Prue 215

Designed by Irving Prue and first flown in 1949, the all metal 215 was taken by Harold Hutchinson to 2nd place in the 1958 Nationals. The design featured a V-tail and retractable wheel, with flaps for glidepath control. One example belongs to the National Soaring Museum.

Wing span: 12.2 m / 40 ft
Wing area: 8.36 sq.m / 90 sq.ft
Empty Weight: 154 kg / 340 lb
Payload: 91 kg / 200 lb
Gross Weight: 245 kg / 540 lb
Wing Load: 29.31 kg/sq.m / 6 lb/sq.ft
Water Ballast: 0
Aspect ratio: 20
Airfoil: Airfoil NACA 23012,8318
L/DMax: 29 84 kph / 45 kt / 52 mph
MinSink: 0.79 m/s / 2.6 fps / 1.54 kt / 64 kph / 35 kt / 40 mph
No. of Seats 1
No. Built 3

Prue II

The all metal Prue IIA first flew in 1964, differing from the original Prue II by having a T-tail, fixed gear and a shorter, lighter, 2 piece wing resulting in an empty weight approximately two hundred pounds less. The IIA held the world multi-place out-and-return record (590,5 km./ 366.88 miles) for six months in 1967 and again, of 684.5 km. / 425.3 miles in 1972. The only IIA belongs to the National Soaring Museum.

Prue IIA
Wing span: 18.29 m / 60 ft
Wing area: 17.19 sq.m / 185 sq.ft
Aspect ratio: 18.3
Airfoil: Naca 63 (3)-618
Empty Weight: 399 kg / 880 lb
Payload: 213 kg / 470 lb
Gross Weight: 612 kg / 1350 lb
Wing Load: 35.6 kg/sq.m / 6.2 lb/sq.ft
L/DMax: 36 96 kph / 52 kt / 60 mph
MinSink: 0.61 m/s / 2.0 fps / 1.18 kt
Seats: 1
No. Built: 1

Prudden-San Diego Airplane Co / Solar Aircraft Co

The Prudden-San Diego Airplane Company was founded in 1927 by George Prudden and seven San Diego area businessmen. Due to differences in management philosophy between Prudden and his investors, Prudden left the company in November 1928.

1929:
1212 Juniper Ave,
San Diego CA,.
USA

Became the Solar Aircraft Company in March 1929.

Later, Prudden developed the Prudden-Whitehead monoplane with the Atlanta Aircraft Corporation. While in Atlanta, Prudden helped develop Candler Field, Atlanta.

The Solar MS-1 was a prototype all-metal sesquiplane airliner built in 1930 at Lindbergh Field, San Diego, California. Due to the Great Depression in 1929, the company was unable to market the aircraft and made only three airplanes. Solar would never build another aircraft after the MS-1, turning to saucepans to survive the depression, and later stainless-steel exhaust shrouds.

During this period, they won a number of contracts to produce jet engine components. Convinced that the gas turbine was the prime mover of the future, the company invested heavily in the development of small turbines.

The company was reincorporated in 1937 as the Solar Aircraft Company, dropping the “Ltd” from its name. By 1939, Solar Aircraft Company had a work force of 229. Military orders during World War II led to rapid expansion and by the end of the war the company had a workforce of 5,000, largely part of a massive effort to build more than 300,000 exhaust manifolds for U.S. airplanes.

Business dropped considerably after World War II and the management developed a plan to diversify into producing other stainless steel products including caskets, frying pans, bulk milk containers and even redwood furniture; immediately after World War II, the company also produced the Solar Midget race car. Solar’s expertise in hard-to-manufacture parts able to withstand high-temperatures led to contracts to produce jet engine components. Solar Aircraft began to design and manufacture completed turbine engines for the United States military for applications such as auxiliary power units, fuselages, and rocket engine components of guided missiles.

Solar Aircraft Company’s expertise in high-temperature metallurgy led to work producing components for some of the first US jet engines, including the General Electric I-40 and a contract from the US Navy to build an afterburner for the Westinghouse J34. Solar Aircraft Company also won contracts for the Allison J33, Allison J35, Avro Canada Orenda, and Bristol Olympus. It was during this time that one of its engineers, Wendell Reed, developed the pneumatic engine microjet controller, for which he won the Wright Brothers Medal in 1955 and which became widely used for gas turbines, afterburners, and ramjets.

Solar Aircraft Company’s work in the jet engine field convinced the company’s president, Edmund Price, that the turbine would be the main prime mover in the future. Solar Aircraft Company assembled a team under the direction of Paul Pitt in 1946 and started developing a small 80 horsepower (60 kW) axial-flow turbine as an auxiliary power unit for the US Army Air Force’s Convair B-36 strategic bomber. The Army eventually cancelled this contract, but Solar Aircraft Company soon won a contract from the US Navy in 1947 for a 250 kW system to provide emergency power on ships. First running in 1949, the T-400 would go on to provide power on minesweepers and landing craft.

In 1947, Leon Wosika and Eric Balje set up a second design line and developed a centrifugal-flow system that was much more compact than Solar’s previous designs. Originally known as the MPM-45, the unit was delivered as the 45 horsepower (34 kW) “Mars”. The Navy purchased the Mars to power portable fire-fighting pumps on ships and gave it the designation T41. In 1956, the Navy turned to Solar to provide a slightly larger design to power a small helicopter, the Gyrodyne XRON-1. Solar Aircraft Company responded by developing a slightly larger version of the Mars, the 55 horsepower (41 kW) “Titan”, which the Navy designated the T62. When the Navy abandoned development of Gyrodyne’s XRON helicopter, Solar Aircraft Company adapted the Titan for service as an auxiliary power unit. Deliveries of this auxiliary power unit started in 1962.

Solar did win the contract to provide the APU for the first 632 KC-135A tankers for the Strategic Air Command.

In the late 1950s, the Navy once again turned to Solar, this time for a larger 750-kilowatt (1,010 hp) unit that would be used as an engine in a high-speed boat. The result was the axial-flow “Saturn” engine, which entered production in 1960. Solar started marketing the Saturn to industrial users needing a 1,000-horsepower (750 kW) unit for any role, and it went on to become the world’s most widely used industrial gas turbine with some 4800 units in 80 countries.

During the next decade, the Solar Division introduced a number of new designs, both larger and smaller than the Saturn. The Centaur, which first entered service in 1968, supplied 2,700 horsepower (2,000 kW), while the modern versions supply 4,700 horsepower (3,500 kW). In 1973, Solar exited the aviation industry to concentrate its resources on industrial gas turbines.

The turbine never came to be the main prime mover, but Solar’s expertise in small turbines found a number of niche roles. The company was purchased by International Harvester Company in early 1960, becoming the Solar Division of International Harvester in 1963. In 1973, the Solar Division exited the aerospace industry to focus solely on industrial turbines. In 1975, the development and manufacture of the Solar Division’s radial engines was moved into a newly formed Radial Engines Group, renamed the Turbomach Division in 1980.

In 1977, the Solar Division introduced a larger version of the Centaur, the 10,600 horsepower (7,900 kW) Mars, re-using the name from the earlier smaller engine.

Solar Turbines Incorporated became a wholly owned subsidiary of Caterpillar Tractor Co. after Caterpillar purchased the assets of the Solar Division and the Turbomach division from International Harvester on 31 May 1981. The newly acquired assets were organized as a wholly owned subsidiary of Caterpillar Tractor Co. named Solar Turbines Incorporated.

After the purchase, Caterpillar assigned development and manufacturing of the Caterpillar Model 5600 to Solar Turbines. The 5600 was originally developed by The Boeing Company as the Boeing 551/553 series, which Caterpillar had purchased when Boeing decided to exit the gas turbine business in 1966.

In 1985, Caterpillar sold the Turbomach Division to Sundstrand Corporation (now Collins Aerospace), exiting the Centrifugal gas turbine engine business.

Solar Turbines Incorporated continued to introduce new versions of their axial-flow industrial engines throughout the 1980s and 90s, often re-using older names instead of introducing new names.

In 2004 Caterpillar acquired Swiss company Turbomach S.A. which had long been a packager of industrial turbines from Solar, Rolls-Royce, and Trent.

Solar has sold more than 15,000 gas turbine systems, with a combined operating history of over 2 billion hours of use, equivalent to over 100,000 years.

Projekt 8 Dolphin

The Danish Dolphin tandem two-seater motor glider was designed and built by the Projekt 8 I/S company of Roskilde, and 10 construction of the prototype was taking place at three separate sites near Copenhagen,
and it was expected that the first flight was to be made late in 1978.

The Dolphin is a cantilever mid-wing monoplane of mixed constrution with a T-tail, powered by a 54hp Volkswagen VW1600 engine driving a two-blade pusher propeller, mounted on a pylon and retracting rearwards behind closed doors into the top of the fuselage aft of the wings. The wings, which have 4° dihedral, have an aluminium centre section and wood and glassfibre outer panels, flaps and ailerons; there are aluminium air brakes in the upper surfaces just ahead of the flaps. The forward fuselage is a welded steel tube framework covered with a light glassfibre shell, and the rear fuselage is a wooden structure reinforced by glassfibre. The tail unit is likewise of wood, with a fixed incidence tailplane, a central trim tab in the elevator and an inset tab at the base of the rudder. There is a semiretractable rubber-sprung mainwheel plus a nosewheel and a steerable tailwheel, as well as retractable wing tip balancer wheels. The one-piece cockpit canopy opens sideways.

Span: 61 ft 5 in
Length: 27 ft 10.75 in
Height: 4 ft 3.25 in
Wing area: 223.9 sq ft
Aspect ratio: 16.8
Empty weight: 1,058 lb
Max weight: 1,653 lb
Max speed: 163 mph
Max aero-tow speed: 77.5 mph
Min sinking speed: 2.30 ft/sec at 50 mph
Best glide ratio: 32:1 at 62 mph

Proctor Kittiwake I / Mitchell-Proctor Kittiwake I

G-ATXN Mitchell-Procter Kittiwake

Originally designed in 1964-65 by R. G. Proctor and C. G. B. Mitchell as a dedicated single-seat glider tug aircraft. Mitchell-Procter Aircraft was set up to produce the Kittwake prototype. It was a development of the Mitchell-Prizeman Scamp design study of 1964. ‘Kit’ Mitchell was the Kittiwake’s designer, with Roy Procter in charge of building it. It had excellent visibility, sturdy landing gear.

The Kittiwake was of all-metal stressed skin construction with tricycle landing gear. The nose-wheel was steerable for taxiing and the aircraft was fitted with hydraulic brakes.

Mitchell-Proctor Kittiwake Under Construction 1 Jan 1967

The aircraft would be capable of aerobatics with a rate of Roll 200 degrees at 103 mph (90 kn; 166 km/h). The Kittiwake had a rate of climb of 700 feet (213 metres) per minute with a 1,000 lb (454 kg) glider in tow.

The single-seat Kittiwake I is an all-metal aircraft, with low cantilever wings of parallel chord built around a single spar carrying 5° of dihedral. NACA single slotted flaps occupy the whole of the trailing edge inboard of the ailerons. The wings attach to a centre section which is integral with the fuselage, a feature intended to help construction in a small space like a garage. The straight tapered fin carries a horn balanced rudder and the constant chord tailplane has a starboard side trim tab.

The Kittiwake’s fuselage is built around four longerons, with flat sides and bottom and single curvature decking. Its overwing cockpit has a rearward sliding canopy and its fixed tricycle undercarriage has cantilever angled steel spring main legs attached to the lower longerons, giving a track of 5 ft 9 in (1.75 m). The Kittiwake I was powered by a 100 hp (75 kW) Continental O-200 engine.

The wing had generous flaps with high operating speeds which allowed for a fast descent. It had a self-starter system, provision for a radio. The Kittiwake also had a mechanism for retracting the tow rope during the descent. This design was fully aerobatic and additional fuel tanks could be fitted to extend the range.

Mitchell-Proctor Kittiwake Under Construction 1966

By the middle of 1965 production tooling were being made for the wing ribs as well as spars machined.

The Kittiwake single-seat, low-wing monoplane was designed to make full use of all-metal materials and modern construction while retaining a simplicity of design that lends itself to homebuilding.

Mitchell-Proctor Kittiwake I G-ATXN Cranfield 22 Jun 2002

The prototype was started at Camberley but completed by BEA Engineering in 1966-7, powered by a Continental O-200-A. First flown at Lasham on 23 May 1967, it was registered G-ATXN PFA.1306. It was re-engined with a fan-cooled Lycoming O-290 at Lasham in 1972. The prototype was later known as the Mitchell-Procter Kittiwake I. Around a year and a half later the partnership was dissolved and plans for home builders were produced by Procter Aircraft Associates.

A second was built at RNAS Lee-on-Solent as an apprentice project under Lieutenant Commander Cudmore, started in 1969. First flying on 21 October 1971 sn serial XW784, at Lee-on-Solent, powered by a Rolls-Royce/Continental O-200-A.

It was subsequently registered G-BBRN. Built, one by Royal Navy apprentices in 1971 for glider towing, a larger diameter (6 ft 4 in, 1.93 m) propeller is fitted, increasing the rate of climb by 24%. A tow release hook is fitted under the tail. Only one Kittiwake II, the prototype, was built.

In later years the prototype was re-engined with a Lycoming O-290-D2 engine.

Mitchell continued development and produced the Mitchell Kittiwake II two-seater. Plans were available for both single-seat and two-seat versions, but only four were constructed. Examples built of the Kittiwake I: G-AXTN, G-BBRN (marked as XW784).

One Kittiwake was active until at least at 2005 and the other is still active. They remain on the UK Civil Register. These are the prototype, G-ATXN and the ex-Naval G-BBRN. The latter is painted, as in its Naval days, as XW784.

Gallery

Kittiwake I
Engine: 1 × Rolls Royce-Continental O-200-A, 100 hp (75 kW)
Propeller: 2-bladed McCauley 69CM52, 5 ft 9 in (1.75 m) diameter metal, fixed pitch
Wing span: 24 ft 0 in (7.32 m)
Wing area: 105 sq ft (9.8 m2)
Length: 19 ft 7 in (5.97 m)
Height: 7 ft 6 in (2.29 m)
Empty weight: 910 lb (413 kg)
Gross weight: 1,250 lb (567 kg) for aerobatic flight
Maximum take-off weight: 1,350 lb (612 kg)
Fuel capacity 26 USG
Maximum speed: 131 mph (211 km/h; 114 kn)
Cruise speed: 122 mph (106 kn; 196 km/h) at 75% power
Stall 48 mph
Range: 540 miles (469 nmi; 869 km) at 92 mph (148 km/h)
Ferry Range with additional tanks: 600 miles (521 nm; 966 km)
Rate of climb: 850 ft/min (4.3 m/s)
Crew: 1

PROCAER Cobra F.400 / F.480

In 1960, under the direction of Stelio Frati, Procaer built the F.400 Cobra, a two-seater jet powered by a Turbomeca Marboré II.

Construction of Cobra is mixed wood and all metal and the outer coating of birch plywood covered with a pure aluminum foil bonded over the entire surface.

The prototype was destroyed during its return from the Paris Air Show to Italy.

A second prototype, with four seats and a Marboré VI, the Procaer F-480, was maintained in the collection of Charles Bezard.

Engine: Turbomeca Marboré II
Wingspan: 8.70 m
Length: 7.80 m
Height: 2.80 m
Wing area: 11.70 m²
Aspect ratio: 6.5
Empty weight: 700 kg
Loaded weight: 1300 kg
Wing loaded: 111 Kg / m²