Titan 3C Media Gallery

Titan 3A with five segment solid motors. Man-rated design originally developed for Dynasoar spaceplane.

Manufacturer: Martin. Launches: 36. Failures: 5. Success Rate: 86.11%. First Launch Date: 1965-06-18. Last Launch Date: 1982-03-06. Launch data is: complete. LEO Payload: 13,100 kg (28,800 lb). to: 185 km Orbit. Payload: 3,000 kg (6,600 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Advanced Vela, ATS-6, Chalet, DODGE, DSCS II, DSP, ERS, Gemini, GGTS, IDCSP, IMEWS, LCS, LES, MOL, Oscar, OV1, OV2, OV4, OV5, Solrad, Tacsat, Dynasoar. Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 626,190 kg (1,380,510 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 42.00 m (137.00 ft). Launch Price $: 18.000 million. in: 1965 price dollars. Flyaway Unit Cost $: 66.700 million. in: 1985 unit dollars.

Post-MOL standardisation of Titan 3C, with man-rated systems removed, upgraded first stage engines, digital avionics, blowdown solid rocket motor thrust vector control in place of pressure-regulated system, simplified Transtage attitude control system.

Manufacturer: Martin. LEO Payload: 13,100 kg (28,800 lb). to: 185 km Orbit. Payload: 3,000 kg (6,600 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 626,190 kg (1,380,510 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 42.00 m (137.00 ft).

• Stage Number: 0. 2 x Stage: Titan UA1205 . Gross Mass: 226,233 kg (498,758 lb). Empty Mass: 33,798 kg (74,511 lb). Thrust (vac): 5,849.411 kN (1,315,000 lbf). Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 25.91 m (85.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1205. Status: Out of production.

• Stage Number: 1. 1 x Stage: Titan 3A-1. Gross Mass: 116,573 kg (256,999 lb). Empty Mass: 5,443 kg (11,999 lb). Thrust (vac): 2,339.760 kN (525,999 lbf). Isp: 302 sec. Burn time: 147 sec. Isp(sl): 250 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 22.28 m (73.09 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-11. Status: Out of production.

• Stage Number: 2. 1 x Stage: Titan 3A-2. Gross Mass: 29,188 kg (64,348 lb). Empty Mass: 2,653 kg (5,848 lb). Thrust (vac): 453.714 kN (101,999 lbf). Isp: 316 sec. Burn time: 205 sec. Isp(sl): 145 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 7.90 m (25.90 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-11. Status: Out of production.

• Stage Number: 3. 1 x Stage: Titan Transtage. Gross Mass: 12,247 kg (27,000 lb). Empty Mass: 1,950 kg (4,290 lb). Thrust (vac): 71.166 kN (15,999 lbf). Isp: 311 sec. Burn time: 440 sec. Isp(sl): 0 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 4.57 m (14.99 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: AJ10-138. Other designations: Transtage. Status: Out of production.

1959 June 1 - Launch Vehicle: Titan 1, Titan 2, Titan 3C.

• Dyna-Soar contractors Boeing and Martin selected. Nation: USA. Spacecraft: Dynasoar. The Dyna-Soar source selection board completed its evaluation of the proposals of the Boeing Airplane Company and the Martin Company. The board recommended the development of the Boeing glider but also favored the employment of the orbtal Titan C booster offered by Martin.

• Plans for advanced launch vehicles Nation: USA. Program: Apollo. The ARPA-NASA Booster Evaluation Committee appointed by Herbert F. York, DOD Director of Defense Research and Engineering, April 15, 1959, convened to review plans for advanced launch vehicles. A comparison of the Saturn (C-1) and the Titan-C boosters showed that the Saturn, with its substantially greater payload capacity, would be ready at least one year sooner than the Titan-C. In addition, the cost estimates on the Titan-C proved to be unrealistic. On the basis of the Advanced Research Projects Agency presentation, York agreed to continue the Saturn program but, following the meeting, began negotiations with NASA Administrator T. Keith Glennan to transfer the Army Ballistic Missile Agency (and, therefore, Saturn ) to NASA.References: 16.

• Martin to develop the Dyna-Soar booster airframe. Nation: USA. Spacecraft: Dynasoar. The Air Force gave the Martin Company responsibility for the development of the Dyna-Soar booster airframe.

• Aero-Jet to develop booster engines for the Dyna-Soar system. Spacecraft: Dynasoar. The Air Force authorized the Aero-Jet General Corporation to develop booster engines for the Dyna-Soar system.

• Titan II instead of Titan I for Dyna-Soar. Nation: USA. Spacecraft: Dynasoar. The Assistant Secretary of the Air Force requested ARDC to examine the feasiblity of employing Titan II instead of Titan I for Dyna-Soar suborbital flights.

• First segmented solid motor test. Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. Successful firing of a solid-propellant rocket motor using "building block" method was announced by NASA. References: 17.

• Martin C plan for Dyna-Soar Step IIA booster. Nation: USA. Spacecraft: Dynasoar. A Dyna-Soar technical evaluation board recommended the Martin C plan for a Step IIA booster.

• Phoenix A388 space launch system recommended for Dyna-Soar Step IIA booster. Nation: USA. Spacecraft: Dynasoar. The Dyna-Soar Directorate of the Space Systems Division recommended employment of the Phoenix A388 space launch system for the Step IIA booster.

• Solid motor segment test. Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. Segmented solid-propellent rocket engine fired by United Technology Corp. at Sunnyvale, generating over 200,000 pounds of thrust in 80-second firing. Developed under NASA contract, center section of engine contained over 55,000 pounds of propellant, the largest single piece yet manufactured in the United States.References: 18.

• Titan III selected as the space launch system for the Air Force. Nation: USA. Spacecraft: Dynasoar. The Department of Defense approved the Titan III as the space launch system for the Air Force.

• Working group on large launch vehicles Nation: USA. Program: Apollo. In a memorandum to D. Brainerd Holmes, Director, Office of Manned Space Flight (OMSF), Milton W. Rosen, Director of Launch Vehicles and Propulsion, OMSF, described the organization of a working group to recommend to the Director a large launch vehicle program which would meet the requirements of manned space flight and which would have broad and continuing national utility for other NASA and DOD programs. The group would include members from the NASA Office of Launch Vehicles and Propulsion (Rosen, Chairman, Richard B. Canright, Eldon W. Hall, Elliott Mitchell, Norman Rafel, Melvyn Savage, and Adelbert O. Tischler); from the Marshall Space Flight Center (William A. Mrazek, Hans H. Maus, and James B. Bramlet); and from the NASA Office of Spacecraft and Flight Missions (John H. Disher). (David M. Hammock of MSC was later added to the group.) The principal background material to be used by the group would consist of reports of the Large Launch Vehicle Planning Group (Golovin Committee), the Fleming Committee, the Lundin Committee, the Heaton Committee, and the Debus-Davis Committee. Some of the subjects the group would be considering were:
  1. an assessment of the problems involved in orbital rendezvous,
  2. an evaluation of intermediate vehicles (Saturn C-3, C-4, and C-5),
  3. an evaluation of Nova-class vehicles,
  4. an assessment of the future course of large solid-fuel rocket motor development,
  5. an evaluation of the utility of the Titan III for NASA missions, and
  6. an evaluation of the realism of the spacecraft development program (schedules, weights, performances).
  Rosen set November 20 as a target date for a recommended program.References: 16.

• Recommendation that the weapon system of the Titan II, with minimal modifications, be approved for the Mercury Mark II rendezvous mission. Spacecraft: Gemini. On the basis of a report of the Large Launch Vehicle Planning Group, Robert C. Seamans, Jr., NASA Associate Administrator, and John H. Rubel, Department of Defense Deputy Director for Defense Research and Engineering, recommended to Secretary of Defense Robert S. McNamara that the weapon system of the Titan II, with minimal modifications, be approved for the Mercury Mark II rendezvous mission. The planning group had first met in August 1961 to survey the Nation's launch vehicle program and was recalled in November to consider Titan II, Titan II-1/2, and Titan III. On November 16, McNamara and NASA Administrator James E. Webb had also begun discussing the use of Titan II.

• First test of UTC 1205 rocket motors. Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. Solid-propellent rocket motor generating nearly 500,000 pounds of thrust was fired in a static test of 80-second duration by United Technology Corp. at Sunnyvale, Calif., under USAF contract. References: 18.

• USAF announces Titan III for Dynasoar Nation: USA. Class: Manned. Type: Spaceplane. Spacecraft: Dynasoar. With continued weight growth USAF announces Titan III to be developed for Dynasoar orbital missions. References: 26.

• US Department of Defense announced Titan III launch vehicle. Nation: USA. The Department of Defense announced plans to develop a Titan III launch vehicle powered by both solid and liquid fuel rocket motors with a total thrust of over 11 million newtons (2.5 million Ibs). .Scheduled to become operational in 1965, the Titan III would be used to launch the Air Force's X-20 (Dyna Soar) manned spacecraft, as well as heavy unmanned military satellites. Martin Marietta Corporation had been selected as prime contractor for the project, at an estimated cost of between $500 million and $1 billion. At a news conference the following day, Defense Secretary Robert S. McNamara cited the Titan III as a major step toward overtaking the Soviet Union in various phases of military space development.

• X-20 flight dates compatible with Titan IIIC schedules. Nation: USA. Spacecraft: Dynasoar. The Dyna-Soar program completed a system package program, which made the X-20 flight dates compatible with projected Titan IIIC schedules.

• Titan III research and development begun. Nation: USA. Spacecraft: Dynasoar. Following Congressional approval of development funding, Air Force headquarters issued System Program Directive 9, authorizing research and development of Titan III, System 624A. By this time the funding and schedule for development of the Titan IIIC booster was the pacing item in the Dynasoar project. The launch schedule had to be revised and reduced yet once again. Delivery of the first Dyna-Soar was to be made by October 1964 and first orbital launch by the end of 1965. While the first glider test would be 14 months later than the original July 1957 schedule, the first orbital flight was expected six months earlier.

• McNamara requests review of the Titan III nd Gemini programs. Nation: USA. Spacecraft: Dynasoar, Gemini. The Secretary of Defense directed a review of the Titan III program and the Gemini program of NASA.

• McNamara briefed on Titan III and Dyna-Soar. Nation: USA. Spacecraft: Dynasoar. Secretary McNamara was briefed on the Titan III and Dyna-Soar programs at the Martin Company facilities in Denver, Colorado.

• Three firms received authorization to begin work on space station studies. Nation: USA. Spacecraft: MOL. Secretary of the Air Force Eugene M. Zuckert announced that three firms, Douglas Aircraft Company, General Electric Company, and The Martin Company, had received authorization to begin work on space station studies. Zuckert predicted also that the Titan III would be test-flown that summer and would launch the Manned Orbiting Laboratory sometime in 1967 or 1968.

• Titan 3C Transtage 5 Nation: USA. Payload: Lead Ballast / Transtage 5. Mass: 9,694 kg (21,371 lb). Agency: USAF. Perigee: 168 km (104 mi). Apogee: 191 km (118 mi). Inclination: 32.10 deg. Period: 88.10 min. COSPAR: 1965-047A. USAF Sat Cat: 1412. Decay Date: 1965-06-29. Launch vehicle test. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• LCS 2 Nation: USA. Payload: OV2-01 / Transtage 4. Class: Calibration. Spacecraft: LCS. Agency: USAF. Perigee: 730 km (450 mi). Apogee: 785 km (487 mi). Inclination: 32.30 deg. Period: 99.98 min. COSPAR: 1965-082A. USAF Sat Cat: 1624. Decay Date: 1965-10-15. Dual launch with OV2-1; upper stage broke up. References: 5, 126.

• OV2-01 Nation: USA. Mass: 170 kg (370 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV2. Agency: -. Perigee: 708 km (439 mi). Apogee: 791 km (491 mi). Inclination: 32.60 deg. Period: 99.80 min. COSPAR: 1965-082B. USAF Sat Cat: 1624. Decay Date: 1972-07-27. Dual launch with LCS 2; upper stage broke up. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• LCS 2 Nation: USA. Spacecraft: OV2. Agency: USAF. COSPAR: 1965-082xx. References: 279.

• Transtage 4 Nation: USA. Spacecraft: OV2. Agency: USAF. COSPAR: 1965-082xx. USAF Sat Cat: 1624. Decay Date: 1972-07-27. References: 279.

• OV2-03 Nation: USA. Mass: 193 kg (425 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV2. Agency: USAF. Perigee: 321 km (199 mi). Apogee: 22,846 km (14,195 mi). Inclination: 26.80 deg. Period: 399.30 min. COSPAR: 1965-108A. USAF Sat Cat: 1863. Decay Date: 1975-08-17. Upper stage separation failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• LES 4 Nation: USA. Mass: 52 kg (114 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 189 km (117 mi). Apogee: 33,632 km (20,897 mi). Inclination: 26.60 deg. Period: 589.20 min. COSPAR: 1965-108B. USAF Sat Cat: 1870. Decay Date: 1977-08-01. Lincoln Experimental Satellite; experimental commsat; transmitted in X-band. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Oscar 4 Nation: USA. Program: Oscar. Mass: 13 kg (28 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: OSCAR. Perigee: 162 km (100 mi). Apogee: 33,549 km (20,846 mi). Inclination: 26.80 deg. Period: 587.50 min. COSPAR: 1965-108C. USAF Sat Cat: 1902. Decay Date: 1976-04-12. OSCAR IV was launched piggyback with three United States Air Force satellites. The launch vehicle had a partial failure and placed the spacecraft in a low orbit preventing widespread amateur use. Orbit 29120 x 168 km. Inclination 26.8 degrees. Period 587.5 minutes. Weight 18.1 kg. Four monopole antennas. OSCAR IV was built by the TRW Radio Club of Redondo Beach, California. It had a 3 Watt 10 kHz wide linear transponder (144 MHz uplink and 432 MHz downlink). In operation until March 16, 1966. Re-entry April 12, 1976. Total operation 85 days. OSCAR IV provided the first US-Soviet amateur link.References: 2, 5, 6.

• LES 3 Nation: USA. Mass: 16 kg (35 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 267 km (165 mi). Apogee: 4,829 km (3,000 mi). Inclination: 26.50 deg. Period: 139.90 min. COSPAR: 1965-108D. USAF Sat Cat: 1941. Decay Date: 1968-04-06. Radio signal source for commsat tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Transtage 8 Nation: USA. Spacecraft: OV2. Agency: USAF AFSC. COSPAR: 1965-108xx. USAF Sat Cat: 1863. Decay Date: 1975-08-17. References: 279.

• Start of construction (site preparation) for SLC-6 Nation: USA. Class: Manned. Type: Space station. Spacecraft: MOL. Start of construction (site preparation) for Space Launch Complex 6 facilities at former Sudden Ranch property. References: 88.

• GGTS 1 Nation: USA. Mass: 47 kg (103 lb). Class: Technology. Type: Gravity gradient. Spacecraft: GGTS. Agency: USAF. Perigee: 33,663 km (20,917 mi). Apogee: 33,858 km (21,038 mi). Inclination: 4.20 deg. Period: 1,334.00 min. COSPAR: 1966-053A. USAF Sat Cat: 2207. Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-1 Nation: USA. Payload: IDCSP 1. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,656 km (20,912 mi). Apogee: 33,888 km (21,056 mi). Inclination: 8.30 deg. Period: 1,334.40 min. COSPAR: 1966-053B. USAF Sat Cat: 2215. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-2 Nation: USA. Payload: IDCSP 2. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,657 km (20,913 mi). Apogee: 33,923 km (21,078 mi). Inclination: 4.90 deg. Period: 1,335.30 min. COSPAR: 1966-053C. USAF Sat Cat: 2216. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-3 Nation: USA. Payload: IDCSP 3. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,669 km (20,920 mi). Apogee: 33,955 km (21,098 mi). Inclination: 8.30 deg. Period: 1,336.40 min. COSPAR: 1966-053D. USAF Sat Cat: 2217. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-4 Nation: USA. Payload: IDCSP 4. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,694 km (20,936 mi). Apogee: 34,017 km (21,137 mi). Inclination: 8.00 deg. Period: 1,338.60 min. COSPAR: 1966-053E. USAF Sat Cat: 2218. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-5 Nation: USA. Payload: IDCSP 5. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,712 km (20,947 mi). Apogee: 34,093 km (21,184 mi). Inclination: 8.90 deg. Period: 1,340.90 min. COSPAR: 1966-053F. USAF Sat Cat: 2219. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-6 Nation: USA. Payload: IDCSP 6. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,707 km (20,944 mi). Apogee: 34,215 km (21,260 mi). Inclination: 8.70 deg. Period: 1,343.90 min. COSPAR: 1966-053G. USAF Sat Cat: 2220. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 1-7 Nation: USA. Payload: IDCSP 7. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,711 km (20,947 mi). Apogee: 34,359 km (21,349 mi). Inclination: 5.00 deg. Period: 1,347.60 min. COSPAR: 1966-053H. USAF Sat Cat: 2221. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP (8) ... IDCSP (14) Nation: USA. Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: U.S. Air Force. COSPAR: F660826A. Decay Date: 1966-08-26. 8 satellites, each weighing 45 kg. References: 5, 126.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826B. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826C. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826D. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826E. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826F. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826G. References: 279.

• IDCSP Nation: USA. Payload: IDCSP. Spacecraft: IDCSP. Agency: USAF. COSPAR: F660826H. References: 279.

• OV4-03 Nation: USA. Class: Technology. Spacecraft: OV4. Agency: USAF. Perigee: 298 km (185 mi). Apogee: 305 km (189 mi). Inclination: 32.80 deg. Period: 90.40 min. COSPAR: 1966-099A. USAF Sat Cat: 2524. Decay Date: 1967-01-09. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV4-01R Nation: USA. Class: Technology. Spacecraft: OV4. Agency: USAF. Perigee: 289 km (179 mi). Apogee: 292 km (181 mi). Inclination: 32.80 deg. Period: 90.30 min. COSPAR: 1966-099B. USAF Sat Cat: 2526. Decay Date: 1967-01-05. Whispering gallery experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV1-06S Nation: USA. Mass: 202 kg (445 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV1. Agency: USAF. Perigee: 287 km (178 mi). Apogee: 290 km (180 mi). Inclination: 32.80 deg. Period: 90.30 min. COSPAR: 1966-099C. USAF Sat Cat: 2527. Decay Date: 1966-12-31. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV4-01T Nation: USA. Mass: 109 kg (240 lb). Class: Technology. Spacecraft: OV4. Agency: USAF. Perigee: 289 km (179 mi). Apogee: 317 km (196 mi). Inclination: 32.80 deg. Period: 90.60 min. COSPAR: 1966-099D. USAF Sat Cat: 2528. Decay Date: 1967-01-11. Whispering gallery experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Gemini B Nation: USA. Payload: Gemini SC2. Mass: 1,800 kg (3,900 lb). Class: Manned. Type: Spacecraft. Spacecraft: Gemini. Agency: U.S. Air Force. COSPAR: 1966-099xx. During the ascent to orbit, the Gemini capsule atop the MOL Cannister was ejected and made a suborbital reentry and splashdown in the Atlantic Ocean. The spacecraft was the Gemini 2 reentry module, reused to test reentry with hatch cut into the heat shield. The capsule was successfully recovered and it was found that the reentry actually melted hatch shut, indicating that the design was valid for MOL.References: 22, 279.

• MOL Mockup Nation: USA. Payload: MOL Mockup (Titan fuel tank). Mass: 9,680 kg (21,340 lb). Class: Manned. Type: Space station. Spacecraft: MOL. Agency: U.S. Air Force. COSPAR: 1966-099xx. This modified Titan 2 propellant tank represented the MOL station itself. It allowed study of the aerodynamic loads associated with launching the MOL into orbit and validated the very long length to diameter core represented by the MOL/Titan 3M configuration. It is possible certain prototype MOL equipment was flown as well.References: 22, 279.

• IDCSP 2-1 Nation: USA. Payload: IDCSP 8. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,518 km (20,827 mi). Apogee: 33,829 km (21,020 mi). Inclination: 8.70 deg. Period: 1,329.50 min. COSPAR: 1967-003A. USAF Sat Cat: 2645. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-2 Nation: USA. Payload: IDCSP 9. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,533 km (20,836 mi). Apogee: 33,830 km (21,020 mi). Inclination: 8.50 deg. Period: 1,329.90 min. COSPAR: 1967-003B. USAF Sat Cat: 2649. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-3 Nation: USA. Payload: IDCSP 10. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,549 km (20,846 mi). Apogee: 33,843 km (21,029 mi). Inclination: 8.30 deg. Period: 1,330.70 min. COSPAR: 1967-003C. USAF Sat Cat: 2650. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-4 Nation: USA. Payload: IDCSP 11. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,579 km (20,864 mi). Apogee: 33,873 km (21,047 mi). Inclination: 8.50 deg. Period: 1,332.10 min. COSPAR: 1967-003D. USAF Sat Cat: 2651. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-5 Nation: USA. Payload: IDCSP 12. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,599 km (20,877 mi). Apogee: 33,935 km (21,086 mi). Inclination: 8.50 deg. Period: 1,334.20 min. COSPAR: 1967-003E. USAF Sat Cat: 2652. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-6 Nation: USA. Payload: IDCSP 13. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,631 km (20,897 mi). Apogee: 33,995 km (21,123 mi). Inclination: 11.80 deg. Period: 1,336.50 min. COSPAR: 1967-003F. USAF Sat Cat: 2653. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-7 Nation: USA. Payload: IDCSP 14. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,622 km (20,891 mi). Apogee: 34,127 km (21,205 mi). Inclination: 8.60 deg. Period: 1,339.50 min. COSPAR: 1967-003G. USAF Sat Cat: 2654. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 2-8 Nation: USA. Payload: IDCSP 15. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,666 km (20,919 mi). Apogee: 34,224 km (21,265 mi). Inclination: 8.60 deg. Period: 1,343.10 min. COSPAR: 1967-003H. USAF Sat Cat: 2655. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Vela 7 Nation: USA. Payload: Vela 4A. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 108,948 km (67,697 mi). Apogee: 112,627 km (69,983 mi). Inclination: 32.10 deg. Period: 6,652.10 min. COSPAR: 1967-040A. USAF Sat Cat: 2765. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Vela 8 Nation: USA. Payload: Vela 4B. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 107,372 km (66,717 mi). Apogee: 114,578 km (71,195 mi). Inclination: 33.10 deg. Period: 6,668.10 min. COSPAR: 1967-040B. USAF Sat Cat: 2766. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• ERS 18 Nation: USA. Mass: 9.00 kg (19.80 lb). Class: Earth. Type: Magnetosphere. Spacecraft: ERS. Agency: USAF. Perigee: 8,991 km (5,586 mi). Apogee: 110,842 km (68,873 mi). Inclination: 0.00 deg. Period: 2,831.30 min. COSPAR: 1967-040C. USAF Sat Cat: 2767. Radiation research. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV5-03 Nation: USA. Payload: ERS 20. Mass: 9.00 kg (19.80 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 8,604 km (5,346 mi). Apogee: 111,229 km (69,114 mi). Inclination: 32.80 deg. Period: 2,829.60 min. COSPAR: 1967-040D. USAF Sat Cat: 2768. Radiation research; deployed ERS 20. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV5-01 Nation: USA. Payload: ERS 27. Mass: 9.00 kg (19.80 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 8,979 km (5,579 mi). Apogee: 110,746 km (68,814 mi). Inclination: 32.80 deg. Period: 2,827.80 min. COSPAR: 1967-040E. USAF Sat Cat: 2769. Materials research; deployed ERS 27. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 3-1 Nation: USA. Payload: IDCSP 16. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,030 km (20,520 mi). Apogee: 33,515 km (20,825 mi). Inclination: 11.90 deg. Period: 1,309.60 min. COSPAR: 1967-066A. USAF Sat Cat: 2862. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 3-2 Nation: USA. Payload: IDCSP 17. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,046 km (20,533 mi). Apogee: 33,517 km (20,826 mi). Inclination: 11.90 deg. Period: 1,310.00 min. COSPAR: 1967-066B. USAF Sat Cat: 2863. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 3-3 Nation: USA. Payload: IDCSP 18. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,079 km (20,554 mi). Apogee: 33,547 km (20,845 mi). Inclination: 11.90 deg. Period: 1,311.60 min. COSPAR: 1967-066C. USAF Sat Cat: 2864. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 3-4 Nation: USA. Payload: IDCSP 19/DATS. Mass: 68 kg (149 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,145 km (20,595 mi). Apogee: 33,560 km (20,850 mi). Inclination: 11.90 deg. Period: 1,313.50 min. COSPAR: 1967-066D. USAF Sat Cat: 2865. Antenna tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• LES 5 Nation: USA. Mass: 194 kg (427 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 33,196 km (20,626 mi). Apogee: 33,609 km (20,883 mi). Inclination: 12.00 deg. Period: 1,316.00 min. COSPAR: 1967-066E. USAF Sat Cat: 2866. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• DODGE 1 Nation: USA. Mass: 102 kg (224 lb). Class: Technology. Type: Gravity gradient. Spacecraft: DODGE. Agency: USN NASC. Perigee: 33,257 km (20,664 mi). Apogee: 33,670 km (20,920 mi). Inclination: 12.00 deg. Period: 1,319.10 min. COSPAR: 1967-066F. USAF Sat Cat: 2867. Gravity gradient experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-1 Nation: USA. Payload: IDCSP 20. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,725 km (20,955 mi). Apogee: 33,850 km (21,030 mi). Inclination: 11.90 deg. Period: 1,335.20 min. COSPAR: 1968-050A. USAF Sat Cat: 3284. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-2 Nation: USA. Payload: IDCSP 21. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,724 km (20,955 mi). Apogee: 33,863 km (21,041 mi). Inclination: 7.40 deg. Period: 1,335.50 min. COSPAR: 1968-050B. USAF Sat Cat: 3285. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-3 Nation: USA. Payload: IDCSP 22. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,722 km (20,953 mi). Apogee: 33,901 km (21,065 mi). Inclination: 9.40 deg. Period: 1,336.40 min. COSPAR: 1968-050C. USAF Sat Cat: 3286. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-4 Nation: USA. Payload: IDCSP 23. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,743 km (20,966 mi). Apogee: 33,939 km (21,088 mi). Inclination: 9.20 deg. Period: 1,337.90 min. COSPAR: 1968-050D. USAF Sat Cat: 3287. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-5 Nation: USA. Payload: IDCSP 24. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,721 km (20,953 mi). Apogee: 34,035 km (21,148 mi). Inclination: 7.40 deg. Period: 1,339.60 min. COSPAR: 1968-050E. USAF Sat Cat: 3288. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-6 Nation: USA. Payload: IDCSP 25. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,739 km (20,964 mi). Apogee: 34,118 km (21,199 mi). Inclination: 9.40 deg. Period: 1,342.20 min. COSPAR: 1968-050F. USAF Sat Cat: 3289. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-7 Nation: USA. Payload: IDCSP 26. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,721 km (20,953 mi). Apogee: 34,256 km (21,285 mi). Inclination: 7.50 deg. Period: 1,345.20 min. COSPAR: 1968-050G. USAF Sat Cat: 3290. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IDCSP 4-8 Nation: USA. Payload: IDCSP 27. Mass: 45 kg (99 lb). Class: Communications. Type: Military. Spacecraft: IDCSP. Agency: USAF. Perigee: 33,752 km (20,972 mi). Apogee: 34,442 km (21,401 mi). Inclination: 7.70 deg. Period: 1,350.60 min. COSPAR: 1968-050H. USAF Sat Cat: 3291. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV2-05 Nation: USA. Mass: 204 kg (449 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV2. Agency: USAF. Perigee: 35,113 km (21,818 mi). Apogee: 35,745 km (22,210 mi). Inclination: 12.30 deg. Period: 1,417.90 min. COSPAR: 1968-081A. USAF Sat Cat: 3428. Completed Operations Date: 1968-09-01. Environmental research. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). As of 22 August 2001 located at 128.37 deg E drifting at 4.618 deg E per day. As of 2007 Feb 27 located at 91.48E drifting at 4.631E degrees per day.References: 1, 2, 5, 6.

• OV5-02 Nation: USA. Payload: ERS 28. Mass: 10 kg (22 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 184 km (114 mi). Apogee: 35,786 km (22,236 mi). Inclination: 26.40 deg. Period: 630.80 min. COSPAR: 1968-081B. USAF Sat Cat: 3429. Decay Date: 1971-02-15. Particle radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV5-04 Nation: USA. Payload: ERS 21. Mass: 13 kg (28 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 35,775 km (22,229 mi). Apogee: 35,786 km (22,236 mi). Inclination: 3.00 deg. Period: 1,435.80 min. COSPAR: 1968-081C. USAF Sat Cat: 3430. Completed Operations Date: 1968-09-01. Examined heat transfer in liquids in zero-g. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Last known longitude (19 July 1995) 138.85 deg E drifting at 0.103 deg W per day. References: 1, 2, 5, 6.

• LES 6 Nation: USA. Mass: 163 kg (359 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 35,776 km (22,230 mi). Apogee: 35,839 km (22,269 mi). Inclination: 12.80 deg. Period: 1,437.20 min. COSPAR: 1968-081D. USAF Sat Cat: 3431. Completed Operations Date: 1976-01-01. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Atlantic Ocean at 38 deg W in 1968-1975 As of 26 August 2001 located at 61.90 deg W drifting at 0.101 deg E per day. As of 2007 Mar 9 located at 73.59W drifting at 0.201E degrees per day.References: 1, 2, 5, 6.

• Tacsat 1 Nation: USA. Mass: 730 kg (1,600 lb). Class: Technology. Type: Comsat. Spacecraft: Tacsat. Agency: USAF. Perigee: 35,939 km (22,331 mi). Apogee: 36,044 km (22,396 mi). Inclination: 1.00 deg. Period: 1,446.60 min. COSPAR: 1969-013A. USAF Sat Cat: 3691. Completed Operations Date: 1977-01-01. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Americas at 107 deg W in 1969?-1970; over the Pacific Ocean 173 deg W in 1970; over the Pacific Ocean 179 deg W in 1971-1972; over the Pacific Ocean170 deg E in 1972 Last known longitude (9 June 1995) 176.44 deg E drifting at 0.150 deg E per day.References: 1, 2, 5, 6.

• OV5-05 Nation: USA. Payload: ERS 29. Mass: 259 kg (570 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 59,630 km (37,050 mi). Apogee: 69,130 km (42,950 mi). Inclination: 33.00 deg. Period: 3,121.90 min. COSPAR: 1969-046A. USAF Sat Cat: 3950. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV5-06 Nation: USA. Payload: ERS 26. Mass: 259 kg (570 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 59,540 km (36,990 mi). Apogee: 69,022 km (42,888 mi). Inclination: 33.60 deg. Period: 3,115.40 min. COSPAR: 1969-046B. USAF Sat Cat: 3951. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• OV5-09 Nation: USA. Mass: 11 kg (24 lb). Class: Earth. Type: Magnetosphere. Spacecraft: OV5. Agency: USAF. Perigee: 59,543 km (36,998 mi). Apogee: 69,011 km (42,881 mi). Inclination: 33.50 deg. Period: 3,115.10 min. COSPAR: 1969-046C. USAF Sat Cat: 3952. VLF plasma wave detection. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Vela 9 Nation: USA. Payload: Vela 5A. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 77,082 km (47,896 mi). Apogee: 145,638 km (90,495 mi). Inclination: 61.60 deg. Period: 6,700.90 min. COSPAR: 1969-046D. USAF Sat Cat: 3954. Decay Date: 1992-12-31. Solar flare particle detectors. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Vela 10 Nation: USA. Payload: Vela 5B. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 72,080 km (44,780 mi). Apogee: 150,633 km (93,598 mi). Inclination: 61.00 deg. Period: 6,700.70 min. COSPAR: 1969-046E. USAF Sat Cat: 3955. Decay Date: 1992-12-31. Radiation, low-energy particle, solar flare data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• MOL Program cancelled Nation: USA. Class: Manned. Type: Space station. Spacecraft: MOL. Department of Defense announced cancellation of the planned Manned Orbiting Laboratory (MOL) program from Space Launch Complex 6 at Vandenberg AFB. The cancellation was expected to save $ 1.5 billion of the projected total $ 3.0 billion program costs. The SLC-6 launch facility at Vandenberg, 90% complete, would be finished and mothballed. MOL reconnaisance systems useful on unmanned satellites would be completed for a total cost of $ 225 million. Ten thousand aerospace workers were laid off as a result of the cancellation.References: 26.

• Vela 12 Nation: USA. Payload: Vela 6A. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 101,261 km (62,920 mi). Apogee: 121,227 km (75,326 mi). Inclination: 61.20 deg. Period: 6,691.00 min. COSPAR: 1970-027A. USAF Sat Cat: 4366. Decay Date: 1992-12-31. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• Vela 11 Nation: USA. Payload: Vela 6B. Mass: 317 kg (698 lb). Class: Surveillance. Type: Nuclear Detection. Spacecraft: Advanced Vela. Agency: USAF. Perigee: 103,570 km (64,350 mi). Apogee: 119,313 km (74,137 mi). Inclination: 57.40 deg. Period: 6,707.90 min. COSPAR: 1970-027B. USAF Sat Cat: 4368. Decay Date: 1992-12-31. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IMEWS 1 Nation: USA. Payload: DSP Phase 1 s/n 1. Mass: 900 kg (1,980 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 25,840 km (16,050 mi). Apogee: 36,128 km (22,448 mi). Inclination: 16.40 deg. Period: 1,197.90 min. COSPAR: 1970-093A. USAF Sat Cat: 4630. Completed Operations Date: 1973-12-31. First generation geosynchronous ballistic missile launch detection satellite; placed in incorrect subsynchronous orbit. One account claimed that it exhausted its propellant before it could be put into operation, but a 2007service history chart showed that is was considered operational for three years, well beyond its planned life.References: 1, 2, 5, 6, 127.

• IMEWS 2 Nation: USA. Payload: DSP Phase 1 s/n 2. Mass: 900 kg (1,980 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 36,156 km (22,466 mi). Apogee: 36,527 km (22,696 mi). Inclination: 10.50 deg. Period: 1,464.60 min. COSPAR: 1971-039A. USAF Sat Cat: 5204. Completed Operations Date: 1983-01-10. First generation geosynchronous ballistic missile launch detection satellite. First completely sucessful operational satellite, remained in service for nearly 12 years. Positioned over the Indian Ocean at 75 deg E in 1979-1982. As of 1983 May 11 located at 73.28W drifting at 7.684W degrees per day.References: 1, 2, 5, 6, 127.

• DSCS II-01 Nation: USA. Program: DSCS. Payload: DSCS II F-1. Mass: 520 kg (1,140 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 35,765 km (22,223 mi). Apogee: 35,815 km (22,254 mi). Inclination: 13.80 deg. Period: 1,436.30 min. COSPAR: 1971-095A. USAF Sat Cat: 5587. Completed Operations Date: 1979-05-01. Defense Satellite Communications System. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Americas at 106 deg W in 1972-?; over the Americas at 81 deg W in 1977-1979; over the Americas at 100-110 deg W in drift 1979-1998 As of 1 September 2001 located at 103.05 deg W drifting at 0.044 deg W per day. As of 2007 Mar 9 located at 110.10W drifting at 0.035W degrees per day.References: 1, 2, 5, 6.

• DSCS II-02 Nation: USA. Program: DSCS. Payload: DSCS II F-2. Mass: 520 kg (1,140 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 35,819 km (22,256 mi). Apogee: 35,824 km (22,259 mi). Inclination: 13.60 deg. Period: 1,437.90 min. COSPAR: 1971-095B. USAF Sat Cat: 5588. Completed Operations Date: 1972-01-01. Defense Satellite Communications System. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit over the Americas at 112 deg W in 1972. As of 30 August 2001 located at 146.34 deg E drifting at 0.101 deg W per day. As of 2007 Mar 5 located at 36.33W drifting at 0.201E degrees per day.References: 1, 2, 5, 6.

• IMEWS 3 Nation: USA. Payload: DSP Phase 1 s/n 3. Mass: 900 kg (1,980 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,416 km (22,006 mi). Apogee: 35,962 km (22,345 mi). Inclination: 0.20 deg. Period: 1,429.90 min. COSPAR: 1972-010A. USAF Sat Cat: 5851. Completed Operations Date: 1981-08-03. First generation geosynchronous ballistic missile launch detection satellite, remained in service for over nine years. Positioned over the Pacific Ocean at 165 deg E in 1979-1980. As of 2003 Mar 5 located at 74.63E drifting at 0.712W degrees per day. References: 1, 2, 5, 6, 127.

• IMEWS 4 Nation: USA. Payload: DSP Phase 1 s/n 4. Mass: 900 kg (1,980 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,777 km (22,230 mi). Apogee: 35,786 km (22,236 mi). Inclination: 0.30 deg. Period: 1,435.90 min. COSPAR: 1973-040A. USAF Sat Cat: 6691. Completed Operations Date: 1980-11-01. First generation geosynchronous ballistic missile launch detection satellite, remained in service for over seven years. Positioned in geosynchronous orbit over the Indian Ocean at 75E in 1973; over the Americas at 105 deg W in 1979-1980. As of 1983 Jan 3 located at 73.21W drifting at 1.648W degrees per day.References: 1, 2, 5, 6, 127.

• DSCS II-03 Nation: USA. Program: DSCS. Payload: DSCS II F-3. Mass: 566 kg (1,247 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 36,413 km (22,625 mi). Apogee: 36,661 km (22,780 mi). Inclination: 13.90 deg. Period: 1,474.60 min. COSPAR: 1973-100A. USAF Sat Cat: 6973. Completed Operations Date: 1982-08-01. Defense Satellite Communications System; 13 deg W. 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 13 deg W in 1974-1977; over the Atlantic Ocean 57-66 deg W in 1977-1979 As of 3 September 2001 located at 104.01 deg E drifting at 9.429 deg W per day. As of 2007 Mar 9 located at 148.24W drifting at 9.427W degrees per day.References: 1, 2, 5, 6.

• DSCS II-04 Nation: USA. Program: DSCS. Payload: DSCS II F-4. Mass: 566 kg (1,247 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 36,300 km (22,500 mi). Apogee: 36,837 km (22,889 mi). Inclination: 13.50 deg. Period: 1,476.30 min. COSPAR: 1973-100B. USAF Sat Cat: 6974. Completed Operations Date: 1993-12-20. Defense Satellite Communications System; 175 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 175 deg E in 1974-1977; over the Indian Ocean 65 deg E in 1977-1980; over the Indian Ocean 60-61 deg E in 1980-1984; over the Indian Ocean 66 deg E in 1984-1987; over the Americas at 56-62 deg W in 1989-1993 As of 5 September 2001 located at 138.02 deg W drifting at 9.919 deg W per day. As of 2007 Mar 3 located at 146.85E drifting at 9.914W degrees per day.References: 1, 2, 5, 6.

• ATS 6 Nation: USA. Program: ATS. Payload: ATS F. Mass: 930 kg (2,050 lb). Class: Technology. Type: Comsat. Spacecraft: ATS-6. Agency: NASA GSF. Perigee: 35,184 km (21,862 mi). Apogee: 35,444 km (22,023 mi). Inclination: 13.10 deg. Period: 1,412.00 min. COSPAR: 1974-039A. USAF Sat Cat: 7318. Completed Operations Date: 1979-08-02. Application Technology Satellite; experimental communications satellite. The purpose of the ATS-6 flight experiment was to demonstrate north-south stationkeeping of a geosynchronous satellite using two cesium ion engine systems. Thruster development tests included a life test of 2614 hours and 471 cycles. Thruster input power was 0.15 kW, which resulted in a thrust of 4.5 mN at a specific impulse of 2500 s. One of the ion engines operated for about one hour and the other for 92 hours. Both of the engines failed to provide thrust on restart due to discharge chamber cesium flooding. The feed system flooding problem caused overloading of the discharge and high voltage power supplies. This failure mechanism was verified through a series of ground tests. However engine operation demonstrated an absence of EMI related to spacecraft systems, verified predictions of spacecraft potential with engines operating, and demonstrated compatibility with the spacecraft's star tracker. It was found that the ion engines or just the neutralizer could discharge large negative spacecraft potentials at all times. Positioned in geosynchronous orbit over the Americas at 94 deg W in 1974-1975; over the Indian Ocean 35 deg E in 1975-1976; over the Americas at 140 deg W in 1976-1979. As of 2 September 2001 located at 172.56 deg W drifting at 6.144 deg E per day. As of 2007 Mar 8 located at 29.12W drifting at 6.125E degrees per day.References: 1, 2, 5, 6.

• DSCS II-05 Nation: USA. Program: DSCS. Payload: DSCS II F-5. Mass: 566 kg (1,247 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 160 km (90 mi). Apogee: 256 km (159 mi). Inclination: 28.60 deg. Period: 88.60 min. COSPAR: 1975-040A. USAF Sat Cat: 7807. Decay Date: 1975-05-26. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• DSCS II-06 Nation: USA. Program: DSCS. Payload: DSCS II F-6. Mass: 566 kg (1,247 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 160 km (90 mi). Apogee: 256 km (159 mi). Inclination: 28.60 deg. Period: 88.60 min. COSPAR: 1975-040B. USAF Sat Cat: 7808. Decay Date: 1975-05-26. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1, 2, 5, 6.

• IMEWS 5 Nation: USA. Payload: DSP Phase 2 s/n 7. Mass: 1,040 kg (2,290 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,671 km (22,164 mi). Apogee: 35,785 km (22,235 mi). Inclination: 3.00 deg. Period: 1,436.00 min. COSPAR: 1975-118A. USAF Sat Cat: 8482. Completed Operations Date: 1987-12-31. Second generation geosynchronous ballistic missile launch detection satellite, remained in service for over twelve years. As of 1982 Dec 16 located at 34.61E drifting at 0.823E degrees per day. References: 1, 2, 5, 6, 127.

• LES 8 Nation: USA. Mass: 454 kg (1,000 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 35,728 km (22,200 mi). Apogee: 35,835 km (22,266 mi). Inclination: 11.40 deg. Period: 1,435.80 min. COSPAR: 1976-023A. USAF Sat Cat: 8746. Completed Operations Date: 1992-01-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication. Also tested pulsed plasma engines. Positioned in geosynchronous orbit over the Atlantic Ocean at 1976-77; over the Americas at 106-110 deg W in 1978-1986; over the Atlantic Ocean 60-70 deg W in 1987-1991;over the Americas at 94-106 deg W in 1991-1992. As of 6 September 2001 located at 105.16 deg W drifting at 0.010 deg E per day. As of 2007 Mar 9 located at 107.51W drifting at 0.001E degrees per day.References: 1, 2, 5, 6.

• LES 9 Nation: USA. Mass: 454 kg (1,000 lb). Class: Technology. Type: Comsat. Spacecraft: LES. Agency: USAF. Perigee: 35,745 km (22,210 mi). Apogee: 35,825 km (22,260 mi). Inclination: 17.00 deg. Period: 1,436.00 min. COSPAR: 1976-023B. USAF Sat Cat: 8747. Completed Operations Date: 1992-01-01. Spacecraft engaged in practical applications and uses of space technology such as weather or communication. Also tested pulsed plasma engines. Positioned in geosynchronous orbit over the Atlantic Ocean at 30-40 deg W in 1976-78; over the Americas at 90-100 deg W in 1980-81; over the Americas at 100-106 deg W in 1981-1990; over the Atlantic Ocean 10 deg W in 1991; over the Americas at 105 deg W in 1992-on. As of 1 September 2001 located at 103.85 deg W drifting at 0.023 deg W per day. As of 2007 Mar 11 located at 107.07W drifting at 0.018W degrees per day.References: 1, 2, 5, 6.

• Solrad 11A Nation: USA. Mass: 181 kg (399 lb). Class: Solar. Spacecraft: Solrad. Agency: USAF. Perigee: 118,383 km (73,559 mi). Apogee: 119,180 km (74,050 mi). Inclination: 25.70 deg. Period: 7,344.30 min. COSPAR: 1976-023C. USAF Sat Cat: 8748. Solar radiation data. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• Solrad 11B Nation: USA. Mass: 181 kg (399 lb). Class: Solar. Spacecraft: Solrad. Agency: USAF. Perigee: 115,720 km (71,900 mi). Apogee: 116,645 km (72,479 mi). Inclination: 25.60 deg. Period: 7,116.70 min. COSPAR: 1976-023D. USAF Sat Cat: 8749. Solar radiation data. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1, 2, 5, 6.

• IMEWS 6 Nation: USA. Payload: DSP Phase 2 s/n 8. Mass: 1,040 kg (2,290 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,620 km (22,130 mi). Apogee: 35,860 km (22,280 mi). Inclination: 0.50 deg. Period: 1,433.30 min. COSPAR: 1976-059A. USAF Sat Cat: 8916. Completed Operations Date: 1984-07-01. Second generation geosynchronous ballistic missile launch detection satellite, remained in service for over eight years. Positioned over the Atlantic Ocean from 1976 to 1981: at 35 deg W in 1976-1977; at 65 deg W in 1977-1979; and 35 deg W in 1979-1980; and 65 deg W in 1980-1981. Then moved over the Pacific Ocean at 125 deg W, then 140 deg W in 1981-1982; then over the Indian Ocean at 75 deg E in 1982-1984.References: 1, 2, 5, 6, 127.

• IMEWS 7 Nation: USA. Payload: DSP Phase 2 s/n 9. Mass: 1,040 kg (2,290 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,620 km (22,130 mi). Apogee: 35,860 km (22,280 mi). Inclination: 0.50 deg. Period: 1,433.30 min. COSPAR: 1977-007A. USAF Sat Cat: 9803. Completed Operations Date: 1984-01-01. Second generation geosynchronous ballistic missile launch detection satellite, remained in service for nearly seven years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1977-1979; over the Indian Ocean 70 deg E in 1979-1984. References: 1, 2, 5, 6, 127.

• DSCS II-07 Nation: USA. Program: DSCS. Payload: DSCS II F-7. Mass: 565 kg (1,245 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 36,759 km (22,840 mi). Apogee: 36,894 km (22,924 mi). Inclination: 15.80 deg. Period: 1,489.60 min. COSPAR: 1977-034A. USAF Sat Cat: 10000. Completed Operations Date: 1981-12-20. 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 12 deg W in 1977-1979; over the Atlantic Ocean 5 deg W in 1979; over the Pacific Ocean 140 deg E in 1980-1981 As of 28 August 2001 located at 152.07 deg W drifting at 12.959 deg W per day. As of 2007 Mar 10 located at 47.37W drifting at 12.959W degrees per day.References: 1, 2, 5, 6.

• DSCS II-08 Nation: USA. Program: DSCS. Payload: DSCS II F-8. Mass: 565 kg (1,245 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 37,061 km (23,028 mi). Apogee: 37,343 km (23,203 mi). Inclination: 15.50 deg. Period: 1,509.00 min. COSPAR: 1977-034B. USAF Sat Cat: 10001. Completed Operations Date: 1990-02-01. 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 175 deg E in 1977-1979 over the Atlantic Ocean 12 deg W in 1979-80 over the Pacific Ocean 175 deg E in 1980-1983 over the Pacific Ocean180 deg E in 1983-1986 over the Atlantic Ocean 1 deg W in 1986-1989 As of 3 September 2001 located at 143.55 deg W drifting at 17.451 deg W per day. As of 2007 Mar 9 located at 13.13E drifting at 17.445W degrees per day.References: 1, 2, 5, 6.

• DSCS II-09 Nation: USA. Program: DSCS. Payload: DSCS II F-9. Mass: 550 kg (1,210 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: U.S. Air Force. COSPAR: F780325A. Decay Date: 1978-03-25. Launched with DSCS F10. References: 5, 126.

• DSCS II F-10 Nation: USA. Program: DSCS. Payload: DSCS II F-10. Spacecraft: DSCS II. Agency: USAF AFSC. COSPAR: F780325B. References: 279.

• Chalet 1 Nation: USA. Payload: Chalet 1 (Vortex 1). Mass: 820 kg (1,800 lb). Class: Sigint. Spacecraft: Chalet. Agency: NRO/USAF. Perigee: 29,929 km (18,596 mi). Apogee: 42,039 km (26,121 mi). Inclination: 12.00 deg. Period: 1,446.30 min. COSPAR: 1978-058A. USAF Sat Cat: 10941. First launch of the heavier, mored advanced CHALET ELINT satellites. (the project was renamed VORTEX when the code name CHALET appeared in the New York Times). References: 1, 2, 5, 6.

• DSCS II-11 Nation: USA. Program: DSCS. Payload: DSCS II F-11. Mass: 550 kg (1,210 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 37,515 km (23,310 mi). Apogee: 37,749 km (23,456 mi). Inclination: 9.80 deg. Period: 1,531.40 min. COSPAR: 1978-113A. USAF Sat Cat: 11144. Completed Operations Date: 1993-12-13. 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 1979-1983 over the Pacific Ocean 129 deg W in 1983-1989 As of 5 September 2001 located at 62.62 deg W drifting at 22.467 deg W per day. As of 2007 Mar 10 located at 96.59E drifting at 22.469W degrees per day.References: 1, 2, 5, 6.

• DSCS II-12 Nation: USA. Program: DSCS. Payload: DSCS II F-12. Mass: 550 kg (1,210 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 36,283 km (22,545 mi). Apogee: 36,332 km (22,575 mi). Inclination: 9.80 deg. Period: 1,462.80 min. COSPAR: 1978-113B. USAF Sat Cat: 11145. Completed Operations Date: 1993-12-13. 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 175 deg E in 1979-1981 over the Indian Ocean 66 deg E in 1981-1983 over the Indian Ocean 60 deg E in 1983-1987 over the Pacific Ocean177 deg E in 1988-1989 over the Indian Ocean 71 deg E in 1990-1992 As of 1 September 2001 located at 93.28 deg E drifting at 6.600 deg W per day. As of 2007 Mar 8 located at 143.60E drifting at 6.589W degrees per day.References: 1, 2, 5, 6.

• IMEWS 10 Nation: USA. Payload: DSP MOS/PIM s/n 11. Mass: 1,170 kg (2,570 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,712 km (22,190 mi). Apogee: 35,854 km (22,278 mi). Inclination: 1.80 deg. Period: 1,435.90 min. COSPAR: 1979-053A. USAF Sat Cat: 11397. Completed Operations Date: 1984-06-01. First Multi-Orbit Satellite / Performance Improvement ballistic missile launch detection satellite, remained in service for nearly six years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1979-1982; 85 deg W in 1982-1984; 135 deg W in 1984; 125 deg W in 1985..References: 1, 2, 5, 6, 127.

• Chalet 2 Nation: USA. Payload: Chalet 2 (Vortex 2). Mass: 820 kg (1,800 lb). Class: Sigint. Spacecraft: Chalet. Agency: NRO/USAF. Perigee: 30,443 km (18,916 mi). Apogee: 41,497 km (25,784 mi). Inclination: 7.50 deg. Period: 1,445.50 min. COSPAR: 1979-086A. USAF Sat Cat: 11558. Chalet ELINT satellite. References: 1, 2, 5, 6.

• DSCS II-13 Nation: USA. Program: DSCS. Payload: DSCS II F-13. Mass: 611 kg (1,347 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 37,104 km (23,055 mi). Apogee: 37,195 km (23,111 mi). Inclination: 13.60 deg. Period: 1,506.30 min. COSPAR: 1979-098A. USAF Sat Cat: 11621. Completed Operations Date: 1994-07-19. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 12 deg W in 1980-1981; 131 deg W in 1981-1983; 179 deg W in 1983; 175 deg E in 1983-1989;179 deg W in 1989-1993 As of 3 September 2001 located at 21.08 deg E drifting at 16.828 deg W per day. As of 2007 Mar 10 located at 37.50W drifting at 16.828W degrees per day.References: 1, 2, 5, 6.

• DSCS II-14 Nation: USA. Program: DSCS. Payload: DSCS II F-14. Mass: 611 kg (1,347 lb). Class: Communications. Type: Military. Spacecraft: DSCS II. Agency: USAF. Perigee: 36,316 km (22,565 mi). Apogee: 36,351 km (22,587 mi). Inclination: 13.30 deg. Period: 1,464.10 min. COSPAR: 1979-098B. USAF Sat Cat: 11622. Completed Operations Date: 1995-06-19. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 66 deg E in 1980-1981; 12 deg W in 1981-1986; 179 deg W in 1986-1990; 174 deg E in 1990; 65 deg E in 1991-1994 As of 31 August 2001 located at 27.01 deg W drifting at 6.916 deg W per day. As of 2007 Mar 11 located at 50.79E drifting at 6.926W degrees per day.References: 1, 2, 5, 6.

• IMEWS 11 Nation: USA. Payload: DSP MOS/PIM s/n 10. Mass: 1,170 kg (2,570 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,463 km (22,035 mi). Apogee: 35,527 km (22,075 mi). Inclination: 2.00 deg. Period: 1,421.20 min. COSPAR: 1981-025A. USAF Sat Cat: 12339. Completed Operations Date: 1992-01-01. Multi-Orbit Satellite / Performance Improvement ballistic missile launch detection satellite, remained in service for nearly eleven years. Positioned in geosynchronous orbit over the Pacific Ocean at 69 deg W in 1981-1982; 135 deg W in 1982-1984; 75 deg E in 1984-1985. As of 2003 Mar 6 located at 40.27E drifting at 0.598E degrees per day.References: 1, 2, 5, 6, 127.

• Chalet 3 Nation: USA. Payload: Chalet 3 (Vortex 3). Mass: 820 kg (1,800 lb). Class: Sigint. Spacecraft: Chalet. Agency: NRO/USAF. Perigee: 134 km (83 mi). Apogee: 382 km (237 mi). Inclination: 29.30 deg. Period: 90.40 min. COSPAR: 1981-107A. USAF Sat Cat: 12930. Chalet ELINT satellite. References: 1, 2, 5, 6.

• IMEWS 13 Nation: USA. Payload: DSP MOS/PIM s/n 13. Mass: 1,170 kg (2,570 lb). Class: Early Warning. Spacecraft: DSP. Agency: USAF. Perigee: 35,520 km (22,070 mi). Apogee: 35,598 km (22,119 mi). Inclination: 2.00 deg. Period: 1,424.40 min. COSPAR: 1982-019A. USAF Sat Cat: 13086. Completed Operations Date: 1998-12-31. Multi-Orbit Satellite / Performance Improvement ballistic missile launch detection satellite, remained in service for over sixteen years. Positioned in geosynchronous orbit over the Pacific Ocean at 68 deg W in 1982; 35 deg W in 1983-1988; 165 deg W in 1988-1989; 35 deg W in 1989-1991.References: 1, 2, 5, 6, 127.

• 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...

• Titan Marketing Brochure, Martin Company, 1967.