Encyclopedia Astronautica
Delta M


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Delta M6
Credit: © Thomas Kladiva - Thomas Kladiva
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Delta M6 no. 83
Delta M6 no. 83 - COSPAR 1971-019
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Delta M no. 80
Delta M no. 80 - COSPAR 1970-062
American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E / Burner 2 (Star 37D) upper stages.

LEO Payload: 355 kg (782 lb). Payload: 355 kg (782 lb) to a GTO in 1985 dollars. Flyaway Unit Cost $: 22.300 million.

Stage Data - Delta M

  • Stage 0. 6 x 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. Status: In Production.
  • Stage 1. 1 x 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 2. 1 x 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): 0.0000 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. Status: Out of Production.
  • Stage 3. 1 x 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. Status: Out of Production. 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).

AKA: Long Tank Thor.
Status: Out of production.
Gross mass: 103,681 kg (228,577 lb).
Payload: 355 kg (782 lb).
Height: 34.00 m (111.00 ft).
Diameter: 2.44 m (8.00 ft).
Thrust: 2,140.70 kN (481,249 lbf).
First Launch: 1968.09.19.
Last Launch: 1971.02.03.
Number: 12 .

More... - Chronology...
Associated Countries
Associated Spacecraft
  • IMP American earth magnetosphere satellite. 10 launches, 1963.11.27 (Explorer 18) to 1973.10.26 (Explorer 50). More...
  • Intelsat 3 American communications satellite. 8 launches, 1968.09.19 (Intelsat-3 F-1) to 1970.07.23 (Intelsat 3 F-8). Intelsat 3 spacecraft were used to relay commercial global telecommunications including live TV. More...
  • NATO 1 British military communications satellite. 4 launches, 1969.11.22 (Skynet 1A) to 1971.02.03 (NATO 2). Military communications. More...
Associated Engines
  • AJ10-118E Aerojet Nitric acid/UDMH rocket engine. 35.1 kN. Isp=278s. Used on Delta E, Delta G, Delta J, Delta L, Delta M, Delta N upper stages. First flight 1965. More...
  • MB-3-3 Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H-1. Isp=290s. First flight 1964. More...
  • Star 37 Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963. More...
  • TX-354-3 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960. More...
See also
  • Delta The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Development began in 1955 and it continued in service in the 21st Century despite numerous candidate replacements. More...
Associated Manufacturers and Agencies
  • Douglas American manufacturer of rockets, spacecraft, and rocket engines. Boeing Huntington Beach, Huntington Beach, CA, USA. More...
Associated Programs
  • Intelsat Intelsat operated the world's first commercial communications satellite. It has provided the scheduled transoceanic television and voice and data communications service ever since. More...
  • NATO Military communications satellite network. More...
Associated Launch Sites
  • Cape Canaveral America's largest launch center, used for all manned launches. Today only six of the 40 launch complexes built here remain in use. Located at or near Cape Canaveral are the Kennedy Space Center on Merritt Island, used by NASA for Saturn V and Space Shuttle launches; Patrick AFB on Cape Canaveral itself, operated the US Department of Defense and handling most other launches; the commercial Spaceport Florida; the air-launched launch vehicle and missile Drop Zone off Mayport, Florida, located at 29.00 N 79.00 W, and an offshore submarine-launched ballistic missile launch area. All of these take advantage of the extensive down-range tracking facilities that once extended from the Cape, through the Caribbean, South Atlantic, and to South Africa and the Indian Ocean. More...
  • Cape Canaveral LC17A Delta launch complex. Part of a dual launch pad complex built for the Thor ballistic missile program in 1956. Pad 17A supported Thor, Delta, and Delta II launches into the 21st Century. More...
Associated Stages
  • Castor 2 Solid propellant rocket stage. Loaded/empty mass 4,424/695 kg. Thrust 258.92 kN. Vacuum specific impulse 262 seconds. More...
  • Delta Thor LT Lox/Kerosene propellant rocket stage. Loaded/empty mass 70,354/3,715 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds. More...
  • Delta E Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 6,009/785 kg. Thrust 35.10 kN. Vacuum specific impulse 278 seconds. More...
  • Star 37D Solid rocket stage. 45.00 kN (10,116 lbf) thrust. Mass 718 kg (1,583 lb). More...

Delta M Chronology
1968 September 19 - . 00:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 529/D59. FAILURE: Control system failure; destroyed by range safety.. Failed Stage: G.
1968 December 19 - . 00:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 536/D63.
  • Intelsat 3 F-2 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-01-25 . USAF Sat Cat: 3623 . COSPAR: 1968-116A. Apogee: 37,111 km (23,059 mi). Perigee: 35,984 km (22,359 mi). Inclination: 15.1000 deg. Period: 1,475.20 min. 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.
1969 February 6 - . 00:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 530/D66.
  • Intelsat 3 F-3 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1979-12-13 . USAF Sat Cat: 3674 . COSPAR: 1969-011A. Apogee: 35,803 km (22,246 mi). Perigee: 35,767 km (22,224 mi). Inclination: 6.1000 deg. Period: 1,436.00 min. 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.
1969 May 22 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 533/D68.
  • Intelsat 3 F-4 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-05-13 . USAF Sat Cat: 3947 . COSPAR: 1969-045A. Apogee: 39,752 km (24,700 mi). Perigee: 39,486 km (24,535 mi). Inclination: 6.1000 deg. Period: 1,636.30 min. 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).
1969 July 26 - . 02:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 547/D71. FAILURE: Third stage failure; left in unusable orbit.. Failed Stage: 3.
  • Intelsat 3 F-5 - . Mass: 269 kg (593 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Decay Date: 1988-10-14 . USAF Sat Cat: 4051 . COSPAR: 1969-064A. Apogee: 433 km (269 mi). Perigee: 211 km (131 mi). Inclination: 30.2000 deg. Period: 91.00 min. Summary: 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)..
1969 November 22 - . 00:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 554/D74.
  • Skynet 1A - . Mass: 243 kg (535 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 1. Completed Operations Date: 1980-01-01 . USAF Sat Cat: 4250 . COSPAR: 1969-101A. Apogee: 35,894 km (22,303 mi). Perigee: 35,682 km (22,171 mi). Inclination: 13.9000 deg. Period: 1,436.20 min. 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.
1970 January 15 - . 00:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 557/D75.
  • Intelsat 3 F-6 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-05-13 . USAF Sat Cat: 4297 . COSPAR: 1970-003A. Apogee: 36,126 km (22,447 mi). Perigee: 36,079 km (22,418 mi). Inclination: 14.3000 deg. Period: 1,452.30 min. 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.
1970 March 20 - . 23:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 558/D77.
  • NATO 1 - . Payload: NATO IIA. Mass: 243 kg (535 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 1. Completed Operations Date: 1977-01-01 . USAF Sat Cat: 4353 . COSPAR: 1970-021A. Apogee: 35,801 km (22,245 mi). Perigee: 35,768 km (22,225 mi). Inclination: 13.4000 deg. Period: 1,436.00 min. 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.
1970 April 23 - . 00:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 559/D78.
  • Intelsat 3 F-7 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1972-05-01 . USAF Sat Cat: 4376 . COSPAR: 1970-032A. Apogee: 35,791 km (22,239 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.9000 deg. Period: 1,435.90 min. 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).
1970 July 23 - . 23:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 563/D79.
  • Intelsat 3 F-8 - . Mass: 270 kg (590 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1970-07-25 . USAF Sat Cat: 4478 . COSPAR: 1970-055A. Apogee: 36,599 km (22,741 mi). Perigee: 33,877 km (21,050 mi). Inclination: 12.1000 deg. Period: 1,408.20 min. 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.
1970 August 19 - . 12:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 561/D80.
  • Skynet 1B - . Mass: 243 kg (535 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 1. USAF Sat Cat: 4493 . COSPAR: 1970-062A. Apogee: 37,460 km (23,270 mi). Perigee: 278 km (172 mi). Inclination: 25.9000 deg. Period: 665.40 min. Summary: AKM failure left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .
1971 February 3 - . 01:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta M. LV Configuration: Thor Delta M 560/D82.
  • NATO 2 - . Payload: NATO IIB. Mass: 243 kg (535 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 1. Completed Operations Date: 1984-06-01 . USAF Sat Cat: 4902 . COSPAR: 1971-009A. Apogee: 35,802 km (22,246 mi). Perigee: 35,772 km (22,227 mi). Inclination: 13.9000 deg. Period: 1,436.10 min. 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.
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