Delta 2914 no. 146

The Delta 2000 series used Castor 2 strap-ons together with an Extended Long Tank core equipped with the more powerful RS-27 engine. This engine was derived from surplus H-1 engines intended for the Saturn IB booster of the Apollo programme. The Delta P upper stage used surplus Apollo lunar module engines.

The Aerojet history recalls how the company lost the Delta upper stage business for nearly a decade from the mid-1970's to the mid-1980's:

The tug-of-war between the overall vehicle contractor and component system supplier over who should supply how much of the product, began as might be expected. As long as the project remained in Azusa, we had been able to keep the costs below anything Douglas could match. However, at the time when it was to be moved to Sacramento, management required the use of the "new" Commitment Proposal Estimating System which resulted in higher estimated costs. Also, the Douglas Huntington Beach plant was extremely low on work. As a final touch, Aerojet solved the problem by arrogantly sticking to the much higher price to our customer (Douglas). They promptly responded by replacing our system with a similar unit from TRW (surplus LM units) that unfortunately had slightly lower performance. Most of the production from NASA in that time period continued with this TRW engine. Douglas also had kept wearing away at Aerojet's share of the project so that we went from supplying the complete stage to the present status of supplying only the thrust chamber assembly and propellant feed lines.

Manufacturer: Douglas. Launches: 44. Failures: 1. Success Rate: 97.73%. First Launch Date: 1974-01-19. Last Launch Date: 1981-10-06. Launch data is: complete. Payload: 724 kg (1,596 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AE, CAMEO, COS, CS-1, CTS, ESA-Geos, GMS, GOES, HS 333, Intasat, ISEE, ITOS, IUE, Lageos, Landsat 1-2-3, Marisat, Meteosat, Microsat SSTL, NATO 3, Nimbus, Oscar, PIX, SCATHA, Sirio, Skynet, SME, SMS, Spacebus 100, Symphonie, Yuri. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,392 kg (287,465 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 28.520 million. in: 1985 unit dollars.

3 stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Apogee: 1,500 km (900 mi). Liftoff Thrust: 1,737.000 kN (390,493 lbf). Total Mass: 131,000 kg (288,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

3 stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D

Payload: 500 kg (1,100 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 1,737.000 kN (390,493 lbf). Total Mass: 131,000 kg (288,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

3 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Apogee: 3,000 km (1,800 mi). Liftoff Thrust: 2,560.000 kN (575,510 lbf). Total Mass: 131,000 kg (288,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

3 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D

LEO Payload: 2,000 kg (4,400 lb). Payload: 700 kg (1,540 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 100,000 km (60,000 mi). Liftoff Thrust: 2,560.000 kN (575,510 lbf). Total Mass: 131,800 kg (290,500 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

4 stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E

Payload: 724 kg (1,596 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,392 kg (287,465 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

• Stage Number: 0. 9 x Stage: Castor 2. Gross Mass: 4,424 kg (9,753 lb). Empty Mass: 695 kg (1,532 lb). Thrust (vac): 258.915 kN (58,206 lbf). Isp: 262 sec. Burn time: 37 sec. Isp(sl): 232 sec. Diameter: 0.79 m (2.59 ft). Span: 0.79 m (2.59 ft). Length: 6.04 m (19.81 ft). Propellants: Solid. No Engines: 1. Engine: TX-354-3.

• Stage Number: 1. 1 x Stage: Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Isp(sl): 262 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 22.37 m (73.39 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27. Other designations: Extended Length Thor RS-27. Status: Out of production.

• Stage Number: 2. 1 x Stage: Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Isp(sl): 0 sec. Diameter: 1.38 m (4.52 ft). Span: 1.38 m (4.52 ft). Length: 5.97 m (19.58 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: TR-201. Other designations: TR-201.

• Stage Number: 3. 1 x Stage: Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Isp(sl): 220 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 0.84 m (2.75 ft). Propellants: Solid. No Engines: 1. Engine: Star 37. Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications. Burner II was designed for use with the Thor booster, but was readily adapted for use on the complete range of standard launch vehicles. Its general assignment was to place small- and medium size payloads into orbit. The Burner II motor, guidance system and reaction control system were integrated to provide attitude stability and precise control of flight rate and burnout velocity for orbital injection and earth-escape missions. Boeing had delivered 8 flight vehicles under its original contract. Under terms of a follow-on contract, it built 6 additional flight models. Four Thor-Burner II combinations were launched successfully from Vandenberg Air Force Base, California. The third launch placed 2 unclassified satellites in Earth orbit. A SECOR satellite, built for the U.S. Army Corps of Engineers by the Cubic Corporation, and an Aurora satellite, developed by Rice University for the Office of Naval Research, were placed in circular orbits 3,300 km above the Earth. As integration contractor for the Air Force Space Experiment Support Program (SESP) Office, Boeing designed, built and tested the injection stage, or "payload dispenser," which carried the 2 satellites on top of a standard Burner II stage and placed them in precise orbits. The satellites were mounted on opposite sides of the injection stage, which housed a640 kgf thrust, solid-propellant rocket motor. The Burner II was used as an upper stage by NASA for deep space probes. Prime Contractor: The Boeing Company. Major Subcontractors Thiokol Chemical Corporation (solid rocket motor); Honeywell Inc. (pre-programmed inertial guidance system); Walter Kidde Co. (reaction control system).

1974 January 19 - 01:38 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17. Launch Pad: LC17B. Launch Vehicle: Delta 2000. Model: Delta 2313. LV Configuration: Delta 2313 587/D100. FAILURE: Partial Failure. Failed to reach planned orbit.

• Skynet 2A Nation: UK. Program: Skynet. Mass: 129 kg (284 lb). Class: Communications. Type: Military. Spacecraft: Skynet. Agency: UK MoD. Perigee: 104 km (64 mi). Apogee: 1,803 km (1,120 mi). Inclination: 37.50 deg. Period: 104.10 min. COSPAR: 1974-002A. USAF Sat Cat: 7096. Decay Date: 1974-01-25. Partial Failure. Failed to reach planned orbit. References: 1, 2, 5, 6.

• Westar 1 Nation: USA. Program: Westar. Mass: 500 kg (1,100 lb). Class: Communications. Spacecraft: HS 333. Agency: WUTC. Perigee: 35,886 km (22,298 mi). Apogee: 35,900 km (22,300 mi). Inclination: 13.40 deg. Period: 1,441.50 min. COSPAR: 1974-022A. USAF Sat Cat: 7250. Completed Operations Date: 1983-05-02. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 99 deg W in 1974-1982; over the Americas at 100 deg W in 1982; over the Americas at 97 deg W in 1982; over the Americas at 79 deg W in 1982-1983 As of 5 September 2001 located at 85.83 deg W drifting at 1.372 deg W per day. As of 2007 Mar 10 located at 89.54E drifting at 1.381W degrees per day.References: 1, 2, 5, 6.

• SMS 1 Nation: USA. Payload: SMS A. Mass: 243 kg (535 lb). Class: Earth. Type: Weather. Spacecraft: SMS. Agency: NASA GSF. Perigee: 36,216 km (22,503 mi). Apogee: 36,303 km (22,557 mi). Inclination: 15.50 deg. Period: 1,460.30 min. COSPAR: 1974-033A. USAF Sat Cat: 7298. Completed Operations Date: 1981-01-29. Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 45 deg W in 1974-1975; over the Atlantic Ocean 75 deg W in 1975; over the Americas at 105 deg W in 1976-1978; over the Americas at 91 deg W in1978; over the Atlantic Ocean 75 deg W in 1979; over the Atlantic Ocean 70 deg W in 1979; over the Pacific Ocean 132 deg W in 1980 As of 3 September 2001 located at 84.60 deg W drifting at 5.986 deg W per day. As of 2007 Mar 10 located at 116.51E drifting at 5.981W degrees per day.References: 1, 2, 5, 6.

• Westar 2 Nation: USA. Program: Westar. Mass: 500 kg (1,100 lb). Class: Communications. Spacecraft: HS 333. Agency: WUTC. Perigee: 35,895 km (22,304 mi). Apogee: 35,910 km (22,310 mi). Inclination: 9.50 deg. Period: 1,442.00 min. COSPAR: 1974-075A. USAF Sat Cat: 7466. Completed Operations Date: 1986-05-07. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 123 deg W in 1974-1982; over the Americas at 79 deg W in 1982-1986 As of 2 September 2001 located at 144.45 deg E drifting at 1.482 deg W per day. As of 2007 Mar 8 located at 6.53W drifting at 1.482W degrees per day.References: 1, 2, 5, 6.

• NOAA 4 Nation: USA. Program: Tiros. Payload: ITOS G. Mass: 340 kg (740 lb). Class: Earth. Type: Weather. Spacecraft: ITOS. Agency: NOAA. Perigee: 1,445 km (897 mi). Apogee: 1,459 km (906 mi). Inclination: 101.80 deg. Period: 114.90 min. COSPAR: 1974-089A. USAF Sat Cat: 7529. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Oscar 7 Nation: USA. Program: Oscar. Payload: Amsat-Oscar-7. Mass: 29 kg (63 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: AMSAT-NA. Perigee: 1,440 km (890 mi). Apogee: 1,459 km (906 mi). Inclination: 101.80 deg. Period: 114.90 min. COSPAR: 1974-089B. USAF Sat Cat: 7530. AMSAT-OSCAR 7 was launched piggyback with ITOS-G (NOAA 4) and the Spanish INTASAT. The second phase 2 satellite (Phase II-B). Weight 28.6 kg. Octahedrally shaped 360 mm high and 424 mm in diameter. Circularly polarized canted turnstile VHF/UHF antenna system and HF dipole. Firsts: Satellite-to-satellite relay communication via AO-6; Early demonstrations of low-budget medical data relay and doppler location of ground transmitters for search-and-rescue operations were done using this satellite. AO-7 was fully operational for 6.5 years until a battery failed in mid 1981. However the satellite was still functional in day-side passes when its ever-degrading solar cells could function, and was still responding to amateurs as of August 2006.Additional Details: Oscar 7(1731). References: 1, 2, 5, 6.

• Intasat 1 Nation: Spain. Payload: Intasat. Mass: 20 kg (44 lb). Class: Technology. Type: Comsat. Spacecraft: Intasat. Agency: INTA. Perigee: 1,442 km (896 mi). Apogee: 1,459 km (906 mi). Inclination: 101.80 deg. Period: 114.90 min. COSPAR: 1974-089C. USAF Sat Cat: 7531. References: 1, 2, 5, 6.

• Skynet 2B Nation: UK. Program: Skynet. Payload: Skynet 2A. Mass: 129 kg (284 lb). Class: Communications. Type: Military. Spacecraft: Skynet. Agency: UK MoD. Perigee: 35,782 km (22,233 mi). Apogee: 35,822 km (22,258 mi). Inclination: 12.20 deg. Period: 1,436.90 min. COSPAR: 1974-094A. USAF Sat Cat: 7547. Completed Operations Date: 1992-01-01. Military communications. Positioned in geosynchronous orbit over the Indian Ocean at 50-55 deg E in 1975-1977; drifting As of 3 September 2001 located at 18.23 deg E drifting at 0.206 deg W per day. As of 2007 Feb 27 located at 54.93E drifting at 0.393E degrees per day.References: 1, 2, 5, 6.

• Symphonie 1 Nation: France. Payload: Symphonie MV1. Mass: 221 kg (487 lb). Class: Technology. Type: Comsat. Spacecraft: Symphonie. Agency: CNES/DFV. Perigee: 35,853 km (22,277 mi). Apogee: 35,893 km (22,302 mi). Inclination: 14.90 deg. Period: 1,440.50 min. COSPAR: 1974-101A. USAF Sat Cat: 7578. Completed Operations Date: 1983-08-03. Experimental commsat. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.305) and France (A/AC.105/INF.306). Symphonie flying model no. 1, constructed jointly by France and the Federal Republic of Germany. Description: Experimental teleco mmunications satellite. Orbit: geostationary. Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1977; over the Indian Ocean 49 deg E in 1977-1983 As of 25 August 2001 located at 179.98 deg E drifting at 1.086 deg W per day. As of 2007 Mar 11 located at 72.77E drifting at 1.184W degrees per day.References: 1, 2, 5, 6.

• Landsat 2 Nation: USA. Program: Landsat. Payload: Landsat B. Mass: 953 kg (2,101 lb). Class: Earth. Type: Landsat. Spacecraft: Landsat 1-2-3. Agency: NASA GSF. Perigee: 900 km (550 mi). Apogee: 913 km (567 mi). Inclination: 99.30 deg. Period: 103.10 min. COSPAR: 1975-004A. USAF Sat Cat: 7615. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• SMS 2 Nation: USA. Payload: SMS B. Mass: 627 kg (1,382 lb). Class: Earth. Type: Weather. Spacecraft: SMS. Agency: NASA GSF. Perigee: 35,941 km (22,332 mi). Apogee: 36,060 km (22,400 mi). Inclination: 12.00 deg. Period: 1,447.10 min. COSPAR: 1975-011A. USAF Sat Cat: 7648. Completed Operations Date: 1982-08-11. Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at (GOES W) 115 deg W in 1975-1976; over the Pacific Ocean (GOES W) 135 deg W in 1976-1978; over the Atlantic Ocean (GOES E) 75 deg W in 1979-1981; over the Americas at 106 deg W in 1982 As of 29 August 2001 located at 123.04 deg W drifting at 2.760 deg W per day. As of 2007 Feb 27 located at 127.44E drifting at 2.742W degrees per day.References: 1, 2, 5, 6.

• Anik A3 (Telesat 3) Nation: Canada. Program: Anik. Payload: Anik A3. Mass: 286 kg (630 lb). Class: Communications. Spacecraft: HS 333. Agency: Telesat. Perigee: 35,845 km (22,273 mi). Apogee: 35,851 km (22,276 mi). Inclination: 9.00 deg. Period: 1,439.20 min. COSPAR: 1975-038A. USAF Sat Cat: 7790. Completed Operations Date: 1984-11-23. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 104 deg W in 1975-1976; over the Americas at 114 deg W in 1976-1984 As of 4 September 2001 located at 32.38 deg E drifting at 0.812 deg W per day. As of 2007 Mar 9 located at 138.81W drifting at 0.829W degrees per day.References: 1, 2, 5, 6.

• Nimbus 6 Nation: USA. Payload: Nimbus F. Mass: 829 kg (1,827 lb). Class: Earth. Type: Weather. Spacecraft: Nimbus. Agency: NASA GSF. Perigee: 1,101 km (684 mi). Apogee: 1,114 km (692 mi). Inclination: 100.00 deg. Period: 107.40 min. COSPAR: 1975-052A. USAF Sat Cat: 7924. Environmental research. The experiments selected for Nimbus-6 were the earth radiation budget (ERB), electrically scanning microwave radiometer (ESMR), high-resolution infrared radiation sounder (HIRS), limb radiance inversion radiometer (LRIR), pressure modulated radiometer (PMR), scanning microwave spectrometer (SCAMS), temperature-humidity infrared radiometer (THIR), tracking and data relay experiment (T+DRE), and the tropical wind energy conversion and reference level experiment (TWERLE). This complement of advanced sensors was capable of mapping tropospheric temperature, water vapor abundance, and cloud water content; providing vertical profiles of temperature, ozone, and water vapor; transmitting real-time data to a geostationary spacecraft (ATS 6); and yielding data on the earth's radiation budget.References: 1, 2, 5, 6.

• COS-B; COS B Nation: Europe. Payload: COS B. Mass: 280 kg (610 lb). Class: Technology. Spacecraft: COS. Agency: ESA. Perigee: 442 km (274 mi). Apogee: 99,002 km (61,516 mi). Inclination: 90.30 deg. Period: 2,203.90 min. COSPAR: 1975-072A. USAF Sat Cat: 8062. Decay Date: 1986-01-18. Eighth CERS/ESRO satellite, first European Space Agency satellite. Launch time 0147:59 GMT. Argument of perigee 344.7 deg. Also registered by the United States in A/AC.105/INF.331 as 1975-72A, category B satellite with orbit 2203.9 min, 442 x 99002 km x 9 0.3 deg.References: 1, 2, 5, 6.

• Symphonie 2 Nation: France. Payload: Symphonie MV2. Mass: 398 kg (877 lb). Class: Communications. Spacecraft: Spacebus 100. Agency: CNES/DFV. Perigee: 35,866 km (22,286 mi). Apogee: 35,873 km (22,290 mi). Inclination: 12.70 deg. Period: 1,440.40 min. COSPAR: 1975-077A. USAF Sat Cat: 8132. Completed Operations Date: 1985-01-01. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.329) and France (A/AC.105/INF.330). Symphonie flying model no II. Experimental telecommunications satellite. Orbit: geostationary. Also registered by the United Stat es in A/AC.105/INF.331 as 1975-77A, category C, with orbit 1427.4 min, 35364 x 35870 km x 0.0 deg Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1985 As of 1 September 2001 located at 164.06 deg W drifting at 1.071 deg W per day. As of 2007 Mar 8 located at 167.97E drifting at 1.046W degrees per day.References: 1, 2, 5, 6.

• Explorer 54 Nation: USA. Program: Explorer. Payload: AE D. Mass: 676 kg (1,490 lb). Class: Earth. Type: Atmosphere. Spacecraft: AE. Agency: NASA GSF. Perigee: 151 km (93 mi). Apogee: 3,819 km (2,373 mi). Inclination: 90.10 deg. Period: 126.80 min. COSPAR: 1975-096A. USAF Sat Cat: 8353. Decay Date: 1976-03-12. Atmospheric Explorer; atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• GOES 1 Nation: USA. Payload: GOES A. Mass: 295 kg (650 lb). Class: Earth. Type: Weather. Spacecraft: GOES. Agency: NOAA. Perigee: 35,787 km (22,236 mi). Apogee: 35,811 km (22,251 mi). Inclination: 14.80 deg. Period: 1,436.70 min. COSPAR: 1975-100A. USAF Sat Cat: 8366. Completed Operations Date: 1985-01-01. Geostationary Operational Environmental Satellite. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit over the Atlantic Ocean at 55 deg W in 1975-1976; over the Pacific Ocean 135 deg W in 1976-1978; over the Atlantic Ocean 10 deg W in 1978; over the Indian Ocean 58 deg E in 1978-1979; over the Pacific Ocean 135 deg W in 1979-1980; over the Atlantic Ocean 93 deg W in 1980; over the Pacific Ocean 130 deg W in 1980-1985 As of 3 September 2001 located at 81.97 deg W drifting at 0.051 deg E per day. As of 2007 Mar 9 located at 81.95W drifting at 0.055W degrees per day.References: 1, 2, 5, 6.

• Explorer 55 Nation: USA. Program: Explorer. Payload: AE E. Mass: 721 kg (1,589 lb). Class: Earth. Type: Atmosphere. Spacecraft: AE. Agency: NASA GSF. Perigee: 154 km (95 mi). Apogee: 3,002 km (1,865 mi). Inclination: 19.70 deg. Period: 117.70 min. COSPAR: 1975-107A. USAF Sat Cat: 8440. Decay Date: 1981-06-10. Atmospheric Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• CTS 1 Nation: Canada. Payload: Hermes. Mass: 500 kg (1,100 lb). Class: Communications. Spacecraft: CTS. Agency: CRC. Perigee: 35,704 km (22,185 mi). Apogee: 35,840 km (22,260 mi). Inclination: 12.80 deg. Period: 1,435.40 min. COSPAR: 1976-004A. USAF Sat Cat: 8585. Completed Operations Date: 1979-12-08. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 116 deg W in 1976-79; over the Pacific Ocean 142 deg W in 1979 As of 5 September 2001 located at 135.36 deg W drifting at 0.161 deg W per day. As of 2007 Mar 10 located at 131.55W drifting at 0.190W degrees per day.References: 1, 2, 5, 6.

• Marisat 1 Nation: USA. Payload: Marisat 101. Mass: 655 kg (1,444 lb). Class: Communications. Spacecraft: Marisat. Agency: Comsat. Perigee: 36,033 km (22,389 mi). Apogee: 36,143 km (22,458 mi). Inclination: 13.90 deg. Period: 1,451.50 min. COSPAR: 1976-017A. USAF Sat Cat: 8697. Completed Operations Date: 1997-04-02. Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1976-1990; over the Americas at 106 deg W in 1990-1997 As of 2 September 2001 located at 168.03 deg W drifting at 3.834 deg W per day. As of 2007 Mar 10 located at 20.39E drifting at 3.837W degrees per day.References: 1, 2, 5, 6.

• NATO 3A Nation: NATO. Program: NATO. Mass: 310 kg (680 lb). Class: Communications. Type: Military. Spacecraft: NATO 3. Agency: NATO. Perigee: 35,801 km (22,245 mi). Apogee: 36,017 km (22,379 mi). Inclination: 13.30 deg. Period: 1,442.40 min. COSPAR: 1976-035A. USAF Sat Cat: 8808. Completed Operations Date: 1992-12-17. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 18 deg W in 1976-1982; over the Atlantic Ocean 30 deg W in 1982-1984; over the Atlantic Ocean 50 deg W in 1984-1985; over the Atlantic Ocean at 30 deg W in 1985-1989; over the Americas at 125 deg W in 1989-1991 As of 5 September 2001 located at 4.12 deg E drifting at 1.524 deg W per day. As of 2007 Mar 9 located at 142.00E drifting at 1.522W degrees per day.References: 1, 2, 5, 6.

• Lageos Nation: USA. Payload: Lageos 1. Mass: 411 kg (906 lb). Class: Earth. Type: Geodetic. Spacecraft: Lageos. Agency: NASA MSF. Perigee: 5,839 km (3,628 mi). Apogee: 5,947 km (3,695 mi). Inclination: 109.90 deg. Period: 225.50 min. COSPAR: 1976-039A. USAF Sat Cat: 8820. LAGEOS (Laser Geodetic Satellite) was a very dense (high mass-to-area ratio) laser retroreflector satellite which provided a permanent reference point in a very stable orbit for such precision earth-dynamics measurements as crustal motions, regional strains, fault motions, polar motion and earth-rotation variations, solid earth tides, and other kinematic and dynamic parameters associated with earthquake assessment and alleviation. The performance in orbit of LAGEOS was limited only by degradation of the retroreflectors, so many decades of useful life can be expected. The high mass-to-area ratio and the precise, stable (attitude-independent) geometry of the spacecraft, together with the orbit, made this satellite the most precise position reference available. Because it is visible in all parts of the world and has an extended operation life in orbit, LAGEOS can serve as a fundamental standard for decades.Additional Details: Lageos(1983). References: 1, 2, 5, 6.

• Marisat 2 Nation: USA. Payload: Marisat 102. Mass: 362 kg (798 lb). Class: Communications. Spacecraft: Marisat. Agency: Comsat. Perigee: 36,513 km (22,688 mi). Apogee: 37,604 km (23,365 mi). Inclination: 14.90 deg. Period: 1,501.60 min. COSPAR: 1976-053A. USAF Sat Cat: 8882. Completed Operations Date: 1996-09-25. Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1976-1991 over the Pacific Ocean 178 deg W in 1991-1996 As of 5 September 2001 located at 158.48 deg W drifting at 15.761 deg W per day. As of 2007 Mar 10 located at 162.62W drifting at 15.745W degrees per day.References: 1, 2, 5, 6.

• Palapa 1 Nation: Indonesia. Program: Palapa. Payload: Palapa A1. Mass: 300 kg (660 lb). Class: Communications. Spacecraft: HS 333. Agency: Perumtel. Perigee: 35,818 km (22,256 mi). Apogee: 35,852 km (22,277 mi). Inclination: 8.60 deg. Period: 1,438.60 min. COSPAR: 1976-066A. USAF Sat Cat: 9009. Completed Operations Date: 1986-01-01. Palapa A1 and A2 were the initial elements of Indonesia's domestic communications satellite system. The spacecraft were identical to Canada's Anik and Western Union's Westars except for a modified parabolic reflector, enlarged to give maximum illumination of the Indonesian land mass. Operational lives for Palapa A1 and A2 ended June 1985 and January 1988, respectively. Spacecraft: Based on Hughes HS-333 design.1.5 m diameter parabolic reflector with 12 transponders working through 125 Earth stations. Spin stabilised with despun antenna and feeds. Payload: Both satellites carried 12 transponders that provided 4000 voice circuits or 12 simultaneous TV channels to the country's 6000+ inhabited islands. Positioned in geosynchronous orbit over the Indian Ocean at 83 deg E in 1976-1986? As of 28 August 2001 located at 177.38 deg E drifting at 0.588 deg W per day. As of 2007 Mar 10 located at 51.89W drifting at 0.649W degrees per day.References: 1, 2, 5, 6.

• NOAA 5 Nation: USA. Program: Tiros. Payload: ITOS H. Mass: 340 kg (740 lb). Class: Earth. Type: Weather. Spacecraft: ITOS. Agency: NOAA. Perigee: 1,507 km (936 mi). Apogee: 1,523 km (946 mi). Inclination: 102.30 deg. Period: 116.30 min. COSPAR: 1976-077A. USAF Sat Cat: 9057. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Marisat 3 Nation: USA. Payload: Marisat 103. Mass: 362 kg (798 lb). Class: Communications. Spacecraft: Marisat. Agency: Comsat. Perigee: 35,782 km (22,233 mi). Apogee: 35,789 km (22,238 mi). Inclination: 11.60 deg. Period: 1,436.10 min. COSPAR: 1976-101A. USAF Sat Cat: 9478. Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 73 deg E in 1976-on. As of 26 August 2001 located at 33.84 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 34.60W drifting at 0.007W degrees per day.References: 1, 2, 5, 6.

• NATO 3B Nation: NATO. Program: NATO. Mass: 701 kg (1,545 lb). Class: Communications. Type: Military. Spacecraft: NATO 3. Agency: NATO. Perigee: 37,079 km (23,039 mi). Apogee: 37,421 km (23,252 mi). Inclination: 10.50 deg. Period: 1,511.50 min. COSPAR: 1977-005A. USAF Sat Cat: 9785. Completed Operations Date: 1993-07-29. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1977-1979 over the Atlantic Ocean 20 deg W in 1979-1982 over the Atlantic Ocean 18 deg W in 1983-1986 over the Atlantic Ocean60 deg W in 1987-1993 As of 5 September 2001 located at 74.61 deg W drifting at 18.018 deg W per day. As of 2007 Mar 10 located at 40.43E drifting at 18.015W degrees per day.References: 1, 2, 5, 6.

• Palapa 2 Nation: Indonesia. Program: Palapa. Payload: Palapa A2. Mass: 574 kg (1,265 lb). Class: Communications. Spacecraft: HS 333. Agency: Perumtel. Perigee: 35,843 km (22,271 mi). Apogee: 35,867 km (22,286 mi). Inclination: 7.60 deg. Period: 1,439.60 min. COSPAR: 1977-018A. USAF Sat Cat: 9862. Completed Operations Date: 1986-01-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 80 deg E in 1977-1986? As of 5 September 2001 located at 64.27 deg W drifting at 0.845 deg W per day. As of 2007 Mar 11 located at 69.73E drifting at 0.893W degrees per day.References: 1, 2, 5, 6.

• ESA-Geos 1 Nation: Europe. Payload: ESA GEOS 1. Mass: 573 kg (1,263 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ESA-Geos. Agency: ESA. Perigee: 2,939 km (1,826 mi). Apogee: 38,214 km (23,745 mi). Inclination: 26.60 deg. Period: 734.00 min. COSPAR: 1977-029A. USAF Sat Cat: 9931. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• GOES 2 Nation: USA. Payload: GOES B. Mass: 627 kg (1,382 lb). Class: Earth. Type: Weather. Spacecraft: GOES. Agency: NOAA. Perigee: 35,985 km (22,360 mi). Apogee: 36,080 km (22,410 mi). Inclination: 14.10 deg. Period: 1,448.70 min. COSPAR: 1977-048A. USAF Sat Cat: 10061. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 75 deg W in 1977-1978 over the Americas at 100-110 deg W in 1979-1984 over the Americas at 112-114 deg W in 1984-1990 over the Atlantic Ocean 60 deg W in 1990-1992 over the Pacific Ocean 135 deg W in 1992-1995; over the Pacific Ocean 177 deg W in 1995-on. As of 4 September 2001 located at 147.59 deg W drifting at 3.154 deg W per day. As of 2007 Mar 8 located at 1.58W drifting at 3.141W degrees per day.References: 1, 2, 5, 6.

• Himawari 1 Nation: Japan. Payload: GMS 1. Mass: 670 kg (1,470 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 36,005 km (22,372 mi). Apogee: 36,148 km (22,461 mi). Inclination: 11.10 deg. Period: 1,451.00 min. COSPAR: 1977-065A. USAF Sat Cat: 10143. Completed Operations Date: 1989-09-17. Geostationary meteorological satellite. Positioned in geosynchronous orbit over the Pacific Ocean at 140 deg E in 1977-1981; over the Pacific Ocean 160 deg E in 1981-1984; over the Pacific Ocean 140 deg E in 1984; over the Pacific Ocean160 deg E in 1984-1989 As of 29 August 2001 located at 10.47 deg W drifting at 3.675 deg W per day. As of 2007 Mar 10 located at 112.63E drifting at 3.690W degrees per day.References: 1, 2, 5, 6.

• Sirio 1 Nation: Italy. Mass: 220 kg (480 lb). Class: Technology. Type: Comsat. Spacecraft: Sirio. Agency: CNR. Perigee: 35,755 km (22,217 mi). Apogee: 35,869 km (22,287 mi). Inclination: 9.60 deg. Period: 1,437.40 min. COSPAR: 1977-080A. USAF Sat Cat: 10294. Completed Operations Date: 1989-09-28. Experimental commsat. SIRIO (Satellite Italiano Ricerca Industriale Orientata). Launch time 2350:00 GMT. Geographical longitude of geostationary orbit 15 deg W. SIRIO is a spin stabilized geostationary experimental communications satellite. Characteristics of satellite: Weight at launch 398 kg, in orbit 218 kg. Configuration - cylindrical, height 1.981m, diameter 1.433 m, nominal life two years. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1977-1981; over the Atlantic Ocean 25 deg W in 1981-1983; over the Indian Ocean 65 deg E in 1983-1985 As of 4 September 2001 located at 86.65 deg E drifting at 0.265 deg E per day. As of 2007 Mar 11 located at 75.38E drifting at 0.003E degrees per day.References: 1, 2, 5, 6.

• ISEE 1 Nation: USA. Payload: ISEE A. Mass: 340 kg (740 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ISEE. Agency: NASA GSF. Perigee: 436 km (270 mi). Apogee: 137,806 km (85,628 mi). Inclination: 12.70 deg. Period: 3,441.00 min. COSPAR: 1977-102A. USAF Sat Cat: 10422. Decay Date: 1987-09-26. International Sun-Earth Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• ISEE 2 Nation: Europe. Payload: ISEE B. Mass: 166 kg (365 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ISEE. Agency: ESA. Perigee: 406 km (252 mi). Apogee: 137,765 km (85,603 mi). Inclination: 13.50 deg. Period: 3,438.50 min. COSPAR: 1977-102B. USAF Sat Cat: 10423. Decay Date: 1987-09-26. International Sun-Earth Explorer. References: 1, 2, 5, 6.

• Meteosat 1 Nation: Europe. Mass: 697 kg (1,536 lb). Class: Earth. Type: Weather. Spacecraft: Meteosat. Agency: ESA. Perigee: 35,777 km (22,230 mi). Apogee: 35,854 km (22,278 mi). Inclination: 11.90 deg. Period: 1,437.60 min. COSPAR: 1977-108A. USAF Sat Cat: 10489. Completed Operations Date: 1985-06-01. European Space Agency satellite. Launch time 0135 GMT. Reached definitive position, 0 deg longitude over the Gulf of Guinea, on 7 December. Launched by United States Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at E-4 deg W in 1977-1981; 8E-12 deg E in 1981-1984; 2E-6 deg E in 1984-1985 As of 29 August 2001 located at 51.23 deg E drifting at 0.354 deg E per day. As of 2007 Mar 3 located at 11.52E drifting at 0.055W degrees per day.References: 1, 2, 5, 6.

• Sakura Nation: Japan. Program: CS. Payload: CS-1A. Mass: 676 kg (1,490 lb). Class: Communications. Spacecraft: CS-1. Agency: NASDA. Perigee: 36,169 km (22,474 mi). Apogee: 36,176 km (22,478 mi). Inclination: 10.50 deg. Period: 1,455.90 min. COSPAR: 1977-118A. USAF Sat Cat: 10516. Completed Operations Date: 1985-11-19. Medium-capacity Communications Satellite for Experimental Purposes . Launch vehicle Delta 2914-137. Launch time 0047 UT. Geographical longitude on geostationary orbit: 135 deg E. CS is a spin stabilized geostationary communications satellite. Characteris tics of satellite: Weight approx 340 kg at an early stage in orbit, configuration: cylindrical, height 3.48 m, diameter 2.18m, Expected life more than three years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg E in 1977-1983 over the Pacific Ocean 150 deg E in 1984-1985 As of 25 August 2001 located at 78.79 deg E drifting at 4.904 deg W per day. As of 2007 Mar 10 located at 94.72W drifting at 4.901W degrees per day.References: 1, 2, 5, 6.

• IUE 1 Nation: USA. Payload: IUE. Mass: 672 kg (1,481 lb). Class: Astronomy. Spacecraft: IUE. Agency: NASA/ESA. Perigee: 30,285 km (18,818 mi). Apogee: 41,296 km (25,660 mi). Inclination: 34.30 deg. Period: 1,436.30 min. COSPAR: 1978-012A. USAF Sat Cat: 10637. Completed Operations Date: 1996-09-30. International Ultraviolet Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 30 deg W in-60 deg W in 1978-1996 As of 3 September 2001 located at 35.66 deg E drifting at 0.773 deg W per day. As of 2007 Mar 8 located at 14.14W drifting at 0.700W degrees per day.References: 1, 2, 5, 6.

• Landsat 3 Nation: USA. Program: Landsat. Payload: Landsat C. Mass: 960 kg (2,110 lb). Class: Earth. Type: Landsat. Spacecraft: Landsat 1-2-3. Agency: NASA GSF. Perigee: 895 km (556 mi). Apogee: 915 km (568 mi). Inclination: 98.90 deg. Period: 103.10 min. COSPAR: 1978-026A. USAF Sat Cat: 10702. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Oscar 8 Nation: USA. Program: Oscar. Payload: Amsat-Oscar-8. Mass: 27 kg (59 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: AMSAT-NA. Perigee: 894 km (555 mi). Apogee: 903 km (561 mi). Inclination: 99.20 deg. Period: 103.00 min. COSPAR: 1978-026B. USAF Sat Cat: 10703. AMSAT-OSCAR 8 was launched piggyback with LandSat 3 (ERTS 3) and PIX. The third phase 2 satellite (Phase II-D). Weight 27.2 kg. Box shaped, 33 cm high, 38 x 38 cm. Circularly polarized VHF canted turnstile, UHF quarter wave monopole, and HF half-wave dipole antenna system. Another cooperative international effort (United States, Canada, Germany and Japan). AO-8 had a similar store-and-forward service as AO-7 and carried Mode A (145.850-900 MHz uplink and 29.400-500 MHz downlink) and Mode J (145.900-146.000 MHz uplink and 435.100 MHz downlink (inverted)) linear transponders and telemetry beacons on 435.095 MHz and 29.402 MHz. AO-8's primary mission was for educational applications and amateur communications. It was in operation for six years until the battery failed on June 24, 1983.References: 1, 2, 5, 6.

• PIX Nation: USA. Payload: PIX 1 / Delta 139. Mass: 350 kg (770 lb). Class: Technology. Spacecraft: PIX. Agency: NASA GSF. Perigee: 903 km (561 mi). Apogee: 920 km (570 mi). Inclination: 99.10 deg. Period: 103.20 min. COSPAR: 1978-026C. USAF Sat Cat: 10704. Decay Date: 1981-01-27. Plasma Interaction Experiment. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Yuri 1 Nation: Japan. Program: BS. Payload: BSE-1. Mass: 678 kg (1,494 lb). Class: Technology. Type: Comsat. Spacecraft: Yuri. Agency: NASDA. Perigee: 35,736 km (22,205 mi). Apogee: 35,868 km (22,287 mi). Inclination: 11.70 deg. Period: 1,436.90 min. COSPAR: 1978-039A. USAF Sat Cat: 10792. Completed Operations Date: 1982-01-28. Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.References: 1, 2, 5, 6.

• GOES 3 Nation: USA. Payload: GOES C. Mass: 627 kg (1,382 lb). Class: Earth. Type: Weather. Spacecraft: GOES. Agency: NOAA. Perigee: 35,767 km (22,224 mi). Apogee: 35,812 km (22,252 mi). Inclination: 9.80 deg. Period: 1,436.30 min. COSPAR: 1978-062A. USAF Sat Cat: 10953. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1978-1981 over the Americas at 90 deg W in 1982-1984 over the Pacific Ocean 135 deg W in 1985-1987 over the Americas at129 deg W in 1987-1990 over the Pacific Ocean 175 deg W in 1990-1995 over the Americas at 102-110 deg W in 1996-on. As of 5 September 2001 located at 101.78 deg W drifting at 0.017 deg W per day. As of 2007 Mar 9 located at 105.91W drifting at 0.030W degrees per day.References: 1, 2, 5, 6.

• ESA-Geos 2 Nation: Europe. Payload: ESA GEOS 2. Mass: 573 kg (1,263 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ESA-Geos. Agency: ESA. Perigee: 36,027 km (22,386 mi). Apogee: 36,049 km (22,399 mi). Inclination: 14.60 deg. Period: 1,449.00 min. COSPAR: 1978-071A. USAF Sat Cat: 10981. Completed Operations Date: 1984-01-24. Magnetospheric research. European Space Agency satellite. Launch time 1043 GMT. Reached initial operational position of 6 deg East on 26 Jul 1978. During the two years of its mission, it will be maintained in position between longitude 0 and 35 deg east in geosynchronous orbit. Positioned in geosynchronous orbit over the Atlantic Ocean at 36 deg E in 1978-1979 over the Atlantic Ocean 6-36 deg E in 1979-1981; over the Atlantic Ocean 24 deg E in 1981; over the Atlantic Ocean 33-37 deg E in 1981-1984 As of 3 September 2001 located at 177.77 deg W drifting at 3.212 deg W per day. As of 2007 Mar 9 located at 179.12E drifting at 3.212W degrees per day.References: 1, 2, 5, 6.

• ISEE 3 Nation: USA. Payload: ISEE C. Mass: 479 kg (1,056 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ISEE. Agency: NASA GSF. Perigee: 181 km (112 mi). Apogee: 1,089,200 km (676,700 mi). Inclination: 1.00 deg. Period: 67,852.90 min. COSPAR: 1978-079A. USAF Sat Cat: 11004. International Sun-Earth Explorer; later renamed the International Cometary Explorer. Measured interaction between solar wind and Earth; rendezvoused with comet Giacobini-Zinner September 11, 1985. After several passes through the Earth's magnetotail, with gravity assists from lunar flybys in March, April, September and October of 1983, a final close lunar flyby (119.4 km above the moon's surface) on December 22, 1983, ejected the spacecraft out of the Earth-Moon system and into a heliocentric orbit ahead of the Earth, on a trajectory intercepting that of Comet Giacobini-Zinner. A total of fifteen propulsive maneuvers (four of which were planned) and five lunar flybys were needed to carry out the transfer from the halo orbit to an escape trajectory from the earth-moon system into a heliocentric orbit. The primary scientific objective of ICE was to study the interaction between the solar wind and a cometary atmosphere. As planned, the spacecraft traversed the plasma tail of Comet Giacobini-Zinner on September 11, 1985, and made in situ measurements of particles, fields, and waves. It also transited between the Sun and Comet Halley in late March 1986, when other spacecraft (Giotto, Planet-A, MS-T5, VEGA) were also in the vicinity of Comet Halley on their comet rendezvous missions. ICE became the first spacecraft to directly investigate two comets. An update to the ICE mission was approved by NASA headquarters in 1991. It defined a Heliospheric mission for ICE consisting of investigations of coronal mass ejections in coordination with ground-based observations, continued cosmic ray studies, and special period observations such as when ICE and Ulysses are on the same solar radial line. As of January 1990, ICE was in a 355 day heliocentric orbit with an aphelion of 1.03 AU, a perihelion of 0.93 AU and an inclination of 0.1 degree. This will bring it back to the vicinity of the earth-moon system in August, 2014. Termination of operations of ISEE 3 was authorized May 5, 1997.Additional Details: ISEE 3(2324). References: 1, 2, 5, 6, 296.

• Nimbus 7 Nation: USA. Payload: Nimbus G. Mass: 907 kg (1,999 lb). Class: Earth. Type: Weather. Spacecraft: Nimbus. Agency: NASA GSF. Perigee: 943 km (585 mi). Apogee: 957 km (594 mi). Inclination: 99.00 deg. Period: 104.10 min. COSPAR: 1978-098A. USAF Sat Cat: 11080. Environmental research. The experiments carried were a limb infrared monitoring of the stratosphere (LIMS), stratospheric and mesopheric sounder (SAMS), coastal-zone color scanner (CZCS), stratospheric aerosol measurement (SAM II), earth radiation budget (ERB), scanning multichannel microwave radiometer (SMMR), solar backscatter UV and total ozone mapping spectrometer (SBUV/TOMS), and temperature-humidity infrared radiometer (THIR). These sensors were capable of observing several parameters at and below the mesospheric levels. After 11 years in orbit, three experiments, SAM II, SBUV/TOMS, and ERB, were still functioning successfully.References: 1, 2, 5, 6.

• CAMEO Nation: USA. Payload: CAMEO Li Canister/CAMEO Ba Canister. Mass: 350 kg (770 lb). Class: Earth. Type: Magnetosphere. Spacecraft: CAMEO. Agency: NASA GSF. Perigee: 924 km (574 mi). Apogee: 968 km (601 mi). Inclination: 99.40 deg. Period: 104.00 min. COSPAR: 1978-098B. USAF Sat Cat: 11081. Released barium cloud. References: 1, 2, 5, 6.

• NATO 3C Nation: NATO. Program: NATO. Mass: 720 kg (1,580 lb). Class: Communications. Type: Military. Spacecraft: NATO 3. Agency: NATO. Perigee: 36,289 km (22,548 mi). Apogee: 36,299 km (22,555 mi). Inclination: 11.80 deg. Period: 1,462.10 min. COSPAR: 1978-106A. USAF Sat Cat: 11115. Completed Operations Date: 1992-06-15. Positioned in geosynchronous orbit over the Atlantic Ocean at 50 deg W in 1979-1982 over the Atlantic Ocean 21 deg W in 1983-1986 over the Atlantic Ocean 18 deg W in 1987-1991 over the Atlantic Ocean21 deg W in 1991-1992 As of 31 August 2001 located at 122.29 deg E drifting at 6.431 deg W per day. As of 2007 Mar 10 located at 114.22E drifting at 6.438W degrees per day.References: 1, 2, 5, 6.

• SCATHA Nation: USA. Payload: P 78-2. Mass: 360 kg (790 lb). Class: Technology. Type: Comsat. Spacecraft: SCATHA. Agency: USAF. Perigee: 28,018 km (17,409 mi). Apogee: 42,860 km (26,630 mi). Inclination: 10.20 deg. Period: 1,418.40 min. COSPAR: 1979-007A. USAF Sat Cat: 11256. Completed Operations Date: 1991-05-28. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.References: 1, 2, 5, 6.

• Westar 3 Nation: USA. Program: Westar. Mass: 572 kg (1,261 lb). Class: Communications. Spacecraft: HS 333. Agency: WUTC. Perigee: 35,868 km (22,287 mi). Apogee: 35,883 km (22,296 mi). Inclination: 10.20 deg. Period: 1,440.60 min. COSPAR: 1979-072A. USAF Sat Cat: 11484. Completed Operations Date: 1990-01-24. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 91 deg W in 1979-1990 As of 2 September 2001 located at 7.26 deg W drifting at 1.139 deg W per day. As of 2007 Mar 9 located at 158.25E drifting at 1.129W degrees per day.References: 1, 2, 5, 6.

• SME Nation: USA. Payload: Solar Mesosphere Explorer. Mass: 437 kg (963 lb). Class: Astronomy. Spacecraft: SME. Agency: JPL/UC-L. Perigee: 335 km (208 mi). Apogee: 337 km (209 mi). Inclination: 97.60 deg. Period: 91.30 min. COSPAR: 1981-100A. USAF Sat Cat: 12887. Decay Date: 1991-03-05. Solar Mesosphere Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Oscar 9 Nation: UK. Program: Oscar. Payload: UoSAT 1. Mass: 52 kg (114 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Microsat SSTL. Agency: SSTL. Manufacturer: Surrey. Perigee: 372 km (231 mi). Apogee: 374 km (232 mi). Inclination: 97.60 deg. Period: 92.00 min. COSPAR: 1981-100B. USAF Sat Cat: 12888. Decay Date: 1989-10-13. University of Surrey research microsatellite. Radio science; also carried amateur radio package. Communication and geophysics research satellite. Launch time 1127 GMT. Also registered by the United States in ST/SG/SER.E/59, with category D and orbital parameters 95.3 min, 531 x 533 km x 97.5 deg. UoSAT-OSCAR 9 was launched piggyback with Solar Mesosphere Explorer satellite. Weight 52 kg. Box shaped 740 x 420 x 420 mm. Deployable gravity gradient boom. Firsts: First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments. Built by the University of Surrey in the United Kingdom, UO-9 was UoSAT's first experimental satellite. It was a scientific and educational low-Earth orbit satellite containing many experiments and beacons but no amateur transponders. UO-9 was fully operational until it re-entered October 13, 1989 from a decaying orbit after nine years of service.References: 1, 2, 5, 6.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975. ISBN: 0713735058. Covers rocketry of all nations. More at amazon.com...

• Wilson, Andrew, Spaceflight, "Delta Digest", 1979, Volume 10, page 413.