Based on the ASO’s Viper trike, this machine is fully road legal in Germany. After removing the wings an auxiliary engine drives through a fourth wheel at the rear.
Viper 582 Street Empty weight: 165 kg Wing span: 10.38 m Wing area: 10 sq.m Fuel capacity: 50 lt Engine: Rotax 582, 64 hp MAUW: 400 kg Seats: 2 Max speed: 140 kph Cruise speed: 110 kph Minimum speed: 65 kph Climb rate: 4 m/s Fuel consumption: 12 lt/hr Price (1998): 79 000 DM
The Skyline Cruiser ZK-VOK was fully enclosed with strut batwing doors and built over four year period. Powered by a Rotax UL Blue Head 582 and equipped with Micro Aviation B22 Bantam specs-wings, box spar aluminium leading edge, fabric covered, deltron paint scheme.
The all metal trapezoidal wing with two spar construction consists of the outer parts and the wing center section. The short wing center section is firmly placed into the fuselage. The outer parts of the wing are separable for transport.
Wing profile is GA – 1 at the root and the GA – 2 at the tip. The main wing spar is placed in 33 % of the profile depth and is perpendicular to the longitudinal aircraft axis. The main spar is created from the dural beams and web. The beams are from metallurgical L – profiles, milled spanwise and riveted with web using full rivets. The web with changing thickness is relieved by the lightening holes spanwise. The ribs are stamped including lightening holes. The back spar is created by the L-profile and riveted web, which is relieving with lightening holes too. The cover is riveted with the pop rivets to the beams and the ribs. The flaps hinges are from dural sheets with milled grooves for flaps extending. Three safe attachment points attach the wing outer section parts with the wing center section.
The flaps – Fowler type with a proportional depth 29 % have 10 deg and 35 deg deflections. The flaps drive is mechanical in standard. The electrical system is available as an option. The mechanical drive system is created by toothed wheels with racks. The flap controller is placed in tunnel of the cockpit. Left and right parts of the flap drive are connected together. Flap construction is created by spar, ribs and cover, which are riveted with pop rivets.
The aileron is all metal with one spar. Construction consists of control rods and bent levers in the transverse control. The aileron deflections are differentiated.
The wing center section composed with two spars similar to the outer wing ones. These spars are firm attached into the fuselage construction. There are two fuel integral tanks in the front part of the wing center section, each one with 8.5 gallons of fuel capacity. The main landing gear is attached to the wing center section, so it creates an independent set, which can be moved at manufacturing or emergency transported during operation.
The all metal fuselage construction is created by dural L – form stringers, by metallic bulkheads and by cover. The stringers are attached together through the whole length of the fuselage and create a base supporting system of the fuselage. A transverse cross-section of the fuselage is shaped so that the cover could be unrolled and so was stabilized for an increasing of a critical tension. In the cockpit area is the supporting system replenished by steely spar of the closed square cross-section – middle panel of the cockpit. The seats are lengthwise adjustable and equipped by 4 points seat belts. The canopy creates perspex, which is inset into fiberglass frame with reinforcement from carbon and cevlar fibers. The canopy allows a perfect view backwards. The control is dual with control sticks and pedals. The directional control is funicular with turnbuckles.
The landing gear is retractable, controlled by electric motor with manual emergency control. Fixed Landing gear is determined for the Light Sport.
Both wheels of main landing gear and the nose wheel are towed and they are sprung with rubber shock absorbers, created by circular rubber segments. The nose landing gear is at protuberant position connecting with the foot’s control and is controllable at +15° range. The main landing gear wheels are braked with a central manual hydraulic brake lever at the control stick.
Skyleader 500 LSA
The airplane is equipped with Rotax 912 UL (80hp) engine, optionally with Rotax 912 ULS (100hp) or Rotax 914 UL (115hp turbo) engine. The engine is attached by welded bed with the use of rubber shock absorbers through the firewall into the fuselage stringers and central tunnel. Three (3) blade on-ground adjustable propeller is delivered with the plane as standard. As the optional order can be airplane equipped with mechanically or electrically in-flight adjustable propeller, two or three blade.
All metal tail units are standard alignment with a rudder and an elevator. The profile of Vertical Stabilizator and Horizontal Stabilizator is symmetrical to NACA 0012. They are created by spars, ribs and cover. An elevator is divided; therefore it is possible to take it down without disconnecting the controls. The same construction is used at the others control surfaces. A stabilizer is attached to the fuselage by four hinges and is possible to dismantle it without disconnecting the controls.
The aircraft has two integral tanks with capacity of 2×32 liters (total 64l) of the fuel. Optionally can be installed the additional fuel tanks supplying the aircraft with additional 2×15 liters (total 30 liters) of the fuel. Therefore max. amount of the fuel should rise up to 94 liters. The tanks are created by lead box inside the wing center section, out of the fuselage. They are riveted through caulk mastic and the wing center section cover forms concurrently a tank wall. The fuel delivery is ensured by a pneumatic pump for the overflowing the system and in the reason of an error or delivery deficient of the pneumatic pump is possible to use an additional electric pump. A fuel amount is indicated by two analogue fuel gauges.
The aircraft is in UL category furnished with standard instruments for flight and engine control. The Radio, Transponder, Glass Panel, GPS or another flight and engine instruments are installed on the customer’s request. Color painting, upholstery and internal cockpit surface adjustment of the aircraft is realized individually on basis of plentiful amount of offered services and products.
1946 aviation periodicals told of a “new twin-boom Skylark project” in three versions: two-place 246, four-place 446, and five–place 546. When the prototype appeared, it was as 447, with model number amended to fit the year.
The 1946 two-place Skycraft 246 featured wing ailerons and flaps. It is unknown if any were built in this designation, possibly was an evolutionary project, prised at $3,800-4,200.
No record of production found for the 1945 four-place Skycraft 445 and Skycraft 545. Partially-retracting gear to prevent structural damage in the event of a wheels-up landing, the 545 was noted in a brochure as slated for “Air Taxi service.”
Skycraft Rendering of unspecified model (company brochure)
The 1947 four-place Skycraft 446 and 447 featured all-metal construction, twin booms and tails; no ailerons, but wing spoilers served that purpose.
Partially-retracting gear to prevent structural damage in the event of a wheels-up landing. Priced at $5,800-7,500, one was built, NX25607 (registration also belonged to a North American NA-50A that went to Thailand).
The 1930 Skylark Aircraft Co 3-95 (2-281) was a two-place, open cockpit biplane developed from the Driggs Skylark 3. Four were built, including NC817Y and NC11328
Single seat single engined high wing mono¬plane with two axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by fully flying canard; yaw/roll control by angled ¬pivot tip rudders; control inputs through stick for pitch and yaw/roll. Wing braced from above by kingpost and cables, from below by cables; wing profile Clark Y derived; 100% double surface. Undercarriage has three wheels in tricycle formation; no suspension on nosewheel and suspension (type to be decided) on main wheels. Push right go right nose¬wheel steering independent from yaw control. Brakes on main wheels.
Aluminium tube and fabric fuselage, totally enclosed. Engine mounted below wing driving pusher propeller. Windscreen made from rigid plastic sheet, side windows from Mylar film. Bainbridge Dacron used for flying surfaces.
Designer Len Gabriels has aimed to create a machine which will appeal to hang gliding and sailplane enthusiasts as well as microlighters, and in its initial form the machine is unpowered.
As first shown at the British Hang Gliding Association’s annual general meeting in March 1983, the Orion is a fully enclosed hang glider/sailplane with pitch control by weight shift moving a fully flying canard. Combined roll and yaw control is provided by tip rudders mounted under the ends of the wing and with their pivots angled at 45O to the vertical, so that they provide roll at the same time as yaw. Both may be deployed simul¬taneously, to provide air braking.
This unpowered version of the Orion uses two wheels in tandem without suspension or brakes and is basically intended as a foot¬-launched aircraft. Powered versions, howev¬er, will have a tricycle layout with the weight shift pitch control being replaced by a stick. Pedals will steer the nosewheel but will not be connected to the yaw/roll control. Retention of the weight shift pitch control will be an option.
The wing is based on a Clark Y section, though as it is to some degree a flex wing, it will probably not behave entirely as a Clark Y in the air.
As a hang glider, in April 1983, test flights in unpowered form were about to begin.
Length overall 12.0 ft, 3.66 m Wing span 42.0 ft, 12.80 m Chord at root 5.0ft, 1.52m Chord at tip 3.0ft, 0.91m Canard span 12.0 ft, 3.66 m Canard chord 2.0 ft, 0.61 m Total wing area 176 sq.ft, 16.4 sq.m Main wing area 152 sq.ft, 14.1 sq.m Canard area 24sq.ft, 2.2sq.m Wing aspect ratio 9.5/1 Empty weight 154 lb, 70 kg
A single seat single engined flex wing aircraft with conventional three axis control. Rogallo wing. Undercarriage has three wheels in tricycle formation; no suspension on any wheels. Push right go right nosewheel steer¬ing connected to yaw control. No brakes. Aluminium tube trike unit, without pod. Engine mounted below wing driving pusher propeller.
This experimental machine is an attempt to mate three axis controls to a Rogallo wing. It uses the same power pack as the TR1 MkII trike unit, plus a modified Sabre wing. The trike unit is fixed to the wing structure rather than being sus¬pended from it, and the wing is mounted much lower than the normal hang point of a trike. No test flights have been carried out on this aircraft by 1982.
Engine: Engine: Solo 210 cc, 12 hp at 5500 rpm Propeller diameter 50 inch, 1.28m V belt reduction, ratio 2.5/1 Max static thrust > 100 lb, 45 kg
The Skyhook Sailwings TR2 Mk.I/Cutlass CD is a side by side two seat twin engined flex wing aircraft with weight shift control. Rogallo wing with keel pocket. Pilot suspended below wing in trike unit, using bar to control pitch and yaw/roll by altering relative positions of trike unit and wing. Wing braced from above by kingpost and cables, from below by cables, fixed cross tube construction with 30% dou-ble surface not enclosing cross tube; pre¬formed ribs. Undercarriage has three wheels in tricycle formation; no suspension on any wheels. Push right go left nosewheel steering independent from yaw control. Brake on nosewheel. Aluminium tube trike unit, with¬out pod. Engines mounted below wing driving pusher propellers. Trike unit and wing use aluminium tube to British HT30TF specifica¬tion, bright polished and sleeved at stress points. Wing rigged with plastic coated stain¬less steel wires; wing material is Bainbridge Dacron.
At the beginning of 1981, Len Gabriels was seeking an engine powerful enough to turn his TR1 Mk.I trike unit into a two seater. He was not satisfied with the reliability of any of the larger engines then available, so he decided instead to build a power pack using two of the 210cc Solo engines.
Rather than use two engines to drive one large propeller, he doubled up the drive system as well, creating a power pack with two contra rotating propellers driven from concentric shafts, each by its own engine an reduction drive. The safety attractions of such duplication are obvious, as the aircraft can at least maintain height after an engine failure.
The rest of the trike unit needed little alteration beyond the inclusion of a dual seat and a nosewheel brake. Allied to the Cutlass CD wing, the TR2 proved itself to be a viable training machine, but was dropped from production at the end of 1982 in favour of the TR2 Mk.II.
The Skyhook Sailwings TR2 Mk.I (Single Seat Special)/Cutlass CD is a single seat twin engined flex wing aircraft with weight shift control. Rogallo wing with keel pocket. Pilot suspended below wing in trike unit, using bar to control pitch and yaw/roll by altering relative positions of trike unit and wing. Wing braced from above by kingpost and cables, from below by cables; fixed cross tube construction with 30% double surface not enclosing cross tube; pre¬formed ribs. Undercarriage has three wheels in tricycle formation; no suspension on any wheels. Push right go left nosewheel steering independent from yaw control. Optional brake on nosewheel. Aluminium tube trike unit, with optional pod. Engines mounted below wing driving pusher propellers. Trike unit and wing use aluminium tube to British HT30TF specification, bright polished and sleeved at stress points. Wing rigged with plastic coated stainless steel wires; wing mate¬rial is Bainbridge Dacron.
Although the TR2 Mk I was intended as a two seater trike unit, it was also offered in single seat form a simple conversion, as with the TRI Mk.l. Like the TR2 Mk 1 from which it is derived, this variant is now discontinued. The Skyhook Sailwings TR2 Mk.II/Cutlass CD is a side by side two seat single engined flex wing aircraft with weight shift control. Rogallo wing with keel pocket. Pilot suspended below wing in trike unit, using bar to control pitch and yaw/roll by altering relative positions of trike unit and wing. Wing braced from above by kingpost and cables, from below by cables; fixed cross tube construction with 30% dou-ble surface not enclosing cross tube; pre¬formed ribs. Undercarriage has three wheels in tricycle formation; no suspension on any wheels. Push right go left nosewheel steering independent from yaw control. Brake on nosewheel. Aluminium tube trike unit without pod. Engine mounted below wing driving pusher propeller. Trike unit and wing use aluminium tube to British HT30TF specifica¬tion, bright polished and sleeved at stress points. Wing rigged with plastic coated stain¬less steel wires; wing material is Bainbridge Dacron.
The TR2 Mk.II was the 1982 two seat trike unit from Skyhook Sailwings and is identical in all respects to the Mk.I except that the twin engined power pack is replaced by a Hunting HS525A twin-¬cylinder engine, with conventional reduction drive and propeller.
TR2 Mk.I/Cutlass CD Engines: 2 x Solo 210 cc, 12 hp each at 5500 rpm Two propellers diameter and pitch 50 x 30 inch, 1.28 x 0.76 m V belt reduc¬tion, ratio 2.7/1 Max static thrust 200 lb, 91 kg Power per unit area 0.12 hp/sq.ft, 1.3hp/sq.m Fuel capacity 3.6 US gal, 3.0 Imp gal, 13.6 litre Length overall 12.7 ft, 3.87 m Total wing area 198 sq.ft, 18.4 sq.m Nosewheel diameter overall 12 inch, 305 mm Main wheels diameter overall 12 inch, 305 mm Empty weight 2251b, 102kg Max take off weight 640 lb, 290kg Payload 392 lb, 178kg Max wing loading 3.23 lb/sq.ft, 15.8 kg/sq.m Max power loading 26.7 lb/hp, 11.9kg/hp Load factors; >+3.75 ultimate Max level speed >60mph, >97kph Economic cruising speed 40 mph, 64 kph Stalling speed 32 mph, 51 kph Max climb rate at sea level 200 ft/min, 1.0m/s Min sink rate 500ft/min at 32mph, 2.5 m/s at 51 kph Take off distance 150 ft, 45 m
TR2 Mk.I (Single Seat Special)/Cutlass CD Engines: 2 x Solo 210 cc, 12 hp each at 5500 rpm Two propellers diameter and pitch 50 x 30 inch, 1.28 x 0.76 m V belt reduc¬tion, ratio 2.7/1 Max static thrust 200 lb, 91 kg Power per unit area 0.12 hp/sq.ft, 1.3hp/sq.m Fuel capacity 3.6 US gal, 3.0 Imp gal, 13.6 litre Length overall 12.7 ft, 3.87 m Total wing area 198 sq.ft, 18.4 sq.m Nosewheel diameter overall 12 inch, 305 mm Main wheels diameter overall 12 inch, 305 mm Empty weight 220 lb, 100kg Max take off weight 640 lb, 290kg Payload 392 lb, 178kg Max wing loading 3.23 lb/sq.ft, 15.8 kg/sq.m Max power loading 26.7 lb/hp, 11.9kg/hp Load factors; >+3.75 ultimate
Skyhook Sailwings TR2 Mk.II/Cutlass CD Engine: Hunting HS525A Propeller diameter and pitch 54 x 36 inch, 1.37 x 0.91 m Length overall 12.7 ft, 3.87 m Total wing area 198 sq.ft, 18.4 sq.m Nosewheel diameter overall 12 inch, 305 mm Main wheels diameter overall 12 inch, 305 mm
– 1 at the root and the GA 
All Aero 