Delta 1913 no. 95

The Delta 1000 series used Castor 2 strap-ons and the Extended Long Tank core with MB-3 engine.

Manufacturer: Douglas. Launches: 8. Success Rate: 100.00%. First Launch Date: 1972-09-23. Last Launch Date: 1975-06-21. Launch data is: complete. Associated Spacecraft: AE, Geos, HS 333, IMP, OSO, RAE. Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,286 kg (287,231 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft). Flyaway Unit Cost $: 26.490 million. in: 1985 unit dollars.

3 stage vehicle consisting of 4 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201

Apogee: 900 km (550 mi). Liftoff Thrust: 1,863.000 kN (418,819 lbf). Total Mass: 110,000 kg (240,000 lb). Core Diameter: 2.44 m (8.00 ft). Total Length: 35.00 m (114.00 ft).

4 stage vehicle consisting of 6 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F + 1 x Star 37C

Payload: 600 kg (1,320 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 200,000 km (120,000 mi). Total Mass: 118,000 kg (260,000 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/MB-3 + 1 x Delta F

Apogee: 4,000 km (2,400 mi). Liftoff Thrust: 2,410.000 kN (541,780 lbf). Total Mass: 130,000 kg (280,000 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/MB-3 + 1 x Delta P /TR-201

Apogee: 550 km (340 mi). Liftoff Thrust: 2,410.000 kN (541,780 lbf). Total Mass: 130,000 kg (280,000 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/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37D

Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 2,410.000 kN (541,780 lbf). Total Mass: 130,000 kg (280,000 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/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37C

Liftoff Thrust: 2,287.500 kN (514,250 lbf). Total Mass: 130,286 kg (287,231 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 ELT. Gross Mass: 84,067 kg (185,336 lb). Empty Mass: 4,059 kg (8,948 lb). Thrust (vac): 1,030.208 kN (231,600 lbf). Isp: 296 sec. Burn time: 222 sec. Isp(sl): 262 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 22.40 m (73.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27. Other designations: Extended Length Tank Thor. 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).

1972 September 23 - 01:20 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17. Launch Pad: LC17B. Launch Vehicle: Delta 1000. Model: Delta 1604. LV Configuration: Delta 1604 579/D90.

• Explorer 47 Nation: USA. Program: Explorer. Payload: IMP H. Mass: 376 kg (828 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 201,100 km (124,900 mi). Apogee: 235,600 km (146,300 mi). Inclination: 17.20 deg. Period: 17,670.00 min. COSPAR: 1972-073A. USAF Sat Cat: 6197. Investigated cislunar radiation, Earth's magnetosphere, interplantary magnetic field. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Anik A1 Nation: Canada. Program: Anik. Payload: Telesat 1. Mass: 557 kg (1,227 lb). Class: Communications. Spacecraft: HS 333. Agency: Telesat. Perigee: 36,145 km (22,459 mi). Apogee: 36,247 km (22,522 mi). Inclination: 11.30 deg. Period: 1,457.10 min. COSPAR: 1972-090A. USAF Sat Cat: 6278. Completed Operations Date: 1982-07-15. Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 114 deg W in 1973-1976; over the Americas at 104 deg W in 1976-1982 As of 1 September 2001 located at 66.14 deg W drifting at 5.205 deg W per day. As of 2007 Mar 9 located at 107.03W drifting at 5.211W degrees per day.References: 1, 2, 5, 6.

• Anik A2 Nation: Canada. Program: Anik. Payload: Telesat 2. Mass: 272 kg (599 lb). Class: Communications. Spacecraft: HS 333. Agency: Telesat. Perigee: 35,886 km (22,298 mi). Apogee: 35,952 km (22,339 mi). Inclination: 13.70 deg. Period: 1,442.90 min. COSPAR: 1973-023A. USAF Sat Cat: 6437. Completed Operations Date: 1982-10-28. Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 109 deg W in 1973-1979; over the Americas at 106 deg W in 1979-1981; over the Americas at 114 deg W in 1981-1982 As of 26 August 2001 located at 0.59 deg E drifting at 1.690 deg W per day. As of 2007 Mar 9 located at 150.94E drifting at 1.684W degrees per day.References: 1, 2, 5, 6.

• Explorer 49 Nation: USA. Program: Explorer. Payload: RAE B. Mass: 328 kg (723 lb). Class: Astronomy. Spacecraft: RAE. Agency: NASA GSF. COSPAR: 1973-039A. USAF Sat Cat: 6686. Radio Astronomy Explorer; measured galactic, stellar radio noise. Lunar Orbit (Selenocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Explorer 50 Nation: USA. Program: Explorer. Payload: IMP J. Mass: 371 kg (817 lb). Class: Earth. Type: Magnetosphere. Spacecraft: IMP. Agency: NASA GSF. Perigee: 190,749 km (118,525 mi). Apogee: 244,361 km (151,838 mi). Inclination: 31.60 deg. Period: 17,576.70 min. COSPAR: 1973-078A. USAF Sat Cat: 6893. Solar flare and radiation monitor. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Explorer 51 Nation: USA. Program: Explorer. Payload: AE C. Mass: 658 kg (1,450 lb). Class: Earth. Type: Atmosphere. Spacecraft: AE. Agency: NASA GSF. Perigee: 155 km (96 mi). Apogee: 4,306 km (2,675 mi). Inclination: 68.10 deg. Period: 132.50 min. COSPAR: 1973-101A. USAF Sat Cat: 6977. Decay Date: 1978-12-12. Atmospheric Explorer; upper atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Geos 3 Nation: USA. Payload: GEOS C. Mass: 341 kg (751 lb). Class: Solar. Spacecraft: Geos. Agency: NASA Wal. Perigee: 817 km (507 mi). Apogee: 848 km (526 mi). Inclination: 115.00 deg. Period: 101.60 min. COSPAR: 1975-027A. USAF Sat Cat: 7734. Geodynamics Experimental Ocean Satellite. The mission of GEOS 3 (Geodynamics Experimental Ocean Satellite) was to provide the stepping stone between the National Geodetic Satellite Program (NGSP) and the Earth and Ocean Physics Application Program. It provided data to refine the geodetic and geophysical results of the NGSP and served as a test for new systems. A major achievment was the flight of a radar altimeter. Further mission objectives: intercomparison of tracking systems, investigation of solid-earth dynamic phenomena through precision laser tracking, refinement of orbit determination techniques, determination of interdatum ties and gravity models, and support of the calibration and position determination of NASA Spaceflight Tracking and Data Network (STDN) S-band tracking stations.References: 1, 2, 5, 6.

• OSO 8 Nation: USA. Payload: OSO I. Mass: 1,066 kg (2,350 lb). Class: Solar. Spacecraft: OSO. Agency: NASA GSF. Perigee: 539 km (334 mi). Apogee: 553 km (343 mi). Inclination: 32.90 deg. Period: 95.60 min. COSPAR: 1975-057A. USAF Sat Cat: 7970. Decay Date: 1986-07-09. Orbiting Solar Observatory. 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.