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Cape Canaveral LC14
Part of Cape Canaveral Family
Atlas launch complex. The complex was built for the Atlas ballistic missile program. Launch sites 11 to 14 were accepted between August 1957 and mid-April 1958. After its final Atlas missile launch, Complex 14 was converted into an Atlas /Agena launch complex, and later turned over to NASA. Complex 14 supported 32 Atlas and Atlas/Agena missions, including four manned Mercury missions and seven unmanned Gemini target vehicle launches. Complexes 11, 12 and 14 were deactivated in 1967. Complex 14 and the gantry on Complex 13 were declared national historic landmarks in April 1984.

First Launch: 1957-06-11. Last Launch: 1966-11-11. Number: 32 . Longitude: -80.5469 deg. Latitude: 28.4911 deg.

Spacecraft: Mercury, Pioneer P 3, Midas, Gemini Agena Target Vehicle, Atlas Target Docking Adapter. Launch Vehicles: Atlas Able, Atlas B, Atlas A, Atlas D, Atlas Agena A, Atlas SLV-3 Agena D, Atlas SLV-3. Launch Sites: Cape Canaveral.



1957 June 11 - . 19:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A. FAILURE: Failure in the booster fuel system.. Failed Stage: 1.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 3.00 km (1.80 mi).

    The first Atlas Series A flight test missile (4A) had to be destroyed shortly after launch from Cape Canaveral due to a booster engine shutdown and loss of thrust. From a technical standpoint, however, this first booster-only launch successfully demonstrated the launching mechanism, structural integrity of the airframe, subsystems performance, and operating procedures for launch crew personnel. First test flight of prototype WS-107A Atlas was detonated by command signal at 10,000 feet following a failure in the booster fuel system. The 23-second flight was considered a partial success.


1957 September 25 - . 19:57 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A. FAILURE: Failure in the booster fuel system.. Failed Stage: 1.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 4.00 km (2.40 mi).

    The second Atlas flight test missile (6A) was destroyed 32 seconds into the flight because of an engine shutdown. Atlas was again destroyed by command signal at three minutes into flight following a failure in the booster fuel system. The 50-second active flight was considered a partial success.


1957 December 17 - . 17:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 120 km (70 mi).

    The third flight test missile (12A) became the first successful Atlas Series A missile flight. A short-range, booster-only flight was completed with the booster impacting 575 miles down range from Cape Canaveral. During the flight, all systems performed satisfactorily. First successful test firing of USAF Atlas ICBM, the missile landing in the target area after a flight of 600 miles.


1958 February 7 - . 19:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A. FAILURE: Failure. Failed Stage: 1.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 120 km (70 mi).

1958 April 5 - . 17:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas A. FAILURE: Failure. Failed Stage: 1.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi). USAF Atlas A ICBM was successfully flown from Cape Canaveral, Fla., to the impact area some 600 miles away..

1958 September 14 - . 05:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas B.
  • Research and development / AFSWC-2 test - . Nation: USA. Agency: USAF. Apogee: 900 km (550 mi).

1958 November 29 - . 02:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas B.
  • Research and development / AFSWC-3 test - . Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Less than 18 months after the first flight, a USAF Atlas made its first successful full-range operational test flight in a 6,325 statute-mile flight, landed close to its target..

1959 January 16 - . 04:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas B. FAILURE: Failure. Failed Stage: 1.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).

1959 May 19 - . 04:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D. FAILURE: Failure. Failed Stage: 1.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi).

1959 September 9 - . 08:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D. FAILURE: Failure. Failed Stage: 1.
  • Mercury BJ-1 - . Nation: USA. Agency: USAF. Apogee: 153 km (95 mi).

    A SAC crew conducted the first west coast launch of an Atlas operational configuration missile, 12D, from Vandenberg AFB, to a target near Wake Island, Afterward, General Thomas S. Power, CINCSAC, declared the Atlas system to be operational. This marked the attainment of operational status for the Atlas one year earlier than the six years that the von Neumann Committee had projected in its February 1954 report. The first prototype of the Mercury-Atlas capsule for NASA's Project Mercury was launched atop Atlas 10D from Cape Canaveral. NASA boilerplate model of Mercury capsule successfully launched on an Atlas (Big Joe) missile from AMR and recovered in South Atlantic after surviving reentry heat of more than 10,000°F.


1959 November 26 - . 07:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas Able. FAILURE: Payload shroud failed after 45 sec, broke away prematurely.. Failed Stage: S.
  • Pioneer (P 3) - . Payload: Pioneer P 3 / Able IVB. Mass: 168 kg (370 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft Bus: Pioneer P 3. Spacecraft: Pioneer P 3. Decay Date: 1959-11-26 . Apogee: 1,000 km (600 mi).

    An intended lunar probe launched from the Atlantic Missile Range by an Atlas-Able booster disintegrated about 45 seconds later when the protective sheath covering the payload detached prematurely. The probe was sponsored by NASA, developed by the Jet Propulsion Laboratory, and launched by the Air Force Ballistic Missile Division.


1960 February 26 - . 17:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas Agena A. FAILURE: Second stage failed to separate.. Failed Stage: U.
  • Midas 1 - . Payload: Midas / Agena TV 1008. Mass: 2,025 kg (4,464 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. Decay Date: 1960-02-26 .

    The Air Force MIDAS I satellite was launched from Cape Canaveral in the first successful launch of the Atlas D/Agena A booster-upper stage combination. MIDAS I, however, failed to achieve orbit because an accident at the Atlas-Agena staging damaged the Agena. The entire vehicle reentered and burned up about 2,500 miles downrange. Missile Defense Alarm System.


1960 May 24 - . 17:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas Agena A.
  • Midas 2 - . Payload: Midas / Agena TV 1007. Mass: 2,300 kg (5,000 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. Decay Date: 1974-02-07 . USAF Sat Cat: 43 . COSPAR: 1960-Zeta-1. Apogee: 494 km (306 mi). Perigee: 473 km (293 mi). Inclination: 33.0000 deg. Period: 94.30 min.

    Missile Defense Alarm System. Test launch with W-17 sensor. The last Atlas D/Agena A booster to be used by the Air Force placed into orbit the MIDAS II infrared scanning satellite designed to detect and give early warning of missile launchings. Although intended to function for 40 months, the satellite's telemetry system failed on 26 May. MIDAS II was the first early warning satellite system placed in orbit.


1960 June 22 - . 14:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D. FAILURE: Electrical Failure.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). 50th Atlas to be flown at AMR, successful.

1960 July 29 - . 13:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D. FAILURE: Structural failure of Atlas.. Failed Stage: 1.
  • Mercury MA-1 - . Nation: USA. Agency: USAF. Program: Mercury. Spacecraft Bus: Mercury. Spacecraft: Mercury. Apogee: 13 km (8 mi).

    The first Mercury-Atlas -D (MA-1) was successfully launched from Cape Canaveral to test the Mercury capsule and Atlas D booster for future use in NASA's Project Mercury manned orbital flight program. Mercury-Atlas 1 (MA-1) was launched from the Atlantic Missile Range in a test of spacecraft structural integrity under maximum heating conditions. After 58.5 seconds of flight, MA-1 exploded and the spacecraft was destroyed upon impact off-shore. None of the primary capsule test objectives were met. The mission objectives were to check the integrity of the spacecraft structure and afterbody shingles for a reentry associated with a critical abort and to evaluate the open-loop performance of the Atlas abort-sensing instrumentation system. The spacecraft contained no escape system and no test subject. Standard posigrade rockets were used to separate the spacecraft from the Atlas, but the retrorockets were dummies. The flight was terminated because of a launch vehicle and adapter structural failure. The spacecraft was destroyed upon impact with the water because the recovery system was not designed to actuate under the imposed flight conditions. Later most of the spacecraft, the booster engines, and the liquid oxygen vent valve were recovered from the ocean floor. Since none of the primary flight objectives was achieved, Mercury-Atlas 2 (MA-2) was planned to fulfill the mission.


1960 September 19 - . 18:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Research and development test - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi). Atlas ICBM fired 9030 statute miles, from Cape Canaveral to the Indian Ocean off the Cape of Good Hope in 50 minutes, the second record distance flight..

1960 October 22 - . 05:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).

1961 February 21 - . 14:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-2 - . Nation: USA. Agency: USAF. Program: Mercury. Spacecraft Bus: Mercury. Spacecraft: Mercury. Apogee: 182 km (113 mi).

    Mercury-Atlas 2 (MA-2) was launched from Cape Canaveral in a test to check maximum heating and its effects during the worst reentry design conditions. The flight closely matched the desired trajectory and attained a maximum altitude of 114.04 statute miles and a range of 1,431.6 statute miles. Inspection of the spacecraft aboard the recovery ship some 55 minutes after launch (actual flight time was 17.56 minutes) indicated that test objectives were met, since the structure and heat protection elements appeared to be in excellent condition. The flight control team obtained satisfactory data; and the complete launch computing and display system, operating for the first time in a flight, performed satisfactorily.


1961 April 25 - . 16:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D. FAILURE: Destroyed by range safety.. Failed Stage: G.
  • Mercury MA-3 - . Payload: Mercury SC8. Mass: 1,355 kg (2,987 lb). Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Mercury. Spacecraft: Mercury. Decay Date: 1961-04-25 .

    Mercury-Atlas 3 (MA-3) was launched from Cape Canaveral in an attempt to orbit the spacecraft with a 'mechanical astronaut' aboard. After lift-off, the launch vehicle failed to roll to a 70 degree heading and to pitch over into the proper trajectory. The abort-sensing system activated the escape rockets prior to the launch vehicle's destruction by the range safety officer after approximately 40 seconds of flight that had attained an altitude of 16,400 feet. The spacecraft then coasted up to 24,000 feet, deployed its parachutes, and landed in the Atlantic Ocean 2,000 yards north of the launch pad. The spacecraft was recovered and was found to have incurred only superficial damage; it was then shipped to McDonnell for refitting.


1961 September 13 - . 14:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-4 - . Payload: Mercury SC8A. Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Mercury. Spacecraft: Mercury. Decay Date: 1961-09-13 . USAF Sat Cat: 183 . COSPAR: 1961-A-Alpha-1. Apogee: 248 km (154 mi). Perigee: 156 km (96 mi). Inclination: 32.8000 deg. Period: 88.40 min.

    Mercury-Atlas 4 (MA-4) was launched from Cape Canaveral with special vibration and noise instrumentation and a mechanical crewman simulator aboard in addition to the normal spacecraft equipment. This was the first Mercury spacecraft to attain an earth orbit. The orbital apogee was 123 nautical miles and the perigee was 86 nautical miles. After one orbit, the spacecraft's orbital timing device triggered the retrograde rockets, and the spacecraft splashed in the Atlantic Ocean 161 miles east of Bermuda. Recovery was made by the USS Decatur. During the flight, only three slight deviations were noted - a small leak in the oxygen system; loss of voice contact over Australia; and the failure of an inverter in the environmental control system. Overall, the flight was highly successful: the Atlas booster performed well and demonstrated that it was ready for the manned flight, the spacecraft systems operated well, and the Mercury global tracking network and telemetry operated in an excellent manner and was ready to support manned orbital flight.


1961 November 29 - . 15:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-5 - . Payload: Mercury SC9. Mass: 1,300 kg (2,800 lb). Nation: USA. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Spacecraft Bus: Mercury. Spacecraft: Mercury. Decay Date: 1961-11-29 . USAF Sat Cat: 208 . COSPAR: 1961-A-Iota-1. Apogee: 237 km (147 mi). Perigee: 158 km (98 mi). Inclination: 32.6000 deg. Period: 88.30 min.

    Atlas D (53D) was the first missile to be launched by SAC from Vandenberg in the operation test (Category III) launch program. Mercury-Atlas 5 (MA-5), the second and final orbital qualification of the spacecraft prior to manned flight was launched from Cape Canaveral with Enos, a 37.5 pound chimpanzee, aboard. Scheduled for three orbits, the spacecraft was returned to earth after two orbits due to the failure of a roll reaction jet and to the overheating of an inverter in the electrical system. Both of these difficulties could have been corrected had an astronaut been aboard. The spacecraft was recovered 255 miles southeast of Bermuda by the USS Stormes. During the flight, the chimpanzee performed psychomotor duties and upon recovery was found to be in excellent physical condition. The flight was termed highly successful and the Mercury spacecraft well qualified to support manned orbital flight.


1962 February 20 - . 14:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-6 - . Call Sign: Friendship 7. Crew: Glenn. Backup Crew: Carpenter. Payload: Mercury SC13. Mass: 1,355 kg (2,987 lb). Nation: USA. Related Persons: Carpenter, Glenn. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-6. Spacecraft Bus: Mercury. Spacecraft: Mercury. Duration: 0.21 days. Decay Date: 1962-02-20 . USAF Sat Cat: 240 . COSPAR: 1962-Gamma-1. Apogee: 265 km (164 mi). Perigee: 159 km (98 mi). Inclination: 32.5000 deg. Period: 88.60 min.

    The 6555th Aerospace Test Wing launched the Mercury/Atlas D (MA-6), "Friendship 7," that placed the Mercury capsule containing LtColonel John Glenn, USMC, into orbit for the first Project Mercury manned orbital flight. "Friendship 7" completed three orbits before successful reentry and recovery in the Atlantic Ocean. First US manned orbital mission. John Glenn finally puts America in orbit. False landing bag deploy light led to reentry being started with retropack left in place on heat shield. It turned out that indicator light was false and a spectacular reentry ensued, with glowing chunks of the retropack whizzing by the window. After four hours and 43 minutes the spacecraft reentered the atmosphere and landed at 2:43 pm EST in the planned recovery area NE of the Island of Puerto Rico. All flight objectives were achieved. Glenn was reported to be in excellent condition. Beause of failure of one of the automatic systems, the astronaut took over manual control of the spacecraft during part of the flight. With this flight, the basic objectives of Project Mercury had been achieved.


1962 May 24 - . 12:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-7 - . Call Sign: Aurora 7. Crew: Carpenter. Backup Crew: Schirra. Payload: Mercury SC18. Mass: 1,349 kg (2,974 lb). Nation: USA. Related Persons: Carpenter, Schirra. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-7. Spacecraft Bus: Mercury. Spacecraft: Mercury. Duration: 0.21 days. Decay Date: 1962-05-24 . USAF Sat Cat: 295 . COSPAR: 1962-Tau-1. Apogee: 260 km (160 mi). Perigee: 154 km (95 mi). Inclination: 32.5000 deg. Period: 88.50 min.

    BSD's 6555th Aerospace Test Wing launched Mercury/Atlas 7 (MA-7), "Aurora 7", into orbit carrying Navy Commander M. Scott Carpenter. This was the second U.S. manned orbital flight mission. Scott Carpenter in Aurora 7 is enthralled by his environment but uses too much orientation fuel. Yaw error and late retrofire caused the landing impact point to be over 300 km beyond the intended area and beyond radio range of the recovery forces. Landing occurred 4 hours and 56 minutes after liftoff. Astronaut Carpenter was later picked up safely by a helicopter after a long wait in the ocean and fears for his safety. NASA was not impressed and Carpenter left the agency soon thereafter to become an aquanaut.


1962 October 3 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-8 - . Call Sign: Sigma 7. Crew: Schirra. Backup Crew: Cooper. Payload: Mercury SC16. Mass: 1,374 kg (3,029 lb). Nation: USA. Related Persons: Cooper, Schirra. Agency: NASA. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-8. Spacecraft Bus: Mercury. Spacecraft: Mercury. Duration: 0.38 days. Decay Date: 1962-10-03 . USAF Sat Cat: 433 . COSPAR: 1962-B-Delta-1. Apogee: 285 km (177 mi). Perigee: 153 km (95 mi). Inclination: 32.5000 deg. Period: 88.80 min.

    The Sigma 7 spacecraft with Astronaut Walter M. Schirra, Jr., as pilot was launched into orbit by a Mercury-Atlas vehicle from Atlantic Missile Range. In the most successful American manned space flight to date, Schirra traveled nearly six orbits, returning to earth at a predetermined point in the Pacific Ocean 9 hours, 13 minutes after liftoff. Within 40 minutes after landing, he and his spacecraft were safely aboard the aircraft carrier U.S.S. Kearsarge. Schirra attempted and achieved a nearly perfect mission by sticking rigorously to mission plan.


1963 May 15 - . 13:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas D.
  • Mercury MA-9 - . Call Sign: Faith 7. Crew: Cooper. Backup Crew: Shepard. Payload: Mercury SC20. Mass: 1,376 kg (3,033 lb). Nation: USA. Related Persons: Cooper, Shepard. Agency: NASA Houston. Program: Mercury. Class: Manned. Type: Manned spacecraft. Flight: Mercury MA-9. Spacecraft Bus: Mercury. Spacecraft: Mercury. Duration: 1.43 days. Decay Date: 1963-05-16 . USAF Sat Cat: 576 . COSPAR: 1963-015A. Apogee: 265 km (164 mi). Perigee: 163 km (101 mi). Inclination: 32.5000 deg. Period: 88.70 min. Final Mercury mission, Faith 7, was piloted by Astronaut L. Gordon Cooper, Jr..

1965 October 25 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D. FAILURE: Exploded 6 minutes after takeoff. Failure.. Failed Stage: U.
  • Gemini 6 Agena Target - . Payload: TDA-2. Mass: 3,261 kg (7,189 lb). Nation: USA. Agency: NASA. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 6, Gemini 7. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1965-10-25 . The Agena target vehicle failed to reach orbit. Gemini 6, awaiting launch, was cancelled. In the ashes of this setback, the idea of launching Gemini 6 to rendezvous with Gemini 7 was born..

1966 March 16 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • Gemini 8 Agena Target - . Payload: TDA 3/Agena D 5003 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 8. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1967-09-15 . USAF Sat Cat: 2104 . COSPAR: 1966-019A. Apogee: 299 km (185 mi). Perigee: 285 km (177 mi). Inclination: 28.9000 deg. Period: 90.40 min. Target vehicle for Gemini 8..

1966 May 17 - . 15:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D. FAILURE: Control system failure.. Failed Stage: G.
  • Gemini 9 Agena Target - . Payload: TDA 5. Mass: 3,248 kg (7,160 lb). Nation: USA. Agency: NASA. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 9. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-05-17 .

    The Gemini 9 mission was scrubbed when the Atlas booster launched from Cape Canaveral failed to place the Gemini Agena Target Vehicle (GATV) in its planned circular orbit. A malfunction of the number 2 booster engine of the Atlas caused both the Atlas and Agena to fall into the ocean. The Gemini 9-Atlas/Agena mission was later rescheduled to 1 June using the Augmented Target Docking Adapter (ATDA).


1966 June 1 - . 15:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3.
  • Gemini 9 ATDA - . Payload: TDA 4. Mass: 794 kg (1,750 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 9. Spacecraft Bus: Atlas Target Docking Adapter. Spacecraft: Atlas Target Docking Adapter. Decay Date: 1966-06-11 . USAF Sat Cat: 2186 . COSPAR: 1966-046A. Apogee: 296 km (183 mi). Perigee: 292 km (181 mi). Inclination: 28.8000 deg. Period: 90.40 min.

    The first and only Atlas/Augmented Target Docking Adapter (ATDA) Gemini Agena (#5304) was launched from the Eastern Test Range as part of the Gemini 9 mission. The ATDA was a back-up for the Gemini Agena Target Vehicle (GATV) and similar to it except that it lacked the capability to maneuver in space. The ATDA achieved a near-circular orbit (apogee 161.5, perigee 158.5 nautical miles). One hour and 40 minutes later, the scheduled launch of Gemini IX-A was postponed by a ground equipment failure which prevented the transfer of updating information from Cape Kennedy mission control center to the spacecraft computer. The mission was recycled for launch on June 3, following a prepared 48-hour recycle plan. Anomalous telemetry indicated some sort of problem with the target, but it was not until Gemini IX rendezvoused with it in orbit that it was seen that fairing separation had failed.


1966 July 18 - . 20:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • Gemini 10 Agena Target - . Payload: TDA 1A/Agena D 5005 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 10. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-29 . USAF Sat Cat: 2348 . COSPAR: 1966-065A. Apogee: 296 km (183 mi). Perigee: 290 km (180 mi). Inclination: 28.9000 deg. Period: 90.40 min.

    An Air Force Titan Gemini Launch Vehicle placed the Gemini 10 (GT-10) spacecraft into orbit for the three-day mission of Astronauts John Young and Michael Collins. Rendezvous and docking were accomplished with the Gemini Agena Target Vehicle (GATV) that had been launched from Cape Kennedy aboard an Atlas Booster just ahead of GT-10. Using the GATV-10 Primary Propulsion System (PPS), the docked vehicles achieved a manned-flight altitude record of 476 miles. Reentry was accomplished on 21 July and recovery was made 544 miles east of Cape Canaveral. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).


1966 September 12 - . 13:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • Gemini 11 Agena Target - . Payload: TDA 6/Agena D 5006 GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 11. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-30 . USAF Sat Cat: 2414 . COSPAR: 1966-080A. Apogee: 298 km (185 mi). Perigee: 298 km (185 mi). Inclination: 28.8000 deg. Period: 90.40 min. Docking target for Gemini 11..

1966 November 11 - . 19:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas SLV-3 Agena D.
  • Gemini 12 Agena Target - . Payload: TDA 7A/Agena D 5001R GATV. Mass: 3,175 kg (6,999 lb). Nation: USA. Agency: NASA Houston. Program: Gemini. Class: Manned. Type: Manned logistics spacecraft. Flight: Gemini 12. Spacecraft Bus: Agena. Spacecraft: Gemini Agena Target Vehicle. Decay Date: 1966-12-23 . USAF Sat Cat: 2565 . COSPAR: 1966-103A. Apogee: 310 km (190 mi). Perigee: 243 km (150 mi). Inclination: 28.8000 deg. Period: 89.90 min. Docking target for Gemini 12..


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