TST-10M Atlas


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TST-10M Atlas is a single-seat self-launcher with a retractable power unit, suitable for thermal flights and wave or ridge flights. The aircraft also offers easy handling and the capability of independent take off.

TST-10M Atlas offers comparable performance to other gliders in the standard class and is equipped with a retractable power unit allowing for independent take off and reach of an airfield without thermal support. Engine extraction and retraction is fully automatic and it is controlled by two electronic servo motors. The power unit is operated by the pilot with two push buttons on the instrument panel. 
The handling of a landed Atlas is very easy thanks to its light weight. The wheels on wing ends allow for independent rolling and take off.

Users of the TST-10M Atlas are mainly pilots who enjoy sport thermal flights and also appreciate independent take off, guaranteed reach of destinations even under non-ideal thermal conditions, easy handling of the glider on the ground and the quick assembly/disassembly option. The Atlas offers all for this for a low price with low operational costs.

The Atlas glider can also be delivered in a motorless version (type TST-10), ready for possible future engine installation. This makes it possible for a pilot to acquire a new glider that is prepared for easy installation of an engine at any future date.

Instrumentation of the TST-10M Atlas 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 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 25 Atlas gliders to pilots in seven countries.



Brief Glider Characteristics:
  • 15 meter wing span
  • Glide ratio 40
  • Long-life all-composite structure
  • Retractable Rotax 447 power unit
  • Independent taciing and take-off; no off-airport landings and return transports
  • Ability to extract and retract the engine anytime during the flight
  • Up to 150 km range with the engine engaged
  • Aerotow capable
  • Club class conformance
  • Easy assembly, disassembly and transport
  • Easy maintenance

TST-10M - Technical Description

Airframe
CHARACTERISTICS
The TST-10M 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.
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. Yaw control is transmitted via cables and includes adjustable foot pedals. 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.
   
Power Plant
ENGINE Rotax 447 with two separate membrane carburetors and belt reducer, ratio 1:2. Electric starter.
PROPELLER The propeller is wooden, two-bladed with fixed adjustment; diameter 1200 mm. 
EXTRACTION The power plant is extracted by a 12V DC servo motor. The servo motor also ensures automatic opening and closing of the engine door in the aircraft fuselage and controls the locking pin, which balances the propeller into a horizontal position prior to engine retraction.
CONTROLS
The retractable mechanism is handled inside the cockpit through the instrument panel. The pilot controls the extracting and retracting of the power unit with two push buttons on the instrument panel. The very movement is ensured by an electronic unit controlled by a microprocessor, which takes care of the automatic opening of the engine door, monitors the limit position of the power unit, signals the pilot about the exact situation and activity and connects the starter only in the fully extracted position. This electronic system also prevents any retraction of a running engine. Entire engine extraction/retraction lasts approximately 20 seconds. The retractable mechanism of the power unit enables self-launching and restart during flight.


TST-10M Atlas - Technical Parameters

Technical Data
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 and fuel 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
   
Power unit
Engine
Rotax 447
Power
29.5 kW (40 HP)
Carburetor
2x membrane
Reducer
Belt 1:2
Propeller
Wooden, 1200mm
Fuel tank capacity
14 liters
Fuel consumption when climbing
11 liters / h
Fuel consumption at cruise speed
9 liters / h
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