Tronador II-250
The Tronador II project uses the TII-70 and TII-150 suborbital vehicles with flight control to demonstrate the technological maturity of the propulsion, avionics and structural components required for the launcher. Due to the complexity of the technological development, several experimental tests were conducted, the first being in March 2014 with Vex1A.
LAUNCHER
TRONADOR II-250
Developed for CONAE (National Commission for Space Activities), the Tronador II is a launcher produced in the country. It is the continuation of a project that began in 2007 with the Tronador I.
With the national launcher Tronador II, the country will place its own satellites in orbit from Argentine soil. In this way, the space cycle is completed and sovereignty is gained.
Length 27 Mtsm
Diameter 2.5 mts
Liftoff weight 72 tn
Thrust 90 tn
Launch site Manuel Belgrano Space Center
Payload Satellites between 500 and 750 kilos
Functionality
It will be used to place satellites in polar orbit and to send payloads to low orbits
Propellant
Liquid propellants: kerosene (space grade) and liquid oxygen
launch stages
Up to 100 km altitude, 90% of the fuel will be used. The remaining fuel will be used to place the satellite in orbit (700 km altitude)
Phases of development
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VENG is the main contractor of the ISCUL Program (Inyector Satelital de Cargas Útiles Livianas) of CONAE and responsible for the main stages associated with the objective of developing a satellite launcher, Tronador II and III Project, covering the development of ground, flight and associated critical technologies.
TII-70
Mission
Flight at an altitude of 150 km
Launch
CEPI – Punta Indio Space Center
Launch date Launch date (according to ISCUL plan)
4 (1/2026 – 10/2026 – 4/2027 – 3/2028)
Length
11 m
Diameter
0.7 m
Mass
2.2 Tons
Payload
Technological
The purpose of the Tronador II-70 launcher is to test the Tronador II-250 second stage engine.
TII-150
Mission
Flight at an altitude of 400 km
Launch
CEMB – Manuel Belgrano Space Center
Launch date (according to ISCUL* plan)
2 (4/2029 – 2/2030)
Length
20 m
Diameter
1.5 m
Mass
23 Toneladas
Payload
Technological
The objective of the Tronador II-150 launcher is to test one of the 3 engines that the Tronador II-250 will have for the first flight stage.