury. It was retired to 19 Maintenance Unit at St Athan on May 11, 1959 and was sold to Shackletons on the same date as WZ414. Their date of arrival in Mexico is not known.
In 1970 fears over safety, grounded the Vampires even the Mk 11 trainers were considered to be unsafe as there were no more stocks of cartridges for their ejection seats. This occurred during the tenure of Gral Brig P A Jose Vergara Ahumada, as chief of the air force. For many years the surviving F.3s and the two T.11 s were stored in one of the hangars at BAM 1. It was later reported that some of the F.3s were sent as training aids to the Aviation Mechanic School at BAM 5 at Zapopan, Jalisco. Others provided background scenery for the 1969 Mexican movie Aguilas de Acero (Iron Eagles) filmed at BAM 1.
Years later some of the aircraft were scrapped one of the Mk.IIs met a similar demise, but the cockpit section went to a private collector in Mexico City. The other Mk 11 is preserved at the main army base inside Mexico City where, for many years, there was also Mk 3 No 5 acting as gate guard, wearing an incorrect camouflage scheme. It was removed in 1992, restored and, then put on display in the grounds of the new Mexican Air Force HQ building in Mexico City. No 13 is on display at the Military Aviation School (Colegio del Aire) at BAM-5 at Zapopan, as a tribute to the first jet fighters of the Fuerza Airea Mexicana.

3268 DH-100 Vampires were built, a quarter of them under licence.

Gallery

Vampire
Engine: one 1225 kg (2,700 lb) thrust de Havilland Goblin 1 centrifugal-flow turbojet.
Max speed 824 km/h (512 mph) at 10365 m (34,000 ft)
Initial climb 1235 m (4,050 ft) per minute
Service ceiling 12620 m (41,400 ft)
Range 1190 km (740 miles)
Empty weight 2803 kg (6,180 lb)
Maximum take off 4627 kg (10,200 lb)
Wing span 12.19 m (40 ft 0 in)
Length 9.37 m (30 ft 9 in)
Height 2.69 m (8 ft 10 in)
Wing area 24.71 sq.m (266.0 sq.ft)
Armament: four 20 mm Hispano cannon

Vampire 1
Engine: 1 x de Havilland Goblin 2 engine, 3,100 lbst (1,407kgst).
Max take-off weight: 3890 kg / 8576 lb
Empty weight: 2890 kg / 6371 lb
Wingspan: 12.2 m / 40 ft 0 in
Length: 9.4 m / 30 ft 10 in
Height: 2.7 m / 8 ft 10 in
Wing area: 24.7 sq.m / 265.87 sq ft
Max. speed: 869 km/h / 540 mph
Range w/max.payload: 1175 km / 730 miles
Crew: 1
Armament: 4 x 20mm cannons

Vampire 1
Engine: 1 x de Havilland Goblin, 2700 lbst
Wingspan: 11.58 m / 38 ft 0 in
Length: 10.49 m / 34 ft 6 in
Max. speed: 885 km/h / 531 mph
Crew: 1

F Mk 3
Engine: One 3,100 lb thrust de Havilland Goblin D.Gn.2 turbojet
Span, 40 ft 0 in (12,20 m).
Length, 30 ft 9 in (9,37 m).
Height, 6 ft 3 in (1,9 1 m).
Wing area, 266 sq ft (24,71 sq.m).
Empty weight, 7,134 lb (3239 kg).
Normal loaded weight, 12,170 lb (5 525 kg).
Maximum weight: 11,970 lb (5429 kg)
Max speed, 531 mph (854 km/h) at sea level and 505 mph (813 km/h) at 30,000 ft (9 145 m).
Range, 1,145 mls (1 842 km) at 30,000 ft (9 145 m) at 350 mph (563 km/h).
Initial climb, 4,375ft/min (22,2 m/sec).

FB Mk 5
Engine: de Havilland Goblin turbojet, 3100 lb thrust.
Max speed, 530 mph (846 km/h) at sea level, 540 mph at 20,000 ft, 482 mph (772 km/h) at 40,000 ft (12200 m).
Range, 1,145 mls (1 842 km) at 30,000 ft (15 150 m) at 350 mph (563 km/h).
Empty weight, 7,253 lb (3 310 kg).
Max loaded weight, 12,360 lb (5632 kg).
Span, 38 ft 0 in (11,50 m).
Length. 30 ft 9 in (9,37 m).
Height, 6 ft 3 in (1,91 m).
Wing area, 261 sq ft (24,25 sq.m).
Armament: 4 x 30mm mg + 2000 lb disposable stores.

Vampire Mk. 6
Engine: de Havilland Goblin 2, 3,100lbs (1,405kg)
Wing Span: 40ft (12.2m)
Length: 30ft 9in (9.4m)
Height: 8ft 10in (2.7m)
Speed: 531mph (855km)
Ceiling: 43,500ft (13,260m)
Max ROC: 15,0 m/s
Endurance: 1 hr

FB Mk.9:
Engine: 3350 lb thrust.

Vampire Mk.35
Engine: Goblin centrifugal flow.
Mo: 0.78M.
Seats: 2

Vampire T.11
Engine: 1 x 3,500 lbs.t. (1588 kgp) de Havilland Goblin 35.
Max speed, 549 mph (883 kph) at 20,000ft (6 096 m)
Cruise, 403 mph (649 kph)
Initial climb, 4,500 fpm. (22.86 m/sec)
Range, 853 mls (1373 km).
Empty weights: 7,380 lb (3 347 kg)
Loaded weight: 12,920 lb (5 860 kg).
Wingspan 38 ft (11.58 m)
Length, 34 ft 5 in (10.49 m)
Wing area, 262 sq.ft (24.33 sq.m).
Armament: Two 20 mm cannon.

Sea Vampire F.Mk.20
Span, 38 ft 0 in (11,50 m).
Length. 30 ft 9 in (9,37 m).
Height, 6 ft 3 in (1,91 m).
Wing area, 261 sq ft (24,25 sq.m).
Max speed, 526 mph (846 km/h).
Time to 25,000 ft (7620 m), 10 min.
Range, 1,145 mls (1 842 km) at 30,000 ft (9 144 m) at 350 mph (563 km/h).
Loaded weight, 12,660 lb (5 748 kg).

Sea Vampire T.22
Engine One 3,500lb thrust De Havilland Goblin 35 centrifugal turbojet
Empty weight 7,380 lb
Loaded weight 12,920 lb
Wing Span: 38 ft 10 in
Length: 34 ft 5 in
Height: 6 ft 2 in
Crew 2
Initial Rate of Climb: 4,500 ft per minute
Ceiling: 43,000 ft
Speed: 538 mph
Range: 623 miles
Armament 2 x 20 mm cannon , 8 x 60lb rockets

SNCASE SE 535 Mistral
Engine: Hispano-built RR Nene 104, 5000 lbst
Span: 38 ft 0 in (11,50 m).
Length: 30 ft 9 in (9,37 m)
Height: 6 ft 2 in
Wing area: 262 sq ft (24,25 sq.m).
Empty weight: 7,665 lb (3840kg).
Loaded weight (with drop tanks): 12,643 lb (5740 kg).
Max take-off weight: 13,448 lb / 6100 lb
Max speed: 575 mph (925 km/h) at sea level and 557 mph (896 kmh) at 19,685 ft (6000 m).
Initial climb: 7,086 ft/min (36 m/sec).
Service ceiling: 49,200 ft
Range w/max.fuel: 1118 miles / 1800 km
Armament: 4 x 20 mm cannon
Hardpoints: 2 x 1000 lb

Sud-Est SE 530 Mistral

de Havilland

Geoffrey de Havilland built his first (unsuccessful) aircraft in 1909. His second, flown in 1910, was bought by the War Office, and de Havilland was taken on as designer at the Balloon Factory (later Royal Aircraft Factory), where between 1911 and 1914 he designed the F.E.2, S.E.1, S.E.2, B.E.1, and B.E.2. In 1914 he joined the Aircraft Manufacturing Company at Hendon, designing the D.H.2 pusher fighter, D.H.3, and D.H.10 twin-engined bombers, D.H.5 fighter, and D.H.4 day bomber. The latter was extensively built in the USA. The D.H.9 and 9a were variations; the 9a equipped post-war RAF bomber squadrons and it, too, was built in the USA. Nearly 3,000 were constructed in Russia as the R-1.

Geoffrey de Havilland Article

The Aircraft Manufacturing Co. was sold in 1919 to the B.S.A.-Daimler group who, disappointed at the failure of air transport in 1919-20, shut the firm down. Almost immediately de Havilland and C.C.Walker, financed largely by Holt Thomas, out of money which he got by selling B.S.A. shares which he received in payment for the A.M.C. Ltd, started de Havilland Aircraft Co. Ltd. Airco name was temporarily revived January 1958 for production of D.H.121 jet transport.

The first aeroplane built at Stag Lane was the DH.18.
The D.H.53 Humming Bird ultralight was the best entrant in the 1923 Air Ministry Light Aeroplane competition, but de Havilland realised that their passion for lightness was an error, and in 1925 produced the first Moth to more sensible proportions. It was sold all over the world. A number of cabin monoplanes and a military version, the Tiger Moth, followed; over 8,000 Tigers were built for various air forces.
The three-engined D.H.66 Hercules was flown by Imperial Airways from 1926, and in the 1930s many domestic and foreign airlines used the twin-engined D.H.84/89 Dragon/Dragon Rapide and four-engined D.H.86 Express.
In 1934 de Havilland designed the all-wood D.H.88 Comet twin-engined racer for entrants in the “MacRobertson” England-Australia race. At a fixed unit price of GBP5,000 this gamble paid off; three were entered, and one of these won the speed prize. By 1939 the firm was producing the D.H.91 Albatross, a fast airliner with four engines; the twin-engined D.H.95 Flamingo feederliner and the diminutive D.H.94 Moth Minor. All production of these ceased at the outbreak of war, which also cut short a promising bombertrainer, the D.H.93 Don. In 1938 work started on a fast unarmed wooden bomber, the D.H.98 Mosquito. It became one of the most versatile aircraft of its time, and by the end of the war a single-seat fighter version attained a speed of 760km/h. The Vampire, de Havilland’s first turbojet fighter, Venom, Sea Venom and later Sea Vixen, served for a decade after the war.

Geoffery de Havilland in a Vampire cockpit

The other problem arising from the cancelled Don order was the under-utilisation of woodworking skills at the de Havilland factory. To compensate the Company, on 2nd September 1938 the Air Ministry awarded them orders for a large batch of Tiger Moths, some more Queen Bees, plus a contract to build 150 all wooden Airspeed Oxford trainers for the RAF. When Geoffrey de Havilland read the letter, he saw red – de Havilland’s did build somebody else’s aeroplane. de Havilland gave Nixon a simple order – “Buy that company!”

As it transpired, this order took some doing and it would be several years before de Havilland’s owned Airspeed Ltd, of Portsmouth. Airspeed joined de Havilland in 1951.
Back in civil work, the company produced the twin-engined Dove, four-engined Heron and, in 1949, the first jet airliner in the world, the D.H.106 Comet. The Comet 1 ran into constructional problems, but the Mark IV achieved success. The last DH designs were the D.H.121 Trident, a three-engined airliner for BEA, and the D.H.125 executive jet (both first flown 1962). Both were still in production in 1978, long after the company’s absorbtion into the Hawker Siddeley Group in 1960, and the D.H.125’s successors were still in production at the turn of the new century.

de Havilland Sprite DSpr.2 / Super Sprite DSpr.4

The Sprite was a British rocket engine built by de Havilland for use in RATO applications. For RATO use only a short burn time is required, with simplicity and light weight as major virtues. The intended market was for assisting take-off of de Havilland Comet 1 airliners (as hot and high operations in the British Empire were considered important) and also for V bombers carrying heavy nuclear weapons. 30 successful test flights were carried out by Comets, from May 1951, but gas turbine performance improved rapidly, and so RATO was not required in service.

A hydrogen peroxide monopropellant was used, decomposed into oxygen and steam over a metallic calcium catalyst. The maximum thrust was 5,000 lbf (22 kN), varying over the 16 second burn time for a total impulse of 55,000 lbf (240 kN) seconds. Propellant capacity was 39 gallons. The dry weight was 350 lbs.

The DSpr.2 used a silver-plated nickel-gauze catalyst, tested in Comets during April 1952. A technology update then took place with the proving of silver plated nickel gauze packs as catalysts with the establishment of optimum loadings and flows. This practice was replicated in all future applications with the catalyst no longer consumed. In April 1952 the DSpr.2 proved this modification impressively in Comet demonstration with clean exhaust. The next stage was pursued with the Super Sprite (DSpr.4) following the ATO development precedent with ‘hot’ operation but now enhanced in simplicity by ability to inject kerosene fuel once chamber pressure was established by the catalysed peroxide flow. The units, flight approved in August 1953, reverted to the practice of being parachuted after firing for routine re-use in service operations with the Vickers Valiant V bomber.

The Super Sprite DSpr.4 was a re-development of the Sprite application, using a significantly different ‘hot’ propellant technology, that of hydrogen peroxide / kerosene. Although the peak thrust was actually reduced (4,200 lbf / 18.7kN), burn time was 2.5 times longer (40 seconds), with a proportionate increase in total impulse (120,000 lbf seconds). Propellant capacity was 60 gallons (approx.).

For simplicity, there were no fuel pumps and the tanks were pressurised by nitrogen from nine cylinders wrapped around the combustion chamber.

The Super Sprite was packaged as a self-contained engine in its own nacelle, jettisoned after take-off and retrieved by parachute. Inflatable air bags cushioned its impact with the ground. To obtain a clean separation from the carrier aircraft, the production engines fitted to the Vickers Valiant had a small canard vane at the nose, pitching the nacelle downwards on separation.

De Havilland regarded the 166 units manufactured as a standard production item, supported by their Service Department alongside piston and turbojet engines. It was the first rocket engine to gain formal type approval.

Super Sprite DSpr.4
Super Sprite DSpr.4

de Havilland PS.23 / PS.52 Gyron / Halford H-4

de Havilland Gyron

The de Havilland PS.23 or PS.52 Gyron, originally the Halford H-4, was Frank Halford’s last turbojet design while working for de Havilland. Intended to outpower any design then under construction, the Gyron was the most powerful engine of its era, producing 20,000 lbf (89 kN) “dry”, and 27,000 lbf (120 kN) with afterburner.

The Gyron was Halford’s first axial-flow design, a complete departure from his earlier centrifugal-flow engines based on Whittle-like designs, the Goblin (H-1) and Ghost (H-2). The Gyron was also one of the first engines designed specifically for supersonic flight.

The Gyron first ran in 1953. Flight testing started in 1955 on a modified Short Sperrin (a bomber design that was instead turned into an experimental aircraft), replacing the lower two Rolls-Royce Avons with the much larger Gyrons. Flight rating was 18,000 lbf (80,000 N). In 1955 the DGy.1 received an official rating of 15,000 lbf (67,000 N). Addition of a reheat section boosted output to 20,000 lbf (89,000 N) and then 25,000 lbf (110,000 N) in the Dgy.2

The Gyron was selected for a number of projects, most notably the Hawker P.1121 (sometimes referred to as the Hurricane) supersonic attack aircraft that was to have been the replacement for the Hawker Hunter. However, this project was eventually cancelled. Another design potentially based on the Gyron was the Operational Requirement F.155 interceptor, which optionally used the Rolls-Royce RB.106. F.155 was also cancelled, part of the 1957 Defence White Paper. Government financial support of the Gyron project itself was cancelled in March 1957, at a reported total cost of £ 3.4 million.

The engine was actually too large for most roles and saw no production use. It was later scaled down to 45% of its original size to produce the de Havilland Gyron Junior, which was somewhat more successful.

Specifications

Gyron D.Gy.1
Type: Turbojet
Length: 155.5 in
Diameter: 55.2 in
Dry weight: 4,270 lb
Compressor: Seven stage axial flow
Turbine: Two-stage
Maximum thrust: 20,000 lb
Overall pressure ratio: 5.6
Specific fuel consumption: 1.04 Ib./hr/lb at maximum thrust

Dechaux Helicop-Jet        

The Hélicop-jet was an original design helicopter of Mr. Charles Déchaux and employed the so called pressure-jet principle (compressed air from turbine engine was channelled to exhaust nozzles at the tips of the rotor blades and extreme tail). The aircraft had a rotor as used in the Sud Aviation SO-1221 Djinn and also featured a twin tail boom configuration and used cabin doors of the Panhard PL-24c car.

A full-size model was exhibited at the 1969 Paris Air Show.

mock up in Salon du Bourget 1969

The first example of the Hélicop-jet, F-WZAI, had one 250-260hp Turboméca Palouste IV turbine and it made the first flight in December 1976 at the Issy-les-Moulineaux heliport with Mr. Heurtau, technical director of Héli-Union at the controls.

Trials with this first aircraft showed that only the pilot could be lifted.

The second prototype, F-WZJO made its maiden flight on December 12, 1984, still in Issy-les-Moulineaux. This time it is equipped with a Turbomeca Astazou IIIA 600 hp turbine and a more rounded windshield.

Tests continued at La Ferté-Alais, under the direction of engineer Jean Richard and piloted by Philippe Fouquaux. As with the first prototype, the second seemed largely underpowered. The tests of no 2 ceased in 1985.

Hélicop-Jet Project Management Co was formed in Montreal in 1984 with the objective the production of a helicopter derived from the Hélicop-Jet, without success. Plans for versions with Turboméca TM.319, P&W PT6 and Allison 250 turbine engines were abandoned.

The prototype no 2 was given to CELAG (Center for Studies and Leisure Aerospace Grenoble) in July 2001. Since July 2007, it has been exhibited in the collections of the Lyon-Corbas Aviation Museum. This prototype arrived at the CELAG on July 25, 2001, after a long period of immobilization at Ferté-Alais, where it had been stored by 1985. It was in excellent state, and almost complete.

Gallery

No 2 prototype, F-WZJO
Engine: Turbomeca Astazou IIIA 600 hp
Rotor diameter: 10.08 m
Number of blades: 4
Fuselage length: 5.30 m
Height: 2.72 m
Empty weight: 450 kg
MTOW: 1060 kg
Cruise speed: 200 km / h
Range: 450 km
Seats: 4

De Bernardi MDB 02 Aeroscooter

Having developed the all-metal single-seat Partenavia P.53 Aeroscooter earlier, Mario de Bernardi sought to improve the design as the two-seat de Bernardi M.d.B. 02 Aeroscooter. The aircraft was to be built by CAP in Bergamo, Italy.

The Aeroscooter is a low-wing, two-seat monoplane. The partial welded steel tube fuselage uses aluminum skins. The wing uses a wood spar. The tricycle landing gear uses trailing link suspension. The single-piece plexiglas canopy slides forward to open. All fuel is housed in the 20 l (5.28 US gal; 4.40 imp gal) header tank and 50 l (13.21 US gal; 11.00 imp gal) main tank behind the passenger’s seat.

The prototype was built by De Bernardi with the assistance of two mechanics. In April 1959, De Bernardi died of a heart attack after flying a demonstration of the prototype at Rome Urbe Airport.

An example is on display at Museo Aeronautico Caproni di Taledo, Milano.

The daughter of De Bernardi was offering plans for a modernized version of the Aeroscooter using a Rotax 912UL engine to be flown under Italian microlight category.

M.d.B. 02 Aeroscooter
Engine: 1 × Agusta GA.70/0, 62 kW (83 hp)
Propeller: 2-bladed fixed-pitch
Wingspan: 9.5 m (31 ft 2 in)
Wing area: 8.300 m2 (89.34 sq ft)
Length: 5.5 m (18 ft 1 in)
Height: 1.70 m (5 ft 7 in)
Empty weight: 260 kg (573 lb)
Gross weight: 460 kg (1,014 lb)
Fuel capacity: 60 l (15.85 US gal; 13.20 imp gal)
Maximum speed: 210 km/h (130 mph, 110 kn)
Cruise speed: 190 km/h (120 mph, 100 kn)
Stall speed: 50 km/h (31 mph, 27 kn)
Range: 600 km (370 mi, 320 nmi)
Rate of climb: 6 m/s (1,200 ft/min) at sea level
Take-off run: 50 m (164 ft)
Landing run: 50 m (164 ft)
Crew: 2

Davis-Costin Condor

A two-seat tandem sailplane designed and built by F.Davis and F.Costin in 1953 and built at Portsmouth, UK.

Of conventional wooden construction, the wing was Go.426 mod. At the root, NACA 64, 110 at tip, special at mid-point. The wing was braced with two struts each side. No flaps or airbrakes were fitted but an emergency parachute was fitted.

It was first flown in 1952, it was rebuilt by P.Davis as a Series 2 with a longer nose and other detail alterations in 1960.

It was written off on 25 June 1961. Only the one was built and no C of A was issued.

Condor
Wingspan: 13.56 m / 44 ft 6 in
Length: 7.24 m / 23 ft 9 in
Wing area: 13.94 sq.m / 150 sq.ft
Aspect ratio: 10.4
Empty weight: 189.6 kg / 418 lb
Max L/D: 22 at 65 kph / 40 mph
Min sink: 0.76 m/sec / 2.5 f/se at 55 kph / 34 mph

Condor 2
Wingspan: 13.56 m / 44 ft 6 in
Length: 7.44 m / 24 ft 5 in
Wing area: 13.94 sq.m / 150 sq.ft
Aspect ratio: 10.4
Empty weight: 192.78 kg / 425 lb