Globalstar

The Globalstar constellation was a Medium Earth Orbit system for mobile voice and data communications. The 3-axis stabilized 222 kg satellites had a nominal 7 year life, and were placed in eight planes at 1390 km / 52 degrees inclination. The entire initial constellation of 52 satellites was launched in 1998-2007. A replenishment launch of four satellites was made in 2007.

Typical orbit: 1346 km circular orbit, 52 deg inclination. Mass: 222 kg (489 lb). Associated Launch Vehicle: Delta 7000, Soyuz 11A511U, Zenit-2.

• 1998 February 14 - Globalstar FM2 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.01 deg. Period: 114.08 min.

  Plane 1. Ascending node 43.8 degrees.

• 1998 February 14 - Globalstar FM3 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,509 km (937 mi). Apogee: 1,520 km (940 mi). Inclination: 52.00 deg. Period: 116.30 min.

  Plane 1. Ascending node 42.4 degrees.

• 1998 February 14 - Globalstar FM4 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,416 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Plane 1. Ascending node 43.6 degrees.

• 1998 February 14 - Globalstar FM1 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Plane 1. Ascending node 43.9 degrees.

• 1998 April 24 - Globalstar FM6 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,503 km (933 mi). Apogee: 1,523 km (946 mi). Inclination: 52.00 deg. Period: 116.30 min.

  Plane 2. Ascending node 90.4 degrees.

• 1998 April 24 - Globalstar FM8 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Plane 2. Ascending node 88.9 degrees.

• 1998 April 24 - Globalstar FM14 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Plane 2. Ascending node 90.2 degrees.

• 1998 April 24 - Globalstar FM15 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Plane 2. Ascending node 88.0 degrees.

• 1998 September 9 - Globalstar FM9 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM5 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

  Fell in Siberia.

• 1998 September 9 - Globalstar FM10 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM7 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM12 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM13 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM16 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM17 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM18 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM20 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM21 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1998 September 9 - Globalstar FM11 - Launch Site: Baikonur. Launch Vehicle: Zenit. FAILURE: Computer error caused a very premature engine shutdown during second stage burn. Mass: 222 kg (489 lb).

• 1999 February 9 - Globalstar FM23 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 February 9 - Globalstar FM36 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

  The first launch of the Soyuz- Ikar launch vehicle, selected by Orbcomm after failure of the Zenit launcher. The Ikar upper stage was derived from the Yantar reconnaissance satellite's propulsion module. The Soyuz second stage separated at 8 minutes 48 seconds into flight after placing the Ikar into a 236 km x 884 km x 52.0 deg transfer orbit. The Ikar stage burned at the second apogee passage, at 06:23 GMT, and released the Globalstar satellite at the top of the dispenser into a 915 km x 947 km x 52.0 deg orbit at 07:27 GMT. The three remaining satellites mounted around the side of the dispenser were released into a 903 km x 946 km x 52.0 deg orbit. This was also the first launch carried out by the Starsem organization, a joint venture including Aerospatiale and TsSKB-Progress (the launch vehicle manufacturer). The dispenser was built by Aerospatiale/Aquitaine (Bordeaux).

• 1999 February 9 - Globalstar FM38 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 February 9 - Globalstar FM40 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 March 15 - Globalstar M046 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg.

• 1999 March 15 - Globalstar M037 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 March 15 - Globalstar M041 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 March 15 - Globalstar M022 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  In the second Soyuz/Ikar launch four Globalstar satellites were delivered with the Ikar upper stage into a 235 km x 899 km x 52.0 degree transfer orbit. The Ikar stage then placed itself and its payload into a 897 km x 950 km x 52.0 degree deployment orbit. Satellite M022 was separated first from the top of the dispenser, followed by ejection of the other three satellites from the sides at 06:37 GMT. After dispensing the satellites, the Ikar deorbited itself on March 16.

• 1999 April 15 - Globalstar M042 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 April 15 - Globalstar M044 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 April 15 - Globalstar M045 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 April 15 - Globalstar M019 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 222 kg (489 lb). Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

  The Ikar upper stage entered a 234 km x 900 km transfer orbit, then maneuvered to dispense the four spacecraft into 900 km x 950 km x 52.0 deg parking orbits. The satellite's own thrusters would be used to place them into their 1410 km circular operational orbits. The Ikar stage deorbited itself after one day. The Globalstar satellites, built by Alenia and Loral, are L-band comsats which provide satellite phone service.

• 1999 June 10 - Globalstar 25 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 June 10 - Globalstar 47 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,413 km (877 mi). Inclination: 52.00 deg.

• 1999 June 10 - Globalstar 49 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 June 10 - Globalstar 52 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 10 - Globalstar 51 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 10 - Globalstar 30 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 10 - Globalstar 35 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 10 - Globalstar 32 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 25 - Globalstar 43 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 July 25 - Globalstar 48 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 25 - Globalstar 26 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 July 25 - Globalstar 28 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 August 17 - Globalstar 24 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 August 17 - Globalstar 27 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg.

• 1999 August 17 - Globalstar 53 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 August 17 - Globalstar 54 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 1999 September 22 - Globalstar 55 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,412 km (877 mi). Apogee: 1,416 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 September 22 - Globalstar 58 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,413 km (877 mi). Apogee: 1,413 km (877 mi). Inclination: 52.00 deg.

• 1999 September 22 - Globalstar 50 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg.

• 1999 September 22 - Globalstar 33 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,412 km (877 mi). Apogee: 1,416 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

  The third stage put the complex into a 235 km x 906 km x 51.9 degree transfer orbit. The Ikar upper stage maneouvered, placed the four satellites into their final parking orbit, then made a deorbit burn and re-entered on September 24.

• 1999 October 18 - Globalstar 59 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,413 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 October 18 - Globalstar 56 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 October 18 - Globalstar 57 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,412 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 October 18 - Globalstar 31 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  At the time of this launch Globalstar began limited service of its satellite telephone system.

• 1999 November 22 - Globalstar 61 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,411 km (876 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg.

• 1999 November 22 - Globalstar 39 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,410 km (870 mi). Apogee: 1,417 km (880 mi). Inclination: 52.00 deg. Period: 114.10 min.

• 1999 November 22 - Globalstar 29 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Additional launches into Globalstar communications satellite constellation.

• 1999 November 22 - Globalstar 34 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg.

• 2000 February 8 - Globalstar M060 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 450 kg (990 lb). Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Mobile Telephony. These four Globalstar satellites completed the Globalstar initial constellation.

• 2000 February 8 - Globalstar M062 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 450 kg (990 lb). Perigee: 1,417 km (880 mi). Apogee: 1,418 km (881 mi). Inclination: 52.01 deg. Period: 114.09 min.

  Mobile Telephony.

• 2000 February 8 - Globalstar M063 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 450 kg (990 lb). Perigee: 1,413 km (877 mi). Apogee: 1,415 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min.

  Mobile Telephony.

• 2000 February 8 - Globalstar M064 - Launch Site: Cape Canaveral. Launch Vehicle: Delta. Mass: 450 kg (990 lb). Perigee: 915 km (568 mi). Apogee: 934 km (580 mi). Inclination: 52.01 deg. Period: 103.43 min.

  Mobile Telephony.

• 2007 May 29 - Globalstar A - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 914 km (567 mi). Apogee: 932 km (579 mi). Inclination: 52.00 deg. Period: 103.50 min.

  First replenishment launch of the resurgent Globalstar MEO communications satellite constellation after a five-year hiatus.

• 2007 May 29 - Globalstar D - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 919 km (571 mi). Apogee: 938 km (582 mi). Inclination: 52.00 deg. Period: 103.60 min.

• 2007 May 29 - Globalstar C - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 926 km (575 mi). Apogee: 932 km (579 mi). Inclination: 52.00 deg. Period: 103.60 min.

• 2007 May 29 - Globalstar B - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 913 km (567 mi). Apogee: 931 km (578 mi). Inclination: 52.00 deg. Period: 103.50 min.

• 2007 October 20 - Globalstar FM68 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 915 km (568 mi). Apogee: 930 km (570 mi). Inclination: 52.00 deg. Period: 103.50 min.

• 2007 October 20 - Globalstar FM67 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 925 km (574 mi). Apogee: 935 km (580 mi). Inclination: 52.00 deg. Period: 103.60 min.

• 2007 October 20 - Globalstar FM66 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 914 km (567 mi). Apogee: 932 km (579 mi). Inclination: 52.00 deg. Period: 103.50 min.

  Last of the first generation Globalstar satellites, launched to replenish the constellation. The Fregat stage made three burns to deploy the satellites into circular orbit, and then deorbit itself to a reentry over the Pacific Ocean.

• 2007 October 20 - Globalstar FM70 - Launch Site: Baikonur. Launch Vehicle: Soyuz. Mass: 450 kg (990 lb). Perigee: 911 km (566 mi). Apogee: 931 km (578 mi). Inclination: 52.00 deg. Period: 103.40 min.