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TeST TST-13 Junior

test-tst-13


TST-13 Junior 2005is a single-seat ultralight composite glider with an engine installed in the front part of the fuselage and all-composite successor to the TST-9. 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 pleasurable flying and to 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 the same wing span of 15m and the fuselage of the TST-10 was modified 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 controlled tailwheel.

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.

The power unit cab be either Rotax 447 or 503, fitted with a wooden, two-bladed, ground adjustable propeller, dia 1600 mm. Alternatively, propeller SPORTPROP adjustable to a flag position for soaring.Fuel tanks provide for powered flights longer then 6 hours
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. 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.
The fuselage with a shell structure is made in the negative mould together with the fin. The tail is a T-shaped sandwich structure. 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. 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).
The TST-10 ATLAS, TST-13 JUNIOR and TST-14 BONUS – formed the core of the 2009 production program and have brought a great deal of commercial success.

TST-13
Wing span: 15 m
Wing area: 10.03 sq.m
Aspect ratio: 22.8
Length: 7.45 m
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     
Engine: Rotax 447 or Rotax 503
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
Seats: 1

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