Swan Aeroplane

SWAN is a single-seater ultralight aircraft.

There is a version with 115 kg empty weight which meets the requirements of the USA Part 103 regulation and those of Great Britain microlight SSDR regulation.

Another version with 120 kg empty weight meets the requirements of the regulation 120 in Germany.

The third version with an empty weight between 120 and 160 kg (depending on the chosen engine and equipment) complies with many countries regulations for single-seater ultralight aircraft class with MTOW (maximum decelaration mass) of 300 kg.

We intend to build an electric engine version (MTOW=300 kg) and a hydro-aircraft version (MTOW=315 kg).

Every version has, after the name SWAN, the empty aircraft weight in kg and the engine power in HP is noted after the dash.

For example, SWAN 130-30 means the 130 kg empty weight version of the aircraft with an engine of 30 HP.

The electric version has an extra letter E and the hydro-airplane an extra letter H. For example, SWAN H160-50 or SWAN E115-22.

Design

In order to choose the best aerodynamic configuration, the fact that SWAN will be a single-seater aircraft was considered, therefore its future pilot will not be able to perform accommodation dual control flights with an experienced pilot.

For this reason, we ruled out all configurations that can be problematical for an inexperienced pilot: the “concord” configuration, the pusher engine configuration and the tailwheel landing gear configuration.

The result was a classical configuration. We placed the engine up to avoid any dangerous circumstance, including touching the ground with the propeller. We preferred the configuration with top wings for improved balance and stability.

The pilot is set right in the aircraft’s centre of gravity, so that no additional adjustments are needed regarding the pilot’s weight.

SWAN has an enclosed cockpit for smooth, pleasant flights without a heavy and expensive helmet and eases flights in low temperature weather conditions with no need of a sophisticated costume. There are two ventilation systems in the cockpit, including during take-off taxi which prevent the screen from steaming. When flying at high temperatures, the door can be simply removed. When flying at low temperatures, a cockpit heating system can be attached (optionally).

The inside is very generous for pilots up to 2,00 m height to be comfortably seated.

There are large spaces for luggage which are accessible even during the flight.

Depending on the version, the fuel tank can be 25-100 l. In consequence of the constraints imposed by the regulations regarding the empty and equipped weight, these aircrafts must have small, light engines but sufficiently powerful. We suggest the 115-120 kg empty weight version provided with one cylinder, two-stroke, air-cooled German engine, Hirth F33-28 HP.

We recommend the 120-160 kg empty weight version with two opposite cylinders engine, Hirth F23-50 HP. Equipment is available with different engines, two-stroke or four-stroke, air-cooled or liquid cooled, with power between 25 and 60 HP.

To achieve performances with these engines, we were concerned with the importance of the aircraft’s drag coefficient. This is why every part is aerodynamically shaped with much care, so that the resistance to friction to be as low as possible.

A special study was conducted for testing the induced resistance of the wing. The profile of the wing ends/tips was shaped on the computer and aerodynamically adjusted in the wind tunnel, being completed with flight examinations on 1:2,5 scale models.

The propeller is made of carbon, has two blades and it is adjustable at 1500/1600 mm diameter.

We estimated high costs for storing the aircraft in a hangar. As a result, a special design was decided on, so that the aircraft can be easily disassembled and stored in a closed car trailer, which we provide as well, that has a capacity of 750 kg. The trailer is 1,85 x 1,9 x 5,5 m.

The process of assembling and disassembling takes no longer that 20 minutes because only 7 screws need to be removed without affecting the flight controls. Owing to this improvement, expensive rent is avoided and, at the end of the flight, your aircraft is safe, protected from by the sun, wind, rain or snow, and ready to be taken home!

Manufacturing

SWAN is a light composite material made aircraft.

In agreement with the regulations, the plane has a load factor of +4G/-2G as it is built using carbon fiber, aramid fiber or fiberglass in fabrics adapted to each practical purpose: plain, twill or non-crimp (unidirectional, biaxial, triaxial). All fibers have aeronautics accreditation.

The materials used as cores in various parts are cross-linked rigid, expanded PVC and AIREX foam.

We work only with epoxy resins that have German Aviation accreditation.

The metallic parts are generally made of duralumin alloy with high mechanical properties: 7075, 2024, 2017, 2007, 6082.

SWAN is equipped with a safety cage made of CrMo 25CD4S aviation pipes with 30 and 20 mm diameters.

The wing is a composite hard surface with one main spar consisting of unidirectional carbon fiber, biaxial fiberglass, AIREX core and wood. It has 6005 ATS aluminum alloy struts with aerodynamic crossection 52,5 x 22,5 mm.

Wing flaperon, horizontal and vertical tail are all composite hard surfaces.

The fuselage is supported by a 120 mm diameter tube made of 6032T6 aluminum alloy.

The windshields are produced from Lexan polycarbonate.

The door is 0,9m x 0,96m x 0,5m and opens from inside to the wing, butterfly style. The pilot’s seat is a Kevlar-carbon anti-crash piece, fitted with standard seat belts.

SWAN is provided with classical controlling: central stick and polonier.

The stick enables the horizontal amperage through the push-pull cable and the flaperon amperage through aluminum tubes. The flaperons movement is triggered by a mechanical mixer which generates a -5°/+30° movement of the flaps and a ±8° movement of the aileron.

The front wheel is mechanically braked by the action of the stick. Optionally, it can be hydraulically braked or the main train wheels can be differentially hydraulic braked from the pedals.

The standard wheels are 300×100 in diameter with 20 mm bearings. Optionally, 400 mm x 140 mm wheels or 550 mm x 180 mm bush wheels can be assembled. The main landing gear is a blade made of carbon fiber, fiberglass and lamellar wood.

The front undercarriage strut is made of carbon fiber composite, fiberglass and a steel tube silenced by four arches.

Technical Specifications

Wing geometry

  • area 11,6 m2
  • aspect ratio 6,7
  • flaperous area 2x 1,19 m2
  • flaperous 25% chord
  • airfoil thikness 14%

 

Horizontal tail geometry

  • area 2,125 m2
  • aspect ratio 3,43
  • all moving 20% axe
  • NACA 009 airfoil

 

Vertical tail geometry

  • area 1,016 m2
  • aspect ratio 2,156
  • all moving 20% axe
  • NACA 009 airfoil