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Cape Canaveral LC15

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First Launch: 1959-02-06. Last Launch: 1964-04-09. Number: 26 . Longitude: -80.55 deg. Latitude: 28.50 deg.

• Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). First test launch of USAF Titan ICBM (A-3) from Cape Canaveral. Dummy second stage (500 km range)..

• Test mission - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• Test mission - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). Successful dummy second stage separation..

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

  Titan flight test missile G-4 was launched from Cape Canaveral and completed all test objectives in the first successful long-range flight, with the reentry vehicle impacting 4,335-NM downrange. This flight was the longest to date by a Titan and demonstrated the integrity of all basic design parameters as well as Bell Telephone Laboratories radio-inertial guidance systems.

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi). USAF Titan fired 5,000 statute miles / 8000 km and data capsule recovered..

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• RVX-4 test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). A Titan II (N-16) completed a 6,500-mile flight down the Atlantic Missile Range carrying the heaviest payload ever to travel that far on a U.S. missile..

• Mk 6 re-entry vehicle test launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Research and development test - . Nation: USA. Agency: USAF AFSC. Apogee: 500 km (310 mi). Mk 6 re-entry vehicle.

• Research and development test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi). Mk 6 re-entry vehicle.

• Research and development / Pod T-202 test / plume study mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

  Titan II development flight N-24 was launched from the Atlantic Missile Range. This was the first of five flight tests in the Gemini malfunction detection system (MDS) piggyback series. All MDS parameters were lost 81 seconds after liftoff because of a short circuit in the MDS. Operation in the second flight (N-25 on November 1) was normal except for two minor instrumentation problems. Three more test flights (N-29 on December 12, 1963; N-31 on January 15, 1964; and N-33 on March 23, 1964) verified the performance of the Gemini MDS under actual conditions of flight environment and engine operation.

• Research and development / Pod T test / plume study mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

  Titan II development flight N-25 was launched from the Atlantic Missile Range. It carried the oxidizer surge chamber and fuel accumulator kit intended to reduce the amplitude of longitudinal vibration which had characterized earlier flights. NASA regarded 0.25g as the maximum level tolerable in manned space flight; this flight achieved a level of 0.22g, the first to fall within acceptable limits. Although the kit had been tested on only one flight, Gemini Project Office had sufficient confidence in it to decide, on November 6, to procure several more such kits for subsequent installation in Gemini launch vehicles. Two later Titan II development flights (N-29 on December 12, 1963, and N-31 on January 15, 1964) and the flight of Gemini-Titan 1 confirmed the validity of this decision. The required kits for the remaining Gemini launch vehicles were then procured.

• Research and development / Pod T test / plume study mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Research and development / Pod T test - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Research and development launch - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Research and development / Pod T-207 - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

• Research and development / Pod RVIP test / plume study mission - . Nation: USA. Agency: USAF AFSC. Apogee: 1,300 km (800 mi).

  The 23d, and last, Titan II research and development missile (N-3A) to be launched down the Atlantic range completed a success ful flight. With the 10 test flights from Vandenberg, a total of 33 Titan II (XLGM-25C) R&D flights had been completed since 16 March 1962 - 27 successes and only six failures. This Air Force conducted test program contributed significantly to the development of the Gemini launch vehicle; the Gemini malfunction detection system was tested on five flights, Gemini guidance components on three, and the longitudinal oscillation fix on four. In addition to flight testing these (and other) critical components, these flights also enhanced confidence in the use of the Titan II as a launch vehicle. Thirty-two Titan II test flights were analyzed to determine whether any characteristic of the flight would have demanded a Gemini abort; 22 were adjudged successful from the standpoint of a Gemini mission, nine would have required Gemini to abort, and one resulted in a prelaunch shutdown.