The strut high wing aircraft created with attention to every detail. Elegant - safe - comfortable
The JK-05 JUNIOR is a strut high wing aircraft.
All major airframe assemblies have a shell structure made of composites based on glass or carbon fibre. The fuselage in the form of a self-supporting shell stiffened locally with 3D material, houses a double cockpit in the front part with places next to each other.
Cockpi width 1.2 m.
The shell is technologically divided into two symmetrical halves with stiffeners, and an integrated floor - trunk plate, glued in when connecting the halves.
Seats with a shell structure made of composites.
Cockpit cover - a wind-up glass made of ultraviolet-resistant acrylic glass (PMMA polymethyl methacrylate), on a composite frame, divided in the plane of symmetry, hung on a central pillar - opened upwards, inwards.
The unit connecting the wings is a flat steel tubular truss.
Vertical stabilizer integral with the fuselage.
Tricycle landing gear with a front wheel. The main undercarriage legs self-supporting, composite. Main wheels braked together, front wheel steered, coupled to the rudder. Optionally, the wheels are covered with laminated fairings.
Rectangular wings with a characteristic narrowing at the fuselage to improve visibility. The NN-1817 profile was used for its resistance to contamination of the leading edge, with very favorable aerodynamic characteristics - tested on the PW - 5 "SMYK"glider. The wing structure is shell, sandwich, with a load-bearing girder supported by a strut.
Over the entire span, a slotted flaperon of a shell structure, hung to the wing on five booms, driven at the fuselage. The flaperon is made of carbon laminate due to the necessary high torsional stiffness, with the lowest possible weight (anti-flater requirements). There are no complicated installations or control systems inside the wing.
Classic horizontal tail with a rectangular contour, shell structure made of composites. Shell rudder. Pusher control systems.
Elevator trimmer - spring-loaded, electrically adjustable. In the basic version, one joystick in the center of the cockpit.
ROTAX 912 UL engine with 80 HP.
70 liter fuel tanks behind the crew cockpit.
COCKPIT EQUIPMENT
Two seats with a shell structure made of composites with reinforcement of glass and carbon fibers (color of the upholstery to be agreed). Two sets of seat belts. Side air inlets.
CONTROL SYSTEMS
The control planes are powered by a system of rods and torsion tubes. Control of the elevator and ailerons via the central joystick located between the seats. Rudder control by two sets of pedals (in front of the left and right seat). Control of flaps and elevator trimmer, electric, by two sets of buttons on the joystick head. Control of main wheel brakes - with a lever on the joystick. Engine control (gas) - with levers on the sides in the aircraft cockpit. Controlling the mixture composition (choke) - with a lever on the left side of the instrument panel.
DRIVE UNIT
ROTAX 912 UL engine. The engine is fixed to the fuselage on a tubular steel frame by rubber shock absorbers. Aero-Sail three-blade propeller with a diameter of 1.72 m, with a pitch adjustable on the ground. Carbon composite engine covers, fastened with the Cam-Lock quick coupler system. Automatic coolant temperature control (thermostat).
FUEL SYSTEM
The fuel system includes: two connected tanks with a total capacity of 70 l built in the fuselage behind the cockpit, a settler and a fuel filter. Rubber fuel lines.
ELECTRICAL INSTALLATION
Electric receivers
Power
Switches in the cockpit
Pilot-navigation equipment
Powertrain indicators
PAINTING
In white. Cockpit in gray
| engine | ROTAX 912 UL | ||
| engine power | 80 KM | ||
| fuel tank capacity | 70 l | ||
| fuel consumption | 10 l/h | ||
| wingspan | 10,58 m | ||
| bearing surface | 10,2 m2 | ||
| length | 5,7 m | ||
| height | 2,25 m | ||
| empty weight (with GRS) | 299 kg | ||
| maximum weight (with GRS) | 472,5 kg | ||
| cruising speed | 170 km/h | ||
| maximum speed horizontal flight | 205 km/h | ||
| Vne speed | 240 km/h | ||
| stall speed | 55 km/h | ||
| climb speed | 6 m/s | ||
| take-off run | 80 m | ||
| landing run | 100 m | ||
ROTAX 912 UL
| engine power | 80 KM |
| fuel tank capacity | 70 l |
| fuel consumption | 10 l/h |
| wingspan | 10,58 m |
| bearing surface | 10,2 m2 |
| length | 5,7 m |
| height | 2,25 m |
| empty weight (with GRS) | 299 kg |
| maximum weight (with GRS) | 472,5 kg |
| cruising speed | 170 km/h |
| maximum speed horizontal flight | 205 km/h |
| Vne speed | 240 km/h |
| stall speed | 55 km/h |
| climb speed | 6 m/s |
| take-off run | 80 m |
| landing run | 100 m |
