Delta E Credit - © Thom

Thor augmented with 3 x Castor 2 motors with Delta E and FW-4D or other upper stages.

Manufacturer: Douglas. Launches: 23. Failures: 1. Success Rate: 95.65%. First Launch Date: 1965-11-06. Last Launch Date: 1971-04-01. Launch data is: complete. Payload: 150 kg (330 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: GEOS, HEOS, IMP, Intelsat 2, Isis, Pioneer 6-7-8-9-E, Tiros, TOS, TTS. Liftoff Thrust: 1,452.900 kN (326,625 lbf). Total Mass: 69,023 kg (152,169 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 31.00 m (101.00 ft). Flyaway Unit Cost $: 13.930 million. in: 1985 unit dollars.

4 stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x Altair 2

LEO Payload: 540 kg (1,190 lb). Payload: 150 kg (330 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 1,450.000 kN (325,970 lbf). Total Mass: 68,000 kg (149,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 28.00 m (91.00 ft).

4 stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x FW4D

LEO Payload: 540 kg (1,190 lb). Payload: 150 kg (330 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 1,450.000 kN (325,970 lbf). Total Mass: 68,000 kg (149,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 28.00 m (91.00 ft).

• Stage Number: 0. 3 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 TA. Gross Mass: 49,442 kg (109,000 lb). Empty Mass: 3,175 kg (6,999 lb). Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 150 sec. Isp(sl): 256 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 18.41 m (60.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: MB-3-3. Other designations: Thrust Augmented Thor.

• Stage Number: 2. 1 x Stage: Delta E. Gross Mass: 6,009 kg (13,247 lb). Empty Mass: 785 kg (1,730 lb). Thrust (vac): 35.098 kN (7,890 lbf). Isp: 278 sec. Burn time: 400 sec. Isp(sl): 0 sec. Diameter: 1.40 m (4.50 ft). Span: 1.40 m (4.50 ft). Length: 6.28 m (20.60 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: AJ10-118E.

• Stage Number: 3. 1 x Stage: FW-4D. Gross Mass: 300 kg (660 lb). Empty Mass: 25 kg (55 lb). Thrust (vac): 24.997 kN (5,620 lbf). Isp: 287 sec. Burn time: 31 sec. Isp(sl): 250 sec. Diameter: 0.50 m (1.64 ft). Span: 0.50 m (1.64 ft). Length: 1.48 m (4.85 ft). Propellants: Solid. No Engines: 1. Engine: FW4-D.

1965 November 6 - 18:38 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17. Launch Pad: LC17A. Launch Vehicle: Delta E. Model: Thor Delta E. LV Configuration: Thor Delta E 457/D34.

• Explorer 29 Nation: USA. Program: Explorer. Payload: GEOS A. Mass: 175 kg (385 lb). Class: Solar. Spacecraft: GEOS. Agency: NASA GSF. Perigee: 1,120 km (690 mi). Apogee: 2,269 km (1,409 mi). Inclination: 59.40 deg. Period: 120.30 min. COSPAR: 1965-089A. USAF Sat Cat: 1726. The primary objective of GEOS-A was to provide global geodetic measurements for determining the positions of fiducial control points on the Earth to an accuracy of 10 meters in an Earth centre of mass co-ordinate system, and to determine the structure of the Earth's gravity field to 5 parts in 10 million. Instrumentation included (1) four optical beacons, (2) laser reflectors, (3) a radio range transponder, (4) Doppler beacons, and (5) a range and range rate transponder. These were designed to operate simultaneously to fulfil the objectives of locating observation points (geodetic control stations) in a three dimensional earth centre-of-mass co-ordinate system within 10 m of accuracy, of defining the structure of the earth's irregular gravitational field and refining the locations and magnitudes of the large gravity anomalies, and of comparing results of the various systems onboard the spacecraft to determine the most accurate and reliable system. In January 1967, a failure in the satellite's command system rendered several geodetic systems inoperable. Radio doppler measurements and the passive laser reflector experiment could continue indefinitely, however.Additional Details: Explorer 29(480). References: 1, 2, 5, 6, 405.

• Pioneer 6 Nation: USA. Program: Pioneer. Payload: Pioneer A. Mass: 63 kg (138 lb). Class: Solar. Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. COSPAR: 1965-105A. USAF Sat Cat: 1841. Measured solar wind, Sun's magnetic field. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• ESSA 2 Nation: USA. Program: Tiros. Payload: Tiros OT2. Mass: 132 kg (291 lb). Class: Earth. Type: Weather. Spacecraft: Tiros. Agency: ESSA. Perigee: 1,355 km (841 mi). Apogee: 1,415 km (879 mi). Inclination: 101.30 deg. Period: 113.50 min. COSPAR: 1966-016A. USAF Sat Cat: 2091. Environmental Survey Satellite; carried APT cameras. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Explorer 33 Nation: USA. Program: Explorer. Payload: AIMP D. Mass: 93 kg (205 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 265,679 km (165,084 mi). Apogee: 480,762 km (298,731 mi). Inclination: 24.10 deg. Period: 38,792.40 min. COSPAR: 1966-058A. USAF Sat Cat: 2258. Intended to enter lunar orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Pioneer 7 Nation: USA. Program: Pioneer. Payload: Pioneer B. Mass: 63 kg (138 lb). Class: Solar. Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. Perigee: 246 km (152 mi). Apogee: 993 km (617 mi). Inclination: 33.00 deg. Period: 97.20 min. COSPAR: 1966-075A. USAF Sat Cat: 2398. Monitored solar wind, cosmic rays. SOLAR ORB. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• ESSA 3 Nation: USA. Program: Tiros. Payload: TOS A. Mass: 145 kg (319 lb). Class: Earth. Type: Weather. Spacecraft: TOS. Agency: ESSA. Perigee: 1,387 km (861 mi). Apogee: 1,486 km (923 mi). Inclination: 100.90 deg. Period: 114.60 min. COSPAR: 1966-087A. USAF Sat Cat: 2435. Environmental Survey Satellite 3; replace ESSA 1. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Intelsat 2 F-1 Nation: International. Program: Intelsat. Mass: 140 kg (300 lb). Class: Communications. Spacecraft: Intelsat 2. Agency: Intelsat. Perigee: 3,328 km (2,067 mi). Apogee: 37,070 km (23,030 mi). Inclination: 17.30 deg. Period: 718.70 min. COSPAR: 1966-096A. USAF Sat Cat: 2514. Decay Date: 1982-09-07. Unusable orbit due to AKM failure. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Intelsat 2 F-2 Nation: International. Program: Intelsat. Mass: 87 kg (191 lb). Class: Communications. Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,769 km (22,225 mi). Apogee: 35,808 km (22,250 mi). Inclination: 1.60 deg. Period: 1,436.20 min. COSPAR: 1967-001A. USAF Sat Cat: 2639. Completed Operations Date: 1977-05-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1967-1969; over the Pacific Ocean 162-170 deg E in 1969-1970; over the Pacific Ocean 150-160 deg E in 1970-1975 As of 7 August 2001 located at 48.66 deg E drifting at 0.413 deg W per day. As of 2007 Mar 8 located at 63.48W drifting at 0.357W degrees per day.References: 1, 2, 5, 6.

• ESSA 4 Nation: USA. Program: Tiros. Payload: TOS B. Mass: 132 kg (291 lb). Class: Earth. Type: Weather. Spacecraft: TOS. Agency: ESSA. Perigee: 1,326 km (823 mi). Apogee: 1,440 km (890 mi). Inclination: 102.00 deg. Period: 113.40 min. COSPAR: 1967-006A. USAF Sat Cat: 2657. Replaced ESSA 2. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Intelsat 2 F-3 Nation: International. Program: Intelsat. Mass: 192 kg (423 lb). Class: Communications. Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,670 km (22,160 mi). Apogee: 35,899 km (22,306 mi). Inclination: 12.50 deg. Period: 1,436.00 min. COSPAR: 1967-026A. USAF Sat Cat: 2717. Completed Operations Date: 1977-05-01. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1967-1971; over the Atlantic Ocean at 35 deg W in 1972; over the Atlantic Ocean at 15 deg W in 1973. As of 22 August 2001 was at 6.75 deg W drifting at 0.037 deg W per day. As of 2005 Dec 5 located at 13.34E drifting at 0.188W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).References: 1, 2, 5, 6.

• ESSA 5 Nation: USA. Program: Tiros. Payload: TOS C. Mass: 145 kg (319 lb). Class: Earth. Type: Weather. Spacecraft: TOS. Agency: ESSA. Perigee: 1,355 km (841 mi). Apogee: 1,422 km (883 mi). Inclination: 102.00 deg. Period: 113.50 min. COSPAR: 1967-036A. USAF Sat Cat: 2757. Replaced ESSA 3. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Explorer 34 Nation: USA. Program: Explorer. Payload: IMP F. Mass: 75 kg (165 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 242 km (150 mi). Apogee: 214,379 km (133,208 mi). Inclination: 67.10 deg. Period: 6,358.20 min. COSPAR: 1967-051A. USAF Sat Cat: 2817. Decay Date: 1969-05-03. Radiation, magnetic field data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Explorer 35 Nation: USA. Program: Explorer. Payload: AIMP E. Mass: 104 kg (229 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 484 km (300 mi). Apogee: 675 km (419 mi). Inclination: 32.40 deg. Period: 96.26 min. COSPAR: 1967-070A. USAF Sat Cat: 2884. Earth magnetic tail measurements. Lunar Orbit (Selenocentric). The Westinghouse Aerospace Division, under contract to National Aeronautics and Space Administration's Goddard Space Flight Center, engaged in the system design, integration, assembly and launch support for Anchored Interplanetary Monitoring Platform Satellite, officially designated Explorer 35 by the National Aeronautics and Space Administration. It was launched on July 19, 1967, with the primary objectives of investigation of interplanetary plasma and the interplanetary magnetic field out to and at the lunar distance, in either a captured lunar orbit or a geocentric orbit of the earth. In the geocentric orbit, the apogee was near or beyond the lunar distance. In a lunar orbit, additional objectives included obtaining data on dust distribution, lunar gravitational field, ionosphere, magnetic field, and radiation environment around the moon. AIMP-E also studied spatial and temporal relationships of geophysical and interplanetary phenomena simultaneously being studied by several other National Aeronautics and Space Administration satellites. The investigation in the vicinity of the moon provided for measurements of the characteristics of the interplanetary dust distribution, solar and galactic cosmic rays, as well as a study of the magnetohydrodynamic wake of the earth in the interplanetary medium at the lunar distances.References: 1, 2, 5, 6, 405.

• Intelsat 2 F-4 Nation: International. Program: Intelsat. Mass: 87 kg (191 lb). Class: Communications. Spacecraft: Intelsat 2. Agency: INTELSAT. Perigee: 35,729 km (22,200 mi). Apogee: 35,885 km (22,297 mi). Inclination: 13.00 deg. Period: 1,437.10 min. COSPAR: 1967-094A. USAF Sat Cat: 2969. Completed Operations Date: 1977-05-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1967-1970; over the Pacific Ocean 166 deg W in 1971; over the Atlantic Ocean 30-42 deg W in 1972 As of 1 August 2001 located at 36.36 deg W drifting at 0.096 deg E per day. As of 2007 Mar 7 located at 168.68W drifting at 0.093W degrees per day.References: 1, 2, 5, 6.

• ESSA 6 Nation: USA. Program: Tiros. Payload: TOS D. Mass: 132 kg (291 lb). Class: Earth. Type: Weather. Spacecraft: TOS. Agency: ESSA. Perigee: 1,409 km (875 mi). Apogee: 1,485 km (922 mi). Inclination: 102.10 deg. Period: 114.80 min. COSPAR: 1967-114A. USAF Sat Cat: 3035. Returned cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Pioneer 8 Nation: USA. Program: Pioneer. Payload: Pioneer C / TTS 1. Mass: 63 kg (138 lb). Class: Solar. Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. COSPAR: 1967-123A. USAF Sat Cat: 3066. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• TTS 1 Nation: USA. Payload: TTS A. Mass: 20 kg (44 lb). Class: Technology. Type: Tracking network. Spacecraft: TTS. Agency: NASA GSF. Perigee: 287 km (178 mi). Apogee: 490 km (300 mi). Inclination: 32.90 deg. Period: 92.20 min. COSPAR: 1967-123B. USAF Sat Cat: 3067. Decay Date: 1968-04-28. Test and Training Satellite; tested Apollo tracking network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Explorer 36 Nation: USA. Program: Explorer. Payload: GEOS B. Mass: 209 kg (460 lb). Class: Solar. Spacecraft: GEOS. Agency: NASA GSF. Perigee: 1,081 km (671 mi). Apogee: 1,574 km (978 mi). Inclination: 105.80 deg. Period: 112.20 min. COSPAR: 1968-002A. USAF Sat Cat: 3093. The geodetic instrumentation systems included (1) four optical beacons, (2) two C-band radar transponders, (3) a passive radar reflector, (4) a sequential collation of range radio range transponder, (5) a Goddard range and range rate transponder, (6) laser reflectors, and (7) Doppler beacons. Non-geodetic systems included a laser detector and a Minitrack interferometer beacon. The objectives of the spacecraft were to optimise optical station visibility periods and to provide complementary data for inclination-dependent terms established by the Explorer 29 (GEOS 1) gravimetric studies. The spacecraft was placed into a retrograde orbit to accomplish these objectives. Operational problems occurred in the main power system, optical beacon flash system, and the spacecraft clock, and adjustments in scheduling resulted in nominal operations.References: 1, 2, 5, 6.

• Pioneer 9 Nation: USA. Program: Pioneer. Payload: Pioneer D / TTS 2. Mass: 63 kg (138 lb). Class: Solar. Spacecraft: Pioneer 6-7-8-9-E. Agency: NASA ARC. COSPAR: 1968-100A. USAF Sat Cat: 3533. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• TTS 2; TATS 2 (TETR 2) Nation: USA. Payload: TETR 2. Mass: 40 kg (88 lb). Class: Technology. Type: Tracking network. Spacecraft: TTS. Agency: NASA GSF. Perigee: 375 km (233 mi). Apogee: 945 km (587 mi). Inclination: 32.90 deg. Period: 98.00 min. COSPAR: 1968-100B. USAF Sat Cat: 3534. Decay Date: 1979-09-19. Test and Training Satellite; test vehicle for NASA Manned Space Flight Network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• HEOS 1 Nation: Europe. Payload: HEOS A1. Mass: 108 kg (238 lb). Class: Earth. Type: Magnetosphere. Spacecraft: HEOS. Agency: ESRO. Perigee: 20,020 km (12,430 mi). Apogee: 202,780 km (126,000 mi). Inclination: 60.50 deg. Period: 6,704.30 min. COSPAR: 1968-109A. USAF Sat Cat: 3595. Decay Date: 1975-10-28. Highly Eccentric Orbiting Satellite; examined magnetic fields outside of Earth's magnetosphere. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Isis 1 Nation: Canada. Payload: Isis A. Mass: 241 kg (531 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Isis. Agency: CRC. Perigee: 578 km (359 mi). Apogee: 3,458 km (2,148 mi). Inclination: 88.40 deg. Period: 127.60 min. COSPAR: 1969-009A. USAF Sat Cat: 3669. Ionospheric measurements; data correlated with measurements from Alouette 1. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• ESSA 9 Nation: USA. Program: Tiros. Payload: TOS G. Mass: 145 kg (319 lb). Class: Earth. Type: Weather. Spacecraft: TOS. Agency: ESSA. Perigee: 1,425 km (885 mi). Apogee: 1,505 km (935 mi). Inclination: 101.80 deg. Period: 115.20 min. COSPAR: 1969-016A. USAF Sat Cat: 3764. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Explorer 41 Nation: USA. Program: Explorer. Payload: IMP G. Mass: 174 kg (383 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 80,374 km (49,941 mi). Apogee: 98,159 km (60,993 mi). Inclination: 86.00 deg. Period: 4,906.30 min. COSPAR: 1969-053A. USAF Sat Cat: 3990. Decay Date: 1972-12-23. Cislunar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Isis 2 Nation: Canada. Payload: Isis B. Mass: 264 kg (582 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Isis. Agency: CRC. Perigee: 1,358 km (843 mi). Apogee: 1,424 km (884 mi). Inclination: 88.20 deg. Period: 113.60 min. COSPAR: 1971-024A. USAF Sat Cat: 5104. Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). 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.