Pellarini PL-1 / PL-2 / Aerauto AER-1 / PL-5

Luigi Pellarini’s PL-2C flying car, circa 1950.

Luigi Pellarini was about 30 years old when in 1944 he partnered with Carrozzeria Colli, a Milan motor vehicle and coach-building company, to build his first prototype flying car, the PL 1.

He kept improving his prototypes and put out a new and improved model each of the next several years. L’Ala, an Italian magazine, published a description of his PL-2C, dubbed the Aerauto, in its October 1946 issue.

The PL 2 C is an entirely metal touring aircraft, with folded wings, its dimensions are about 2.20 m width for 6 m of length it can easily move on normal roads, always with the propeller thrust.

The PL 2C structure is the fuselage, with a real chassis, consisting of a tubular beam in welded sheet steel and durall bodywork. On the beam are welded the castle in tubes that support the wing and the engine, as well as all the controls, the undercarriage, the seats and the empennages.

There durall fairing covers the front of the beam and provides a to connect the wing to the engine and to the beam, as well as to form the cabin equipped with two side doors and is easily removable. The wing is cantilever monoplane divided into a fixed centre, and in two collapsible semis. The folded wing remains suspended with the front attachment to the central trunk of the wing. Structure the wing is entirely durall and the cover is 8/10 mm. The attachments are steel. Rivets were widely used in the wing tubulars, rather than bolts. The ailerons have a metal frame in durall and a cover in canvas; they can be simultaneously lowered so as to work as flaps. The horizontal plane is of a similar structure to the wing; there fixed part (whose incidence is adjustable in flight with handwheel) is covered in durall. The vertical plane, split, is structurally similar to the horizontal. The undercarriage is tricycle with low pressure wheels, the rear wheels are equipped with brakes, while the front is connected to the pedals for steering.

The prototype engine is a 60-hp Valter that drives a fixed propeller. The controls are of the usual bar and pedal type, the instrument panel the usual equipment of instruments, the brake is a pedal. The cost is 460,000 L without engine.

The following year’s PL-3C also got magazine coverage, this time in Wing.

The Aerauto PL3 C is a small-powered tourism aircraft, single engine, high wing with propeller and tricycle undercarriage. It is a two-seater side by side, with the possibility of a third place. The fuselage beam, in high strength steel sheet with a circular section, formed by two half-shells welded is of simple and easy construction, it represents the longitudinal frame of the aircraft and comes to it welded directly, support for controls, undercarriage, ribs for the support of the fairing, engine frame that also makes to the connection to the wing.

The power train consists of a Walter Micron III engine from 80hp air-cooled, operating a two-bladed propeller with variable pitch. The motor is installed behind the side member of the central trunk, raised from the tail beam in order to allow the propeller rotation. It is supported by the same framework in pipes of welded steel that supports the wing. The tail is built with two side members covered in durall sheet and canvas. The rudders are statically balanced. The undercarriage is tricycle with independent rear wheels and wheel front adjustable.

The aircraft is equipped with the regulatory instrumentation for in-flight and the landing light, installed at the bow of the aircraft, taillights and signalling etc are powered by a 12V battery.

The PL-4 was publicly known as the Aerauto AER-1. L’Ala had a more consumer-oriented article in its July 15, 1948 issue.

PL-5C Aerauto

By 1949, Pellarini thought that his new model, the PL-5C, was ready for the public. Piloted by Leonardo Bonzi and Maner Lualdi, the Aerauto drove and flew across Italy from late 1949 to early 1950, 1800 km in the air and 2200 km on the ground, stopping at Turin, Florence, Pisa, Rome, Naples, Bari, Ancona, Rimini, Venice, Treviso, Vicenza and Milan. The Aerauto would fly to a location outside of a city, fold up its wings, and drive into the city proper, exactly as a commercial flying car was supposed to work. At the end, Pellarini grandly presented the Aerauto to the Archbishop of Milan, Cardinal Schuster.

Naturally, this great stunt garnered even more publicity, with Tempo magazine displaying a picture of the Aerauto, Pellarini, Bonzi, and Lualdi on a public street, taking up no more room than the cars behind them.

A British Pathé newsreel documented the Aerauto on the ground and in the air.

Pellarini immediately filed a U.S. patent application for a “Folding Wing for Roadable Aircraft,” which was granted after much delay in 1954.

Flying cars are hard to sell at the best of times, and with Italy’s economy in 1950 Pellarini got no orders at all. He gave up and emigrated to Australia. The Australian press showered him with articles as soon as he arrived.

PL 2C
Wingspan: 9,80m
Wing area: 12sq.m
Length: 5,70m
Height: 1,60m
Empty weight: 340kg
Payload: 210 kg
Total weight: 550kg
Wing load: 45.8kg / sq m
Maximum speed: 190 kph (at 2000m)
Cruise: 160kmh
Stall: 70kmh
Road speed: 60kmh
Ceiling: 4000m
Range cruise: 600km
Max range: 750km
Take-off dist: 120m
Landing dist: 60m
Fuel consumption: 15 lt/ hr

PL-5C
Engine: 85 hp Continental C85
Max speed: 112 mph
Cruise: 100 mph
ROC: 535 fpm
Service ceiling: 13.120 ft
Range: 500 mi
Empty weight: 1012 lb
Loaded weight: 1540 lb
Wingspan: 33 ft 5.5 in
Length: 20 ft 4 in
Height: 5 ft 9 in

Pegasus Aviation AX2000 / AX3

Publicly owned Pegasus Aviation bought the rights to the French edition of a highly modified Weedhopper. Some of these alterations were completed to bring the machine to a contemporary description. Others were done srictly to meet the demands of British certification under BCAR-S.

The AX2000 (previously known as the AX-3, for 3 axis) is now a fully enclosed, conventional three axis machine.

H-Power introduced the AX2000 to the US at Oshkosh 1997.

In 1998 the Rotax 582 powered version cost £17,619.

Engine: HKS 700, 60 hp
Wing span: 10.3 m
Wing area: 15.6 sq.m
MAUW: 390 kg
Empty weight: 202 kg
Fuel capacity: 64 lt
Max speed: 145 kph
Cruise speed: 105 kph
Minimum speed: 50 kph
Climb rate: 3 m/s
Seats: 2
Fuel consumption: 7.5 lt/hr
Certification: BCAR S

Pegase Aero Pegazair-100 STOL / Tapanee Pegazair-100

Development of the Pegazair started in 1985 by Serg Dufour of Mont-Saint-Michel, Quebec. Originally it consisted of a new set of Pega-STOL wings with retractable leading edge slats to be installed on Zenair CH 701 STOLs to replace its wing which has fixed leading edge slots, first flown in June 1991.

Zenair CH 701 STOL with the original Pega-STOL wing

Dufour went on to develop a new fuselage and tail to match the wings. The Pegazair is a two seats in side-by-side configuration, strut-braced, high-wing monoplane with conventional landing gear. Fuselage construction is welded steel tubing with aluminum skins. The wings employ full length flaperons and leading edge slats that deploy automatically. The tailplane is slotted for slow speed authority. The prototype was outfitted with a 65 hp (48 kW) Continental A-65 engine.

The aircraft was built as the Tapanee Pegazair-100 and the design was later developed into the four seat Tapanee Levitation 4.

Tapanee Pegazair-100 / slats extended

Variants

Pegazair P80
Powered by a 80 hp (60 kW) Rotax 912UL

Pegazair P100
Powered by a 80 hp (60 kW) Continental O-200 or 115 hp (86 kW) Rotax 914

Specifications:

P-80
Engine: Rotax 912
Seats: 2 side by side
Length: 22.5 ft
Wingspan: 29.0 ft
Wing area: 150 sq/ft
Max.flaps: 30 deg
MAUW: 1200 lbs
Empty Weight: 625 lbs
Usefull load: 575 lbs
VSO: 23 mph
Min.speed 50 % pwr: 15 mph
Cruise speed: 95 mph
VNE: 110 mph
Gross takeoff dist: 175 ft
Climb rate at Gross: 900 ft / min.
Usable fuel: 52 litres
Range: 325 milles
Ultimate Load: +6 -3,3 G

Pegazair-100 STOL
Engine: 1 × Continental O-200, 75 kW (100 hp)
Length: 6.83 m (22 ft 5 in)
Wingspan: 9 m (29 ft)
Wing area: 14 m2 (150 sq ft)
Airfoil: NACA 2415
Max.flaps: 30 deg
Empty weight: 374 kg (825 lb)
Gross weight: 658 kg (1,450 lb)
Usable Fuel capacity: 134 litres (29 imp gal; 35 US gal)
Cruise speed: 169 km/h; 91 kn (105 mph)
Stall speed: 45 km/h; 24 kn (28 mph)
Never exceed speed: 201 km/h; 109 kn (125 mph)
Min.speed 50 % pwr: 18 mph
Gross takeoff dist: 300 ft
Climb rate at Gross: 800 ft / min.
Range: 1,014 km; 547 nmi (630 mi)
g limits: +6/-3.3
Wing loading: 47 kg/m2 (9.7 lb/sq ft)
Seats: 2 side by side

P-100
Engine: Rotax 914, 115 hp
Seats: 2 side by side
Length: 22.5 ft
Wingspan: 29.0 ft
Wing area: 150 sq/ft
Max.flaps: 30 deg
MAUW: 1350 lbs
Empty Weight: 760 lbs
Usefull load: 690 lbs
VSO: 28 mph
Min.speed 50 % pwr: 18 mph
Cruise speed: 115 mph
VNE: 125 mph
Gross takeoff dist: 225 ft
Climb rate at Gross: 950 ft / min.
Usable fuel: 134 litres
Range: 793 milles
Ultimate Load: +6 -3,3 G

Peel Glider Boat

The Peel Glider Boat Company of Flushing Bay, NY was in business around 1930, designing and building the Glider Boat, a biplane glider with stepped flying boat hull and wingtip floats. A number of examples were sold.

The two occupants sat in tandem in an open cockpit with conventional controls, but without instruments. The structure was wooden spar, steel ribs, fabric covered, and a duralumin hull.

Normal method of launch was behind a motor boat, the towrope being joined to a bridle which attached to either side of the nose outside the front cockpit.

One example belongs to the National Soaring Museum.

Wing span: 9.45 m / 31 ft
Wing area: 25.08 sq.m / 270 sq.ft
Empty Weight: 113 kg / 250 lb
Payload: 159 kg / 350 lb
Gross Weight: 272 kg / 600 lb
Wing Load: 10.84 kg/sq.m / 2.2 lb/sq.ft
L/DMax: 15
Seats: 2