In 1992 Spain's National Institute for Aerospace Technology (INTA) announced plans to develop a small orbital launch vehicle. INTA apparently acquired materials and technology from Argentina's Condor-II missile project, which was cancelled in 1990. Of particular interest were steerable nozzles and the solid propellant fuel.
The Capricornio is a three-stage
solid propellant launcher designed to carry 60-140 kg payloads into low earth orbit
(LEO). It has an overall length of 18.25 m, a principal body diameter of 1.0 m and
weighs 15,035 kg at launch.
Stage 1 is 8.99 m long and has a body diameter of 1.02 m. It contains a Thiokol Castor 4B motor with HTPB solid propellant, which has a burn time of 61 sec and an average thrust of 429 kN . Attitude control is by TVC and roll control by the automatic control system (ACS) situated above the third stage.
Stage 2, designated DENEB-F, is 3.0 m long, has a body diameter of 0.83 m and weighs 2,549 kg. The motor, which weighs 2,436 kg, contains 2,124 kg of solid propellant, has a burn time of 35.6 seconds and an average thrust of 167.9 kN. Attitude control in pitch and yaw is by nozzle TVC, and roll control by stage 3 ACS.
Stage 3, designated Mizar-B, is 2.1 m long, has a body diameter of 0.83 m and weighs 717 kg. The motor, which weighs 686 kg, contains 607 kg of solid propellant, has a burn time of 33.8 seconds and an average thrust of 50.29 kN. Attitude control is unknown.
In 1999 it was reported that the first flight of Capricornio is scheduled to take place from the Canary Island site in late 1999 or 2000."
Spacial Base in the Canary Islands canceled in 1999 due to protests. Capricornio cancelled in the final phase.