Tronador (rocket)
Tronador II rocket mockup at Tecnópolis
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| Function | Orbital launch vehicle |
|---|---|
| Manufacturer | Comisión Nacional de Actividades Espaciales |
| Country of origin | Argentina |
| Size | |
| Height | 28 m (~92 ft) |
| Diameter | 2.5 m |
| Mass | 67000 kg (including propellant) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | 250 kg (550 lb) (Polar orbit) |
| Launch history | |
| Status | Under development |
| Launch sites | Puerto Belgrano Naval Base |
| First flight | 2019 (projected) |
| First stage - Lower stage | |
| Engines | 3 * T30 |
| Thrust | 3 × 30000 kg |
| Fuel | LOX/RP-1 |
| Second stage - Upper stage | |
| Engines | 1 * other or T4R |
| Thrust | 1400 to 4000 kg |
| Fuel | Monomethylhydrazine(MMH)/N2O4 |
Tronador, also known as Thunderer, is a series of Argentine rockets, including the Tronador I and Tronador II vehicles, to develop a liquid-propellant rocket expendable launch system called ISCUL (Inyector Satelital de Cargas Utiles Ligeras, Light Payloads Satellite Launcher).
The Tronador I is an unguided liquid-fueled rocket used for sub-orbital spaceflight test flights. Its development led to the larger VEx test rocket that will test the technologies needed for the Tronador II, which has a guidance system and would be capable of reaching low Earth orbit.
The Tronador I is an unguided liquid-fueled rocket used for sub-orbital spaceflight test flights.
The Tronador I (T1) vehicle was flown successfully on June 6, 2007 from Puerto Belgrano Naval Base near Bahía Blanca, in the south east of the Buenos Aires Province. This was the first flight of a technology demonstrator vehicle for the program.
The Tronador Ib (T2) vehicle was flown successfully on August 5, 2008 from Puerto Belgrano Naval Base. This was the second technology demonstrator vehicle flown for the program.
This was the first cooperative test flight between Comisión Nacional de Actividades Espaciales and Brazilian Space Agency; it was successfully flown in December 2007 (Operacion Angicos). The payload built by CONAE carried several experiments to validate subsystems for the program such as: IMU (Inertial Measurements Unit, that used IFOG's), GPS receptor (for navigation), all integrated into the on-board computer, and an attitude control system via cold-gas thrusters. The payload unit completed a suborbital flight carried by an AEB-built VS-30 solid-propellant rocket booster, and was then recovered from the sea after landing with parachutes.
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Wikipedia