First launch attempt of MX-770 technology demonstrator. Seven rockets were built in total. There is very inconsistent information on the flight series. One source speaks of six launches, another of four, and a third of three. It seems that there were six launch attempts, three of which never made it very far off the pad, two made it some distance aloft, and only one was considered somewhat successful (reaching Mach 2.23 and an altitude of 18 km).
Full-range test with final dive maneuver. Swan song of vehicle eight after three successful recovered missions. During takeoff the vehicle was aloft, then settled back to the runway with its brakes locked. The tires burst, the gear failed, the gear doors were in contact with the runway, carving grooves in the pavement as they retracted. Then, astonishingly, the vehicle rose from the runway, completed a successful full-range supersonic flight with terminal dive into the waters off Grand Bahamas.
Continuing problems with APU reliability delayed the launch to November. Various problems extended the countdown from the planned 7 hours 30 minutes to 14 hours 30 minutes. Successful launch, then vehicle pitched up and disintegrated 26 seconds after launch, impacting 4 km down range. It was found the pitch rate gyro had been installed backward.
The first Jupiter flight was fired at 1651 hours EST from AMR. The missile achieved a 48,000 foot altitude. Flight terminated at 7.4 seconds because of missile break-up. Failure was attributed to overheating in the tail section. The trajectory to this point was as predicted.
G-26 number two / booster 6 lifted off after a 9 hour 48 minute countdown with nearly five hours of holds, on the first attempt after two successful static firings. However failure of a launch lanyard meant the kerosene start-pod on the booster remained attached. This sheared off at 4500 m, causing extensive booster damage. Thrust decayed. The cruise stage separated at Mach 1.3 at 28,300 feet, but this was below ramjet ignition speed. However the pilot on the ground was able to assume radio control of the vehicle, and flew it in a glide over the ocean, even demonstrating landing gear deployment before it pancaked into the water.
The second Thor flight test missile launched on the Atlantic Missile Range (AMR) was successful until the Range Safety Officer (RSO) accidentally destroyed the missile. Douglas Thor IRBM (XSM-75) was launched at Cape Canaveral, Fla., destroyed by range safety officer. The missile was actually on course throughout its flight. The console wiring error led the range safety officer to believe it was headed inland rather than out to sea, so he hit the destruct button.
Vehicle 4 was still not ready for the first Broomstick flight, so vehicle 5 was substituted. It took five attempts before a 15.6 second static test cleared the booster for launch on 29 March. 8 hours and 42 minutes of hold stretched the five-hour countdown out into the evening. The booster ignited, rose 1.3 m, then shut down. The vehicle fell back onto the pad, exploding. Cause was a 15-second timer that was supposed to shut the engines down 15 seconds after the vehicle hold-downs released if a lanyard had not been pulled free of the vehicle as it rose off the ground. The 15 seconds had been reached before the lanyard pulled free, but by then the vehicle had risen off the pad. This made 15 attempts to launch a Navaho, with only two booster ignitions, both resulting in loss of the vehicle. The Northrop crews at the Cape dubbed their competitor the "Never-Go Navaho" to counter jibes directed at them about the "Snark-infested waters" off the launch area. The Air Force was not amused, and had a tiger-team review of the G-26 on a system-basis which recommended several procedures. Meanwhile G-38 launch plans were further delayed over internal USAF wrangles over launch facility construction.
Army Jupiter IRBM was fired 1,500 miles, limit of its designed range, and to an altitude of 250-300 miles, the first successful launching of an IRBM. Fired from AMR at 1308 hours EST to test the range capability and performance of rocket engine and control system. Although the missile was 253 nm short of its estimated 1,400 nm impact point, this was the first successful flight of the Jupiter. All phases of the test were successful during this first firing of the IRBM in the western world
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.
The missile launched from the repaired LC-9 on the third attempt. At T+42 seconds, Mach 1.63, and 7,000 m altitude, a fire occurred in the engine compartment after a failure of a regenerative cooling valve to the gas generator. The turbopump shut down, and one engine went out. Nevertheless the vehicle continued, first on one engine, then coasting, to 12,000 m altitude, and the booster separated successfully. But the cruise stage was below ramjet ignition velocity. Again ground control could bring the cruise stage under control as a glider, flying it to an impact 87 km downrange
After a 15 hour 18 minute countdown G-26 number four finally left the pad. The boost phase was completed successfully; but then a guidance system malfunction prevented the cruise stage from separating from the booster until an altitude of 25 km was reached. However the autopilot successfully overcome drastic pitch oscillations created by the lofted trajectory, and the ramjets were successfully ignited. The stage cruised at Mach 2.93 for 280 km. However then the vehicle began drifting off course. The ground pilot banked, but the fuselage screened the airflow to the left ramjet intake, resulting in that engine flaming out. The vehicle lost speed and altitude, and the right engine flamed out a minute later. The missile was ordered into a terminal dive, impacting 425 km downrange.
The fourth Jupiter was fired from AMR at 1602 hours EST over IRBM range and was the second successful flight of the series. The range error was 27.5 nm with a 36.5 nm lateral error. Range was predicted for 146 nm. LOX was cut off at 170 seconds. All flight missions were fulfilled satisfactorily. Separation occurred 5 seconds after burnout, as programmed, This was the first test of separation of body from thrust unit.
The booster worked well, the cruise stage separated at 23.5 km altitude. The ramjets ignited, and the cruise stage accelerated to Mach 3.5. After 15 minutes, the missile began drifting off-course, and ground control took over and banked the missile. One of the ramjets flamed out, and the missile was commanded into a terminal dive and impacted 930 km downrange.
First fully successful test flight of Thor intermediate range ballistic missile. (AF Ballistic Missiles Program Status Report.) After four failures, the fifth Thor flight test missile (#105) successfully demonstrated all on-board systems. The engine operated 137 seconds to automatic shutdown, and missile impacted 1,300 nautical miles down range from Cape Canaveral. Complete USAF Thor IRBM first successfully launched from Cape Canaveral. Dummy Warhead sent to 1800 km range.
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.
USAF successfully launched pellets at a speed faster than 15 km/sec (some 3.5 km/sec faster than the velocity necessary to escape from the earth) by an Aerobee rocket to a height of 56 km; the nose section then ascended to a height of 87 km where shaped charges blasted the pellets into space. It is claimed that the Superschmidt Telescope at Sacremento Peak photographed the trajectory with a rotating shutter. These little metal pellets would therefore be the first objects to be shot into interplanetary space, months before the first launch to escape velocity (Luna 1, January 1959). But also see August 1957 nuclear test that may have blasted a manhole cover to escape velocity.
The fifth Jupiter was fired from the AMR at 2007 hours EST. This was the first flight with a heat protected nose cone. The ST-90 inertial guidance stabilised platform was operated with partially closed circuits. Cut-off was effected by the guidance system at 170.37 seconds. Since fuel was not depleted, flight time was 9.5 seconds longer than had been predicted for an approximate 1,100 nm range. The range error was 10.2 nm with a 3.4 nm lateral error. The nose cone survived re-entry and impacted in the general vicinity of the predicted impact point. Again, a successful flight.
The booster functioned well, and the cruise stage separated at 20.4 km altitude and Mach 3.24. The ramjets ignited, but before the ground knew that, the telemetry dropped out completely due to a faulty voltage regulator on the missile. Range safety ordered the missile's self destruction at T+75 seconds.
Fired from AMR at 2110 hours EST. Main stage, lift-off, and powered flight were normal. The missile passed through the critical dynamic pressure period and followed the prescribed trajectory until 202 seconds of flight when the engine thrust was terminated. From an analysis covering the period before thrust termination, mechanical failure of the turbo-pump stopped the flow of propellants to the combustion chamber causing a complete loss of thrust. Telemetry signals ceased at 232 seconds. The missile was at an altitude of 65,000 feet when an explosion was observed from the Test Centre above the horizon. The long range mission of this flight was not accomplished; however, other primary and secondary missions were considered successful.
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.
Fired from AMR at 1507 hours EST. The main-stage, lift-off, and powered flight were normal. The missile followed the prescribed trajectory. Thrust ended abruptly at 116.87 seconds of flight which resulted in a short-range impact. Failure was again attributed to turbo-pump malfunction. The long-range mission. was not accomplished; however, other primary and secondary missions were successfully accomplished. The abrupt shutdown of the power plant resulted in a range of approximately 149 nm and an altitude of approximately 50 nm.
The eighth Thor flight test missile, the fourth success, completed the first fully-guided flight using an all-inertial guidance and control system. A Thor missile, the eighth tested and the fourth successfully, completed the first fully-guided Thor IRBM flight using an all-inertial guidance system.
The booster functioned well, the cruise stage separated at 22 km and Mach 3.15. The ramjets ignited and the cruise stage flew at a sustained speed of Mach 2.8 for forty minutes over a distance of 2000 km. Then the vehicle began a turn for the return to the Cape for recovery. However it seemed the turn was not fast enough; ground control took over, and yet again the right ramjet flamed out in a ground-piloted bank. The missile was commanded into a terminal dive at sea.
The first Thor/Able missile, a special test vehicle designed to examine an improved General Electric lightweight, ablative nose cone at full ICBM ranges failed. Mouse 'Mia' not recovered. This was the first small beginning of a research program to determine the requirements of a space life support system. (Msg SAFIS-3C 47151, SAF to AFBMD, 29 Apr 58.)
AM-5, carrying America's first tactical type re-entry nose cone, was fired from AMR at 0005 hours EST. This was also the first flight test. for first and second stage separation. Impact was 28.3 nm under and 15.6 nm to the right at a range of about 1,275 nm after approximately 960 seconds of flight. In less than five hours, the nose cone was recovered - the world's first recovery of an IRBM nose cone.
The final Series A Atlas missile (16A) was launched from Cape Canaveral. Of the eight research and development launches, five had been failures, but each had provided vast quantities of important data. Last Atlas A flight, considered fully successful. Four of the eight flights were considered successful.
The first Air Force Thor IRBM flight test missile (Number 115) to be fired from a tactical-type launcher was launched at Cape Canaveral. The missile completed a successful flight, impacting 1,170 nautical miles downrange. This was also the first Thor to be launched without a flight readiness firing of its propulsion system. USAF Thor flight tested for the first time from a tactical-type launcher at Cape Canaveral.
In a US Air Force briefing a preliminary astronaut selection for the Man-In-Space Soonest project is made. The list consisted of USAF test pilots Robert Walker, Scott Crossfield, Neil Armstrong, Robert Rushworth, William Bridgeman, Alvin White, Iven Kincheloe, Robert White, and Jack McKay. This was the first preliminary astronaut selection in history. The project was cancelled when NASA was formed in and took responsibility for all manned space flight on 1 August 1958. Prospective contractors estimated it would take from 12 to 30 months to put the first American in orbit. In retrospect the orbital flight portion of NASA's Mercury program was paced by the availability of the Atlas booster. Therefore it is unlikely Man-in-Space-Soonest would have put an American in orbit any earlier than Mercury.
Mouse 'Mia II' reached 1600 km altitude, flew 9600 km range, but re-entry vehicle not recovered. The second Air Force Thor/Able reentry (nose cone) test vehicle, testing a GE ablation-type nose cone, was launched from Cape Canaveral on a 6,000-mile flight down the Atlantic Missile Range. This was the first U.S. reentry vehicle to make a full-range ICBM flight and reentry.
Fired from AMR at 0404 hours EST to a pre-calculated range of 1,241.3 nm. The nose cone impacted 1.0 nm short and 1.5 nm to the right of the predicted impact point. This was the first flight test of the complete inertial guidance system. The nose cone recovery mission was successful. This was also the second successful flight test of a full scale tactical type nose cone, as well as a successful flight test of the Jupiter lightweight, high explosive warhead.
The initial Atlas Series B missile flight test vehicle (3B) malfuncticr.ed and broke up 60 seconds after launch from the Air Force Missile Test Center at Cape Canaveral. To the basic Series A airframe, the Series B missiles added the complete North American Aviation MA-1 propulsion cluster of booster and sustainer engines, General Electric's Mod II airborne radio inertial guidance system (open loop), and GE's Mark II nose cone. First full-powered flight of USAF Atlas B ICBM using both the sustainer and booster engines. 'Marginally successful'.
In its second successful flight test, the Thor/Able (Number 1.19) advanced reentry test vehicle demonstrated proper reentry of the advanced General Electric ablative nose cone during a 5,300-mile test flight. Two successful tests established the two-stage Thor/Able as a reliable vehicle for further special test programs. This allowed the Air Force and other government agencies to complete plans for more advanced space programs. Mouse 'Wickie' not recovered; nose cone lost.
The first successful flight test of a Series B Atlas missile. This was also the first successful staging of a long-range missile. (AF Ballistic Missiles Program Status Report.) Flight test missile 4B was the first Atlas Series B missile to be launched successfully and the first ICBM to complete staging. Its 2,500-mile powered flight was the first time that the MA-1 propulsion cluster operated for the planned duration of flight. Second full-powered flight of USAF Atlas ICBM traveled 2,500 miles with radio-inertial guidance, fully successful.
An Air Force Thor/Able It launch vehicle, carrying the first U.S. International Geophysical Year (IGY) lunar payload, exploded 77 seconds after liftoff from Cape Canaveral because of a first-stage engine failure. First US lunar attempt. The first US Air Force lunar probe, using a Thor-Able booster. An explosion ripped it apart 77 seconds after launch.
Fired from AMR at 1815 hours EST. The countdown was normal. Operations were interrupted by one hold -- a 15 minute delay for minor adjustments. Ignition, main-stage, and lift-off were normal. The missile followed the pre-selected trajectory closely during powered flight, though cut-off was effected by fuel depletion rather than by pre-set guidance cut-off. The nose cone impacted 39 nm short and 15.7 nm to the left of the pre-calculated range of 1,246 nm. Jupiter 7 was the first flight test of the warhead and fuse system. This also marked the second flight test of the :Jupiter all-inertial guidance system, the fourth flight test of the NAA S-3D engine operating at 150,000 pounds thrust, and the first flight test of the solid propellant spin rocket and vernier motor.
North American had received funding to fly seven surplus G-26 missiles in a program dubbed RISE (Research Into Supersonic Environment), ostensibly to obtain real-world data on Mach 3 flight for the F-108 interceptor and B-70 bomber that they were developing for the USAF. On this first attempt, the booster performed well, but after separation the cruise stage fuel system failed, and ramjet ignition never occurred. The cruise stage impacted 150 km downrange.
The remaining X-10's were expended as targets for Bomarc and Nike antiaircraft missiles. The X-10 flew out over the ocean, then accelerated toward the Cape at supersonic speed. A Bomarc A missile came within lethal miss distance. The X-10 then autolanded on the Skid Strip, but both the drag chute and landing barrier failed. The vehicle ran off the runway and exploded.
Fired from AMR at 2249 hours EST. The missile was destroyed after 49 seconds of erratic flight caused by fire in the tail section. The fire was believed to have started by a pin-hole leak near the thrust transducer which burned through the fuel and LOX transducer lines. This was the first Jupiter missile to use swivelled turbine exhaust for roll contral, also first use of solid vernier control.
Gordo launched into space. Fired from AMR at 0353 hours EST. The missile's nose cone impacted in the pre-selected target area at a range of approximately 1,302 nm. The significant mission of the missile was the flight of a South American squirrel monkey `Gordo' up to and down from outer space. Although nose cone recovery efforts failed because the float mechanism attached to the nose cone did not function, telemetry data provided useful biomedical information and disclosed that the Navy-trained squirrel monkey had withstood the space flight and reentry phase without any adverse physiological effects. Gordo was in a weightless state for 8.3 minutes, he experienced a 10g pressure in takeoff, and a 40g pressure upon reentry at 10,000 miles per hour. The flight was considered one of the outstanding achievements of space research. The impact was 5.2 nm over and 0.75 nm to the right of impact point. The overshoot was caused by interaction which occurred at separation between the booster and aft sections. A temporary cable connecting the two bodies had not been removed prior to launch.
Tactical Test. The first Chrysler production qualification missile was fired from AMR at 1910 hours EST. The nose cone impacted in the pre-selected target area at a range of 1,302 nm. Miss distance was 3 nm over and 1 nm to the left of the target. The overshoot was caused by failure of the vernier engine to cut off high resistance of the squib firing circuit. Primary missions were successfully accomplished.
Fired from AMR at 1850 hours EST. The primary mission of impacting the nose cone in a pre-calculated target (MILS Network) was successfully accomplished, The nose cone impacted in the 1,302 nm target area, 2.8 nm over, with no lateral deviations. Again, the vernier engine ran to cut-off rather than the commanded 14 seconds -- a near perfect flight. For the first rime, missile roll was controlled by a turbine exhaust nozzle designed to eliminate problems experienced on previous flights.
In the first use of a Thor as a space booster, the world's first polar orbiting satellite, Discoverer I, was launched by a Thor/Agena (Thor 163) booster combination from Vandenberg AFB. The mission was also the first successful flight test of Lockheed's Agena A upper stage vehicle designed for orbiting U.S. satellite systems.
Fired from AMR at 1934 hours EST. The primary mission of impacting a nose cone in a pre-calculated target area (MILS Network) was successfully accomplished with an impact of 0.8 nm under end 5.0 nm to the left of the 1,302 nm range. The lateral miss was believed to have been caused by a drifting gyro.
A Thor/Able reentry test vehicle launched from Cape Canaveral, Florida, completed a successful flight down the Atlantic Missile Range. The reentry body of the Thor/Able was recovered at the far end of the range in the South Atlantic. This was the first recovery of an ablative nose cone following an ICBM-range flight.
The first Atlas D model flight test missile (3D) had to be destroyed 36 seconds into flight due to a severe engine malfunction and explosions. In addition to other changes, the D series replaced the MA-1 engine package with the Rocketdyne MA-2. The booster engines in the MA-2 produced 309,000 pounds of thrust versus 300,000 pounds for the MA-1. Sustainer engine thrust remained 57,000 pounds. With verniers, total thrust for the MA-2 was 368,000 pounds compared to 357,000 for the MA-1 engine package.
Fired from AMR at 2047 hours EST. All primary missions were essentially successful, although the impact was 69 nm short and 4.9 nm to the right of the 1,302 nm predicted impact point. This undershoot was due to thrust controller deviation which commanded the exceedingly high thrust level during the main power flight pre-selected flight path. Cut-off occurred at 144 seconds of flight.
Fired from AMR at 0052 hours EST to test impact accuracy. This shot may be considered as having hit the target. The impact was: .26 nm over and 0.4 nm to the left of the predicted point of impact. Accuracy of the MILS Network was approximated at plus-or-minus 0.25 nm. All primary and secondary missions were accomplished except for photographic recording of the second separation. This could not be accomplished because of the firing date.
Able and Baker recovered after spaceflight. Fired from AMR at 0235 hours EST. The flight was successful with impact ranging from 0.1 to 0.4 nm from the target. The missile travelled a 1,302 nm range. The significant mission of the missile was to test the effects of cosmic radiation, increased gravity, and weightlessness on live passengers and biomedical experiments of material housed in the nose cone. On board were an American-born rhesus monkey, Able; a squirrel monkey, Baker; and the biomedical experiments -- yeast , corn, mustard seeds, fruit-fly larvae, human blood, mould spore, and fish eggs. Able and Baker were recovered unharmed within one and one-half hours after lift-off. This milestone marked the first recovery of living creatures from a flight through near space. The biomedical experiments were for NASA analysis. Telemetry data disclosed that the responses of the animals were normal for the conditions they were experiencing. During the boost phase, when the higher g-loads were being sustained, body temperature, respiration, pulse rate, and heartbeat rose but were well within tolerable limits. During the weightless period along the trajectory arc, the physiological responses of Able and Baker approached normal - so near, in fact, that according to telemetry data, Baker appeared either to doze or to become drowsy. Upon reentry, the responses rose again, but at landing the animals were nearing a settled physiological state. This flight was another milestone proving that life could be sustained in a space environment.
Fired from AMR at 2001 hours EST to test missile accuracy. All primary and secondary missions were successfully accomplished and impact was well within 1 nm of the pre-selected point, approximately 1,302 nm downrange -- a miss distance of only 0.48 nm short and 0.09 nm to the right.
The first full-scale test of an ablation reentry vehicle (RVX-2) was conducted with the launch and successful flight of Atlas 8C. Following the 4,385 NM flight into the South Atlantic, the reentry vehicle was recovered. A full-scale USAF Atlas ICBM nose cone recovered for the first time after flight down the AMR.
Titan missile B-5, scheduled to be the first fully powered-flight test missile, was heavily damaged when a faulty release mechanism allowed an earlier-than-planned liftoff that resulted in engine shutdown and the missile's dropping back on the launch pad.
The final Atlas Series C missile, 11C, was fired from Cape Canaveral. Three of the six Atlas C research and development test missiles were successful, while the other three were failures. Last successful Atlas C flight (11C); 9C exploded one month later during the Able static firing.
A short range (300 nm) IRBM, was fired from AMR at 2030 hours EST. The nose cone impacted 0.03 nm short and, 0.22 nm to the right, of the intended target. This was the first Jupiter missile to be programmed for a short range flight. All primary and secondary missions were accomplished.
A NASA boilerplate model of the Mercury capsule was launched atop Atlas 10D from Cape Canaveral. Although the range was less than planned due to failure of the Atlas booster engine section to separate, the capsule was recovered in the South Atlantic after surviving reentry heat of more than 10,000°F.
The first silo launch of a tethered, full-scale Minuteman missile was conducted at Edwards AFB, California, using dummy second and third stages. This was the first time in the Air Force ballistic missile program that the initial test of a missile was conducted on schedule. Fuel for 3 seconds only, tethered launch
A participant remembers:
I live near the Cape on Merritt Island and have been here for about 41 years. I worked for the ARMA Corp that developed the Atlas Inertial Guidance System. I was in the Blockhouse at Complex 11 while a static test was performed on an Atlas Able on Complex 12. It did explode. Did it ever! After a couple of hours the six of us were allowed out of the blockhouse and saw all the damage to our complex...I had a tiny piece of that missile for a long time that somehow wound up on my person...labeled 9C.
The next Atlas Able would not fly until over a year later, using the Atlas D as the booster stage.
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.
The first full range tactical prototype, was fired from AMR at 2220 hours EST. All missions assigned to the flight was successfully accomplished. The missile covered a prescribed range of 1,600.448 nm, with the nose cone impacting 0.9 nm short and 0.6 nm to the right. This was the fourth Chrysler-assembled missile to be flight tested.
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.
Fired from AMR at 1948 hours EST to a prescribed range of: 1,299.4 nm. The nose cone impacted 0.04 nm over and 3.27 nm to the left. All missions were successfully accomplished despite elevated temperatures in the tail section. The primary mission of this flight was to test the two-way deflector launch section and to analyse elevated temperatures in the tail
Titan test missile B7A completed a 2,200-mile flight, achieving successful staging and ignition of the second stage engine at high altitude. The Stage II engine, XLR-91-AJ-1, performed as planned, and the missile impacted almost exactly on target. This was the first successful Titan launch and flight since 4 May 1959.
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.
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.
Atlas 56D carried a 3,000-pound payload 7,859 nautical miles (9,040 statute miles) from Cape Canaveral to the target area in the Indian Ocean. This was the longest U.S. missile flight to date. Payload was an operational weight nose cone plus instrumentation. Missile attained an apogee of about 1,000 miles.
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.
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.
A Thor/Agena A launched from Vandenberg AFB placed Discoverer XIII in orbit. On 11 August, the data capsule was ejected during the 17th pass and recovered Pacific Ocean near Hawaii by a Navy helicopter that was part of the 6593d Test Squadron's task force. Although the planned mid-air recovery was not made, the return of Discoverer XIII1s data capsule marked the first successful recovery of a man-made object ejected from an orbiting satellite. KH-1 prototype; designed to test capsule recovery system; did not carry camera; capsule successfully recovered from ocean.
The first successful launch and flight of an operational prototype Titan I occurred on 10 August 1960. After two previous failures, Titan missile J-7 was the first operational prototype to be launched and complete a successful flight test down the Atlantic Missile Range. Titan 1 J (Mk 4 RV)
Maximum Speed - 2851 kph. Maximum Altitude - 41605 m. Established a new altitude record for a manned vehicle of 136,500 feet. This topped Captain Kincheloe's record altitude of 126,200 feet attained on September 7, 1956, in the X-2 rocket research aircraft. Air dropped in Silver Lake DZ.
The second Thor/Agena B to be launched from Vandenberg AFB was the first successful flight of the more advanced Lockheed Agena B upper stage. KH-1; film capsule recovered 2.1 days later. Mission failed. Obtained orbit successfully. Film separated before any camera operation leaving only 1.7 ft of film in capsule. On December 2, the Air Force revealed that exceedingly valuable information had been obtained from human tissues carried by Discoverer 17 (the cover story for the mission). The tissues had been exposed to an unexpectedly heavy dose of radiation for more than 50 hours in flight.
The flight testing of the Series D Atlas missiles was completed with the successful launch and flight of Atlas 90D from Cape Canaveral. This was the 32d Atlas D to be launched in the research and development series and the 55th Atlas missile to be flown since the first attempted launch on 11 June 1957. During the flight test series to date, 35 missiles were flown successfully and 20 were rated failures. Final test flight of USAF Atlas D traveled 5,000 miles to target down Atlantic Missile Range, representing 35 successes, 8 partials, and 6 failures in 49 test launchings for D model. 75th Atlas launched at AMR, successful
An Air Force Atlas D/Agena A was launched from Vandenberg and successfully placed the SAMOS II satellite into orbit. This was the last Air Force use of an Agena A upper stage vehicle. First generation photo surveillance; radio relay of images; micrometeoroid impact data. Poor results.
At 1059 EST, the first Minuteman research and development flight test missile (FTM 401) was launched by the 6555th Test Wing from Pad 31 at the Atlantic Missile Range. All the missiles stages and subsystems were operational, marking the first time that the first flight test missile was launched with all systems and stages functioning. FTM 401 completed a 4,600-mile flight, and its reentry vehicle impacted in the designated target area. This was the most successful first flight recorded in the history of U.S. missile development.
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.
Titan I (M-l) was the first Series M missile and first inertially-guided Titan missile to be launched from Cape Canaveral. Essentially a Titan I with a Titan II inertial guidance system, M-l was only a partial success due to a second stage hydraulic failure and loss of control after sustainer engine ignition.
MIDAS III (Missile Defense Alarm System) satellite was launched into polar orbit from Vandenberg AFB by the first Atlas D/Agena B booster (97D/#1201). This vehicle achieved a record 1,850-mile orbit and was the heaviest U.S. satellite put up to date. Missile Defense Alarm System.
The launch of Atlas 101D from Vandenberg AFB completed the initial operational capability (IOC) launch series for the Atlas D ICBM. In 11 launches, only five missiles were successful. The launch of Atlas 101D from Vandenberg AFB completed the initial operational capability (IOC) launch series for the Atlas D ICBM. In 11 launches, only five missiles were successful.
Small satellite was to have verified the readiness of the worldwide Mercury tracking network. An attempt was made to launch Mercury-Scout 1 (MS-1) into orbit with a communications package further to qualify the radar tracking of the Mercury global network prior to manned orbital flight. Shortly after lift-off, the launch vehicle developed erratic motions and attending high aerodynamic loads, and was destroyed by the Range Safety Officer after 43 seconds of flight. No further attempts were planned. The Mercury-Atlas 4 (MA-4) mission and the successful Mercury-Atlas 5 (MA-5), flown on November 29, 1961, disclosed that the network met all requirements.
The first Oscar Phase I amateur satellite was launched piggyback with Discover 36. A group of enthusiasts in California formed Project OSCAR and persuaded the United States Air Force to replace ballast on the Agena upper stage with the 4.5 kg OSCAR I package. The satellite was box shaped with a single monopole antenna and battery powered. The 140 mW transmitter onboard discharged its batteries after three weeks. 570 Amateurs in 28 countries reported receiving its simple 'HI-HI' morse code signals on the VHF 2 meter band (144.983 MHz) until January 1, 1962. The speed of the HI-HI message was controlled by a temperature sensor inside the spacecraft. OSCAR I re-entered the atmosphere January 31, 1962 after 312 revolutions. Additional Details: here....
First generation photo surveillance; return of camera and film by capsule; SAMOS type satellite. Reached orbit but failed to deorbit and be recovered. In his memoirs Sergei Khrushchev recounts recovery of what he believed to be a recoverable Samos, except the date given is the winter before tests of this configuration actually started. He relates that a second American capsule was recovered in the spring of 1961. It was equipped with a 30 cm lens and 100's of metres of 10 cm wide film. Also recovered were a pear-shaped module made of fibreglass, and an inertial orientation system powered by electric motors. It may have been a SAMOS prototype. The capsule was found by tractor drivers, who disassembled it and used the film to wrap around the frame of their outhouse to provide some privacy in the treeless area. Unfortunately this ruined the film, preventing the Russians from developing it and discovering the technical capabilities of the system.
Atlas 40E, the 18th and last Atlas E research and development flight test missile to be launched from the Atlantic Missile Range, completed its programmed 7,000-mile flight downrange. Of the 18 missiles launched, nine were successes, seven partials, and two failures. Last Atlas E R&D flight.
The 6555th Aerospace Test Wing launched the first Titan II (XLGM-25C) research and development flight test missile (N-2) from Cape Canaveral. The Titan II was the most powerful ICBM yet launched by the U.S., its first stage engines generating 430,000 pounds of thrust and the second stage engine 100,000 pounds. The flight of N-2 also marked the first successful test of the AC Spark Plug inertial guidance system. The Air Force successfully launched a Titan II intercontinental ballistic missile. This was the first full-scale test of the vehicle; it flew 8000 km out over the Atlantic Ocean.
Maximum Speed - 4586 kph. Maximum Altitude - 54860 m. The X-15 was flown in a test of a new automatic control system to be used in the Dyna-Soar and Apollo spacecraft. The previous electronic control system had been automatic only while the X-15 was in the atmosphere; the new system was automatic in space as well. Air dropped in Hidden Hills DZ.
OSCAR II was launched piggyback with a United States Air Force satellite. OSCAR II was very similar to OSCAR I. Differences included (1) changing the surface thermal coatings to achieve a cooler internal spacecraft environment, (2) modifying the sensing system so the satellite temperature could be measured accurately as the batteries decayed, and (3) lowering the transmitter power output to 100 mW to extend the life of the onboard battery. OSCAR II lasted 18 days ceasing operation on June 20, 1962 and re-entered June 21, 1962.
Initial attempt to launch a live nuclear weapon using the Thor IRBM from Johnston Atoll. The range safety radar had been unreliable before launch,. Five minutes after launch, after shutdown of the booster, the Johnston missile tracking system failed. Unable to monitor the warhead's flight path, the range safety officer destroyed it 10 minutes later, prior to warhead detonation.
The first Agena D (#1151) upper stage vehicle was successfully flown on a Thor booster (#340) launched from Vandenberg AFB. The Lockheed Agena D was a redesign of the basic Agena B and was intended to be the standard stage vehicle for most Defense Department and NASA programs. The program was begun in August 1961, revised and accelerated in November, and had its first flight in June 1962. KH-4; film capsule recovered 4.1 days later. Severe corona static.
Successful high-altitude test of a Thor IRBM with a live nuclear warhead. The payload included test instrumentation and a W-49 warhead/Mk-4 re-entry vehicle. The 1.45 megaton bomb exploded at an altitude of 400 km. The explosion was visible 2,600 km away, at Kwajalein Atoll; an artificial aurora lasted seven minutes. The unforeseen and most militarily significant effect was the electromagnetic pulse (EMP) generated by the test. This caused power mains surges in Oahu, knocking out street lights, blowing fuses and circuit breakers, and triggering burglar alarms (and this in the days before microelectronics). The explosion supercharged the Van Allen radiation belts, resulting in several satellites malfunctioning.
Second attempt to launch a nuclear weapon using the Thor IRBM. The payload consisted of two re-entry vehicles, one with an instrument pod, the other with the warhead. The missile engine malfunctioned immediately on ignition. Range safety fired the destruct system whille the missile was still on the launch pad. The Johnston Island launch complex was heavily damaged and contaminated with plutonium. Three months of repairs and decontamination were necessary before tests could resume.
The third attempt to launch a nuclear warhead using a Thor IRBM. At 86 seconds after launch a booster failure occurred and the missile began tumbling. Range safety destroyed the errant booster at 156 seconds after launch. Some radioactive fallout from the warhead was detected on Johnston Atoll.
On the fourth attempt, a Thor IRBM was used to launch a Mk 4 Re-entry Vehicle containing a 186 kg W-50 nuclear warhead of either 200 or 400 kilotons yield. The detonation occurred at an altitude of 50 km, 31 km SSW of Johnston Atoll. A fireball formed, the colourful afterglow continuing for 30 minutes of the explosion. At this altitude the extensive disruption of the ionosphere seen in later explosions did not occur.
A Thor IRBM was used to launch a Mk 4 Reentry Vehicle containing a 186 kg W-50 nuclear warhead of either 200 or 400 kilotons yield. The detonation occurred at an altitude of 98 km, 69 km SSW of Johnston Atoll, and resulted in dramatic aurora-like effects visible as far away as Hawaii. More notably, the explosion had a massive effect on the ionosphere which disrupted radio communications over the entire central Pacific for three hours.
This was a DOD sponsored live test of the Nike Hercules air defense missile system. The low-kiloton range W-31 warhead detonated at 21 km altitude 3 km SSW of Johnston Atoll. This was the last U.S. atmospheric test. On Johnston Island an intense white flash was accompanied by a strong heat pulse. A yellow-orange disc formed, slowly changing to a purple toroid which faded from view after several minutes.
When the high-voltage power supplies were first turned-on, intermittent high-voltage breakdowns occurred, and the beam power supply became inoperative. Post-flight examination of the power supply indicated the high-voltage breakdowns were probably caused by pressure buildup in the primary propulsion unit due to gas vented from the spacecraft batteries. The primary propulsion unit high voltage section was not adequately vented to keep the pressure low enough. Engine thrusting was not accomplished in this test.
An Air Force Thor/Agena B launched from Vandenberg established a number of distinctive records. It was the 200th Thor to be launched since Number 101 was launched at Cape Canaveral on 25 January 1957. It was the first, last and only-Thrust Augmented Thor/Agena B to be used by the Air Force. It was the final Agena B (#2314) to be employed with a Thor booster.
The Air Force launched its first Atlas D/Agena D from Vandenberg. This was the 100th Agena (Number 4702) space vehicle used since 28 February 1959. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Maximum Speed - 5969 kph. Maximum Altitude - 106010 m. Astronaut wings flight. 80 cm diameter balloon dragged on 30 m line to measure air density. First X-15 astronaut flight (FAI definition); fourth astronaut wings flight (USAF definition). Air dropped in Smith Ranch Lake DZ.
A Thor (SLV-2) booster lifted the first Aerothermodynamic/Elastic Structural Systems Environmental Tests (ASSET) program vehicle (ASV-1) on a successful suborbital flight from Cape Canaveral. The ASSET program was designed to test materials and study flight characteristics of glide reentry vehicles. SSD provided the boosters and launch services for the program, while Flight Dynamics Laboratory was responsible for overall program management. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Booster flew to peak altitude of 62 km, then pitched down, driving the spacecraft to separation at 59 km and 4,906 m/s. The spacecraft was sited under its parachute in the recovery zone at Ascension Island, but the flotation bag broke and it sank into the Atlantic.
Space Systems Division, acting.as program manager for the Defense Department, launched two Vela nuclear radiation detection satellites from Cape Canaveral aboard the first Atlas D/Agena D (SLV-3/SS-01A) launch vehicle (197D). The Vela satellites were developed and produced by the TRW Systems and were the first pair in a series of satellites designed to provide information on nuclear detonations in the atmosphere or in outer space to a distance of 100 million miles. The 297-pound satellites were placed in near-circular orbits approximately 70,000 miles above the Earth's surface. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Atlas 109F was the final Atlas research and development flight test missile to be launched. Since the first attempted launch of a Series A Atlas on 11 June 1957, 95 Atlas missiles had been used in the R&D program - eight As, nine Bs, six Cs, 32 Ds, 24 Es, and 16 Fs. All but 12 of these were launched from Cape Canaveral. Of the 95 launches, 57 were considered successful while 38 were failures. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The first Athena test missile was launched from Green River, Utah, toward the White Sands Missile Range (WSMR) in New Mexico. The Athena research rocket was designed for the support of the Advanced Ballistic Reentry Systems (ABRES) program. Subscale models of ballistic reentry vehicles would be flown on the Athenas to test reentry vehicle concepts and phenomena. This first missile only had two operational stages, and several system failures resulted in the premature impact of the missile some 11 miles from Durango, Colorado. This was the first of several hundred launches from Green River, Utah, to impact points in the US Army's White Sands Missile Range in New Mexico. The Athena was designed to simulate the re-entry environment of an intercontinental ballistic missile and was one of the few examples of sustained interstate missile tests within the United States.
The second flight test of the ASSET reentry vehicle from Cape Canaveral failed when the second stage of the Thor/Delta failed to ignite. The test objectives were not met. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Good first stage burn, but the second stage fired, then shut down, repeating the sequence several times. The spacecraft separated, and began to maneuver in a 60 degree bank to recover course, when the self-destruct package blew it apart. The debris impacted the Atlantic 800 km downrange near San Salvador Island.
An Atlas D/Agena D launch vehicle (Atlas 216D), carrying the second set of Vela Nuclear Detection Satellites, was launched from Cape Canaveral and placed the satellites in their prescribed orbits. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
An Atlas D/Agena D launch vehicle (Atlas 216D), carrying the second set of Vela Nuclear Detection Satellites, was launched from Cape Canaveral and placed the satellites in their prescribed orbits. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Aerothermodynamic/elastic Structural Systems Evaluation Test (ASSET) vehicle (ASV-3) was launched down the Eastern Test Range by a Thor booster. The ASV-3 was a boost-glide reentry vehicle that was designed to obtain temperature and pressure distribution data and to test materials and structural concepts during reentry. The vehicle was recovered 1,650 miles southeast of Cape Canaveral after reentering the atmosphere at 13,000 miles per hour and reaching reentry temperatures of 4,000° F. A part of the Spacecraft Technology and Advanced Reentry Tests (START) program managed by Space Systems Division, ASSET provided valuable data on the conditions encountered by a spacecraft during reentry. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Launched after four hours of holds. Tested Dynasoar hardware - tungsten nose cap, molbdenum panels with vapor-deposited disilicide, and liquid-cooled double-walled cockpit bathtub panel. Reached 5,500 m/s and recovered near Ascension Island 12 hours after launch.
The first Atlas/Agena D standard launch vehicle (SLV-3, 7100 Series) was successfully launched from Vandenberg AFB. This vehicle, Number 7101, was the first Atlas booster to be designed and produced to fully standardized specifications. KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The first successful ballistic flight test of a cesium ion contact engine was conducted on a Scout booster launched from Vandenberg. Built by Electro-Optical Systems Corporation under an Air Force contract, the engine was the first of its kind to operate in space. The launch was designed to provide about 30 minutes of flight above an altitude of 370 km. At seven minutes into the flight the engine was operated with ion beam extraction. Full beam current of 94 mA was achieved about 10 minutes later. During the course of engine operation, an electric field strength meter was used to infer payload floating potential relative to space. Spacecraft potential was about 1000 V negative during most of the engine operation with the filament neutralizer. The absolute value of payload potential was about ten times higher than anticipated, and it was suspected that there was inadequate neutralization of the ion beam. The contact ion engine operated for 19 minutes until spacecraft reentry into the atmosphere. In addition to withstanding the environmental rigors of space flight, the ion propulsion system demonstrated electromagnetic compatibility with other spacecraft subsystems and the ability to regulate and control a desired thrust level.
The 6555th Aerospace Test Wing launched the first Titan IIIA space booster (Vehicle #2) from the Eastern Test Range. Essentially the liquid-propellant core section of the Titan IIIC, the Titan IIIA performed satisfactorily except for a transtage (Stage 3) malfunction. After the first two stages had performed flawlessly, a premature shutdown of the transtage engine resulted from the failure of an onboard helium pressure valve and prevented the 3,750-pound dummy test payload from being injected into orbit.
Suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 50.6 km altitude before being released from single-stage Thor SLV-2 launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned. AEV-1 was part of Space Systems Division's Aerothermodynamic/ elastic Structural Systems Evaluation Test (ASSET) program, and the first of two tests to obtain data on structural behavior during reentry, with emphasis on thermoelastic effects.
The 6555th Aerospace Test Wing successfully launched the fifth ASSET reentry test vehicle, a suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 53.2 km altitude before being released from launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned.
First test of a side-looking radar from outer space. The mission lasted only four days, as planned, before the batteries ran out of power during orbits 72-73. The radar operated 14 times in orbit, between 22 and 26 December, imaging swaths of the northeastern and western United States. Data collected from the 14 radar passes were transmitted over a wideband (UHF) data link as they were obtained ("real time") to the Vandenberg or New Boston ground station in view. In addition, during the first seven radar passes data were recorded on film on board the satellite, and on 23 December, during the 33rd orbit, the reentry capsule was jettisoned and recovered. The vehicle and payload performance were within acceptable limits on all parameters. The radar maps covered about 80,000 square miles and the resolution was better than 15 feet in azimuth and 80 feet in ground range. The mission, not declassified until 2012, proved the feasibility of space-based surveillance, leading to the operational Lacrosse satellites of the 1980's.
In this test, an additional wire neutralizer was incorporated and was immersed in the ion beam to provide a higher probability of adequate neutralization. The contact ion engine only achieved about 20% of full-thrust before reentry into the atmosphere. The short test time was due to a very short burn of the Scout vehicle's third stage. The high voltage was applied to the engine 7 minutes into the flight when the altitude was 490 km. Engine operation ended after 4 minutes when the altitude was only 80 km.
The first Air Force Thor/Altair (Burner I) space booster was launched from Vandenberg AFB. The Altair upper stage was the fourth stage of the Scout rocket. Defense Meteorological Satellite Program. Launch date was January 18, 1965. The launch was successful and correct orbit was achieved. However, the heat shield on the second stage did not deploy correctly and the mission objectives were not fully realized. This first Burner I bird is distinguishable in photos by its black second stage.
Titan IIIA, Vehicle #3, was launched from Cape Canaveral. In a maneuverability test involving three separate orbits, the Transtage and two satellites were successfully placed into their programmed orbits. The primary objective of the mission was the triple ignition of the Transtage engine that was required for the three separate orbits. When it placed the Lincoln Experimental Satellite (LES-1) into orbit, the vehicle became the first Titan III to inject an operational payload into orbit. Lincoln Experimental Satellite; communications experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The Aerothermodynamic/elastic Structural Systems Environmental Test (ASSET) program concluded when a Thor booster launched the last of the experimental vehicles from the Eastern Test Range. The payload reentered down range but was not recovered. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Reached 6,000 m/s and 4,350 km range. Tested twelve different kinds of refractory metals and covered with 2000 dots of heat-sensitive paint to characterize thermal profile on reentry. Telemetry indicated that the spacecraft survived reentry, but it evidently sank upon impacting the ocean and could not be recovered as planned.
Operation Long Life, the first test launch of a specially designed Minuteman test missile from an operational launch facility, was successfully concluded at Wing II, Ellsworth AFB, South Dakota. With a first stage engine designed to burn only a short time, the Long Life missile carried dummy second and third stages that were up to full operational weight. The missile landed about a mile from the silo after a first stage burn of seven seconds. Approved by the Secretary of Defense in November 1964, 'Project Long Life' called for the short-range launch from on operational missile base of three modified Minuteman IB ICBMs to provide a realistic test for this system. Each missile would contain enough propellant for a 7-second flight and have inert upper stages and reentry vehicles. This first launch occurred on March 1, 1965, and successfully demonstrated the ability of a SAC missile crew to launch an ICBM.
The 6595th Aerospace Test Wing launched an Atlas/Agena which boosted the Atomic Energy Commission (AEC) Snapshot spacecraft into orbit carrying the SNAP-10A satellite nuclear power supply experiment. The onboard nuclear reactor was used to provide electric power for an ion engine, marking the first attempt to test a reactor-ion system in orbit. Only nuclear reactor ever orbited by the United States. The SNAP-10A reactor provided electrical power for an 8.5 mN ion engine using cesium propellant. The engine was shut off after one hour of operation when high-voltage spikes created electromagnetic interference with the satellite's attitude control system sensors. The reactor continued in operation, generating 39 kWt and more than 500 watts of electrical power for 43 days before the spacecraft telemetry failed.
The fourth Titan IIIA flight test missile (Vehicle #6) was launched from Complex 20 at Cape Canaveral in a maneuverability test for the Transtage. The primary aim was for the Transtage engine to accomplish four separate ignitions, something never before attempted. In the process of successfully completing its four programmed ignitions and burns, the Transtage placed two satellites into orbit - a Lincoln Experimental Satellite (LES-2) and a hollow aluminum radar calibration sphere (LCS-1). By completing its assigned tasks, the Transtage extended the capabilities of the Titan IIIA beyond it's specific requirements. Because of this highly productive mission, the planned fifth Titan IIIA (Vehicle 7/4) launch was cancelled and the booster was converted to a Titan IIIC configuration. Experimental commsat. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The fourth Titan IIIA flight test missile (Vehicle #6) was launched from Complex 20 at Cape Canaveral in a maneuverability test for the Transtage. The primary aim was for the Transtage engine to accomplish four separate ignitions, something never before attempted. In the process of successfully completing its four programmed ignitions and burns, the Transtage placed two satellites into orbit - a Lincoln Experimental Satellite (LES-2) and a hollow aluminum radar calibration sphere (LCS-1). By completing its assigned tasks, the Transtage extended the capabilities of the Titan IIIA beyond it's specific requirements. Because of this highly productive mission, the planned fifth Titan IIIA (Vehicle 7/4) launch was cancelled and the booster was converted to a Titan IIIC configuration. Aluminum sphere used for radar calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Suborbital reentry heating experiment using the FIRE subscale Apollo capsule. An Atlas D booster propelled the instrumented probe, called a "flying thermometer," into a ballistic trajectory over 805 km (500 mi) high. After 26 minutes of flight, when the spacecraft began its descent, a solid-fueled Antares rocket accelerated its fall.
The probe entered the atmosphere at a speed of 40,877 km (25,400 mph) and generated temperatures of about 11,206K (20,000 degrees F). Data on heating were transmitted to ground stations throughout the descent. Thirty-two minutes after the launch - and but six minutes after the Antares was fired - the device impacted in the Atlantic about 8,256 km (5,130 mi) southeast of the Cape.
The first Titan IIIC (SLV-5C) research and development vehicle (Vehicle #7) was successfully launched from Cape Canaveral. The Titan IIIC, the first Air Force vehicle specifically designed and developed as a military space booster under Space Systems Division management, was the first heavy-duty booster to combine the thrust of large-size, strap-on solid rocket motors with a three-stage, liquid-powered rocket. The Titan IIIC weighed more than 1.4 million pounds fully fueled but without its payload. At takeoff, the two United Technology Center solid rocket motors (SRMs) generated a peak thrust of 2,647,000 pounds - making the Titan IIIC the most powerful rocket yet launched. When the two solid motors were jettisoned two minutes after lift-off, the liquid-fueled center core section took over-Stage 1 engines producing 520,000 pounds of thrust, then Stage 2 with 100,000 pounds, and finally Stage 3 (Transtage) with its 16,000-pound thrust engines and carrying the payload. This first Titan IIIC placed a 21,000-pound test payload into a 100-NM (low earth) circular orbit - the heaviest payload yet orbited by the U.S. The Titan IIIC was capable of placing a 3,200-pound payload into a 22,000-mile, synchronous equatorial orbit. When fully operational, the new booster would provide a vast increase in the size and range of satellites that could be placed in orbit. This capability would eliminate one of the primary limitations on a number of satellite programs - the limited payload capability of the present Thor and Atlas space booster families. Launch vehicle test. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The second Titan IIIC (Vehicle #4) was successfully launched from Cape Canaveral. This was the first Titan IIIC to carry an operational payload. Three satellites were placed in orbit - an LCS-2 radar calibration sphere, an OV 2-1 radiation sensor, and a metal-ballasted dummy payload. All systems performed well until the second planned burn of the Transtage engines just prior to the injection of the multiple payload into orbit. At this point in the mission, the Transtage exploded due to a malfunction, abruptly terminating the mission. Dual launch with OV2-1; upper stage broke up.
The second Titan IIIC (Vehicle #4) was successfully launched from Cape Canaveral. This was the first Titan IIIC to carry an operational payload. Three satellites were placed in orbit - an LCS-2 radar calibration sphere, an OV 2-1 radiation sensor, and a metal-ballasted dummy payload. All systems performed well until the second planned burn of the Transtage engines just prior to the injection of the multiple payload into orbit. At this point in the mission, the Transtage exploded due to a malfunction, abruptly terminating the mission.
A Titan IIIC (Vehicle #11) successfully supported a record-setting mission by placing eight satellites into near-synchronous orbits 18,200 miles above the equator. Seven communication satellites and one gravity gradient experimental satellite were included in this first launch in a series designed to establish a ring of experimental communications satellites dispersed around the equator. When completed, this satellite system would provide the Defense Department with a global military communication system designated the Initial Defense Satellite Communication System (IDSCS). Each of the seven satellites could relay 600 voice or 6,000 teletype channels. Space Systems Division was responsible for the development and launch of the spaceborne elements of the IDSCS as well as the Titan IIIC booster and launch services. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
A Titan IIIC (Vehicle #11) successfully supported a record-setting mission by placing eight satellites into near-synchronous orbits 18,200 miles above the equator. Seven communication satellites and one gravity gradient experimental satellite were included in this first launch in a series designed to establish a ring of experimental communications satellites dispersed around the equator. When completed, this satellite system would provide the Defense Department with a global military communication system designated the Initial Defense Satellite Communication System (IDSCS). Each of the seven satellites could relay 600 voice or 6,000 teletype channels. Space Systems Division was responsible for the development and launch of the spaceborne elements of the IDSCS as well as the Titan IIIC booster and launch services. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
After the initial launch attempt oil the 28th was held at T minus 12 seconds, the first Titan IIIB/Agena D was successfully launched from Vandenberg AFB. All primary and secondary test objectives were met during the launch and flight which completed the research and development program for the Titan IIIB. This newest member of the Titan III (SLV-5) KH-8 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
A Titan IIIC (Vehicle #9), the ninth research and development Titan III and sixth Titan IIIC to be launched from Cape Canaveral, completed the most difficult flight plan and most successful mission to date. The primary objective of injecting a modified Gemini spacecraft into a suborbital trajectory to test the reentry heat shield for the Manned Orbiting Laboratory (MOL) program was accomplished. After dipping down to 80 nautical miles to eject the MOL load, the Transtage pitched up and placed a canister containing 11 experiments into a 160-nautical mile circular orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
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.
A Titan IIIC (Vehicle #9), the ninth research and development Titan III and sixth Titan IIIC to be launched from Cape Canaveral, completed the most difficult flight plan and most successful mission to date. The primary objective of injecting a modified Gemini spacecraft into a suborbital trajectory to test the reentry heat shield for the Manned Orbiting Laboratory (MOL) program was accomplished. After dipping down to 80 nautical miles to eject the MOL load, the Transtage pitched up and placed a canister containing 11 experiments into a 160-nautical mile circular orbit. 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.
Launched from Cape Canaveral, a Titan IIIC (Vehicle #13) space booster lifted eight 100-pound military communications satellites into synchronous orbits 21,000 miles above the equator. The satellites, together with the seven placed in orbit on 16 June 1966, formed the Initial Defense Satellite Communication System (IDSCS). Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Launched from Cape Canaveral, a Titan IIIC (Vehicle #13) space booster lifted eight 100-pound military communications satellites into synchronous orbits 21,000 miles above the equator. The satellites, together with the seven placed in orbit on 16 June 1966, formed the Initial Defense Satellite Communication System (IDSCS). Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Two new and heavier Vela Nuclear Detection Satellites and three scientific satellites were placed in orbit by a Titan IIIC (Vehicle #10) launched from Cape Canaveral. The two Vela satellites joined six other Vela spacecraft already on sentry duty 69,000 miles above the earth. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Two new and heavier Vela Nuclear Detection Satellites and three scientific satellites were placed in orbit by a Titan IIIC (Vehicle #10) launched from Cape Canaveral. The two Vela satellites joined six other Vela spacecraft already on sentry duty 69,000 miles above the earth. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
A Titan IIIC booster (Vehicle #14) launched from Cape Canaveral placed a multiple payload of six satellites into orbit. Three of the satellites completed the Pacific link of the Initial Defense Satellite Communication System (IDSCS) program between Washington D.C., and South Vietnam. A fourth was a special communications satellite, the Despun Antenna Test Satellite (DATS), designed to test a despun antenna system for possible use on future communications satellites. DATS was designed to transmit 75 percent of radio signal strength to earth stations compared to the 15 percent for previous systems. Also included in the payload were a Defense Department Gravity Gradient Experiment (DODGE) satellite and a Lincoln Experimental Satellite, LES-5, the first all solid-state Ultra-high Frequency (UHF) band communication satellite intended to test communications with frontline troops. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
Fatal accident, aircraft destroyed. After reaching peak altitude, entered spin at Mach 5. Entered dive at 30,000 m, began high frequency pitch oscillations, disintegrated when these reached 15 Gs.Maximum Speed - 5744 kph. Maximum Altitude - 81080 m. Air dropped in Delamar Dry Lake DZ.
The last scheduled Air Force Thrust Augmented Thor/Agena (SLV-2A //498/SS-01B #2733) to be launched from Vandenberg AFB was the 150th Thor/ Agena vehicle fired from there since Discoverer I was launched on 28 February 1959. From now on, the Air Force would use the more advanced Long Tank Thrust Augmented Thor (SLV-2G) - Thorad - and the newer SLV-2H.
An Air Force Titan IIIC, Vehicle #16, was launched from Cape Canaveral and successfully inserted eight 100-pound communications satellites into near-synchronous orbits. These satellites augmented and completed the deployment of the Initial Defense Satellite Communications System (IDSCS) which now consisted of 26 operational satellites Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
An Air Force Titan IIIC, Vehicle #16, was launched from Cape Canaveral and successfully inserted eight 100-pound communications satellites into near-synchronous orbits. These satellites augmented and completed the deployment of the Initial Defense Satellite Communications System (IDSCS) which now consisted of 26 operational satellites Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The first "stretched" Atlas SLV-3A/ Agena D was launched from the Eastern Test Range. The "stretched" Atlas had an additional 117-inch tank section to provide more fuel, a longer burn time, and increased payload capability. First launch in a communications intelligence program operated by the USAF within the National Reconnaissance Office, on behalf of the National Security Agency. The first generation series, CANYON, was based on the Agena vehicle. The Agena D remained attached to the spacecraft. Positioned in geosynchronous orbit over the Indian Ocean. Last known longitude (30 December 1968) 98.50 deg W drifting at 0.166 deg E per day.
An Atlas/Burner II (SLV-3, #7004), the first Atlas to be launched with a Burner II upper stage, was launched from Space Launch Complex 3 East (SLC-3E) at Vandenberg but failed to place its payload in orbit due to a malfunction of the nose-fairing heat shield separation system. First of two Atlas/Burner II space launches. 1 of 13 satellite launch attempts; investigate effects of ionosphere on radio signals.
A Titan ITIC space booster (Vehicle #5) was launched from Complex 41 at the Eastern Test Range and inserted four satellites into separate earth orbits. The primary payload was the Lincoln Experimental Satellite (LES-6) which was the second all-solid-state ultrahigh frequency (UHF) band communication satellite to be placed into a synchronous orbit. It was designed to test communications with aircraft, ships, and ground forces. The other three satellites were Office of Aerospace Research (OAR) payloads - two Experimental Research Satellites (ERS-21 and ERS-28) and an Orbiting Vehicle (OV 2-5) research satellite. 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.
A Titan ITIC space booster (Vehicle #5) was launched from Complex 41 at the Eastern Test Range and inserted four satellites into separate earth orbits. The primary payload was the Lincoln Experimental Satellite (LES-6) which was the second all-solid-state ultrahigh frequency (UHF) band communication satellite to be placed into a synchronous orbit. It was designed to test communications with aircraft, ships, and ground forces. The other three satellites were Office of Aerospace Research (OAR) payloads - two Experimental Research Satellites (ERS-21 and ERS-28) and an Orbiting Vehicle (OV 2-5) research satellite. 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.
Air Force Titan IIIC, Vehicle #17, was launched from Cape Canaveral and placed the 1,600-pound experimental Tactical Communications Satellite, TACSAT I, into a near-synchronous orbit at an altitude of 19,300 nautical miles above the equator. TACSAT I, built by Hughes Aircraft Company under SAMSO management, was the largest communications satellite yet launched and placed in orbit by the United States. It was to determine the feasibility of using satellite communications repeaters with small mobile ground tactical communications equipment. In addition, using the technology already developed with earlier Despun Antenna Test System (DATS) and Lincoln Experimental Satellites (LES) test spacecraft, TACSAT I would test the feasibility of satellite communications over great distances while also testing the new gyrostat stabilization system. The satellite could handle transmission of television or multiple telephone/ teletype communications channels. 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.
The 13th, and final, Titan IIIC research and development booster (Vehicle #15) lifted two Vela satellites, the fifth pair of such nuclear detection spacecraft, and three experimental satellites into orbit from Cape Canaveral. This launch concluded the highly successful Titan III research and development program initiated in 1962. Out of 13 Titan IIIC and four Titan IITA vehicles launched, 10 Titan IITCs were complete successes, two were partial successes, and only one was a failure, while three of the four Titan IITA launches were rated successful. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The 13th, and final, Titan IIIC research and development booster (Vehicle #15) lifted two Vela satellites, the fifth pair of such nuclear detection spacecraft, and three experimental satellites into orbit from Cape Canaveral. This launch concluded the highly successful Titan III research and development program initiated in 1962. Out of 13 Titan IIIC and four Titan IITA vehicles launched, 10 Titan IITCs were complete successes, two were partial successes, and only one was a failure, while three of the four Titan IITA launches were rated successful. Radiation, low-energy particle, solar flare data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
An Athena test missile launched from Green River, Utah, toward the White Sands Missile Range veered off course and landed some 200 miles inside Mexico. This led to a halt in Athena launches from Green River until the cause of the malfunction could be determined. Went off course and impacted in Mexico.
An Air Force Titan IIIC launched the 500th satellite to be placed in orbit successfully by a vehicle launched from Cape Canaveral. 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.
KH-4B. The launch vehicle had a very cold boattail due to a hose discovered to be leaking away warming air to the boattail. The boattail was colder than usual, below freezing. Based on earlier tests of the Thor for just that condition, as relayed by Ed Dierdorf, Thor chief engineer at the time, the temp low was of no concern.
The only problem was that those tests were made with a Thor that carried a Rocketdyne engine lubricated with "lube oil". The Thor being launched used a fuel additive, "Orinite" (like STP "super snot"). The technician that pumped the Orinite into its cannister later stated, "It wasn't for lack of orinite. I put it in just like the procedure said, and I could feel when it was full (with the hand pump). To make sure, I gave it another slug."
That "other slug" cracked the output valve that was only supposed to be cracked by turbopump output pressure. When it cracked the output valve a bit of the "honey" squirted down the tube toward engine bearing jets. This line had a low spot in it by design. The Orinite settled there. When it was chilled by the low temp air at lox loading, the Orinite formed a plug.
Unaware of this chain of circumstances, Launch Director Philip Payne made the decision to launch. The rocket (carrying Agena D and payload) flew for 18 seconds, then wiped out its gears, causing the turbine to overspeed and shed its vanes. These punctured various parts in the boattail like machine gun bullets. With loss of power, the rocket fell not far from the launch pad into Bear Creek canyon.
The final cause was therefore found to be loss of engine lubrication at startup.
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.
A Titan IIIC, launched from Cape Canaveral, placed into synchronous orbits the first pair of 1,200-pound advanced communications satellites of the Defense Satellite Communication System Phase II (DSCS II). After some initial difficulties with the satellites, telemetry and command links were established with both satellites by 5 November. Under SAMSO program management, TRW Systems Group manufactured these second generation communications satellites that were intended as replacements for the 26-satellite Initial Defense Satellite Communication Systems (IDSCS). Each of the DSCS II (Program 777) satellites would be able to handle voice, teletype, computerized digital data, and video transmissions. 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.
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.
The third Athena H rocket was launched from the Green River, Utah, launch complex. The flight test completed qualification of the vehicle for operational use in the Advanced Ballistic Reentry Vehicle (ABRES) program managed by SAMSO's Deputy for Reentry Systems (RS).
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).
A Thor/Delta booster launched from Cape Canaveral successfully placed a Canadian communications satellite, ANIK I, into orbit. This was the 75th Thor/Delta to be launched from the Cape and the first Long Tank Thrust Augmented Thor/Delta to be launched from the Cape with nine strap-on solid rocket motors. It placed the Telestar-A (ANIK) communications satellite in orbit for Canada. Defense Meteorological Satellite Program.
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.
An Athena H missile was fired from the launch complex at Green River, Utah, carrying an Advanced Ballistic Reentry System (ABRES) payload. This was the 11th Athena H to be fired from Green River in support of the ABRES program and the 141st Athena to be launched from Green River since the beginning of the program in February 1964. Following this launch, the Green River complex was closed and Athena launch operations were transferred to Wake Island.
An Air Force Titan IIIC, launched by the 6555th Aerospace Test Group from the Eastern Test Range, boosted two Program 777 Defense Satellite Communications Systems; 13 deg W. A new inertial guidance system, manufactured by Delco Electronics for the Titan IIIC made its first flight. The new system consisted of an inertial measurement unit and a missile guidance computer. 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.
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.
The newest addition to the Titan III series, the Titan IIIE/Centaur - a meld of Air Force and NASA technology, suffered a partial failure in its first flight test from Cape Canaveral. The Titan/Centaur vehicle will be used as the launch vehicles for NASA's Viking Mars Lander in 1975 and for the United States-German Helios program.
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.
Space Test Program flight P73-3 was launched from the Western Test Range, and the payload - Navy Navigation Technology Satellite #1 (NTS-1) - was successfully placed into orbit. Demonstrated navigation technologies leading eventually to Navstar/GPS system. Operated for 5 years.
The first live demonstration flight of a Pedro Recruit sounding rocket occurred at Wallops Island, Virginia. It was a clear air launch of a carbon-phenolic nosetip from an F-4 aircraft. The launch, part of the Fighter Launched Advanced Materials Experiment (FLAME), was successful, but the payload was not recovered. Attempts on 20 September and 9 October to drop an inert Pedro Recruit rocket from an F-4 aircraft had failed. This was a DNA-sponsored experiment.
Space Test Program flight P72-2 was launched; it carried two infrared radiometers and three other payloads. The launch failed when the Atlas F launch vehicle malfunctioned. A lack of deluge water and collection in the flame bucket of a kerosene/liquid oxygen gel led to the explosion of the gel on lift-off, damaging one of the Atlas engines and leading to complete engine failure during the ascent.
The third pair of Defense Satellite Communications System II satellites was launched; the launch failed due to a malfunction in the Transtage of the Titan IIIC launch vehicle. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
The third pair of Defense Satellite Communications System II satellites was launched; the launch failed due to a malfunction in the Transtage of the Titan IIIC launch vehicle. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).
A Titan IIIC carrying a Space Test Program payload, Flight P74-1, was successfully launched from LC-40, Eastern Test Range. Flight P74-1 was made up of Lincoln Experimental Satellite 8 and 9 (LES 8/9) and Solar Radiation satellites 11A and B (SOLRAD 11A/B). 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.
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.
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.
The third and final flight of the MSV (materials screening vehicle) program was successfully launched on an Athena D booster from Wallops Flight Center, Virginia, through adverse weather. Three small reentry vehicles gathered data on nosetip materials and designs.
A Titan IIIC launched a pair of DSCS II satellites into orbit from Cape Canaveral, Florida. 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.
A Titan IIIC launched a pair of DSCS II satellites into orbit from Cape Canaveral, Florida. 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.
An LV-2F booster launched the second DMSP Block 5D satellite into orbit from Vandenberg AFB, California. The launch was marred by a series of anomalies which put the satellite in a retrograde orbit and a spinning condition. Defense Meteorological Satellite Program.
An Atlas booster and a Global Positioning System Stage Vehicle launched Navigation Technology Satellite 2 into orbit from Vandenberg AFB, California. This was the first use of the GPS Stage Vehicle. Navigation Technical Satellite; GPS precursor. Operated 50% satisfactorily -- still operating 25 years later.
An Atlas booster was launched from Vandenberg AFB carrying the first NAVSTAR Satellite. The launch was successful, and the satellite functioned normally once in orbit. It was declared operational on 31 March. Also known as Navigational Development Satellite 1. Technology prototype of Navstar satellite.
A Titan IIIC was launched from Cape Canaveral carrying DSCS II satellites F-9 and F-10. The vehicle suffered a failure in its second stage hydraulic system about eight minutes after liftoff, and both the vehicle and its payload were lost. Launched with DSCS F10.
An Atlas booster was launched from Vandenberg AFB with the second NAVSTAR satellite. Launch was successful and the satellite functioned normally once in orbit. It began operating at its final station on 27 June. Also known as Navigational Development Satellite 2. Technology prototype of Navstar satellite.
The third NAVSTAR satellite was launched from Vandenberg AFB on board an Atlas booster. Both the booster and the satellite itself functioned normally, and the satellite began operating at its final station on 31 October. Technology prototype of Navstar satellite.
A Titan IIIC was launched from Cape Canaveral carrying DSCS II satellites F-ll and F-12. The vehicle placed the satellites in the proper orbit, and the satellites performed normally once there. They were expected to go into operation in mid-January 1979, at which point the DSCS II system would have a full, four-satellite constellation at its disposal for the first time in its history. 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.
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.
Flight P78-2 was successfully launched by SAMSO's Space Test Program. The mission was designated SCATHA (Spacecraft Charging at High Altitudes) and gathered data on the build-up of electrical charges on satellites operating at geosynchronous altitude. It was sponsored jointly by NASA and the Air Force. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.
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..
The first of two secondary rocket flight tests designated HAVE LENT IV successfully demonstrated the use of aerosol masking dispensers as a penetration aids. The vehicle was a Sergeant-Hydac rocket launched from Barking Sands, Hawaii. Data collection was limited because of erratic behavior of the rocket. The mission was sponsored by ABRES.
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.
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.
Defense Meteorological Satellite Program. Although there was a press release immediately after the launch (by the spacecraft SPO) that said the 2nd stage motor exploded, in reality the problem was found to be due to poor design of the electrical connectors between the 2nd and third stages and a separation problem that ripped the wiring out of the spacecraft.
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.
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.
Positioned in geosynchronous orbit at 15 deg W in 1983-1987; 66 deg E in 1987; 60 deg E in 1987-1994; 65 deg E in 1994-1997 As of 5 September 2001 located at 114.00 deg W drifting at 18.661 deg W per day. As of 2007 Mar 9 located at 172.94E drifting at 18.658W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).
Multi-Orbit Satellite / Performance Improvement ballistic missile launch detection satellite, remained in service for nearly eighteen years. Positioned in geosynchronous orbit at 135 deg W in 1984-1985; 65 deg E in 1985-1988; as of 31 December 1990 at 99.16 deg W drifting at 0.050 deg W per day.
Reserve Phase 2 DSP ballistic missile launch detection satellite fitted with Block 14 sensors, remained in service for nearly eighteen years. Observed Scud launches during Gulf War. Positioned in geosynchronous orbit at 155 deg W in 1985-1988; 65 deg E in 1988-1991; 145 deg E in 1991-1992; 105 deg E in 1992-1993; 5 deg E in 1993-1994.
Released from STS 51J 4 October 1985; boosted into orbit with DSCS 3 F3 on single IUS booster. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit; at 180 deg E in 1994.
Target balloon for F-15-launched ASAT missile. The battery-powered vehicle remained uninflated in orbit until a test was planned. Orbital decay data indicates the balloon was inflated on 18 December 1986. However for operational or political reasons no intercept was ever attempted.
Reserve DSP ballistic missile launch detection satellite fitted with Block 14 sensors, remained in service for only five years.. Observed Scud launches during Gulf War. Positioned in geosynchronous orbit at 35 deg W in 1988-1989; 10 deg E in 1989-1992; 35 deg W in 1992-1993; 105 deg E in 1993; 165 deg W in 1999.
First DSP-1 Block 14 ballistic missile launch detection satellite; first Titan 4 launch. Positioned in geosynchronous orbit at 165 deg W in 1990-1994; 145 deg W in 1999; 166 deg W in 2000.. Still in service as of March 2007. As of 2007 Feb 5 located at 145.23W drifting at 0.014W degrees per day.
Polar Orbiting Geomagnetic Survey satellite designed to measure the Earth's magnetic field vector as a function of position. Data from the experiment was used to improve Earth navigation systems, and was stored in an experimental solid state recorder. Six low cost ground stations were designed, built and located around the world to operate the spacecraft flown on this mission.
DSP-1 Block 14 ballistic missile launch detection satellite, deployed from shuttle STS-44 on 25 November 1991. Only DSP launched from the shuttle before the Challenger disaster moved the payload to the Titan 4. Positioned in geosynchronous orbit at 130 deg W in 1992; 70 deg E in 1992; 8 deg E in 1999; 40 deg W in 2000. Still in service as of March 2007.
Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 12 deg W in 1995-1996. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 175 deg E in 1995-1997.
Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 52 deg W in 1995; 60 deg E in 1997. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).
The Titan 4B placed the IUS upper stages and DSP-1 Block 14 ballistic missile launch detection satellite. payload into a 188 km x 718 km x 28.6 deg parking orbit. The first stage of the IUS burned at 18:14 GMT and put the second stage and payload into a geosynchronous transfer orbit. The IUS second stage fired at 23:34 GMT in order to place the spacecraft in geosynchronous orbit. However, at least one connector remained attached between the stages, and the second stage motor nozzle did not extend properly. When the stage fired, the vehicle tumbled wildly during the burn. Separation of the DSP was achieved. Although it could not perform its primary mission, it did provide a good test case in that the effects of radiation on its systems could be monitored as they underwent twice-daily passages of the Van Allen Radiation Belts. However after some weeks the hydrazine propellant aboard the satellite vented into space due to a broken fuel line. It was believed this had been induced by the wild ride aboard the IUS-2 stage.
The Titan core vehicle operated correctly, but a software error in the Centaur stage resulted in all three planned burns being made at the wrong times, during the first orbit instead of over a six hour period. The three burns planned to place Milstar successively in a 170 x 190 km parking orbit, a geostationary transfer orbit, and finally geosynchronous orbit. Instead, at 19:00 GMT, several hours before the scheduled third burn, Milstar separated into a useless 740 km x 5000 km orbit. Milstar-2 F1 was the first upgraded Milstar with an extra Medium Data Rate payload with a higher throughput. The payload included EHF (44 GHz), SHF (20 GHz) and UHF communications transponders and satellite-to-satellite crosslinks, with narrow beams to avoid jamming.
DSP-1 Block 14 ballistic missile launch detection satellite. Delivered by the two-stage IUS-22 solid rocket into geostationary orbit. Fullfilled mission of DSP 19 launched in 1999 into the wrong orbit when its IUS stage failed. Still in service as of March 2007. As of 2005 Apr 2 located at 8.05E drifting at 0.166E degrees per day.
Military Communications satellite. Launch delayed from October 12 by spacecraft problem. The US Air Force Defense Satellite Communications System satellite was placed by the Centaur upper stage into a 148 km x 898 km x 29.3 deg parking orbit. A second burn put it into a 218 km x 35,232 km x 26.0 deg transfer orbit. The DSCS III B-11 IABS-8 apogee stage, with two Primex R4D liquid apogee engines, circularised the orbit at geostationary altitude on October 21 and then separated from the DSCS.
The Delta stage 2 entered a 153 x 418 km x 37 deg parking orbit followed by a 172 x 1144 km second orbit; the PAM-D solid upper stage then fired to give SVN 41 a 20457 km apogee. The Thiokol Star 37FM solid kick motor was fired prior to November 13 to place the spacecraft in its final circular 20,000 km orbit. Placed in Plane F Slot 1 of the GPS constellation.
Military Communications satellite. Launch delayed from October 30, December 14, 2000, and February 2 and February 24, 2001. The Milstar DFS 4 satellite (the second Milstar Block 2) provided secure communications for the US Department of Defense, with UHF, EHF and SHF band transmitters. Titan 4B-41 with core stage K-30 took off from Cape Canaveral and placed Milstar and the Centaur TC-22 upper stage in a suborbital trajectory. TC-22 then ignited to enter a 200 km parking orbit, and after two more burns delivered Milstar to geosynchronous drift orbit. Small engines on board the Milstar placed it at its targeted geostationary position. USA 157, a 4.5 tonne spacecraft, was the first in the Milstar 2 series which was capable of higher data rates and was more secure against disabling efforts.
Launch postponed from February, then delayed from July 27. USA 159 was a US Air Force Defense Support Program infrared missile early warning satellite was placed by the Titan core into a 328 x 663 km x 28.7 deg parking orbit. The Boeing IUS-16 upper stage then fired its first solid motor to enter geostationary transfer orbit. The second IUS solid motor fired at around 14:00 GMT placing DSP Flight 21 in near-geosynchronous orbit. Still in service as of March 2007.
Possibly last Athena flight. Launch delayed from September 1, 18, 22, 23, 25, 28. This was the first orbital launch from Alaska's Kodiak Island launch site (Foul weather and auroral conditions had delayed the launch many times) . The Lockheed Martin Athena-1's Orbit Adjust Module's (OAM) four MR-107 hydrazine engines fired for 12 minutes to put the payloads in a 237 x 815 km transfer orbit. After a coast to apogee above East Africa, a second burn at 0337 GMT circularized the orbit. USAF Space Test Program satellites Picosat, Sapphire and PCSat were deployed into an 790 x 800 km x 67 deg orbit between 0344 and 0352 GMT; the OAM then made a perigee lowering burn to a 470 x 800 km orbit. Another burn half an orbit later put OAM in a 467 x 474 km orbit, from wish Starshine 3 was deployed. Finally, the OAM made a perigee-lowering depletion burn which left in a 215 x 403 km x 67.2 deg orbit from which would reenter in a few months.
Starshine-3 was a 90 kg, 0.9 m geodetic sphere that was to be observed by students. The NASA satellite was basically a passive light-reflecting sphere, consisting of 1,500 student-built mirrors (polished by kindergarten and grade school students from many countries) and 31 laser "retroreflectors". A few solar cells provide enough power to send a beacon at 145.825 MHz every minute. Ham operators around the world were expected to obtain signal strengths from which the decay (due to magnetic torque) of its spin rate could be determined. The project was managed by NASA GSFC and Starshine was built by the Naval Research Laboratory.
STP P97-1 Picosat was built by Surrey Satellite for the USAF using a Uosat-type bus. The 68 kg satellite was to test electronic components/systems in space conditions. It carried four test payloads: Polymer Battery Experiment (PBEX), Ionospheric Occultation Experiment (IOX), Coherent Electromagnetic Radio Tomagraphy (CERTO) and an ultra-quiet platform (OPPEX). Called Picosat 9 by some Agencies although not related to other satellites in that series.
The Atlas AC-162 Centaur entered a 176 x 907 km x 28.2 deg parking orbit at 0242 GMT and then made a second burn to deploy its payload in a 274 x 37538 km x 26.5 deg geostationary transfer orbit at 0301 GMT. USA 162 was rumoured to be a data relay satellite used to return data from imaging satellites similar to the one launched on October 5 2001. It was also possible that the satellite is a signals intelligence payload. The satellite is owned and operated by the National Reconnaissance Office (NRO).
Military Communications satellite. Launch delayed from December 2001. The Titan core stage shut down 9 min after launch on a suborbital trajectory, and separated from the upper stage, Centaur TC-19. TC-19 made three burns to parking orbit, geostationary transfer orbit, and finally geostationary orbit. It then released Milstar Flt-5. Milstar provided secure communications in the EHF, SHF and UHF bands and would be stationed over European longitudes. As of 2007 Feb 16 located at 29.98E drifting at 0.014W degrees per day.
Coriolis was an Air Force Space Test Program three-year meteorological science mission to demonstrate the viability of using polarimetry to measure ocean surface wind speed and direction from space, and to demonstrate predictions of geomagnetic disturbances through continuous observation of Coronal Mass Ejections. Launch delayed from August 22, November 15, December 15, 16, 17 and 18, 2002 and January 5, 2003.
Mass model payload. First launch of a heavy EELV. The demonstration satellite was supposed to have been inserted into a sub-geosynchronous 36,350 km circular orbit but was instead deployed in a 19,035 km x 36,413 km orbit following a 5-hour and 50-minute flight. A shorter than expected first burn of the Centaur upper stage led to an orbit well below that planned. The Air Force EELV program office claimed that the primary flight objectives were accomplished. These included the heavy boost phase, flight of the new five-meter diameter Centaur upper stage and five-meter payload fairing, extended coast, upper stage third burn and payload separation, and activation and usage of Space Launch Complex 37B. Delayed from September 2003, July 3, September 10, November 18, December 10, 11 and 12.
One of a pair of student-built nanosats for stero cloud imagery. The satellites did not contact the ground after separation from the booster in a lower-than-planned orbit and their fate was unclear. It was believed that they separated but re-entered rapidly from the 105 km perigee orbit.
Delayed from December 2004; February 1, March 17, 2005. Moved up from May 20 2005. Then delayed from May 4, July 29, August 26, September 22, 2005. Became operational at 23:30 GMT on 16 December. First GPS Block IIR-M version, which added extra navigation signals for both civil and military users. The NASA-funded L2C tracking demonstration was managed by JPL and explored the use of a new Civilian code signal (L2C). The data was collected with Trimble NetRS receivers L2C-enabled firmware. The sites were globally distributed: South Africa, Norway, Antarctica, Hawaii, and Alaska.
Defense Meteorological Satellite Program satellite with the Operational Linescan System camera, a microwave imager-sounder, ultraviolet spectrometers, particle detectors, a magnetometer, and a laser threat warning sensor. Reportedly went for a time into safe mode due to software problems after launch. The booster upper stage was conducted a maneuver to deorbit itself after placing the satellite in orbit. After the burn an explosion evidently occurred aboard the stage - dozens of objects were tracked in various orbits with perigees down to 670 km and apogees up to 851 km.
Mission 2a sensor target for the NFIRE satellite. The Minotaur II, a three-stage refurbished Minuteman 2 missile with a new guidance and payload section, was aimed to pass within 4 and 20 km of the NFIRE satellite while its third stage motor was burning, to allow NFIRE's sensors to characterize the the rocket and its exhaust. The Missile Defense Agency reported that Mission 2a was successful.
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