TST-13 Junior


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TST-13 Junior is a single-seat ultralight composite glider with an engine installed in the front part of the fuselage. The aircraft is suitable for tourist flights and leisure thermal flying.

The goal of the development work on the TST-13 was to design an ultralight aircraft for pleasure flying and feature aerodynamics to allow utilization of thermal conditions for gliding and motorless flights. The concept of the TST-13 is based on the high-performance TST-10 Atlas glider. We used 15 m wing of the TST-10 and modified fuselage to enable the installation of the propulsion unit with a thrust propeller in the front part of the fuselage. The fuselage of the TST-13 features an instrumentation panel and design conforming to the category of ultralight motorless aircraft. The landing gear is fitted with two wheels with a steerable tailwheel.

The combination of the proven high-quality wings and the classic concept of motorized aircraft allowed us to build a very convenient motorized glider for both long flights using an engine as well as trouble-free motorless thermal flights.

To improve the aerodynamic performance, the aircraft can be equipped with a propeller that is adjustable during flight, including flag positioning.

Instrumentation for the TST-13 Junior glider is fully optional - the customer can either choose instruments from our list of avionics manufacturers or he/she can supply the instrumentation himself/herself during the production of the ordered aircraft.



Brief Glider Characteristics:
  • Long-life all-composite structure
  • Power unit Rotax 447 or 503
  • On ground or in-flight adjustable propeller
  • Fuel tanks for powered flights longer then 6 hours 
  • 15 meter wing span
  • Glide ratio 29
  • Performance allowing long motorless flights
  • Easy maintenance

TST-13 - Technical Description

CHARACTERISTICS
TST-13 is a one-seated, mid-winged monoplane with a cantilever wing, T-shaped tail and two-wheel undercarriage. Its composite structure is made in negative moulds.
WING
The wings with sandwich structure are equipped with ailerons and air brakes on the upper surface. The strength system of the wing is formed by the main spar, by the aileron spar and by the root rib. All the wing profile of the sandwich structure forms the torsion box.
The wings are interconnected by fittings and two horizontal pins. The connection wing-fuselage is made by means of pins and fittings placed in the fuselage and the wing root rib. The composite ailerons are hung by four hinges with the turning axis on the upper side. Air brakes on the upper side of the wing are made of aluminium and are retracted into pits.
FUSELAGE
The fuselage with a shell structure is made in the negative mould together with the fin.
TAIL
The tail is a T-shaped sandwich structure.
CONTROLS
The controls, enabling pitch, roll, air brake and trim controlling, are of the lever design, with a push-pull rods system. The relevant backstops are placed on the stick. The yaw control with adjustable pedals is transmitted by cables. The airplane can be trimmed by a torsional member in the elevator drive that is controlled by a lever.
UNDERCARRIAGE
The main landing gear with two wheels (300 x 100 mm) is housed in a flexible dural leg. The lever placed on the stick controls the brake. The tail landing gear is provided with turnable tail wheel (120 x 30 mm).
   
Power Plant
ENGINE Rotax 447 or 503 with two separate membrane carburetors and reducer B, ratio 1:2. Electric starter.
PROPELLER is wooden, two-bladed, on the ground adjustable, dia 1600 mm. Alternatively, propeller SPORTPROP adjustable to a flag position for soaring.


TST-13 Junior - Technical Parameters

Technical Data
Wing span
15 m
Wing area
10.03 m2
Aspect ratio
22.8
Length
7.45 m
Number of seats
1
MTOW without BRS
300 kg
MTOW with BRS
322.5 kg 
Weight of pilot and fuel
65 - 122.5 kg
Vne 200 km/h
Max. maneuvering speed 140 km/h
Max. speed with extended air brakes      
140 km/h
Max. speed in aerotow 140 km/h
Stall speed
65 km/h
Cruise speed 
120-160 km/h
Max. glide ratio  24-32 at 93 km/h 
Max. permitted load factor
+4 / -2 
Max. calculated load factor
+4.8 / -2.8
   
Power unit
Engine
Rotax 447 or Rotax 503
Carburetor
2x membrane
Reducer
1:2
Propeller
Wooden, 1600mm
Fuel tank capacity
40 liters
Fuel consumption when climbing
11 liters / h
Fuel consumption at cruise speed
9 liters / h
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