Well, here some projects of INTA (instituto Nacional de Técnica Aerospacial) in the 80's
initially designed as commercial rockets, but under the MoD
INTA-100
INTA-300 (100Kg load)
launched from "El Arenosillo" test Base. Theese rockets were developped paralell to the nuclear military program in the 70's and 80's. In 1986 joining NATO and EU, Spain finally signs NTP.
"The Instituto Nacional de Tecnica Aeroespacial (INTA) is developing a small low cost SLV named Capricornio to deliver
70 kg payloads into 600 km polar orbits. INTA apparently acquired materials and technology from Argentina's Condor 2
missile project, which was cancelled in 1990. Of particular interest were steerable nozzles and the solid propellant fuel.
The programme is being conducted in three phases. The first phase was the development of solid motors for the
INTA 100 and 300 sounding rockets, launched from the Huelva test range in southern Spain. The second phase will fly
Capricornio's stage 2/3 motors as the 9.2 m Argos sounding rocket. The third phase will be the first launch of
Capricornio at El Hierro in the Canary Islands, carrying a micro-satellite built by the Centre of Microelectronics in
Barcelona.
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 Denab-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. The Technology transferred to the european Vega project.
CAPRICORNIO
A link from spanish newspaper ElMundo in 1998
INTA
Spainsat
[URL="http://www.tecnociencia.es/entidades/inta/subsecciones/certificacion/arenosillo.html"]
El Arenosillo Launcher Base
INTA Instituto Nacional de Técnica Aerospacial
initially designed as commercial rockets, but under the MoD
INTA-100
INTA-300 (100Kg load)
launched from "El Arenosillo" test Base. Theese rockets were developped paralell to the nuclear military program in the 70's and 80's. In 1986 joining NATO and EU, Spain finally signs NTP.
"The Instituto Nacional de Tecnica Aeroespacial (INTA) is developing a small low cost SLV named Capricornio to deliver
70 kg payloads into 600 km polar orbits. INTA apparently acquired materials and technology from Argentina's Condor 2
missile project, which was cancelled in 1990. Of particular interest were steerable nozzles and the solid propellant fuel.
The programme is being conducted in three phases. The first phase was the development of solid motors for the
INTA 100 and 300 sounding rockets, launched from the Huelva test range in southern Spain. The second phase will fly
Capricornio's stage 2/3 motors as the 9.2 m Argos sounding rocket. The third phase will be the first launch of
Capricornio at El Hierro in the Canary Islands, carrying a micro-satellite built by the Centre of Microelectronics in
Barcelona.
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 Denab-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. The Technology transferred to the european Vega project.
CAPRICORNIO
A link from spanish newspaper ElMundo in 1998
INTA
Spainsat
[URL="http://www.tecnociencia.es/entidades/inta/subsecciones/certificacion/arenosillo.html"]
El Arenosillo Launcher Base
INTA Instituto Nacional de Técnica Aerospacial