• 
• 
• 

• 

Based on the principle of creating a cheap, simple and light people's aircraft with little horsepower, the light aircraft KE. 8.
Even the external structure makes it easy to see that these principles have been largely realized.
The aircraft is a cantilevered high-wing aircraft with a 15/20 hp U2 Ursinus engine, which is only suitable for the construction of this
type of light aircraft due to its low weight of only 27.5 kg.
In the design of the hull, preference was given to the proven steel raw method, i.e. welded raw steel with tube diagonals. The
outcrossing with steel wire between the individual fields was dispensed with in view of a simpler and cheaper method of production, since a mathematical
check showed almost no difference in weight between the two types of construction. Experience in recent years has shown that tubular steel hulls provide occupants with a higher level of safety in the
event of breakage than wooden hulls, which have a far greater capacity for strength and work. The hull shape
results from covering with fabric. The stick control, which is very simple in construction, can be aligned very
easily after loosening 4 bolts by means of disc supports. The side control is operated by suspended pedals, which are organically connected by means of compensating rollers. The control mechanism is
formed from levers and ropes guided around rope pulleys. All parts are easily accessible and the bearing points are lubricated by means of a sub-nipple.
The Ursinus engine type U2 hangs in a steel welded to the fuselage, and has 3-point suspension, with the simplest possible installation.
For the three-point attachment of the motor, 3 strong claws are arranged on the motor, in such a way that only the upper fastening bolt is
stressed on shear. At the two lower attachment points, the reaction pressure acts almost vertically on the spar. The engine and fuselage bow are
covered in aluminum. Around the cylinders are side hoods, which are open at the front and back, in the style of the well-known town-end ring. The bonnet is divided in the
middle and can be opened or lowered up and down after loosening a few quick-release fasteners, and then allows good control of the engine due to the now completely
exposed engine. There is a fire bulkhead behind the engine.
In front of the fire bulkhead is the 2.5 liter oil tank, and behind the bulkhead on the upper fuselage spars is the approx. 20 liter fuel tank,
which is sufficient for a time of almost 4 full throttle flight hours.
The wing deck with a wingspan of 5.6 m is fixed with 4 bolts on the hull, which is raised and retracted upwards. It is designed in one piece with
two spars with rounded ends while maintaining the same wing depth. In the area of the driver's seat there is a small sectional seat. The wing deck is planked with plywood of 1.2-0.8 mm from
the upper edge of the rear spar over the wing nose to the lower edge of the rear spar. Over the whole surface, a total of 6 normal ribs are formed as box ribs. The plywood planking of the surface is somewhat heavier in execution, butHowever, it is cheaper than internal bracing, especially since the latter has a very unfavorable effect on
the cantilevered wing, and thrust plates also preserve the profile very well, a condition that is a
necessity for these small aircraft. God 593 was used as the profile.
The 0.36 nr ailerons are connected to the rear spar on the outside. Tubular steel version.
In the chassis with a standard gauge of 1.10 m, the pivot point of the sprung axle has been moved downwards in order to
achieve the greatest possible assembly accuracy, without the use of templates. By simply adjusting the inner tension strut, which goes according to the fuselage center, the track gauge can be readjusted at any time
. The non-continuous axle offers the well-known advantages when taking off and landing on uneven or grassy surfaces. The
suspension travel is 50 mm + elasticity of the tire.
The damping fin of 0.43 m2, which can be adjusted on the ground, is designed in two parts in tubular steel and is inserted sideways into the rear cutting edge of the fuselage
. It is supported by steel wire after the stem and up to the side fin spar.
The elevator is also two-part and connected by a tube, there are 2 bearings on each side, which are bushed out with brass bushings.
On the extension of the trunk stem the lateral fin adjoins. The front edge arch is attached to the penultimate frame.
The 0.3 m2 rudder is mounted three times on the side beam and is equipped with brass bushings.
All rudders are covered with fabric planking and are not relieved.
The assembly of the machine is the simplest imaginable. By loosening 4 aileron cables and 4 plug-in pins, the wing can be removed.
Data: Total wing area 5.25 m2, Aerodyn. Wing area 5.0 m2, aspect ratio rt = 0.167 : rt= 1:6; Wing profile Gött: 593,
cruising speed 141 km-h, maximum speed 161 km-h, landing speed 79 km, climb speed 2.3 m-sec.; Setup weight 110 kg, payload
= 100 kg, flying weight 210 kg, wing load 40 kg-m2, power load 10.5 kg-hp, wingspan 5.6 m, length 4.4 m, height 1.45 m, engine: Ursinus U2, 20 hp,
operating radius 500 km