TST-10 Atlas


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TST-10 Atlas is a single-seat motorless composite ultralight glider with optional engine installation.

TST-10 Atlas is designed mainly for performance thermal flights and wave and ridge flying. Its performance parameters are comparable to common gliders within the standard class. Its weight allows for very easy handling when landed during assembly or disassembly. 

The major advantage of the TST-10 is the possible and easy installation of the power unit. This makes the TST-10 different from most gliders. The very reasonable price allows customers to purchase a new heavy-duty glider, which takes off in towing and is suitable for thermal flights with the option of future engine installation in order to upgrade to the TST-10M.

Instruments of the TST-10 Atlas glider are 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 Atlas can be delivered with an entire range of accessories and a trailer.

The flight characteristics, the quality of design, the wide range of instrumentation offered as well as the reliable power unit are key reasons for the popularity and commercial success of the glider. Since the completion and testing of the first prototype in 2004, we have sold 10 Atlas gliders to pilots in seven countries. From our experience, there is greater demand for the TST-10M model, which is the version with an engine installed.



Brief Glider Characteristics:
  • 15 meter wing span
  • Glide ratio 40
  • Long-life all-composite structure
  • Ready for installation of the power unit
  • Aerotow capable
  • Club class conformance
  • Easy assembly, disassembly and transport
  • Easy maintenance
TST-10 - Technical Description
CHARACTERISTICS The TST-10 is a single-seat, mid-winged monoplane with a cantilever wing, T-shaped tail and a classical one-wheel undercarriage. Its composite structure is made in negative molds.
WING The wings with sandwich structure are equipped with ailerons and air brakes on the upper surface. There are no ribs in the wing. 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.
CONTROL 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 in the left of the cockpit.
UNDERCARRIAGE The undercarriage consists of one unsprung wheel 300x100 mm mounted in a flexible fork. The brake handle is on the control stick. The wingtip wheels serve for independent taxiing and take-off. The turnable tail wheel 80x30 mm enables easy manipulation on ground.


TST-10 Atlas - Technické parametry

Wing span 15 m
Wing area
9.85 m2
Aspect ratio
22.8
Length
6.87 m
Number of seats
1
MTOW without BRS
300 kg
MTOW with BRS
322.5 kg 
Weight of the pilot
65 - 115.5 kg
Vne 180 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
60 km/h
Max. theor. glide ratio without winglets  
38 at 88 km/h
Max. glide ratio with winglets  40 at 88 km/h 
Min sink rate
0,62 m/s at 72 km/h
Max permitted load factor
+4 / -2 
Max calculated load factor
+5.26 / -3.26
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