Gals Credit - USAF Phillips Laboratory

Direct broadcasting satellite (new generation of satellites) intended for development of the Russian television system and international cooperation.

The year 1994 marked the long awaited debut of the first of the next-generation Russian geosynchronous communications satellites. The spacecraft, designed and built by the Applied Mechanics NPO, utilized a new, modernized MSS-2500 class bus with greater electrical power, higher precision station-keeping capabilities (including north-south station-keeping), and longer life. The first of these spacecraft to appear was Gals 1 on 20 January 1994, followed by Express 1 on 13 October. Both employed the MSS-2500-GSO-01 spacecraft bus. Two other models (MSS-2500-GSO-02 and MSS-2500-GSO) were still under development.

The Gals television broadcasting satellite, originally expected to be launched by December, 1990, was designed to support a variety of direct broadcast customers, including professional broadcasting firms (having antenna 2.5 m in diameter), community associations (receiving antenna 1.5 m), and individuals (receiving antenna 0.6-0.9 m). The 2500-kg spacecraft with a payload mass of 420 kg originally were scheduled for deployments at two locations: 230 E with three spacecraft and 44 degrees E with two spacecraft. Later, positions degrees 74 degrees E, 110 degrees E, and 140 degrees E were added. The planned constellation was later altered to consist of spacecraft at 36 degrees E, 56 degrees E, 86 degrees E, 110 degrees E, and 140 degrees E. Two solar arrays with a total power of 2.4 kW supported three Ku-band transponders (one 40 W and two 80 W). The spacecraft bus measured 4.1 m by 6.6 m with a 21-m span across the solar arrays. The design lifetime was 5-7 years. Like most Russian geosynchronous spacecraft, Gals 1 was inserted into the geosynchronous ring near 90 degrees E. A western drift was assigned to permit the vehicle to reach 44 degrees E by early February, 1994. After checkout during which problems were detected with one of the three transponders, Gals 1 was unexpectedly transferred to 71 degrees E in May-June to service, not the Russian Federation, but the PRC and Taiwan. Gals 1 remained at 71 degrees E for the remainder of 1994.

Gals 1 also signaled the first civilian control of a major applications spacecraft. The new Main Control Center at Krasnoyarsk in Siberia of the Applied Mechanics NPO), rather than the military satellite control facility at Golitsino-2, was in charge of Gals l's day-to-day operations. Gals 1 further tested the Russian SPT-100 ion thruster created by the Fakel Bureau. This evaluation program was conducted in conjunction with France's SEP firm and U.S.'s Loral Space Systems Company.

Three modifications of Gals were envisioned. Gals-R would add a fourth transponder and permit zonal (broad area) television broadcasting. The Gals-R6 and Gals-R12 variants would carry 6 and 12 transponders, respectively. The first launch of a Gals-R vehicle was tentatively set for 1996. Two Gals-R class spacecraft were reportedly been ordered by a Chinese company for launches beginning in 1998.

However all of these plans came to nothing and the two Gals launched in 1994-1995 remained the only examples.

Design Life: 3 years. Typical orbit: 35953 km x 35955 km at 0 degrees inclination. Mass: 2,500 kg (5,500 lb).

• 1994 January 20 - Gals - Launch Site: Baikonur. Launch Complex: LC81/23. Launch Vehicle: Proton. Mass: 2,500 kg (5,500 lb). Perigee: 36,121 km (22,444 mi). Apogee: 36,121 km (22,444 mi). Inclination: 0.10 deg. Period: 1,453.00 min.
  Direct broadcasting satellite (new generation of satellites) intended for development of the Russian television system and international cooperation. Also tested SPT-100 plasma engine. Positioned in geosynchronous orbit at 71 deg E in 1994-1996; 36 deg E in 1996-1999; 42 deg E in 2000. As of 5 September 2001 located at 37.30 deg E drifting at 0.121 deg W per day. As of 2007 Mar 10 located at 67.44E drifting at 0.298E degrees per day.

• 1995 November 17 - Gals-2 - Launch Site: Baikonur. Launch Complex: LC200/39. Launch Vehicle: Proton. Mass: 2,500 kg (5,500 lb). Perigee: 35,784 km (22,235 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.20 deg. Period: 1,436.00 min.
  Three transponders for direct broadcast television. Stationed at 70 deg E. Used SPT-100 plasma engine. Positioned in geosynchronous orbit at 71 deg E in 1995-1996; 36 deg E in 1996-1999 As of 5 September 2001 located at 36.88 deg E drifting at 0.031 deg E per day. As of 2007 Mar 10 located at 62.06E drifting at 1.427W degrees per day.