Encyclopedia Astronautica

American solar satellite. One launch, 1999.12.21. The NASA ACRIMSAT satellite was managed by JPL, and measured the integrated solar energy output from 0.2 to 2 microns. ACRIMSAT was built by Orbital Sciences.

Principal Investigator for the ACRIMSAT's Earth Observing System/Active Cavity Radiometer Irradiance Monitor (EOS ACRIM) III Experiment was Richard Wilson, Columbia University. The Mission Team consisted of JPL for Mission Management and Payload Development; and Columbia University for Science and Data Processing. The purpose of the EOS ACRIM Experiment was to monitor the Total Solar Irradiance (TSI) with maximum precision and provide an important link in the long term TSI database. The ACRIM III experiment would provide all solar maximum TSI results in solar cycle 23. The result would be a science data set of daily average Total Solar Irradiance at 1 AU for the cycle. Objectives were to extend the TSI database accumulated by Nimbus7/ERB, SMM/ACRIM I, UARSUARS/ACRIM II, and SOHO/VIRGO; and to contribute data to the U.S. Global Change Research Program to understand solar influences on climate.

The single payload of the satellite was the Active Cavity Radiometer Irradiance Monitor (ACRIM) IV. This was Sun-pointing (+/-0.25 deg), had a weight of 13 kg, and detected full spectrum wavelengths of 200 nm to 2000 nm. Power draw was10 watts. Instrument Heritage was SMM/ACRIM I (1980-1989); UARS/ACRIM II (1991-); and the Active Cavity Radiometer (ACR) instrument (4 Shuttle Flights). The planned minimum science mission was a five year lifetime in a 680 km orbit, sun-synchronous orbit.

Major Milestones included Project Start: September 1997; Instrument Delivery: April 1999; Launch: December 1999.

Spacecraft Contractor was Orbital Sciences Corporation; Launch Vehicle was an OSC Taurus.

First Launch: 1999.12.21.
Number: 1 .

More... - Chronology...

Associated Countries
See also
  • Taurus Pad-launched launch vehicle using Pegasus upper stages and Castor-120 first stage. More...

Associated Launch Vehicles
  • Taurus American all-solid orbital launch vehicle. Pad-launched launch vehicle using Pegasus upper stages and Castor-120 first stage. First launch used slightly larger Peacekeeper ICBM first stage instead of Castor-120. Under a 2002 contract from Boeing, Orbital developed a three-stage version of Taurus to serve as the interceptor boost vehicles for the US government's missile intercept system. The firm portion of the company's contract, awarded in early 2002, was valued at $450 million and extended through 2007. More...

Associated Manufacturers and Agencies
  • JPL American agency;manufacturer of rockets, spacecraft, and rocket engines. Jet Propulsion Laboratory, Pasadena, USA. More...
  • NASA American agency overseeing development of rockets and spacecraft. National Aeronautics and Space Administration, USA, USA. More...
  • OSC American manufacturer of rockets, spacecraft, and rocket engines. Orbital Sciences Corporation, USA. More...

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. 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.
  • NASA Report, AcrimSat Launch Press Kit, Web Address when accessed: here.

Associated Launch Sites
  • Vandenberg Vandenberg Air Force Base is located on the Central Coast of California about 240 km northwest of Los Angeles. It is used for launches of unmanned government and commercial satellites into polar orbit and intercontinental ballistic missile test launches toward the Kwajalein Atoll. More...

ACRIMSAT Chronology

1999 December 21 - . 07:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg 576E. LV Family: Pegasus. Launch Vehicle: Taurus 2110. LV Configuration: Taurus 2110 T4.
  • ACRIMSAT - . Mass: 115 kg (253 lb). Nation: USA. Agency: NASA; JPL. Manufacturer: Germantown. Class: Earth. Type: Seismology satellite. Spacecraft: ACRIMSAT . USAF Sat Cat: 26033 . COSPAR: 1999-070B. Apogee: 711 km (441 mi). Perigee: 671 km (416 mi). Inclination: 97.8000 deg. Period: 98.60 min. Summary: Measured the integrated solar energy output from 0.2 to 2 microns. Carried instrument deleted from Terra spacecraft..

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