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TeST TST-10 Atlas

tst10


TST-10 Atlas is a single-seat motorless composite ultralight glider with optional engine installation, 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 in order to upgrade to the TST-10M. TST-10 Atlas M is a self-launching UL glider with electric retractable power plant controlled by electronic system. 2009 Price: 22900 EURO

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, 10 Atlas gliders have sold to pilots in seven countries. There is greater demand for the TST-10M model.

The TST-10 Atlas has a 15 meter wing span, all-composite structure, aerotow capable, and Club class conformant. The TST-10 is a single-seat, mid-winged monoplane with a cantilever wing, T-shaped sandwich structure tail and a classical one-wheel undercarriage. Its composite structure is made in negative molds together with the fin.

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.

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.

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-10M Atlas is a single-seat self-launcher with a retractable Rotax 447 power unit, suitable for thermal flights and long wave or ridge flights. The TST-10M can extract and retract the engine anytime during flight. 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 weight. The wheels on wing ends allow for independent rolling and take off.

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. Aerotow capable and Club class conformant, up to 150 km range is available with the engine engaged.

Since the completion and testing of the first prototype in 2004, Test have sold 25 Atlas gliders to pilots in seven countries.

The Rotax 447 has two separate membrane carburetors and belt reducer, ratio 1:2. Electric starter and the propeller is wooden, two-bladed with fixed adjustment; diameter 1200 mm. 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. 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.

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TST-10M Atlas


In 2007 a development of TST 10 MB has started. The first prototype of this modified version was finished in the spring of 2008 and after series of functionality tests a regular production has begin. Five of these motorized gliders are flying in the Czech Republic and France.

TST-10MB was developed from its predecessor, the TST-10M. As a standard the MB version is equipped with electronic servo motor, which is operated by two ways switch for retracting and extracting. This switch is equipped with safety lock for protection against accidental activation. The extracted position of undercarriage is signalized by green light and retracted position is signalized by red light on instrument panel. For higher level of safety, the unit is equipped with acoustic signal, which informs pilot about retracted undercarriage if air brakes are operated.

In case of electricity problems or empty battery, the pilot has also the possibility to extract the undercarriage by hand operated lever for safe landing. Thanks to retractable undercarriage the glide ratio was increased by one point.

Automatic connection of controls for wing to fuselage assembly simplifies the assembling of aircraft, abbreviates time of preparing before fly and it is contributing to the comfort of operation. Wings are simply joined with fuselage through root pins and controls of air brakes and ailerons are connected simultaneously and automatically, without any further adjustment. Assembling person has to install and secure only two main pins of wings.

A new seat base shape has achieved larger space above a pilot´s head, more comfortable sitting in cockpit and usability for taller people. New design of controls paths enabled an increase of fuel tank capacity up to 20 liters / usable, and reshaping of winglets, an experimentally verified position of zig-zag tapes and eddy generators, have contributed to the increasing of glide ratio by one point.

Up to 250 km range with the engine engaged is possible. The undercarriage consists of one unsprung wheel 300x100 mm, which is fully automatically retracted with the use of electric motor. 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.

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.

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-10
Wing span: 15 m
Wing area: 9.85 sq.m
Aspect ratio: 22.8
Length: 6.87 m
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

TST-10M Atlas
Wing Span: 15m
Wing Area: 9.85sq.m
Empty Weight: 322.5kg
Aspect ratio: 22.8
Structure: all-composite
Engine: Rotax 447
L/DMax: 40 at 88 km/h
MinSink: 0,62 m/s at 72 km/h
Seats: 1
Length: 6.87 m
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 permitted load factor: +4 / -2
Max calculated load factor: +5.26 / -3.26
Engine: Rotax 447, 29.5 kW (40 HP)
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

TST-10MB Atlas
Wing span: 15 m
Wing area: 9.85 sq.m
Aspect ratio: 22.8
Length: 6.87 m
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: 42 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
Engine: Rotax 447, 29.5 kW (40 HP)
Reducer: Belt 1:2
Propeller: Wooden, 1200mm
Fuel tank capacity: 20 liters
Fuel consumption when climbing: 11 liters / h
Fuel consumption at cruise speed: 9 liters / h

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