Encyclopedia Astronautica
Cape Canaveral LC6


Redstone, Jupiter launch complex. Pad 6 supported its first Redstone launch on 20 April 1955, three months before the complex was finally accepted by the U.S. Government. In addition to Redstone and Jupiter launches, the complex supported Explorer and Pioneer missions and all six Redstone /Mercury suborbital flights. On 31 January 1964, Complexes 5 and 6 were reassigned to become part of the USAF Space Museum.

Longitude: -80.5726 deg.
Latitude: 28.4407 deg.
First Launch: 1955.04.20.
Last Launch: 1961.06.27.
Number: 43 .

More... - Chronology...


Associated Launch Vehicles
  • Redstone Redstone was the first large liquid rocket developed in the US using German V-2 technology. Originally designated Hermes C. Redstones later launched the first US satellite and the first American astronaut into space. More...
  • Jupiter A American orbital launch vehicle. The Jupiter A was a modified Redstone missile fitted with Jupiter inertial navigation and control system elements. It also tested Hydyne fuel and other engine modifications for the Jupiter C re-entry vehicle test booster. More...
  • Jupiter C American orbital launch vehicle. Re-entry vehicle test booster and satellite launcher derived from Redstone missile. The Jupiter A version of the Redstone missile was modified with upper stages to test Jupiter re-entry vehicle configurations. Von Braun's team was ordered to ballast the upper stage with sand to prevent any 'inadvertent' artificial satellites from stealing thunder from the official Vanguard program. Korolev's R-7 orbited the first earth satellite instead. The Jupiter C was retroactively named the 'Juno I' by Von Braun's team. More...
  • Jupiter American intermediate range ballistic missile. The Jupiter IRBM was developed for the US Army. By the time development was complete, the mission and the missile was assigned to the US Air Force, which had its own nearly identical missile, the Thor. Jupiters were stationed in Turkey and Italy in the early 1960's, but withdrawn in secret exchange for the withdrawal of Soviet R-5 missiles from Cuba. The Jupiter was used as the first stage of the relatively unsuccessful Juno II launch vehicle, and proposed for the Juno III and Juno IV. Jupiter tooling and engines were used to build the much larger Juno V / Saturn I launch vehicle. More...

Associated Launch Sites
  • Cape Canaveral America's largest launch center, used for all manned launches. Today only six of the 40 launch complexes built here remain in use. Located at or near Cape Canaveral are the Kennedy Space Center on Merritt Island, used by NASA for Saturn V and Space Shuttle launches; Patrick AFB on Cape Canaveral itself, operated the US Department of Defense and handling most other launches; the commercial Spaceport Florida; the air-launched launch vehicle and missile Drop Zone off Mayport, Florida, located at 29.00 N 79.00 W, and an offshore submarine-launched ballistic missile launch area. All of these take advantage of the extensive down-range tracking facilities that once extended from the Cape, through the Caribbean, South Atlantic, and to South Africa and the Indian Ocean. More...

Cape Canaveral LC6 Chronology


1955 April 20 - . 06:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone RS-9. FAILURE: Guidance system malfunction at 310 sec due to air pressure loss. ST-80 lateral guidance only..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 7,000 m..

1955 May 25 - . 04:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone RS-10. FAILURE: Guidance system malfunction at 155, sec due to wiring error..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 17,200 m..

1955 August 31 - . 00:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone RS-7. FAILURE: Excessive temperature in tail section caused malfunction of jet vane control..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 540 m..

1955 September 22 - . 05:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-11. FAILURE: Excessive temperature in tail section caused malfunction of control.. Failed Stage: 1.
  • - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi). RS-11 was launched at 0051 hours EST from AMR after a three-hour hold. The flight was unsuccessful. The LOX container pressure and the combustion chamber decreased 50 seconds after lift-off. The temperature of Fin Number 1 went out of measuring range 72 seconds after lift-off. The servo battery current dropped to zero and the stabilised platform lost its reference. The range safety officer gave the emergency cut-off signal at 79 seconds. Impact occurred approximately 21,000 yards from the launch pad. The RS-11 was the first flight with the complete guidance system. Missed aimpoint by 118,800 m.

1955 December 6 - . 00:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-12.
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). RS-12 was launched from AMR at 1946 hours EST. The flight was successful. The actual range was 144.79 nm; .31 nm over; and 200 meters right of the intended impact point, The primary test objective was to test the complete guidance system. This was the first successful flight with the inertial guidance system. Missed aimpoint by 228,800 m.

1956 March 15 - . 00:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-18. FAILURE: Early cut-off caused by Incorrect guidance cut-off equation pre-setting. ST-80 gyro spilled at 310 sec..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). The first Jupiter A launching, by ABMA at Cape Canaveral. RS-18 was launched at 1936 hours EST from AMR. The flight was successful. The scheduled launching date of this missile was 13 March. Three holds were called because of LOX difficulties, telemetry difficulties, and replacement of a gate valve. The actual range was 133.58 nm; 10.3 nm under; and 5.66 nm right of the intended impact point. Separation occurred before the missile gained its correct velocity. Improper assumption of propellant flow for the trajectory calculation was primarily responsible for the incorrect cut-off. The primary test objectives were to test the complete guidance and control system to establish the performance qualities of the complete missile system. Missed aimpoint by 19,100 m.

1956 May 16 - . 04:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-19. FAILURE: Missile programmed to cut-off at fuel depletion - this combined with known stability problems caused excessive miss distance..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). RS-19 was launched at 2322 hours EST from AMR. The flight was successful. The actual range was 169.4 nm; 13 nm over the intended impact point. Cut-off wee given by the alcohol depletion switch that sensed alcohol injector pressure drop-off. Takeoff occurred 0.156 seconds after firing. The missile followed the correct trajectory with no obvious deviation. Missile cut-off occurred later than predicted and caused the missile to impact approximately 6.5 nm long, During descent the warhead turned left, causing impact to be several miles to the left of the aiming azimuth line. The primary test objectives were to test the angle-of-attack meter hardware (Jupiter control). Missed aimpoint by 25,100 m.

1956 August 8 - . 08:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-20.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). RS-20 was launched at 0325 hours EST from AMR. The flight was successful. The actual range was 139.72 nm; 0.3 nm over the intended impact point. The primary teat objectives were to test the accuracy of the guidance system and to acquire data for the establishment of design criteria for the Jupiter. This was the first time that the combustion chamber pressure was controlled. Missed aimpoint by 175 m.

1956 October 18 - . 09:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-14.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). CC-14 was launched at 0405 hours EST from AMR after a series of short holds. The flight was successful. The actual range was 137.870 nm; 72 meters over and 338 meters right: of the intended impact point. The primary objectives were to test the accuracy of the guidance system and to test angle of-attack meters for the Jupiter. Missed aimpoint by 346 m.

1956 October 31 - . 02:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-25. FAILURE: Malfunction of yaw gyro at approximately 10 sec. Ground cut-off command given.. Failed Stage: G.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 0 km ( mi). RS-25 was launched at 2104 hours EST from AMR. The flight was not successful. The behaviour of the missile appeared normal for the first 13 seconds, an early roll disturbance having been smoothly eliminated. Starting at 13 seconds after range zero, the gyro yaw signal indicated increasing yaw for a few seconds and the tracking devices at the same time showed increased displacement to the left of the standard trajectory. The malfunction apparently occurred between the yaw gyro potentiometer output and the outputs of the yaw amplifier of the mixing computer. The primary test objective was to test power plant performance. Missed aimpoint by 264,900 m.

1956 November 14 - . 02:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-28. FAILURE: Human error in propellant loading plus programmed fuel depletion cut-off..
  • Jupiter A/Sandia PL - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). RS-28 was launched at 2105 EST from AMR. The flight was successful. Actual range was 152.4 nm; 9.51 nm over; and 1.5 kilometres left of the intended impact point. The missile carried the LEV-3 rather than the ST-80 guidance system and used fuel depletion cut-off. The primary test objective was to test the Sandia payload. Missed aimpoint by 19,500 m.

1956 November 29 - . 13:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-15.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 0823 hours EST from AMR. The flight was successful. Actual range was 138.969 nm; .137 nm over and 122 meters left of the intended impact point, a radial miss distance of 260 meters. The primary test objectives were to test the accuracy of the complete guidance system and to test Jupiter control components. Missed aimpoint by 255 m.

1956 December 19 - . 02:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A RS-22. FAILURE: First experimental flight with Hydyne. Specific impulse exceeded predicted values. Re-entry system intentionally unstable to test Jupiter alpha control..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). The flight was successful, Actual range was 401.6 nm; 84.9 nm over the intended impact point. The missile used Hydyne fuel. The primary test objective was to test the control of an unstable missile configuration by using an angle-of-attack meter (boom type) in the ascending phase (Jupiter control). Missed aimpoint by 157,200 m.

1957 January 19 - . 01:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-16. FAILURE: Platform roll control malfunction at 310 sec..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 2037 hours EST from AMR. The flight was successful. Actual range was 61.6 nm; 400 meters left; and 0.21 nm over the intended impact point. The primary objective was to test the accuracy of the guidance system when the missile is fired in a short range trajectory at an extreme attitude to range ratio. The missile closely followed the predicted trajectory for a successful flight which terminated 70 meters beyond and 360 meters to the Left of the expected impact point at 61.553 nm range. The short range trajectory was programmed with an extreme altitude-to-range ratio so the guidance system would be subjected to the most difficult short range expected in future tactical application. Missed aimpoint by 400 m.

1957 March 14 - . 08:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-32. FAILURE: Platform interference caused control malfunction at re-entry..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). The first missile shipped directly from the Chrysler Factory to the test site to be flight tested was launched at 0312 hours EST from AMR The flight was successful. Actual range was 138.178 nm; 2.2 nm under; and 1250 meters left of the intended impact point. The missile functioned properly until 182 seconds when an unexplainable pitch deviation caused a slow tilting of the missile top section. The cut-off function at 120 seconds and the separation function at 135 seconds, after flight zero time, were both satisfactory. Missed aimpoint by 4,183 m.

1957 March 28 - . 01:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-30.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 2022 hours EST from AMR. The flight was successful from the standpoint of missions accomplished, with cut-off time 112 seconds and separation time 126 seconds after range zero time. Impact point was 220 meters short and 320 meters to the right, a radial miss distance of 390 meters, primary objective was to test the accuracy of the guidance system when the missile was fired in a short range trajectory at an extreme altitude to range ratio. Missed aimpoint by 390 m.

1957 May 15 - . 07:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter C. LV Configuration: Jupiter C RS-34. FAILURE: Loss of instrument compartment pressure at 134 seconds causing failure of pitch gyro prior to cut-off..
  • Jupiter re-entry vehicle test flight - . Nation: USA. Agency: USA. Apogee: 655 km (406 mi). The second three-stage re-entry missile, was launched at 0255 hours EST from AMR to test the thermal behaviour of a scaled-down version of the Jupiter nose cone during re-entry. The separated nose cone, which weighed 314 pounds, should have reached a nominal range of 1,212 nm. The missile began. to pitch up at 134 seconds, and impact was 420 nm short of the intended impact point. The composite missile consisted of three stages. The first stage was an elongated Redstone using alcohol and liquid oxygen as propellant. The second and third stages were made up of clusters of 11 and 3 scaled-down Sergeant solid propellant rockets, respectively. The nose cone was not recovered; however, instrument contact with the nose cone through re-entry indicated that the ablative-type heat protection for warheads was successful. Nose Cone Recovery Test

1957 June 26 - . 11:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-31. FAILURE: Human error in calculation of takeoff weight..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 0609 hours EST from AMR to test performance of the inertial guidance system, angle-of-attack meters, separation of explosive screws, and impact and radar fusing systems. Range instrumentation difficulties and deteriorating weather delayed the firing from the initially scheduled time of 0230 hours EST. The flight was successful. Actual range was 135.425 nm; 0.42 nm over; and 389 meters left of the intended impact point. Missed aimpoint by 785 m.

1957 July 12 - . 06:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-35. FAILURE: Control system malfunction at re-entry..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 0130 hours EST from AMR. The primary test objective was to test the accuracy of the guidance system. The flight was successful. Actual range was 130.125 nm; 0.15 nm over; and 285 meters left of the intended impact point. All missions were successfully accomplished. The missile followed the predicted trajectory very closely. Survey of the impact crater indicated a miss distance of 50 meters over and 284 meters to the left of the predicted impact point, giving a radial miss distance of 389.5 meters. Missed aimpoint by 289 m.

1957 July 26 - . 04:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-37.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 2317 hours EST from AMR. The flight was successful. Actual range was 126.227 nm; 147 meters under; and 182 meters left of the intended impact point. The primary test objective was to flight test warhead and fuse functioning as a system. A survey of the warhead impact point: indicated a miss distance of 147 meters short, 182 meters to the left of the predicted impact point, or a radial miss distance of 234 meters. Missed aimpoint by 235 m.

1957 August 8 - . 06:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter C. LV Configuration: Jupiter C RS/CC-40.
  • Jupiter re-entry vehicle test flight - . Nation: USA. Agency: USA. Apogee: 460 km (280 mi). First Nose Cone Recovery. Army-JPL Jupiter-C fired a scale-model nose cone 1,200 miles down range from AMR with a summit altitude of 600 miles. Recovery the next day of aerodynamic nose cone using ablation, resolved reentry heating problem for Jupiter missile. Nose cone was shown to the Nation on TV by President Eisenhower on November 7.

    Fired from AMR at 0159 hours EST, impacted at the predicted range. This success proved conclusively that the planned ablative-type heat protection for Jupiter warheads was satisfactory. The missile was a three-stage configuration--the first stage an elongated Redstone missile, the second and third stages 11 and 3 six-inch scaled Sergeant rockets, respectively. The one-third scale Jupiter nose cone was attached to the final stage with scheme for separation provided. The nose cone travelled to a 1,168 nm range, reached a velocity of 4,004 m/sec, and experienced a total heat input at stagnation point at 95% of that for the full scale nose cone at 1,500 nm. Naval units recovered the scaled nose cone according to plan.


1957 September 11 - . 02:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-38. FAILURE: ST-80 pitch program malfunction..
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at: 2141 hours EST from AMR. The flight was unsuccessful, The missile impacted 14.77 nm from the launch pad. Mechanical failure of the guidance tilt program caused the missile to assume a very steep trajectory which resulted La. a short range flight. Missed aimpoint by 111,000 m.

1957 October 2 - . 19:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-39.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Launched at 1429 hours EST from AMR. The flight was successful, the impact point was 445 metres long and 452 meters to the right of the predicted impact point, giving a radial miss distance of. 634 meters. This was the first flight test of the NAA A-6 engine with a sea level thrust of 78,000 pounds. Missed aimpoint by 572 m.

1957 October 31 - . 04:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-41. FAILURE: Loss of inter-compartment pressure at 68 sec. Ground cut-off command given.. Failed Stage: 1.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 40 km (24 mi). Launched at 2352 hours EST from AMR. The flight was unsuccessful. Actual range was 48 nm, whereas the predicted range wee 130.588 nm. At 68 seconds, a disturbance occurred in the lateral accelerometer and computer systems. Erroneous guidance instructions were transmitted to the control systems, causing a sharp yaw at 70 seconds. Cut-off was initiated at 98.1 seconds. One of the objectives was to indoctrinate troops for participation in the tactical portions of the countdown. Missed aimpoint by 151,000 m.

1957 December 11 - . 00:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-42.
  • Jupiter A - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 1936 hours EST from AMR. The missile followed the trajectory very closely and impacted on target. All missions were successfully accomplished. The predicted impact range was 141.895 nm. The miss distance has bean certified as 153 meters radial, 94 meters over, and 121 meters to the left of the predicted impact point. The primary objective of the rest was to flight test Hardtack adaptation kit components as passengers. Missed aimpoint by 209 m.

1958 January 15 - . 01:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-45.
  • Hardtack pod test - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 2024 hours EST from AMR. The flight was successful in that all missions were accomplished.. The missile followed its predicted trajectory closely. Impact was 370 meters over and 86 meters to the tight of the predicted impact point, a radial miss distance of 380 meters. This wee the fifth complete flight test of warhead and fuse system. Missed aimpoint by 286 m.

1958 February 12 - . 00:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-46.
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 1954 hours EST from AMR. The flight was successful in that all missions were accomplished, with the exception of the Hardtack adaptation kit mission. Impact was 258 meters over and 172 meters to the left of the predicted impact point, a radial miss distance of 310 meters. The primary objectives of the test were to test the warhead and fuse system and the guidance system. Missed aimpoint by 310 m.

1958 February 27 - . 19:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-43.
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 1459 hours EST from the AMR. The flight was successful in that all missions were accomplished. Impact was 461 meters over end 64 meters to the left of the predicted impact point, a radial miss distance of 466 meters. Missed aimpoint by 245 m.

1958 June 12 - . 01:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Jupiter A. LV Configuration: Jupiter A CC-54.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi).

1958 June 25 - . 03:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-48. FAILURE: Human error - thrust controller not connected..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Successfully fired at 2059 hours EST from AMR. The flight was a success in that all missions were accomplished with the exception of failure of the thrust governor. This failure was caused by human error before firing which caused excess velocity, thereby exceeding the predicted impact point by 8.36 nm. Programmed range to impact was 137.31 nm. All other missions were satisfactorily completed. Missed aimpoint by 14,917 m.

1958 September 17 - . 18:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-56. FAILURE: Programmed maneuver at re-entry and impact in deep water. Accurate survey not possible. CC-57.
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 990 m..

1958 November 6 - . 00:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-57. FAILURE: Boost phase normal. Space phase malfunction..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Redstone final development test. Missile test failure. Missed aimpoint by 5,010 m..

1959 October 1 - . 01:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Jupiter. Launch Vehicle: Jupiter. LV Configuration: Jupiter IRBM AM-24.
  • Research and development test - . Nation: USA. Agency: USAF; NASA Huntsville. Apogee: 500 km (310 mi). Fired from AMR at 2028 hours EST. The primary mission of impacting the nose cone in a pre-calculated target area was successfully accomplished . The missile covered a pre-calculated range of 1,299.4 nm, with the nose cone impacting within 1.25 nm of the predicted point. In addition to the usual ST-90 Stabiliser Platform, the missile carried a second system for relative accuracy and for drift investigations. It also housed a telemetry system. A significant mission was to determine environmental flight conditions.

1959 November 5 - . 00:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Jupiter. Launch Vehicle: Jupiter. LV Configuration: Jupiter IRBM CM-33.
  • Research and development test - . Nation: USA. Agency: USAF; NASA Huntsville. Apogee: 500 km (310 mi). Fired from AMR at 1938 hours EST to a pre-selected range of 1,299.4 nm. The nose cone impacted 0.56 nm short and 0.09 nm right of the impact point. The test successfully accomplished all intended missions. This was the first highly successful, Chrysler-assembled Jupiter fired in the test program sad was the first fired without static firing.

1959 December 10 - . 00:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Jupiter. Launch Vehicle: Jupiter. LV Configuration: Jupiter IRBM AM-32.
  • Research and development test - . Nation: USA. Agency: USAF; NASA Huntsville. Apogee: 500 km (310 mi). Summary: Fired from AMR at 1908 hours EST. The original countdown of 480 minutes was shortened to 240 minutes. The flight was successful in all phases. The nose cone impacted 0.3 nm over and 2.0 nm right of the 2,299.4 nm range..

1960 February 5 - . 00:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Jupiter. Launch Vehicle: Jupiter. LV Configuration: Jupiter IRBM AM-30.
  • Research and development test - . Nation: USA. Agency: USAF; NASA Huntsville. Apogee: 500 km (310 mi). Summary: The 28th R&D firing was from AMR at 1919 hours EST to a pre-calculated range of 1,299 nm. The flight successfully accomplished all primary and secondary missions. The nose cone impacted 0.65 nm short and 0.52 nm right of the intended target..

1960 March 22 - . 01:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2020. FAILURE: Control system malfunction during re-entry at 373 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 315 m..

1960 August 10 - . 01:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2023. FAILURE: Erroneously destroyed during boost by range personnel.. Failed Stage: G.
  • - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi). Summary: Missile test failure..

1960 October 6 - . 03:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2037. FAILURE: Control system malfunction during re-entry at 375 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 221 m..

1961 January 22 - . 02:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2038. FAILURE: Control system malfunction during re-entry at 370 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 788 m..

1961 March 9 - . 02:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2040. FAILURE: Control system malfunction during re-entry at 374 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 358 m..

1961 May 18 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2042.
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Successful missile test. Missed aimpoint by 304 m..

1961 June 27 - . 02:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC6. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone 2043. FAILURE: Air vane actuator malfunction at 262 sec..
  • - . Nation: USA. Agency: USA. Apogee: 90 km (55 mi). Summary: Missile test failure. Missed aimpoint by 1,044 m..

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