In 2015 Belite Enterprises LLC said the finished product of Belite Aircraft’s new ultralight kit, the Belite SkyDock, successfully flew for the first time. According to the company, “James did several runs up and down the runway. As soon as the plane started to climb, he reduced power to stay in ground effect.
Belite’s SkyDock prototype undergoing taxi tests
The SkyDock requires less time to build compared to most aircraft kits, and was designed to make building as easy as possible, according to the company. The parts of the kit are made from fiberglass and carbon fiber reinforcements. The SkyDock is made from CNC-cut wood, foam, and aluminum and the parts of the kit come machine cut and drilled, so there’s no welding required.
For the wings, Belite said the builder has to build the spar, put the ribs in place, and apply glue. The low-wing is completely strutless and is designed for efficiency, low drag, and low speed. The SkyDock also features detachable wings for ease of storage and transport.
The Belite SkyDock is available for preorder for $3,995.
In July 2016 Belite Aircraft’s SkyDock had been updated with a molded carbon fiber fuselaget. With 60 hp, the SkyDock will cruise at about 120 mph. With 36.5 hp, full-power speeds are expected to be greater than 85 mph.
The cabin features an aluminum spar carry-through and carbon fiber over foam core construction. The low-wing, strutless design allows for easy building and high strength, yet the wings detach for storage or transport.
When configured as an ELSA, the SkyDock has about 500 miles. Configured as an ultralight, maximum full-power cruise is 62 mph.
Kits for the SkyDock are priced to reflect different builder preferences, skills, and pocketbooks. The base airframe kit, which includes pre-molded carbon-fiber skins, is priced at $11,280. A complete kit, which includes a full complement of machined components and all nuts, bolts, and rivets, is priced at $20,675. The Polini Thor 250 36.5-hp engine sells for $4,500.
A limited number of additional delivery positions are available for late 2016 and throughout 2017.
In 2016 The BeLIte carbon fiber prototype aircraft known as SkyDock was offered for sale without reserve, as-is.
Located in La Moille IL, the landing gear were included but not installed, windshield included, but Firewall Forward is not included.
It weighs about 240 pounds on landing gear, without engine.
In April 2017 the Belite Chipper hadn’t flown. The Chipper was a work in progress and had to be shipped to Lakeland aboard a truck. Belite Aircraft’s Wiebe said he was creating the experimental Chipper two-place tail dragger as a kit powered by either an 80 or a 100 hp Rotax engine. The prototype Chipper moved from Wiebe’s CAD-machine design to the airplane in four months.
The Chipper kit has very little welding and little use of aluminium. Much of the aircraft is covered with Oratex and use composites and a honeycomb material where they fit. The airplane uses a center-of-the-cabin control stick but came with only a single set of rudder pedals and a side throttle on the left. Additional rudder pedals were in the works, as were a host of other changes.
At AirVenture ‘17 the Chipper had flown off its initial 40-hour flight waiver. A Chipper kit costs $8,995 in 2017, that price doesn’t include the engine, propeller or cockpit instruments. A finished Chipper will run about $32,000.
Empty weight: 520 lb Max gross: 1,000 lb Takeoff roll: less than 300 ft
The single seat Belite light sport aircraft first flew on 4 July 2009. The 135 kg aircraft utilises carbon fibre materials in the fabrication of struts, ribs and wing spar. The prototype was powered by a 28 hp / 29 kW MZ-34 engine
A tandem two-seat STOL general-purpose lightplane (first flown September 1988, designed by the Nanjing University of Aeronautics and Astronautics). Features of AD-200 include rear-mounted wings with winglet fins, nose canard and pusher piston engine in the rear of the fuselage pod.
Brothers Aimé and Joseph Behaeghe completed their monoplane, which probably appeared in 1912. This last machine of the Behaeghe brothers was built for the Belgian pilot Duyck. It was fitted with a 50 hp Anzani 5-cylinder and a propeller made by the Behaeghe brothers. Wing span was 7,50 meter, length 4,75 meter and wing surface 12 sq.m.
Brothers Aimé and Joseph Behaeghe completed their first aeroplane, a biplane of their own design powered by a 25hp engine, in 1910, after 12 months work. Evidently this aircraft had a limited performance but, undeterred, the brothers went on to build other aircraft.
Designed by Glen Beets, the G/B is a single-seat, open-cockpit sporting plane featuring a high parasol-braced wing and conventional tailwheel type landing gear. While the fuselage is a fabric-covered steel tube structure, the wing is built with spruce spars and ribs, also fabric covered. All plans, kits, and components are sold through the Stolp Starduster Corp.
The engine uses a 2.5:1 gear reduction unit designed and built by Beets and Fred Nelson.
Engine 70-hp Volkswagen, 1641cc. Gross Wt. 925 lbs. Empty Wt. 603 lbs. Wingspan 25 ft Length 16 ft 4in Top speed 156 mph. Cruise 120 mph. Stall 35 mph. Climb rate 2000 fpm. Takeoff run 200 ft. Landing roll 300 ft. Range: 600 sm.
In 1948 Beech built as a private venture a two-seat trainer developed from the V-tail civil Bonanza. Having tandem seating for pupil and instructor and a conventional tail unit, the aircraft was designated Beech Model 45 Mentor, and flew for the first time on 2 December 1948.
USAF evaluated three examples of the Beech Model 45, two powered by the 153kW Continental E-185-8 engine and one by the 168kW Continental E-225-8; all three were designated YT-34 by the USAF. These three aircraft made their first flights in May, June and July 1950, and were tested extensively during a competition period, being flown not only by evaluation pilots, but also in the primary training role with pupils and instructors. On 4 March 1953, the USAF selected the Model 45 as its new primary trainer, under the designation T-34A Mentor, and ultimately 450 were built for that service, 350 by Beech and 100 by the Canadian Car & Foundry Company in Montreal, Canada. An initial order from the USAF for 34 aircraft was followed by one for 25 from the RCAF and yet another from the USAF for 66. RCAF plans were changed after only one training course and in 1955, 23 of its Mentors were donated to the Turkish Air Force. The last complete airframe to be built by Car Car was the T 34A Mentor.
US Navy evaluation of the Model 45 began soon after the USAF had placed its initial contract with Beech, and on 17 June 1954 the Navy ordered 290 under the designation T-34B. A total of 423 were acquired eventually. In July 1951 one of the original prototypes was modified to mount two 7.62mm machine-guns in the wings, with provision additionally for underwing racks capable of accepting six rockets or two 68kg bombs; this was evaluated by the USAF as a potential light close-support aircraft, but no orders materialised.
The US Navy decided in 1973 to investigate the possibility of retaining the Mentor in service, with its piston engine replaced by turbine powerplant. To evaluate this proposal, the USN instructed Beech to convert two T-34Bs to turbine power, under the designation YT-34C.
The powerplant chosen by Beech for the conversion was a Pratt & Whitney Aircraft of Canada PT6A-25. In this particular application it is provided with a torque limiter that restricts power output to some 56 per cent of maximum, ensuring constant performance over a wide range of altitude/temperature conditions, and also offering long engine life. The first YT-34C was flown on 21 September 1973, and following satisfactory evaluation of the two aircraft, Beech received contracts valued at approximately $72 million for the construction of 184 new aircraft. In addition to the installation of the new engine, the production aircraft were also given structural strengthening to ensure an airframe fatigue life of some 16,000 hours. The first T-34C Turbo-Mentor entered service with the USN’s Naval Air Training Command in November 1977, and student training with the type began during the following January. Since then production has reached 353, with six being transferred to the US Army. The landing gear was designed to survive the hard simulated carrier landings practiced by student pilots and angle of attack indicators, a necessity for carrier approaches, are standard on the T-34C. Even though the Beeches are not operated on carriers, new Navy pilots become aware of the importance of angle of attack right from the beginning. Power off stall speed with gear and flaps down is 56 knots; the stall warning is a rudder shaker felt as a shudder in the pedals when approaching the stall. On 24 June 1976, the US Navy replaced both its North American T 28 Trojan and Beech T 34B Mentor trainers by the improved Beech T 34C turboprop¬-powered version of the Mentor.
In 1981 the US Navy ordered an additional batch of 41 T-34C Turbo Mentors with FY81 funds. Previously a total of 155 T-34Cs had been delivered to the USN, and 81 had been exported to seven nations. Beech developed a T-34C-1 version for armaments system training, equipped with four underwing hardpoints with a total weapons capacity of 544kg. Examples of this version have been supplied to the navies of Argentina, Ecuador, Peru and Uruguay, and to the air forces of Ecuador, Indonesia and Morocco. An export civil version, known as the Turbine Mentor 34C, has also been delivered for use in Algeria’s national pilot training school. In Japan, the Fuji company built 176 T-34s for their own and the Philippine military forces. The Canadian Car and Foundry produced 125 Mentors, and an additional 75 were assembled in Argentina.
T-34 Engine 225-hp Continental. Gross Wt. 2950 lbs. Empty Wt. 2156 lbs. Fuel capacity 50 USG. Top speed 189 mph. Cruise 173 mph. Stall 53 mph. Initial climb rate 1120 fpm. Range 975 sm. Ceiling 20,000 ft. Takeoff distance (50ft) 1200 ft. Landing distance (50ft) 960 ft. Seats 2.
T-34A Engine: Continental O 470 13, 225 hp. Max speed, 189 mph (304 kph) Cruise, 173 mph (227 kph) Initial climb, 1,230 fpm (6.24 m/sec) Service ceiling, 20,000 ft (6096 m) Range, 737 mls (1186 km) Empty weight: 2,156 lb (978 kg) Loaded weight: 2,950 lb (1338 kg) Span, 32 ft 10 in (10 m) Length, 25 ft 11 in (7.9 m) Wing area, 177.6 sq.ft (16.49 sq.m)
T-34B Engine 225-hp Continental O-470-13 Wingspan: 32 ft 10 in Wing area: 177.6 sq.ft Length: 25 ft 10 in Height: 9 ft 7 in Empty weight: 2055 lb Loaded weight: 2750 lb Fuel capacity 50 USG. Max speed: 188 mph Cruise: 167 mph Vne: 280 mph IAS Stall 53 mph. ROC: 1210 fpm Service ceiling: 21.200 ft Max range: 975 mi Takeoff distance (50ft) 1200 ft. Landing distance (50ft) 960 ft. Seats 2.
T-34C Turbo Mentor Engine: Pratt & Whitney PT6A 25, 400 shp. Prop: 3 blade, constant speed, reversible. Length: 28 ft 8 in. Height: 9 ft 11 in. Wingspan: 33 ft 5 in. Wing area: 179 sq.ft. Max ramp weight: 4,325 lbs. Max takeoff weight: 4,300 lbs. Standard empty weight: 3,003 lbs. Max useful load: 1,297 lbs. Max landing weight: 4,300 lbs. Wing loading: 23.9 lb/sq.ft. Power loading: 10.8 lb/hp. Max usable fuel: 130 USG/845 lbs. Max rate of climb, sea level: 1,440 fpm. Max rate of climb, 8,000 ft: 1,350 fpm. Max operating attitude: 20,000 ft. Max speed (17,500 ft): 214 kts. Cruise, max power at 17,500 ft: 214 kts. Cruise, max range at 20,000 ft: 186 kts. Fuel flow at max cruise: 39 USGph. Endurance at max cruise, no res: 3.3 hrs. Stalling speed, clean: 74 kts. Stalling speed, flaps down: 56 kts. Range: 683 nm / 1265 km Turbulent air penetration speed: 195 kts. Crew: 2
T-34C-1 Engine: 1 x P&WAC PT6A, 300 kW. Span: 10.2 m. Length: 8.7 m. Wing area: 16.7 sq.m Empty wt: 1360 kg. MTOW: 1950 kg. Warload: 620 kg. Max speed: 425 kph. Initial ROC: 660 m / min. Ceiling: 9150+ m. T/O run (to 15m): 595 m. Ldg run (from 15m): 470 m. Fuel internal: 490 lt. Range: 1390 km. Combat radius: 555 km.
Allison AT-34 Mentor Average conversion price: US$430,000 Engine: Allison 250B17F, 450 hp TBO: 3500 hr Fuel type: Jet A, Jet A1, JP 5, JP 8, limited AvGas Propeller make/type: 90-inch CS three-blade full-feather reversing Landing Gear type: Tri./Retr. Gross weight: 3400 lb Max landing weight: 3400 lb Empty weight, std: 2020 lb Useful load, std: 1380 lb Fuel capacity, std: 114 USgal Wingspan: 32 ft. 10 in. Overall length: 27 ft. 8 in. Height: 10 ft Wing area: 177.6 sq. ft Wing loading: 16.8 lbs./sq. ft Power loading: 7.6 lbs./hp Wheel track: 9 ft. 7 in. Wheel size: 6.00 x 6 in main; 5.00 x 5 in nose Seating capacity: 2 Cabin doors: 2 Cabin width: 25 in Cabin height: 42 in Baggage capacity: 220lb Cruise speed @12,000 ft.: 200 kt Cruise speed @17,500 ft.: 212 kt Cruise speed @23,000 ft.: 195 kt Fuel consumption @12,000 ft.: 28 USgph Fuel consumption @17,500 ft.: 25 USgph Fuel consumption @23,000 ft.: 21 USgph Stall speed (gear, flaps up) (kts.): 60 Stall speed (gear, flaps down): 55 kt Best rate of climb (sea level): 2500 fpm Service ceiling: 25,000 ft Takeoff ground roll: 600 ft Landing ground roll: 600 ft Landing over 50 ft. obstacle: 670 ft
