AKA: United States Army. Location: Washington, DC.
People: Brucker, Blaik, Toftoy, Schomburg, Barclay, James, Lee, Harr, Day, Low, George, Spring, Adamson, Clegg, Bailey, Voss, McArthur, Hennen, Clifford, Hawker, Gemar, Forrester, Linnehan, Belt, Hoffpauir, Williams, Jeffrey, Currie, Creamer, Wheelock, Kopra, Kimbrough. Country: USA. Spacecraft: Explorer A, Adam, Pioneer 3-4, Courier, SECOR, GGSE, DODECAPOLE, Snapshot, Aurora, TOPO, KE ASAT. Launch Sites: Mace South Korea, Mace Taiwan, Datil, Fort Bliss, Fort Greely, Neu Ulm, Schwaebisch-Gmuend, Waldheide-Neckarsulm. 1946 May 29 - . 21:12 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC33. Launch Vehicle: V-2.Launched 12:18 local time. Reached 104.8 km. Carried cosmic and soalr radiaiton, winds, photography experiments for Applied Physics Lab, John Hopkins University. The John Hopkins camera took motion pictures of the earth at over 100 km altitude (pictures covered 100,000 square km.)
Launched 11:16 local time. Reached 109.7 km. Carried pressure, ionosphere, sky brightness, biological, photo experiments for Air Research and Development Command. First of a series of V-2 firings known as Blossom Project, tested ejection of canister and its recovery by parachute, containing fruit flies and various types of seeds exposed to cosmic rays.
Launched 14:22 local time. Reached 142.7 km. Carried pressure, temperature (Signal Corps Engineering Lab, University of Michigan) experiments for General Electric. The warhead section was replaced with an instrumented full-scale replica of the cylindrical GE A-4 ramjet duct planned for the Hermes B ramjet missile.
Hermes B-1 impacts a graveyard 18.5 km south of Juarez, Mexico on its first test flight. This and the out-of-range V-2 impact on 15 May resulted in new safety measures at WSPG. 'We were the first German unit to not only infiltrate the United States, but to attack Mexico from US soil'. This vehicle was deeply classified at the time. Hermes experiments were conducted with modified V-2 rockets to test the configuration of a ramjet propulsion system. Four Hermes B-1 rockets were flown from Complex 33, none of which were noted in the contemporary records.
Launched 12:15 local time. Reached 156.5 km. Carried Solar radiation (Naval Research Lab); pressure, composition (SCEL) experiments for General Electric. General Electric engineers obtained the first carefully instrumented heat-transfer data from supersonic flight when this V-2 attained 1520 m/s.
Launched 03:22 local time. Reached 62.4 km. Carried pressure, temperature, composition, ionosphere, sky brightness, solar radiation experiments for Air Research and Development Command. Also carried Albert, the first American primate in space, who died of suffocation.
Launched 11:03 local time. Reached 87.1 km. Carried cosmic radiation, photo, pressure, temperature experiments for Applied Physics Lab, John Hopkins University. Fired from White Sands simultaneous with a Navy Aerobee which reached an altitude of 110 km. Both carried cameras which photographed the curvature of the earth.
Launched 15:34 local time. Reached 145.6 km. Carried biological (Harvard), solar radiation (Naval Research Lab), composition (Signal Corps Engineering Lab, University of Michigan) experiments for General Electric. The warhead section was replaced with an instrumented full-scale replica of the cylindrical GE A-4 ramjet duct planned for the Hermes B ramjet missile.
Fully fueled round used and attained highest altitude to that date. In addition to testing equipment the flight was used to measure upper air temperatures. V-2 reached 102 km, 1170 m/s; WAC 400 km, 2300 m/s. Provided information on ion densities in the F-region of the ionosphere.
Launched 08:15 local time. Reached 8.9 km. Carried Solar radiation (Naval Research Lab) experiments for General Electric. The warhead section was replaced with an instrumented full-scale replica of the cylindrical GE A-4 ramjet duct planned for the Hermes B ramjet missile.
Launched 15:35 local time. Reached 133.9 km. Carried cosmic and solar radiation, temperature, pressure, ionosphere, photo experiments for Air Research and Development Command. Second V-2 flight carrying a live AF Aero Medical Laboratory monkey, Albert II. The monkey survived but died on impact.
Launched 16:19 local time. Reached 4.2 km. Carried Composition, ionosphere, meteorites, solar and cosmic radiation, sky brightness, biological experiments for Air Research and Development Command. Third V-2 flight carrying a live AF Aero Medical Laboratory monkey, Albert III. The monkey survived but died on impact.
Launched 12:14 local time. Reached 130.6 km. Carried Composition, ionosphere, meteorites, solar radiation, sky brightness experiments for Air Research and Development Command. Last monkey, Albert IV, launched in V-2 series. The successful flight indicated no ill effects on monkey until impact of V-2.
Bumper No. 8, a German V-2 with a 320 kg Army-JPL Wac Corporal, was fired from the Long-Range Proving Ground at Cape Canaveral at a very low angle of attack. The first-stage V-2 climbed 16 km before it exploded. The second-stage Corporal separated successfully, however, and traveled another 24 km. This was the first missile launch from Cape Canaveral.
Bumper No. 7 was the second missile launch from Cape Canaveral. This was to be a maximum range test of a two-stage vehicle, to study the problems in staging. The launch was delayed because of moisture in the vehicle. But when finally launched, the WAC achieved the highest sustained speed in the atmosphere to that date (Mach 9/2500 m/s) and 35.2 km altitude before impacting 305 km downrange.
Launched 10:09 local time. Reached 136.8 km. Carried Ionosphere, meteorites, sky brightness, density, biological experiments for Air Research and Development Command. Last of five Aeromedical Laboratory experiments (first four known as Albert series), it carried a nonanesthetized mouse, photographed by a camera, which survived the impact.
Launched 00:33 local time. Reached 78.2 km. Carried composition, pressure, magnetic field, solar radiation; cosmic radiation (National Institute of Health); sky brightness (Air Research and Development Command) experiments for Naval Research Lab. V-2 number TF-2 was flown as contractor vehicle 59.
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.
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.
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.
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.
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.
First Jupiter C (a three-stage ABMA-JPL Redstone missile) was launched at Cape Canaveral, Fla., attained an altitude of 1096 km and traveled 5,300 km downrange. The first three-stage re-entry missile, was fired at 0145 hours EST from AMR. This missile attained an estimated range of 3,335 ST miles, an altitude of 682 ST miles, and reached Mach 18 velocity. The primary objective of the firing was the propulsion and separation tart of a multi-stage vehicle. The missile was a four-stage configuration with the last stage inactive. The first stage was an elongated Redstone missile, the second and third stages were up of 11 and 3 six-inch scaled SERGEANT rockets, respectively. The payload consisted of approximately 20 pounds of instrumentation attached to the inactive fourth stage. The flight was successful and the sequence of operations occurred as programmed. This vehicle could have obtained sufficient velocity to place it in orbit, if the last stage had been activated. First deep penetration of space. Serial number coding for early Redstones and related vehicles used the following substitution cipher: 1234567890 = HUNTSVILLEX
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.
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.
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.
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.
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.
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.
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.
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.
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
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.
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.
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.
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.
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.
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.
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.
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.
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.
Explorer I, the first U.S. earth satellite, was launched by a modified Army Ballistic Missile Agency Jupiter-C. Explorer I, developed by the Jet Propulsion Laboratory, carried the U.S.-IGY (International Geophysical Year) experiment of James A. Van Allen and resulted in the discovery of the radiation belt around the earth.
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.
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.
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.
Teak was a rocket-launched test of a live W-39 nuclear warhead. Purpose was to measure the effects of high altitude nuclear explosions in order to design warheads for the Nike-Zeus anti-ballistic missile system. The Hardtack Configuration Redstone shot the 3.8 megaton warhead to an altitude of 77.8 km. This was the first rocket-launched nuclear test by the United States.
Orange was a rocket-launched test of the W-39 warhead. Purpose was to measure the effects of high altitude nuclear explosions in order to design warheads for Nike-Zeus anti-ballistic missile system. The Hardtack Configuration Redstone shot the 3.8 megaton warhead to an altitude of 43 km.
Army fired its Pershing solid-fuel tactical missile from Cape Canaveral on a 200-mile flight, testing accuracy, warhead components, and blast and heat factors at launch in relation to operational crew protection. This was the seventh straight successful firing of the Pershing.
Redstone launched as ballistic missile target for a US Navy Terrier surface-to-air missile launched from Point Mugu, California. It was reported that there were two Redstone launches as part of Project Defender from November 30 to December 13, 1965, but details of the second launch are not known.
A Martlet 2C launched from the 16 inch L86 gun established the world altitude record for a sub-orbital gun-launched projectile. A Martlet 2C was fired to an altitude of 180 km with a flight time of over 400 seconds. Launched from Yuma Proving Ground, Arizona - Latitude: 32.87 N, Longitude:114.32 W.
An Atlas F/Burner IIA launch vehicle, carrying SAMSO's Space Test Program Flight 72-1, was launched from Vandenberg. This was the first use of this booster/upper stage combination. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
An Athena H was launched from Wake Island in the HAVE MILL program, the Army Special Targets Program. This was the seventh Athena H launched in support of Army requirements and the final programmed use of the Athena H test missile by SAMSO*s Deputy for Reentry Systems.
During the mission the TRW team monitored a mission telephone com channel real time in Redondo Beach. Participants recall the intense, "nail biting" anxiety as they waited the approximate 30 minutes it took for the RV to reach the nominal intercept point, over the Pacific and closer to Hawaii than to Kwajalein Atoll. Launch of the Minuteman I target from Vandenberg AFB came at 1803:00.3, launch of the ERIS interceptor at 1824:24.2, and kinetic intercept over Pacific at 1832:08.2.
This second test or ERIS against a Minuteman I was considered successful enough that no further tests were planned. A second launch attempt on 11 May 1991 had been scrubbed after launch of the target missile but before launch of the interceptor. Further develoment of the technology was to be accomplished by the Orbital Sciences' Aries test vehicle with spectacularly poor results.
After deploying the TERRIERS satellite, the conical Payload Adapter Fitting (1998-26E) was jettisoned at 05:21 GMT, leaving the disk-shaped MUBLCOM satellite attached to the Pegasus XL PRIMEX HAPS-Lite stage. The second HAPS burn at 05:22 GMT raised apogee to 775 km, followed by a third, apogee burn at 06:10 GMT which circularised the orbit. MUBLCOM was deployed to a 769 km x 776 km x 97.7 degree orbit. The final HAPS burn then placed the depleted HAPS stage in a lower 388 km x 722 km x 97.1 degree disposal orbit. MUBLCOM (Multiple beam Beyond Line-of-sight Communications) was an experimental satellite funded by DARPA and managed by the US Army's Communications-Electronics Command (CECOM) at Ft Monmouth, New Jersey. It was built by Orbital Sciences using the Microstar (Orbcomm type) bus and carries a payload testing hand-held radio satellite communications for the armed forces.
Six years later MUBLCOM was the target for the DART Autonomous Rendezvous Technology mission. On April 16, 2005, DART closed within 100 m of MUBLCOM satellite, then evidently began a series of out-of-control maneuvers resulting in an in-space collission and MUBLCOM being bumped into a 3 to 5 km higher orbit. DART was deorbited while MUBLCOM, still functioned, continued on in space. Air dropped in Point Arguello WADZ.
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