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GemStar

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GemStar 1 (VitaSat) Credit: Manufacturer Image

Status: Operational 1995. First Launch: 1995-08-15. Last Launch: 1995-08-15. Number: 1 . Gross mass: 113 kg (249 lb).

REX American earth ionosphere satellite. The REX satellites were designed to study scintillation effects of the Earth's atmosphere on RF transmissions. Experimental satellite built by DSI (#1), CTA (#2) for USAF STP (Space Test Program), USA. Launched 1991 - 1996. Used the GemStar Bus bus.

ACRIMSAT American solar satellite. 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. Solar observing satellite built by Orbital Sciences Corporation (OSC) for NASA, USA. Launched 1999. Used the MiniStar bus.

• REX - . Payload: REX 1. Mass: 85 kg (187 lb). Nation: USA. Agency: USAF Rome. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: GemStar. Spacecraft: REX. USAF Sat Cat: 21527 . COSPAR: 1991-045A. Apogee: 869 km (539 mi). Perigee: 767 km (476 mi). Inclination: 89.50 deg. Period: 101.30 min. Radiation Experiment; tested communications components in high radiation environment. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

• GemStar 1 (VitaSat) - . Payload: Gemstar DSS-1. Mass: 113 kg (249 lb). Nation: USA. Agency: LMSC. Class: Communications. Type: Civilian communications satellite. Spacecraft: GemStar. Decay Date: 1995-08-15 . Global Electronic Messaging Satellite..

• REX-II - . Mass: 85 kg (187 lb). Nation: USA. Agency: USAF STP. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: GemStar. Spacecraft: REX. USAF Sat Cat: 23814 . COSPAR: 1996-014A. Apogee: 835 km (518 mi). Perigee: 799 km (496 mi). Inclination: 90.00 deg. Period: 101.20 min. LEO Air dropped in Point Arguello WADZ..

• ACRIMSAT - . Mass: 115 kg (253 lb). Nation: USA. Agency: JPL, NASA. Manufacturer: Germantown. Class: Earth. Type: Seismology satellite. Spacecraft Bus: GemStar. Spacecraft: ACRIMSAT . USAF Sat Cat: 26033 . COSPAR: 1999-070B. Apogee: 711 km (441 mi). Perigee: 671 km (416 mi). Inclination: 97.80 deg. Period: 98.60 min.

  Measured the integrated solar energy output from 0.2 to 2 microns. Carried instrument deleted from Terra spacecraft, studying the total solar output. Failed on 2013 December 14 due to battery problems, months after a review recommended its continued operation. The ACRIM series of experiments, critical data for climate change studies, flew on Solar Max (1980), Spacelab-1 (1983), UARS (1991), and ACRIMSAT. The similar TIM instrument on the SORCE satellite (2003) continued operating, but it was unclear if it would continue in operation until a replacement instrument would be launched on the JPSS satellite in 2017 at the earliest.