The 1979 M79S Wasp II was a two place Ag modification of the Bell 47G. First flown on 6 January 1979.
First flown in 1979 with a piston engine, the M79T Jet Wasp II was a two-seat turboshaft powered modification of the Bell TH-13T helicopter. One was built (N1001X) in 1982.
M79S Wasp II
Engine: TVO-435, 270hp
Rotor: 37’1″
Length: 36’0″
Useful load: 1480 lb
Max speed: 106 mph
Cruise: 80 mph
Range: 300 mi
Seats: 2
M79T Jet Wasp II
Engine: Soloy-Allison 250
Seats: 2
Certified in 1976, the M74 Wasp was a single-seat piston-engined agricultural/utility modifications of Bell OH-13E (Bell 47) helicopter.
The 1977 M74A Wasp applied the modifications to Bell OH-13H.
M74 Wasp
Engine: Lycoming TVO-435-A1E, 200hp
Rotor: 35’1″
Length: 31’5″
Useful load: 1020 lb
Max speed: 100 mph
Cruise: 80 mph
Range: 150 mi
Seats: 1
M74A Wasp
Engine: Lycoming TVO-435, 240hp
Seats: 1
In 1949-50 the Texas A&M College in the USA developed a concept aircraft, the first purpose built agricultural aircraft designed by Fred E Weick and Hugh DeHaven, designated Ag 1 which flew in January 1950, piloted by Ted von Rosenberg. It was a low wing monoplane of all metal construction, powered by a 225 hp piston engine and designed to carry a chemical load of 1,200 lb (544 kg).
Built with US government support, the Ag 1 N222 was demon¬strated widely throughout the USA and was well received by the six or seven hundred pilots who flew it. The main criticism was that it was underpowered, and a decision was taken to refit it with a 300 hp engine. Before this could be done the Ag 1 collided with a powerline pole and ended up on its back. But the crash demonstrated one of the qualities for which it was designed: the aircraft was destroyed except for the cockpit area, but the pilot was uninjured, even though he had been subjected to forces more than 25 times that of gravity, according to the dynamometers installed for test purposes.
Engine: Continental E-225, 225hp
Wingspan: 39’0″
Length: 29’8″
Useful load: 1200 lb
Max speed: 115 mph
Cruise speed: 100 mph
Stall: 45 mph
Range: 400 mi
Seats: 1
“Ning Hai” was the name of the Chinese Navy light cruiser that carried a floatplane. The ship’s name was painted on the sides of its aircraft, hence the confusion.
Originally, the Ning Hai carried a Japanese Aichi AB-3 seaplane. But the aircraft had to be disassembled and stowed after use, because it lacked folding wings. This limited the plane’s usefulness.
So Mar Te-Tsu of the Navy yard at Shanghai designed and built a replacement in the 1934-35 timeframe. The Hsin (Xin) was a twin-float, single-seater powered by the same 130-hp Gasuden Jimpu radial engine used in the Aichi AB-3. It generally resembled its predecessor except that the new airplane had folding wings.
The 1933 Teston Low-Wing, N11552 c/n R-1, was a two place, open cockpit, low wing monoplane, built in Georgia, USA. The only one built was powered by a 95hp Cirrus Mk III.
TST-14 Bonus is designed mainly for leisure thermal flights. Its performance is comparable to common two-seat gliders. The wheels on the wing ends allow for independent taxiing and take off.
The major advantage of the TST-14 is the possible and easy installation of the power unit in order to upgrade to the TST-14M. Bonus is equipped with complete duplicate controls and avionics. These make it suitable for flying schools that provide training on motorless and motorized gliders. Aerotow capable
Instrumentation of the TST-14 Bonus 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 Bonus can be delivered with an entire range of accessories and a trailer.
Since the completion and testing of the first prototype in 2005, we have sold 10 Bonus gliders to pilots in seven countries. There is greater demand for the TST-14M model, which is the version with the engine installed.
The TST-14 is a tandem two-seat, mid-winged monoplane with a cantilever wing, T-shaped tail and two-wheel tandem undercarriage. Its composite structure is made in negative molds. The wings with sandwich structure is 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 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 in the left of the front cockpit. The undercarriage consists of one unsprung main wheel 350×100 mm and one fixed front wheel. The brake handle is on the left side of the floor. The tail wheel 80×30 mm is turnable.
TST-14M Bonus is a two-seat motorized composite ultralight self-launcher with a retractable power unit, suitable for thermal flying, long wave or ridge flights and for flying schools. The aircraft also offers easy handling and the capability of independent take off. TST-14M Bonus is designed mainly for leisure thermal flights. Its performance is comparable to common two-seat gliders. The plane is equipped with a retractable power unit enabling independent take off and reach of an airfield without any thermal support. Engine extraction and retraction is fully automatic and is controlled by electronic servo motors. The power unit is operated by the pilot using two buttons on the instrument panel. The handling of a landed Bonus is very easy thanks to its weight. The wheels on wing ends allow for independent rolling and take off. Production commenced in 2004.
Steve Meassick, a dealer of TeST gliders in the USA, has successfully finalized the certification of the two-seater self-launcher TST-14M Bonus in the LSA category.
The Bonus glider can also be delivered in a motorless version (type TST-14), ready for possible future engine installation. Since the completion and testing of the first prototype in 2005, Test have sold 18 Bonus gliders to pilots in seven countries.
With a 17 meter wing span, complete duplicate controls and the ability to extract and retract the engine anytime during the flight, up to 150 km range is possible with the Rotax 503 engine engaged. The TST-14M is still aerotow capable. The Rotax 503 has two carburetors and reducer B, ratio 1:2. An electric starter is standard. The propeller is wooden, two-bladed with fixed adjustment; diameter 1200 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.
The TST-14J BonusJet is a two seat, high performance, self-launching, jet powered sailplane. Featuring a PBS TJ-100 turbine engine on a retractable pod, it is capable of self launching, cross country soaring and cruising flight.
Phase one flight tests have been completed. All systems are functioning perfectly. Initial flight tests show a climb rate in excess of 900 ft/minute.
TST-14 Bonus
Wing span: 17 m
Wing area: 12.01 sq.m
Aspect ratio: 24
Length: 8.24 m
Seats: 2
MTOW without BRS: 450 kg
MTOW with BRS: 472.5 kg
Weight of crew: 65 – 180 kg
Vne: 205 km/h
Max. maneuvering speed: 150 km/h
Max. speed with extended air brakes: 150 km/h
Max. speed in aerotow: 150 km/h
Stall speed: 65 km/h
Max. theor. glide ratio without winglets: 37 by 105 km/h
Max. glide ratio with winglets: 39 by 105 km/h
Min sink rate: 0,65 m/s at 85 km/h
Max. permitted load factor: +4 / -2
Max. calculated load factor: +5.2 / -2.6
TST-14M Bonus
Wing Span: 12m
Wing Area: 12.01sq.m
Aspect ratio: 24
Length: 8.24 m
Empty Weight: 472kg
MTOW without BRS: 450 kg
MTOW with BRS: 472 kg
Weight of crew and fuel: 65 – 188 kg
Structure: all-composite
Seats: 2
Vne: 205 km/h
Max. maneuvering speed: 150 km/h
Max. speed with extended air brakes: 150 km/h
Max. speed in aerotow: 150 km/h
Stall speed: 65 km/h
Max. theor. glide ratio without winglets: 37 at 105 km/h
Max. glide ratio with winglets: 39 at 105 km/h
Min. sink rate: 0,65 m/s at 85 km/h
Max. permitted load factor: +4 / -2
Max. calculated load factor: +5.2 / -2.6
Engine: Rotax 503, 34 kW (46 HP)
Reducer: 1:2
Propeller: Wooden, 1200mm
Fuel tank capacity: 30 liters
Fuel consumption when climbing: 11 liters / h
Fuel consumption at cruising speed: 9 liters / h
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
TST-12, a tandem low-wing plane combining modern features and traditional wooden construction (flown in summer of 2004; built as a prototype only).
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 300×100 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 80×30 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.
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 300×100 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 80×30 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
The TST-9 Junior is a modernized TST-7 with an elliptical fuselage and T-shaped tailplanes, first flown in 2000.
A motorglider / microlight aircraft, with Rotax 447 engine at front and nose wheel undercarriage the TST-9 Junior is JAR 22 certified.
All Aero 