LSA/UL

Ultavia Aircraft Ultavia

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Single seat single engined high wing mono¬plane with conventional three axis control. Wing has swept back leading and trailing edges, and constant chord; no tail, canard wing. Pitch control by fully flying canard; yaw control by tip rudders; roll control by spoilers; control inputs through yoke for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile; single surface. Undercar¬riage has three wheels in tricycle formation; suspension NC on nosewheel and glass fibre suspension on main wheels. Push right go-¬right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube framework, with pod. Engine mounted below wing driving pusher propeller. Rudders and canard are covered in Stits polyriber fabric.

The prototype having made its first flights at the end of the summer in 1982. The prototype used a KFM 107ER motor which gives, according to Ultavia Aircraft, 25 hp at 6300 rpm and is becoming optional on the production models, the standard version coming with a Cuyuna 430R; a 2/1 reduction drive system for the 430R is also optional for $300 extra. The Ultavia is fitted with a yoke, rather than a stick. Its spoilers can be used differentially to control roll and together to act as air brakes. This machine comes as standard with a glass fibre nose cone, fitted with a Lexan transparent windscreen. The accent is put by the manufacturer on rapid rigging and de rigging, with single ¬surface resin impregnated Dacron wings which can be rolled up around the spars and stored in a bag, like a Rogallo wing. A genuine 15 min rigging time is claimed.

The Ultavia will be available during the summer of 1983, as a kit requiring 30h assembly at a price of $4595 (with a Cuyuna 430D) or factory built for $5395. A KFM 107ER engine costs $640 extra; an instrument panel is also available.

Engine: Cuyuna 430R
Max power 30hp at 5500rpm
Propeller diameter and pitch 54 x 17 inch, 1.37 x 0.43 m
Belt reduction, ratio 2.0/1
Power per unit area 0.19 hp/sq.ft, 2.1 hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Wing span 32.0ft, 9.75m
Constant chord 5.0 ft, 1.52 m
Main wing area 155 sq.ft, 14.4 sq.m
Main wing aspect ratio 6.6/1
Nosewheel diameter overall 11 inch, 28 cm
Main wheels diameter overall 11 inch, 28cm
Empty weight 230 lb, 104kg
Max take off weight 480 lb, 217kg
Payload 250 lb, 113kg
Max wing loading 3.09 lb/sq.ft, 15.1kg/sq.m
Max power loading 16.0lb/hp, 7.2kg/hp
Never exceed speed 55mph, 88kph
Stalling speed 24mph, 39 kph
Best glide ratio with power off 10/1
Take off distance 150 ft, 45 m
Service ceiling 13,000 ft, 4000 m

ULPower UL350

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UL350iS

The engines feature FADEC (full authority digital engine control) with multi-point electronic fuel injection, and dual electronic ignition (with variable timing), excellent power-to-weight ratio, and high fuel efficiency in a conventional configuration: Air-cooled, direct drive, horizontally opposed four-cylinder.

UL Power Engines have been developed specifically for use in light aircraft and are manufactured with fully electronic ignition and multi-point fuel injection (FADEC) system as standard equipment.

  • Four-stroke, air cooled, four-cylinder opposed engine
  • Dual (redundant) electronic spark ignition (variable timing)
  • Multi-point electronic fuel injection with automatic altitude and temperature compensation
  • Electronic RPM limiter
  • Direct propeller drive
  • Wet sump forced lubrication with integrated pressure regulator
  • 5 bearing crankshaft with thrust ball bearing
  • Ram air cooled cylinders and cylinder heads
  • Electric fuel pump and pressure regulator to eliminate vapor lock and facilitate starting even under adverse conditions.

UL Power engines are manufactured in Europe.

UL350i
Capacity: 3503 cc / 214 cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 100 mm / 3.937 in
Max Power: 118hp @ 3300 rpm
Max Torque: 305Nm / 225 ft.lb @ 2400 rpm
Installed Weight: 78.4 kg/172.8 lb
Compression Ratio: 8:1
Fuel: min 95 OCT / 87 MON
Cylinders: 4
Firing Order: 1 – 3 – 2 – 4
Configuration: Flat-4, direct propeller drive, air-cooled
Direction of Rotation: Clockwise – seen from cockpit
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y

UL350iF
Max Power: 90 kW (120 hp)
Capacity: 3503 cc
Configuration: Flat-4, direct propeller drive, air-cooled

UL350iS
Capacity: 3503 cc / 214 cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 100 mm / 3.937 in
Max Power: 130 hp @ 3300 rpm
Max Torque: 320Nm / 236 ft.lb @ 2400 rpm
Installed Weight: 78.4 kg/172.8 lb
Compression Ratio: 8.7:1
Fuel: min 98 OCT / 89 MON
Cylinders: 4
Firing Order: 1 – 3 – 2 – 4
Configuration: Flat-4, direct propeller drive, air-cooled
Direction of Rotation: Clockwise – seen from cockpit
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y

ULPower UL260

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ULPower UL260i

The engines feature FADEC (full authority digital engine control) with multi-point electronic fuel injection, and dual electronic ignition (with variable timing), excellent power-to-weight ratio, and high fuel efficiency in a conventional configuration: Air-cooled, direct drive, horizontally opposed four-cylinder.

UL Power Engines have been developed specifically for use in light aircraft and are manufactured with fully electronic ignition and multi-point fuel injection (FADEC) system as standard equipment.

  • Four-stroke, air cooled, four-cylinder opposed engine
  • Dual (redundant) electronic spark ignition (variable timing)
  • Multi-point electronic fuel injection with automatic altitude and temperature compensation
  • Electronic RPM limiter
  • Direct propeller drive
  • Wet sump forced lubrication with integrated pressure regulator
  • 5 bearing crankshaft with thrust ball bearing
  • Ram air cooled cylinders and cylinder heads
  • Electric fuel pump and pressure regulator to eliminate vapor lock and facilitate starting even under adverse conditions.

UL Power engines are manufactured in Europe.

The UL260iF is specially dedicated to the French market. The engine is based on the UL260iS and specially adapted to be compliant with the French ULM (ultralight) regulations.

On 7 October 2013 the first Europa (G-BWUP) to be fitted with a UL Power UL260iS 107 Hp engine flew for the first time from a Private strip in Wiltshire, UK. With the test pilot going up for a 30 min first flight and no real probs reported apart from the Constant speed prop needed adjusting. The second flight was a little shorter but the Prop was working well now and the take off roll with one up and half fuel and nil wind was only 220 meters.

UL260i
Configuration: Flat-4, direct propeller drive, air-cooled
Max Power: 72 kW / 97 hp @ 3300 rpm / 82 hp @ 2800 rpm
Capacity: 2592 / 158 cc / cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 74 mm / 2.913 in
Max Torque: 207Nm
Weight: 72.3 kg/ 159.3 lb
Compression Ratio: 8.16:1
Fuel: min 95 OCT / 87 MON
Cylinders: 4
Firing Order: 1 – 3 – 2 – 4
Oil capacity: 2.5 lt / 0.66 US gal
Direction of Rotation: Clockwise – seen from cockpit
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y

UL260iS
Configuration: Flat-4, direct propeller drive, air-cooled
Capacity: 2592 cc / 158 cu.in
Bore: 105.6 mm / 4.157 in
Stroke: 74 mm / 2.913 in
Max Power: 80 kW / 107 hp @ 3300 rpm
Max Torque: 240 Nm / 177 ft.lb @ 2800 rpm
Installed Weight: 72.3 kg/159.3 lb
Compression Ratio: 9.1:1
Firing Order: 1 – 3 – 2 – 4
Direction of Rotation: Clockwise – seen from cockpit
Fuel: min 98 OCT / 89 MON
Cylinders: 4
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y

UL260iF
Configuration: Flat-4, direct propeller drive, air-cooled
Max Power 74 kW / 100 hp @ 3000 rpm
Max Torque 240 Nm @ 2800 rpm
Capacity: 2592 cc
Bore: 105.6 mm
Stroke: 74 mm
Compression ratio: 9.10 : 1
Firing order: 1 – 3 – 2 – 4
Weight: 72.3 kg/159.3 lb
Fuel: min 98 OCT / 89 MON
Cylinders: 4
Oil capacity: 2.5 lt / 0.66 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 1500h / 10y

UL260iSA
Configuration: Flat-4, direct propeller drive, air-cooled
Displacement: 2592 cc / 158.17 cu in
Bore: 105.6 mm / 4.157 in
Stroke: 74 mm / 2.913 in
Compression Ratio: 9.10 : 1
Max Power: 80 kW / 107 hp @ 3300 rpm
Max Torque: 240Nm / 177 ft.lb @ 2800 rpm
Firing Order: 1 – 3 – 2 – 4
Direction of Rotation: Clockwise – seen from cockpit
Installed Weight: 74.8 kg/164.9 lb
Fuel: min 98 OCT / 89 MON
Cylinders: 4
Oil capacity: 3.0 lt / 0.79 US gal
DC output: 30 Amp (+/- 15 Amp available above engine/fuel pump needs)
TBO: 250h
Equipped with an inverted oil kit

UL Power

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ULPower Aero Engines is a Geluveld, Belgian engineering company which manufactures engines specifically designed for light aircraft/rotorcraft use.

For several years a Belgian group of enthusiastic private individuals financed and developed a new modern technology, light weight engine for aircraft application. After 3 years of development and testing of several prototypes the first UL260i 72 kW (97 hp) engine was installed in an aircraft (a Lambert Mission M106). First flight tests were performed in December 2005. After proving the engine reliability on the ground and in the air, the project was merged into an official company structure.

ULPower Aero Engines was officially formed in March 2006 to concentrate on the further design and manufacture of engines where lightweight, power and reliability are important to the client. Series production commenced by the end of that year.

Over the first years, the UL260i has equipped several popular light aircraft, e.g. Storch, Zenair Zodiac CH601, Escapade, Dynaero MCR01, Hannuman X-Air.

In 2009, ULPower launched some new engine types: the UL260iS 80 kW (107 hp), the UL260iSa 80 kW (107 hp) (with inverted oil system for aerobatics) and the UL350iS 93 kW (125 hp). For the French market specifically, two adapted versions are also available: the UL260iF 74 kW (100 hp) based on the UL260iS and the UL350iF 90 kW (120 hp) based on the UL350iS, specifically for gyrocopter application.