LSA/UL

Airmass Inc

TerryLeave a comment

John C. Massey of Texas began hang gliding in the early days but after being transferred to Kansas City by IBM began thinking powered machines. He began building his own design hang gliders in his garage and eventually became a dealer, building and maintaining hang gliders and ultralight lines.

The business eventually grew and moved it to an old schoolhouse in DeSota Kansas.

1982: Airmass Inc, 16845 Kenneth Road, Hillside Airport, Stilwell, Kansas 66085, USA.
By 1983 Airmass had ceased trading.

AirLony Highlander

TerryLeave a comment

The Highlander is a modern biplane, constructed for higher limit factors than most ultralights.
The lower wing has the NACA 2412 profile, and upper the NACA 415 profile. Wings, fuselage and wing canopy are mutually braced by steel profiled struts and wires. The wingtips are rounded, and the ailerons are on both wings, their deflections are diferential.

The tail assembly is of classic elevator and rudder, and tailplane and fin profile is plain plate. The tail assembly is braced by steel struts and wires. The landing gear is fixed, tail wheel type, and the main landing gear is created by laminated spring. The wheels have independent hydraulic brakes, controlled by pedals on the rudder steering. The tail wheel is controlable with the rudder.

Any engine of 80 HP can be used and propeller of 1800 mm diameter. Allowable weight of engine: 70-100 kg.

Controls are single, in the rear cockpit only (with optional dual). Ailerons and elevator are controlled by rods and levers, rudder by steel cables.

The airplane is in standard equipped by instruments for flight and engine monitoring.

Stall: 35 kt / 40 mph / 65 kmh
Cruise: 86 kt / 99 mph / 160 kmh
VNE: 102 kt / 117 mph / 188 kmh
Empty Weight: 240 kg / 529 lbs
MTOW Weight: 450 kg / 992 lbs
Climb Ratio: 2000 ft/min / 10 m/s

AirLony Skylane

TerryLeave a comment

Skylane is classic design, two seat, shoulder-wing monoplane. Although it is an ultralight, this plane is noted as a “small Cessna“.This plane can be used for towing of sail planes too.

The wing is strut-braced, wooden design, with a semi-laminar profile MS (1)-313. The centre section is rectangular and outer parts are trapezoidal, with short winglets on the tips. The main spar, situated in 37% of chord, is made of wood. In front of main spar, in rectangular part, is torsion box, with integral fuel tanks (2×35 litres). Trapezoidal part of torsion box is coated by plywood. Behind the main spar, wing consists of wooden ribs and short auxiliary spar. The ribs are coated by aviation fabric.

Landing flaps are single-slotted, in 29% of depth, made of wood and consist of spar, ribs, plywood and fabric coating. They have fixed positions at 13°, 29°and 37°, and are electric servo operated.

The ailerons are all-wood, with one spar, ribs, plywood and fabric coating and are operated by rods with diferential deflections.

The all-wood tail assembly structure is with elevator and rudder. The profile of fin and tailplane is symetric, NACA 0012. Design of tailplane assembly is the same as design of landing flaps and the fin is integrated part of fuselage.

The undercarriage is fixed, three wheel type and the main landing gear is laminated spring. The wheels have independent hydraulic brakes, controlled by pedal brake on the rudder steering. Towed type nose gear is spring loaded by steel spring with hydraulic absorber. It is not steered; freely slewing round about 360°.

An engine of 50-100 HP can be used and propeller can be fixed blade, adjustable blade or variable pitch blade with diameter of 1700 mm. Weight of engine assembly should be 50-80 kg.

Ailerons and elevator are controlled by rods and levers, and the rudder is controlled by steel cables.

Stall: 35 kt / 40 mph / 65 kmh
Cruise: 97 kt / 112 mph / 180 kmh
VNE: 112 kt / 129 mph / 207 kmh
Empty Weight: 258 kg / 569 lbs
MTOW Weight: 450 kg / 992 lbs
Climb Ratio: 1200 ft/min / 6 m/s