Encyclopedia Astronautica
STRV


British technology satellite. 4 launches, 1994.06.17 (STRV-1B) to 2000.11.16 (STRV-1d).

The Space Technology and Research Vehicles STRV-1a and -1b were a pair of microsatellites designed to test new space technologies and make measurements of the space environment and its effect on spacecraft systems. The emphasis of the project was on low-cost, short timescale access to space and the rapid dissemination of experimental data. Although built and operated by the UK's Defense Research Agency, many experiments were collaborative, involving the Ballistic Missile Defense Organization, the European Space Agency and universities. After 2.5 years of operation the spacecraft were turned over to NASA and the University of Colorado for communications experiments.

Each spacecraft had a 50 cm cubic structure based on carbon/PEEK thermoplastic skinned aluminum honeycomb panels. Four GaAs solar panels provided 31-33W (BoL) to a 28V power distribution bus and 16 NiCd batteries. Platform requirements were approximately 19W, leaving 13W for payload operations. On-board data handling used a GEC Plessey MIL-STD-1750 processor employing radiation tolerant SOS technology. ESA CCSDS telemetry and telecommand standards were observed. Communications were through the S-band (2.2GHz); 125bps uplink and 1kbps downlink through a 1W omni-direction antenna.

Both STRVs were spin-stabilized at approximately 5rpm with attitude determination achieved via V-slit Sun and Earth sensors and analogue Sun sensors. Control was through magnetorquers and a cold gas thruster system.

Both spacecraft carried a variety of space technology and environment experiments. Even the spacecraft's' carbon/PEEK structures were considered experimental. Specific payloads on -1a were the Atomic Oxygen Experiment, Battery Recharge, Cold Ion Detector, Cosmic Ray and Dosimetry Monitor, Langmuir Probe, Radiation Dose Rate Sensor, Surface Charge Detector and the Xenon Plasma Charge Neutralizer. On-board the -1b were the Cryocooler/Vibration Suppression Experiment, Infrared Detectors, Neural Network Microprocessors, Radiation Environment Monitor, Single Event Upset and Radiation Monitor and the Solar Cell Technology Experiment.

AKA: Space Technology Research Vehicle.
Height: 0.45 m (1.47 ft).
First Launch: 1994.06.17.
Last Launch: 2000.11.16.
Number: 4 .

More... - Chronology...


Associated Countries
See also
  • Ariane 5 The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000. More...
  • Ariane First successful European commercial launch vehicle, developed from L3S Europa launch vehicle replacement design. Development of the Ariane 1 was authorised in July 1973, took eight years, and cost 2 billion 1986 Euros. More...

Associated Launch Vehicles
  • Ariane French orbital launch vehicle. First successful European commercial launch vehicle, developed from L3S Europa launch vehicle replacement design. Development of the Ariane 1 was authorised in July 1973, took eight years, and cost 2 billion 1986 Euros. More...
  • Ariane 44LP French orbital launch vehicle. Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons. More...
  • Ariane 5 French orbital launch vehicle. The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000. More...
  • Ariane 5G French orbital launch vehicle. Initial version of the Ariane 5, a bit too large for the main commercial geosynchronous communications satellite payloads. More...

Associated Manufacturers and Agencies
  • JPL American agency;manufacturer of rockets, spacecraft, and rocket engines. Jet Propulsion Laboratory, Pasadena, USA. More...
  • BMDO American agency overseeing development of spacecraft. Ballistic Missile Defence Organization (formerly SDIO), USA. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: here.
  • NASA/GSFC Orbital Information Group Website, Web Address when accessed: here.
  • Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: here.

Associated Launch Sites
  • Kourou After the agreement with newly independent Algeria for France to evacuate their launch sites in that country, a location near Biscarosse was selected for French missile testing. However since only launches westwards across the Bay of Biscay could be made from this site, it was unsuitable for France's Diamant orbital launch vehicle. After reviewing 14 potential sites, a location in the South American French colony of Guiana was selected. This would allow over-water launches to a tremendous range of possible orbital inclinations -- from -100.5 deg to 1.5 deg. Being near the equator, it would provide the maximum assist from the earth's rotation for launches into equatorial orbits. The decision was formalized in April 1964 and in July 1966 ELDO chose the site for future launches of the Europa II launch vehicle. More...

STRV Chronology


1994 June 17 - . 07:07 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP. LV Configuration: Ariane 44LP V64.
  • STRV-1B - . Mass: 50 kg (110 lb). Nation: UK. Class: Technology. Type: Navigation technology satellite. Spacecraft: STRV. USAF Sat Cat: 23125 . COSPAR: 1994-034B. Apogee: 31,817 km (19,770 mi). Perigee: 278 km (172 mi). Inclination: 7.5000 deg. Period: 557.00 min. Summary: 50 cm cube; Space Technology and Research Vehicle; included solar cell tests..
  • STRV-1A - . Mass: 53 kg (116 lb). Nation: UK. Class: Technology. Type: Navigation technology satellite. Spacecraft: STRV. USAF Sat Cat: 23126 . COSPAR: 1994-034C. Apogee: 31,321 km (19,461 mi). Perigee: 273 km (169 mi). Inclination: 7.4000 deg. Period: 547.70 min. Summary: 50 cm cube; Space Technology and Research Vehicle; included solar cell tests..

2000 November 16 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V135 507.
  • STRV-1d - . Mass: 4,758 kg (10,489 lb). Nation: UK. Agency: Arianespace. Manufacturer: Farnborough. Class: Technology. Type: Navigation technology satellite. Spacecraft: STRV. USAF Sat Cat: 26611 . COSPAR: 2000-072D. Apogee: 39,282 km (24,408 mi). Perigee: 605 km (375 mi). Inclination: 7.1000 deg. Period: 708.30 min. STRV-1c and 1d were small satellites built by the DERA (former Royal Aircraft Establishment), Farnborough, England. Mass was around 95 kg each. STRV-1d carries an NRL Space Test Program experiment (S97-2), a camera, and technology and computer experiments.
  • STRV-1c - . Mass: 4,758 kg (10,489 lb). Nation: UK. Agency: Arianespace. Manufacturer: Farnborough. Class: Technology. Type: Navigation technology satellite. Spacecraft: STRV. USAF Sat Cat: 26610 . COSPAR: 2000-072C. Apogee: 39,789 km (24,723 mi). Perigee: 680 km (420 mi). Inclination: 6.3000 deg. The two small STRV cubes were then ejected from the Ariane EPS stage ASAP-5 secondary payload structure at 0141 GMT. STRV-1c and 1d were small satellites built by the DERA (former Royal Aircraft Establishment), Farnborough, England. Mass was around 95 kg each. STRV-1c performed accelerated life testing of new components and materials in the high radiation environment of geosynchronous transfer orbit.

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