|Function||Orbital launch vehicle|
|Manufacturer||Instituto Nacional de Técnica Aeroespacial (INTA)|
|Country of origin||Spain|
|Height||18.25 m (59.9 ft)|
|Diameter||1.00 m (3.28 ft)|
|Mass||15,035 kg (33,147 lb)|
|Payload to LEO|
|Mass||140 kg (310 lb)|
|Launch sites||El Hierro|
|First stage – Castor 4B|
|Thrust||429 kN (96,000 lbf)|
|Burn time||61 sec|
|Second stage – Deneb-F|
|Thrust||167.9 kN (37,700 lbf)|
|Burn time||35.6 sec|
|Third stage – Mizar-B|
|Thrust||50.29 kN (11,310 lbf)|
|Burn time||33.8 sec|
Capricornio was a Spanish satellite launch vehicle developed by the Instituto Nacional de Técnica Aeroespacial (INTA) in the 1990s. It was expected to be a low cost solution to place up to 70 kg payloads into 600 km polar orbits or 60 to 140 kg payloads into low Earth orbit. The Capricornio program was cancelled in 2000.
Three-stage solid propellant launcher. Overall length of 18.25 m, body diameter of 1.0 m and weighs 15,035 kg at launch.
The first flight of Capricornio was scheduled to take place from El Hierro Launch Centre in late 1999 or 2000. It would carry two small satellites: Nanosat 01 (developed by the Polytechnic University of Madrid) and Venus (Polytechnic University of Madrid and other universities in Mexico and Argentina).