Cohete Capricornio (5655343045).jpg
FunctionOrbital launch vehicle
ManufacturerInstituto Nacional de Técnica Aeroespacial (INTA)
Country of originSpain
Height18.25 m (59.9 ft)
Diameter1.00 m (3.28 ft)
Mass15,035 kg (33,147 lb)
Payload to LEO
Mass140 kg (310 lb)
Launch history
Launch sitesEl Hierro
First stage – Castor 4B
Powered by1 Solid
Maximum thrust429 kN (96,000 lbf)
Burn time61 sec
Second stage – Deneb-F
Powered by1 Solid
Maximum thrust167.9 kN (37,700 lbf)
Burn time35.6 sec
Third stage – Mizar-B
Powered by1 Solid
Maximum thrust50.29 kN (11,310 lbf)
Burn time33.8 sec

Capricornio was a Spanish satellite launch vehicle developed by the Instituto Nacional de Técnica Aeroespacial (INTA) in the 1990s.[1] 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.

Projected flights

The first flight of Capricornio was scheduled to take place from El Hierro Launch Centre[5] in late 1999 or 2000. It would carry two small satellites:[1] Nanosat 01 (developed by the Polytechnic University of Madrid) and Venus (Polytechnic University of Madrid and other universities in Mexico and Argentina).

See also


  1. ^ a b "Capricorno". Archived from the original on December 28, 2016. Retrieved 2012-08-20.
  2. ^ "Capricornio project". 1998-10-19. Retrieved 2012-08-20.
  3. ^ "Thiokol to Supply Rocket Boosters for Spain's Capricornio Launch Vehicle New Three-Stage Booster Under Development for Small Payloads - Free Online Library". 1997-06-16. Retrieved 2012-08-20.
  4. ^ a b "Capricornio". Retrieved 2013-10-22.
  5. ^ "Spain in Space" (PDF). Retrieved 2013-10-22.