Delta M6 Credit - © Thom Media Gallery

Long Tank Thor augmented with 3-6 Castor 2 boosters and Delta E / Burner 2 upper stages.

Manufacturer: Douglas. Launches: 13. Failures: 2. Success Rate: 84.62%. First Launch Date: 1968-09-19. Last Launch Date: 1971-03-13. Launch data is: complete. Payload: 454 kg (1,000 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: IMP, Intelsat 3, NATO 1. Liftoff Thrust: 2,140.700 kN (481,249 lbf). Total Mass: 103,681 kg (228,577 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 34.00 m (111.00 ft). Flyaway Unit Cost $: 22.300 million. in: 1985 unit dollars.

4 stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1B + 1 x Delta E x Star 37D

Payload: 355 kg (782 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 1,590.000 kN (357,440 lbf). Total Mass: 91,000 kg (200,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 32.40 m (106.20 ft).

4 stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E + 1 x Star 37D

Payload: 450 kg (990 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 2,411.000 kN (542,014 lbf). Total Mass: 103,700 kg (228,600 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 32.40 m (106.20 ft).

• Stage Number: 0. 6 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 LT. Gross Mass: 70,354 kg (155,104 lb). Empty Mass: 3,715 kg (8,190 lb). Thrust (vac): 866.710 kN (194,844 lbf). Isp: 290 sec. Burn time: 215 sec. Isp(sl): 256 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 21.43 m (70.30 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: MB-3-3. Other designations: Long Tank Thor. Status: Out of production.

• 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: 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).

1968 September 19 - 00:09 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17. Launch Pad: LC17A. Launch Vehicle: Delta M. Model: Thor Delta M. LV Configuration: Thor Delta M 529/D59. FAILURE: Control system failure; destroyed by range safety.

• Intelsat-3 F-1 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: Intelsat. COSPAR: F680919A. Decay Date: 1968-09-18. References: 5, 126.

• Intelsat 3 F-2 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,984 km (22,359 mi). Apogee: 37,111 km (23,059 mi). Inclination: 15.10 deg. Period: 1,475.20 min. COSPAR: 1968-116A. USAF Sat Cat: 3623. Completed Operations Date: 1977-01-25. Over Brazil. 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 24 deg W in 1969-1970. As of 3 September 2001 located at 96.04 deg E drifting at 9.557 deg W per day. As of 2007 Mar 9 located at 48.04W drifting at 9.553W degrees per day.References: 1, 2, 5, 6.

• Intelsat 3 F-3 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,767 km (22,224 mi). Apogee: 35,803 km (22,246 mi). Inclination: 6.10 deg. Period: 1,436.00 min. COSPAR: 1969-011A. USAF Sat Cat: 3674. Completed Operations Date: 1979-12-13. Stationed at 63 deg E. 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 1969; over the Indian Ocean 062 deg E in 1969-1975. Last known longitude (24 May 1979) 66.72 deg E drifting at 0.017 deg E per day.References: 1, 2, 5, 6.

• Intelsat 3 F-4 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 39,486 km (24,535 mi). Apogee: 39,752 km (24,700 mi). Inclination: 6.10 deg. Period: 1,636.30 min. COSPAR: 1969-045A. USAF Sat Cat: 3947. Completed Operations Date: 1977-05-13. Positioned in geosynchronous orbit over the Pacific Ocean at 175 deg E in 1969-1972; ? 1972-1977; over the Pacific Ocean 166 deg W in 1977. Last known longitude (20 May 1977) 161.73 deg E drifting at 44.175 deg W 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.

• Intelsat 3 F-5 Nation: International. Program: Intelsat. Mass: 269 kg (593 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 211 km (131 mi). Apogee: 433 km (269 mi). Inclination: 30.20 deg. Period: 91.00 min. COSPAR: 1969-064A. USAF Sat Cat: 4051. Decay Date: 1988-10-14. Third stage failure; left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Skynet 1A Nation: UK. Program: Skynet. Mass: 243 kg (535 lb). Class: Communications. Type: Military. Spacecraft: NATO 1. Agency: UK MoD. Perigee: 35,682 km (22,171 mi). Apogee: 35,894 km (22,303 mi). Inclination: 13.90 deg. Period: 1,436.20 min. COSPAR: 1969-101A. USAF Sat Cat: 4250. Completed Operations Date: 1980-01-01. Over Indian Ocean. Military communications. Previously registered by the United States in A/AC.105/INF.220: 1969-101A, orbital data 276 x 36716 km x 28.0 deg, category C. Positioned in geosynchronous orbit over the Indian Ocean at 41 deg E in 1969-1972?; ??? 1972-1977; over the Americas at 100-110 deg W in 1977-1998 As of 26 August 2001 located at 104.51 deg W drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 106.94W drifting at 0.015W degrees per day.References: 1, 2, 5, 6.

• Intelsat 3 F-6 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 36,079 km (22,418 mi). Apogee: 36,126 km (22,447 mi). Inclination: 14.30 deg. Period: 1,452.30 min. COSPAR: 1970-003A. USAF Sat Cat: 4297. Completed Operations Date: 1977-05-13. Stationed at 336 deg E. 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 25 deg W in 1970; over the Atlantic Ocean 30 deg W in 1970-1971; over the Atlantic Ocean 20 deg W in 1971 Apr-1972 Mar; over the Indian Ocean 64 deg E in 1972-1974; over the Pacific Ocean 177 deg W in 1975 As of 5 September 2001 located at 163.49 deg E drifting at 4.024 deg W per day. As of 2007 Feb 27 located at 47.49E drifting at 4.027W degrees per day.References: 1, 2, 5, 6.

• NATO 1 Nation: NATO. Program: NATO. Payload: NATO IIA. Mass: 243 kg (535 lb). Class: Communications. Type: Military. Spacecraft: NATO 1. Agency: NATO. Perigee: 35,768 km (22,225 mi). Apogee: 35,801 km (22,245 mi). Inclination: 13.40 deg. Period: 1,436.00 min. COSPAR: 1970-021A. USAF Sat Cat: 4353. Completed Operations Date: 1977-01-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 18 deg W in 1970-1972; over the Americas at 100-110 deg W in 1977-1998 As of 3 September 2001 located at 101.97 deg W drifting at 0.023 deg E per day. As of 2007 Mar 9 located at 100.55W drifting at 0.016W degrees per day.References: 1, 2, 5, 6.

• Intelsat 3 F-7 Nation: International. Program: Intelsat. Mass: 293 kg (645 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 35,775 km (22,229 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.90 deg. Period: 1,435.90 min. COSPAR: 1970-032A. USAF Sat Cat: 4376. Completed Operations Date: 1972-05-01. Stationed at 341 deg E. Positioned in geosynchronous orbit over the Atlantic Ocean at 19 deg W in 1970-1971 Last known longitude (1 January 1972) L 139.45 deg E drifting at 0.022 deg E 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.

• Intelsat 3 F-8 Nation: International. Program: Intelsat. Mass: 270 kg (590 lb). Class: Communications. Spacecraft: Intelsat 3. Agency: INTELSAT. Perigee: 33,877 km (21,050 mi). Apogee: 36,599 km (22,741 mi). Inclination: 12.10 deg. Period: 1,408.20 min. COSPAR: 1970-055A. USAF Sat Cat: 4478. Completed Operations Date: 1970-07-25. Unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). As of 28 August 2001 located at 175.58 deg E drifting at 7.155 deg E per day. As of 2007 Mar 9 located at 110.93W drifting at 7.169E degrees per day.References: 1, 2, 5, 6.

• Skynet 1B Nation: UK. Program: Skynet. Mass: 243 kg (535 lb). Class: Communications. Type: Military. Spacecraft: NATO 1. Agency: UK MoD. Perigee: 278 km (172 mi). Apogee: 37,460 km (23,270 mi). Inclination: 25.90 deg. Period: 665.40 min. COSPAR: 1970-062A. USAF Sat Cat: 4493. AKM failure left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• NATO 2 Nation: NATO. Program: NATO. Payload: NATO IIB. Mass: 243 kg (535 lb). Class: Communications. Type: Military. Spacecraft: NATO 1. Agency: NATO. Perigee: 35,772 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 13.90 deg. Period: 1,436.10 min. COSPAR: 1971-009A. USAF Sat Cat: 4902. Completed Operations Date: 1984-06-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 26 deg W in 1971-1975?; over the Americas at 105 deg W in 1976-1983; over the Americas at 110 deg W in 1983; over the Americas at 105 deg W in 1983-1998 As of 5 September 2001 located at 104.88 deg W drifting at 0.004 deg W per day. As of 2007 Mar 9 located at 105.24W drifting at 0.007W degrees per day.References: 1, 2, 5, 6.

• Explorer 43 Nation: USA. Program: Explorer. Payload: IMP I. Mass: 288 kg (634 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 1,845 km (1,146 mi). Apogee: 203,130 km (126,210 mi). Inclination: 31.20 deg. Period: 5,957.90 min. COSPAR: 1971-019A. USAF Sat Cat: 5043. Decay Date: 1974-10-02. Earth magnetosphere 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.