One of a steadily increasing number of American companies catering for the burgeoning homebuilder’s market, Sun Aerospace is a comparatively small concern based at Nappanee, Indiana. Sun Aerospace’s main product is the Sun Ray 100, a canard type that first flew in prototype form during September 1983 and is one of many sporting lightplanes clearly derived from the pioneering canard work of Burt Rutan.

The type is available in kit form, and it is estimated that some 500 man-hours are required for assembly of such a kit. The result is a trim single-seater with enclosed accommodation and non-retractable tricycle landing gear, but the overall appearance is perhaps marred by the size of its twin vertical surfaces, located above the main wing to the sides of the engine and its pusher propeller.

Sun Aerospace Sun Ray 100 Article

The construction of the Sun Ray 100 is typical of many current aircraft for the homebuilt market, and is centred on a fuselage that uses a primary structure of welded aluminium alloy tubes covered with three pre-moulded glassfibre shells. The main wing is attached to the top of the rear fuselage, and is sharply anhedralled to the locations of the vertical surfaces, and is flat outboard of that point: the wing structure has extensive reinforcement of spruce and comprises a pre-moulded glassfibre leading edge, an aluminium alloy trailing edge and glassfibre-wrapped ribs all covered with Ceconite or Stits Poly-Fiber. The canard foreplanes use pre-moulded glassfibre skins, and all the control surfaces (twin rudders, two wing-mounted ailerons and two canard-mounted elevators) are made of aluminium tubing.

Companies such as Sun Aerospace are keen to capitalize on all the possibilities of a successful basic design, and it is thought that under development are an amphibious version of the Sun Ray 10 and a two-seater known as the Sun Ray 200.

First flying on 13 January 1987, N222SR, another showed up at the 1987 Paris Air Show, N103SR c/n 100-103

Type: sport lightplane
Powerplant: one 38.8-hp (52-kW) Rotax 503
Maximum cruising speed 100 mph (161 km/h)
Initial climb rate 800 ft (244 m) per minute
Service ceiling 13,500 ft (4115 m)
Range 425 miles (684 km)
Empty weight 550 lb (249 kg)
Maximum take-off 850 lb (386 kg)
Wingspan 32 ft (9.75 m)
Length 13 ft (3.96 m)
Height 6 ft (1.83 m)
Wing area 157 sq.ft (14.59 sq.m) including canard foreplanes
Accommodation: one

High monowing with enclosed cabin. Control surfaces include tip rudders, which can be split When applied simultaneously they act as air brakes. Construction consists of layered foam and fiberglass from premolded external skins and some spruce. Wings, tail surfaces and fuselage are covered with fiberglass. Powerplant: One Yamaha mounted in a pusher position aft of the wing on the centerline. A reduction gear of 3.6:1 turns a two-blade wooden Ritz propeller. Fuel is carried in a fiberglass tank mounted in the wing. Landing Gear: Shock-mounted tricycle gear with a fiberglass leaf spring and steerable nosewheel. Options include wheel fairings for all three wheels for $100, larger diameter wheels (16 inch, 40 cm) $105, skis $150, floats $750, removable side windows $100, instrument panel, radio, shoulder harness $22, ballistic deployment parachute $850.

Engine displacement 100 or 225cc, 12 or 20 hp
Static thrust, 70 lbs or 110 lbs
Wingspan, 32 ft
Wing area, 151 sq.ft
Aspect ratio, 7:1
Overall length, 14 ft
Empty weight. 185 lb
Usable payload (include fuel), 250 lb
Wing loading, 31 lbs/sq.ft
L/D power-off glide ratio,17:l
Cruise speed (85% power), 59 mph
Stall speed, 18 mph
Ap¬proach speed, 35 mph
Flair speed, 25 mph
Liftoff speed, 25 mph
Takeoff roll distance, 225 ft
Rate of climb, 250 fpm
Fuel capacity, 5 Usgal
Range at cruise, .325 mi

A high monowing with enclosed cabin. Three-axis controls with conventional aileron, rudder and elevator. The elevator and rudder are operated separately, and all are operated by a control stick. Construction makes use of some spruce, but is mostly composed of layered foam and fiberglass from premolded external skins. The wings. tail surfaces and fuselage are covered by some fabric. POWER-PLANT: One Cuyuna mounted in a tractor position forward of the wing on the centerline. A 2:1 reduction gear turns a two-blade wooden Ritz propeller. Fuel is carried in a fiberglass tank mounted in the wings. LANDING GEAR: Shock-mounted tricycle gear with a fiberglass leaf spring, a steerable nosewheel and no brakes. All wheels are 12-inch. Options include wheel fairings for all three wheels for $100, larger diameter wheels (16 inch, 40 cm) $105, skis $150, floats $750, removable side windows $100, instrument panel, radio, shoulder harness $22, ballistic deployment parachute $850.

First year built. 1981. Units delivered by June 1981 4.

Trike undercarriage, brake on steerable nosewheel.

Sky Ranger
Engine: Cuyuna 429cc, 40 hp
Static thrust 300 lb
Wingspan, 36 ft
Wing area, 180 sq.ft
Aspect ratio, 7:1
Overall length, 17 ft
Empty weight, 360 lb
Usable payload (include fuel), 440 lb
Wing loading, 4.5 lbs/sq.ft
L/D power-off glide ratio, 15:1
Cruise speed (85% power), 77mph
Stall speed, 30 mph
Approach speed, 40mph
Flair speed, 35 mph
Liftoff speed, 35 mph
Takeoff roll distance, 250 ft
Rate of climb, 1000 fpm
Fuel capacity, 5 Usgal
Range at cruise, 250 mi
Max pilot wt: 470 lb
First year built: 1981

Sky Ranger Silver Cloud
Engine: Cuyuna 430, 420cc, 30 hp
Wingspan 33’6”
Wing area 127 sq.ft
Aspect ratio 8.6:1
Length 16’
Empty weight 350 lb
Payload 450 lb
Gross weight 800 lb
Wing loading 7 lbs/sq.ft
L/D 13:1
Cruise speed 80 mph
Stall speed 29mph (flaps)
Takeoff and landing roll 250 ft
Climb rate 600 fpm
Fuel capacity 10 USG

The prototype Lone Ranger made its first flight on the 23 October 1980. It is a development of the Super Flac with which it shares the integral cockpit, but unlike its predecessors, the Lone Ranger has a triangular section spar carrying a conventional tailplane and its wing is fitted with ailerons. Sold in kit form, one requiring 150 h for assembly (fast flight kit) and the other less elaborate (economy kit), the Lone Ranger was tried with various engines and in 1982 was offered with Yamaha KT100S 15 hp, Zenoah G25B 20 hp, or Cuyuna 215R 20 hp engines.

Striplin Lone Ranger Article

In a dramatic development at Sun’n’Fun in March 1983 at Lakeland, Florida, the company announced that it was renamed Ranger Aviation and released literature on a single seater named the Silver Cloud. Differing from the earlier Lone Ranger, the principal modifications involve the wing, which benefits from a new high lift profile, wind tunnel and flight tested, and which exhibits a coefficient of lift of 1.9. As well, the rectangular planform wing (without leading edge sweepback) of the Lone Ranger has been dropped for a tapered wing having 7 deg of leading edge sweepback.

The Lone Ranger shown at Sun ‘n’ Fun in 1983 had already abandoned the two V struts under each wing in favour of a single strut, which according to the previews will disappear altogether on the Silver Cloud to give a cantilever wing, an arrangement which was purely optional for the earlier models. Another modification is that the ailerons are not tacked on to the trailing edge but are integral within the wing profile and run full span, using the same new profile as the wing.

They are usable not only as ailerons but also together as flaps, coming down to 30 deg, and are quoted as giving a coefficient of lift of more than 2.4, which lowers the stalling speed to 25 mph (40 kph). Finally, the preview plans showed that the monobloc elevator of the new model is now carried midway down the tail cone instead of being level with its top surface.

The Silver Cloud is not only different in terms of design; it also represents a change of marketing policy, as it will be sold complete rather than in kit form one of the first composite construction ultralights to be produced in quantity. Ready to fly it costs around $10,000, exact price depending on specification. Options include wheel fairings for all three wheels for $100, larger diameter wheels (16 inch, 40 cm) $105, skis $150, floats $750, removable side windows $100, instrument panel, radio, shoulder harness $22, ballistic deployment parachute $850. Three engine types are offered: the Zenoah G25B with 22 hp, a Rotax whose type is not quoted giving 20 hp, and the Cuyuna 215R.

Single seat single engined high wing monoplane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; conventional tall. Pitch control by fully flying tail; yaw control by fin mounted rudder; roll control by full span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nosewheel steering connected to yaw control.

Composite construction fuselage partially enclosed (totally enclosed optional). Engine mounted above wing driving tractor propeller. Construction uses carbon fibre, Keylar, fibreglass, various foams and epoxy resin; steel and aluminium fittings.

First year built 1980. Units delivered by June 1981 150.

The Sky Ranger Silver Cloud is a two-place version of Lone Ranger SC. The Silver Cloud II was basically the same as the Silver Cloud except being a side by side two seater. glass fibre on main wheels. Fuselage totally enclosed. As with the single seater, the reshuffle at Striplin reflects directly on this product. Previously called Sky Ranger, the company’s two seater is now called Silver Cloud II and is classified in the US as an experimental aircraft, requiring a pilot’s licence.

The prototype Sky Ranger, developed by Keith Striplin from the Lone Ranger, was on static display in August 1981 at Oshkosh and differs principally from its successor by having Fowler flaps and a T tail. The latter was dropped in 1982 for a conventional tail which is retained for the Silver Cloud II.

At Sun ‘n’ Fun in March 1983 Ken had on show the first prototype of the Sky Ranger, but this aircraft is being used as a flying test bed and has changed greatly since its debut in 1981. It sported not only a conventional tail but also a new wing with flaperons (ailerons usable as flaps) and the new profile destined for the Silver Cloud IL The two V struts carrying each wing had been replaced by single struts, although production models will be cantilevered. The landing gear had also been redesigned to give greater ground clearance.

Originally the Sky Ranger prototype used an engine mounted above the cabin and driving two twin blade propellers mounted on the leading edges, but at Sun ‘n’ Fun a similar motor was used to drive a single tractor propeller. An engine mount shaped like a fairing allows this propeller to operate in front of the fuselage nose, the engine intended for the standard Silver Cloud II being the Rotax 503.

The aircraft was sold ready to fly for $15,000 in 1983 in the standard version, which includes wheel fairings, removable side windows, shoulder harness, instrument panel and strobe. Otherwise, the options are as for the single seater.

Lone Ranger
Engine: Yamaha 100cc, 12 or 20 hp
Static thrust, 70 lbs or 110 lbs
Wingspan, 32 ft
Wing area, 144 sq.ft
Aspect ratio, 7:1
Overall length, 15 ft 8 in
Empty weight 196 lbs
Usable payload (include fuel), 240 lbs
Wing loading, 31 lbs/sq.ft
L/D power-off glide ratio, 17:1
Cruise speed (85% power), 61 mph
Stall speed, 21 mph
Approach speed, 40 mph
Flair speed, 29 mph
Liftoff speed, 27 mph
Takeoff roll distance, 225 ft
Rate of climb, 250 fpm
Fuel capacity, 5 Usgal
Range at cruise, 350 mi
Max pilot wt: 230 lbs
First year built: 1980

Lone Ranger Silver Cloud
Engine: Cuyuna 215R, 20 hp at 5500 rpm
Propeller diameter and pitch 54 x 27 inch, 1.37 x 0.68 m
Planetary gear reduction, ratio 2.2/1
Power per unit area 0.17 hp/sq.ft, 1.8hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 16.0 ft, 4.87 m
Height overall 7.0ft, 2.13m
Wing span 32.0ft, 9.75m
Chord at root 4.0ft, 1.22m
Chord at tip 3.0ft, 0.91m
Dihedral 5 deg
Sweepback 7 deg
Total wing area 120 sq.ft, 11.14 sq.m
Wing aspect ratio 8.6/1
Wheel track 4.0 ft, 1.22 m
Wheel¬base 4.0 ft, 1.22 m
Nosewheel diameter over¬all 8 inch, 20 cm
Main wheels diameter overall 8 inch, 20cm
Empty weight 245 lb, 111kg
Max take off weight 500 lb, 227kg
Payload 255 lb, 116kg
Max wing loading 4.18 lb/sq.ft, 20.4kg/sq.m
Max power loading 25.0 lb/hp, 11.3kg/hp
Load factors +6.0, 4.0 design
Max level speed 63 mph, 101 kph
Never exceed speed 80 mph, 129 kph
Stalling speed 25 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.1 m/s
Best glide ratio with power off 14/1
Take off distance 75ft, 23m
Landing dis¬tance 75ft, 23m
Range at average cruising speed 210 mile, 338 km

Silver Cloud II
Engine: Rotax 503, 46hp at 6500rpm
Propeller diameter and pitch 60 x 36 inch, 1.52 x 0.91 m
Power per unit area 0.36hp/sq.ft, 3.9hp/sq.m
Fuel capacity 10.0 US gal, 8.3 Imp gal, 37.8 litre
Length overall 16. 0 ft, 4.87 m
Height overall 8.0ft, 2.44m
Wing span 33.4ft, 10.18m
Mean chord 3.8ft, 1.16m
Dihedral 5 deg
Sweepback 7 deg
Total wing area 127sq.ft, 11.8sq.m
Wing aspect ratio 8.6/1
Nosewheel diameter overall 8 inch, 20 cm
Main wheels diameter overall 8 inch, 20cm
Empty weight 350 lb, 159kg
Max take off weight 1000 lb, 453 kg
Payload 650 lb, 295 kg
Max wing loading 7.87 lb/sq.ft, 38.4 kg/sq.m
Max power loading 21.7 lb/hp, 38.6 kg/hp
Never exceed speed 100mph, 161kph
Max cruising speed 80mph, 129kph
Stalling speed 29mph, 47 kph
Max climb rate at sea level 600 ft/min, 3.1 m/s
Best glide ratio with power off 13/1
Take off distance 150ft, 23m
Range at average cruising speed 250 mile, 402 km