Redstone Credit - via Andreas Parsch

Short range ballistic missile. IOC: 1958. Family:

Redstone was the first large liquid rocket developed in the US using German V-2 technology. Originally designated Hermes C. Redstones later launched the first US satellite and the first American astronaut into space.

Historical Essay © Andreas Parsch

Chrysler SSM-A-14/M8/PGM-11 Redstone

The Redstone was the U.S. Army's first operational MRBM (Medium Range Ballistic Missile). Although its service life as a weapon was relatively short, it played a major role in the early American space program.

In November 1944, the Army contracted General Electric to study and develop long-range guided missiles under the general name of Hermes. The Hermes program consisted of many different projects, and also included the Hermes C1 for a ballistic surface-to-surface missile in the 800 km (500 miles) range class. However, because of limited funding and higher priority assigned to other Hermes projects, progress on the C1 was slow. This changed in 1950, when the Korean War led to a sharp increase in military spending, and responsibility for the Hermes C1 project was transferred from G.E. to the Army's Guided Missile Center. At that time, the formal designation of SSM-G-14 was assigned to the Hermes C1 missile. In early 1951, the payload requirements for the missile were significantly increased, reducing the planned range to 400 km (250 miles). Im mid-1951, the program was transferred again, to the Army's Redstone Arsenal, and the missile designator was changed to SSM-A-14. It was not until April 1952, that the name Redstone was officially assigned, after the names Ursa and Major had also been used briefly.

Major design work on the Redstone was finished during 1952, and in October that year, Chrysler received a contract for production of the missile. The SSM-A-14 incorporated some firsts in missile technology, like an all-inertial guidance system. and a separable warhead section to reduce drag (and thereby increase range) during reentry. It used a single North American Rocketdyne NAA75-110 liquid-fueled rocket engine (also known as A-6), a development of the XLR43-NA-1 engine. In August 1953, the first successful flight of an XSSM-A-14 occurred, and in 1955, Chrysler began the production of Redstone missiles. Many Redstone test missiles were converted to Jupiter A and Jupiter C test missiles to support the SM-78/PGM-19 Jupiter IRBM program. The first production missile flew in July 1956, and by June 1958, the first fully operational Redstone unit had been deployed to West Germany. By that time, the designation Guided Missile, Field Artillery, M8 had been assigned to the Redstone. Non-flying dummy missiles used as trainers were designated XM9.

The Redstone was a capable MRBM, which could lift its 4 MT W-39 thermonuclear warhead to a range of 325 km (175 nm) with an accuracy of about 300 m (1000 ft) CEP. Howerver, a Redstone battalion was very cumbersome to move, consisting of almost 20 heavy vehicles. When a launch site was reached, its exact position had to be determined, the launch pad had to be leveled, and the three sections of the missile had to be assembled and erected. All this took more than 8 hours to complete. After receiving the launch order, fueling would need another 15 minutes, before the Redstone could finally be launched.

In June 1963, the M8 and XM9 missiles were redesignated as PGM-11A and PTM-11B, respectively. At that time, phase-out of the Redstone had already begun, and in late 1964, the PGM-11 was no longer in U.S. Army service. The Redstone was replaced by the much more advanced and far easier to use solid-fueled MGM-31 Pershing MRBM. In total, about 120 Redstone missiles were produced by Chrysler between 1955 and 1960.

The Redstone was an important rocket in the early U.S. space program. It formed the base of the Jupiter C, which was the launcher for the first American satellite, and it was used in the very important Mercury-Redstone program of suborbital flights, which led directly to the first U.S. manned orbital space flight with a Mercury-Atlas rocket.

Note: Data given by several sources show slight variations. Figures given below may therefore be inaccurate!

Data for PGM-11A:

[1] James N. Gibson: "Nuclear Weapons of the United States", Schiffer Publishing Ltd, 1996
[2] Bill Gunston: "The Illustrated Encyclopedia of Rockets and Missiles", Salamander Books Ltd, 1979
[3] Redstone Arsenal Historical Information Website

Manufacturer: von Braun. Launches: 100. Failures: 47. Success Rate: 53.00%. First Launch Date: 1953-08-20. Last Launch Date: 1967-11-29. Launch data is: complete. Apogee: 90 km (55 mi). Associated Spacecraft: Mercury, Adam. Liftoff Thrust: 367.500 kN (82,617 lbf). Total Mass: 27,980 kg (61,680 lb). Core Diameter: 1.83 m (6.00 ft). Total Length: 21.13 m (69.32 ft). Span: 3.66 m (12.00 ft). Standard warhead mass: 3,580 kg (7,890 lb). Maximum range: 320 km (190 mi). Number Standard Warheads: 1. Standard warhead: W39. Standard warhead yield: 3,750 KT. Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 5,650 kph (3,510 mph). Development Cost $: 92.500 million. in: 1956 average dollars. Recurring Price $: 4.934 million. Total Number Built: 120. Total Development Built: 35. Total Production Built: 85. Flyaway Unit Cost $: 1.994 million. in: 1959 unit dollars. Cost comments: Launch price and flyaway price transposed?.

• Stage1: 1 x Jupiter C. Gross Mass: 28,430 kg (62,670 lb). Empty Mass: 3,890 kg (8,570 lb). Motor: 1 x A-7. Thrust (vac): 416.184 kN (93,562 lbf). Isp: 265 sec. Burn time: 155 sec. Length: 17.58 m (57.67 ft). Diameter: 1.77 m (5.80 ft). Propellants: Lox/Hydyne.

• Stage1: 1 x Redstone. Gross Mass: 28,440 kg (62,690 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x A-6. Thrust (vac): 414.340 kN (93,147 lbf). Isp: 265 sec. Burn time: 155 sec. Length: 17.58 m (57.67 ft). Diameter: 1.77 m (5.80 ft). Propellants: Lox/Alcohol.

Launches: 9. Failures: 5. First Launch Date: 1956-09-20. Last Launch Date: 1958-10-23. LEO Payload: 11 kg (24 lb). Apogee: 1,000 km (600 mi). Associated Spacecraft: Beacon 1, Explorer A, Explorer B, Explorer C. Liftoff Thrust: 369.000 kN (82,954 lbf). Total Mass: 29,060 kg (64,060 lb). Core Diameter: 1.78 m (5.83 ft). Total Length: 21.20 m (69.50 ft). Development Cost $: 92.500 million. in: 1956 average dollars. Flyaway Unit Cost $: 1.994 million. in: 1959 unit dollars. Cost comments: Development, flyaway cost for Redstone missile.

• Stage1: 1 x Jupiter C. Gross Mass: 28,430 kg (62,670 lb). Empty Mass: 3,890 kg (8,570 lb). Motor: 1 x A-7. Thrust (vac): 416.184 kN (93,562 lbf). Isp: 265 sec. Burn time: 155 sec. Length: 17.58 m (57.67 ft). Diameter: 1.77 m (5.80 ft). Propellants: Lox/Hydyne.

• Stage2: 11 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

• Stage3: 3 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

• Stage4: 1 x Sergeant. Gross Mass: 42 kg (92 lb). Empty Mass: 21 kg (46 lb). Motor: 1 x Sergeant. Thrust (vac): 6.660 kN (1,497 lbf). Isp: 235 sec. Burn time: 6.00 sec. Length: 1.00 m (3.20 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.

LEO Payload: 11 kg (24 lb). Apogee: 5,000 km (3,100 mi). Liftoff Thrust: 357.000 kN (80,256 lbf). Total Mass: 28,500 kg (62,800 lb). Core Diameter: 1.78 m (5.83 ft). Total Length: 21.20 m (69.50 ft). Version:

Redstone MRLV.

Redstone Mercury Credit - © Thom

Suborbital launch vehicle.

Greatly modified Redstone rocket used to launch the Mercury manned spacecraft on a suborbital trajectory, typically 380 km downrange, 220 km altitude, and a speed of 6800 kph.

The Redstone used for the Mercury manned flights was derived from the Jupiter-C version of the Redstone originally developed as the first stage of a satellite launch vehicle. The designers of the Redstone and Jupiter missile systems proposed an extensive list of basic modifications to adapt the vehicle to the Mercury capsule. The fundamental change made to the Jupiter-C airframe was the elimination of its staging capability. Other modifications stripped it of its more sophisticated components while permitting it to retain greater performance characteristics than the original single-stage Redstone.

The elongated fuel tanks of the Jupiter-C had to be retained for 20 extra seconds of engine burning time, especially since they decided to revert to alcohol for fuel rather than use the more powerful but more toxic hydyne that fueled the Jupiter-C. Another high-pressure nitrogen tank to pressurize the larger fuel tank and an auxiliary hydrogen peroxide fuel tank to power the engine turbopump also had to be added. To increase the reliability of the advanced Redstone, they had to simplify other parts of the Jupiter-C system. Instead of the sophisticated autopilot called ST-80, one of the first inertial guidance systems (the LEV-3 ) was reinstalled as the guidance mechanism. The after unit of the payload on the old Redstone, which had contained a pressurized instrument compartment, became the permanent forebody of the main tank assembly, there being no need to provide terminal guidance for the new payload. A spacecraft adapter ring likewise had to be designed to simplify interface coordination and to ensure clean separation between capsule and booster. At the other end of the launch vehicle it was necessary to use the most recent engine model, the A-7, to avoid a possible shortage of spare parts. Von Braun's propulsion engineers took the basic responsibility for "manrating" this engine.

Although NASA engineers bought the Redstone in the first place because it was considered an "off-the-shelf" rocket, they gradually learned that the Mercury-Redstone was in danger of being modified in about 800 particulars, enough to vitiate the record of reliability established by the earlier Redstones and Jupiter-Cs. Too much redesign also meant reopening the Pandora's box of engineering "trade-offs," the compromises between overdesign and underdesign. Von Braun's team tended in the former direction; NASA's in the latter. Von Braun's team wanted "positive redundancy" to ensure aborts whenever required, whereas NASA wanted more "negative redundancy" to avoid aborts unless absolutely essential. This distinction was the crux of the dispute and the essence of the distinction between "pilot safety" and "mission success."

Launches: 6. Failures: 1. First Launch Date: 1960-11-21. Last Launch Date: 1961-07-21. Apogee: 200 km (120 mi). Associated Spacecraft: Mercury. Liftoff Thrust: 357.000 kN (80,256 lbf). Total Mass: 28,400 kg (62,600 lb). Core Diameter: 1.78 m (5.83 ft). Total Length: 20.00 m (65.00 ft).

• Stage1: 1 x Redstone Mercury. Gross Mass: 28,440 kg (62,690 lb). Empty Mass: 3,125 kg (6,889 lb). Motor: 1 x A-7. Thrust (vac): 414.340 kN (93,147 lbf). Isp: 265 sec. Burn time: 155 sec. Length: 17.58 m (57.67 ft). Diameter: 1.77 m (5.80 ft). Propellants: Lox/Alcohol.

Launches: 10. Failures: 1. First Launch Date: 1966-11-28. Last Launch Date: 1967-11-29. LEO Payload: 45 kg (99 lb). to: 300 km Orbit. at: 28.00 degrees. Apogee: 1,100 km (600 mi). Associated Spacecraft: Wresat. Liftoff Thrust: 357.000 kN (80,256 lbf). Total Mass: 30,000 kg (66,000 lb). Core Diameter: 1.78 m (5.83 ft). Total Length: 21.80 m (71.50 ft).

• Stage1: 1 x Jupiter C. Gross Mass: 28,430 kg (62,670 lb). Empty Mass: 3,890 kg (8,570 lb). Motor: 1 x A-7. Thrust (vac): 416.184 kN (93,562 lbf). Isp: 265 sec. Burn time: 155 sec. Length: 17.58 m (57.67 ft). Diameter: 1.77 m (5.80 ft). Propellants: Lox/Hydyne.

• Stage2: 1 x Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x X-259. Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Length: 2.90 m (9.50 ft). Diameter: 0.78 m (2.55 ft). Propellants: Solid.

• Stage3: 1 x SPARTA-3. Gross Mass: 100 kg (220 lb). Empty Mass: 28 kg (61 lb). Motor: 1 x BE-3. Thrust (vac): 34.000 kN (7,643 lbf). Burn time: 9.00 sec. Length: 0.60 m (1.96 ft). Diameter: 0.60 m (1.96 ft). Propellants: Solid.

November 1943 - Development of ballistic missiles authorized. Gen. H. H. Arnold, Chief of Air Staff, directed and authorized emphasis on research, development, and procurement of guided missiles, as indicated by known German advances.

1944 November 20 - Project Hermes Ordnance Department entered into a research and development contract with the General Electric Company for study and development of long-range missiles that could be used against ground targets and high-altitude aircraft. This was the beginning of the Hermes project.

1946 June 1 - Hermes C1 General Electric began a feasibility study of the Hermes C1 which later formed the basis for early Redstone missile research.

1947 January 23 - White Sands -. Hermes telemetry system test. Telemetry operated successfully in a V-2 firing at WSPG, Army Ordnance's Hermes telemetry system.

1948 September 15 - Hermes project extended to cover satellite launch. Committee on Guided Missiles of the Research and Development Board approved recommendation that Army Hermes project "be given the task of providing the National Military Establishment with a continuing analysis of the long-range rocket problem as an expansion of their task on an earth satellite vehicle."

1949 June 1 - Redstone Arsenal selected for rocket research. Redstone Arsenal was reactivated from standby status as the site of the Ordnance Rocket Center.

1949 October 28 - Von Braun team moved to Huntsville. The Secretary of the Army approved the transfer of the Ordnance Research and Development Division, Sub-Office (Rocket) at Fort Bliss, Texas, to Redstone Arsenal. Among those transferred were Dr. Wernher von Braun and his team of German scientists.

1950 July 10 - Hermes production version studied. Office, Chief of Ordnance directed that the Ordnance Guided Missile Center conduct a preliminary study of the technical requirements and possibilities of developing a 500-mile tactical missile that would be used principally in providing support for the operations of the Army Field Forces.

1950 September 11 - Hermes work transferred from General Electric to Von Braun team. Ordnance Department directed that the Hermes contract with General Electric Company be amended to transfer responsibility for the Hermes C1 project to the Ordnance Guided Missile Center.

1951 July 10 - Hermes work transferred to Redstone arsenal. The Office, Chief of Ordnance formally transferred the responsibility for conducting the research and development phase of the HERMES Cl project to Redstone Arsenal

1951 October 31 - Hermes project transferred to Redstone Arsenal. Responsibility for Hermes II transferred to Army Ordnance Guided Missile Center at Redstone Arsenal; Hermes II redesignated the RVA-A-3 test vehicle.

1952 April 1 - Contractor to build Redstone rocket. The Office, Chief of Ordnance (OCO) disapproved Redstone Arsenal's proposed development plan for what would become the Redstone missile. The arsenal had intended to implement the manufacturing program for these missiles by creating an assembly line in its own development shops. The OCO, however, required that the development effort be done by a prime contractor. Nonetheless, delays in the acquisition of production facilities for the prime contractor caused Redstone Arsenal to fabricate and assemble the first 12 Redstone missiles along with missiles 18 through 29.

1952 April 8 - Redstone rocket named. The Redstone missile system officially received its popular name. Previously, this missile was known at various times and places as the Hermes C1, Major, Ursa, XSSM-G-14, and XSSM-A-14.

1952 October 1 - Chrysler receives Redstone contract. Chrysler Corporation issued a letter order contract to proceed with active work as the prime contractor on the Redstone missile system. This contract was definitized on 19 Jun 53.

1953 August 20 - 14:37 GMT - Cape Canaveral LC4. Redstone RS-1 FAILURE: Control System malfunction followed by Power Plant malfunction at approximately 80 sec. Ground cut-off command given.. Agency: USA. Apogee: 6.00 km (3.70 mi). Redstone missile No. 1 was fired by Army Redstone Arsenal personnel at AFMTC, Cape Canaveral. Missile test failure. Missed aimpoint by 240,000 m.

1954 January 27 - 15:20 GMT - Cape Canaveral LC4. Redstone RS-2 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 8,400 m.

1954 May 5 - 17:28 GMT - Cape Canaveral LC4. Redstone RS-3 FAILURE: Ejector burnout immediately following lift-off. Agency: USA. Apogee: 0 km ( mi). Missile test failure. Missed aimpoint by 277,000 m.

1954 June 25 - Project Orbiter begun. Spacecraft: Explorer A. In a meeting, Dr. Wernher von Braun, Frederick C. Durant III, Alexander Satin, David Young, Dr. Fred L. Whipple, Dr. S. Fred Singer, and Commander George W. Hoover agreed that a Redstone rocket with a Loki cluster as the second stage could launch a satellite into a 200-mile orbit without major new developments. This became a joint Army-Navy study project after meeting at Redstone Arsenal on August 3. Project Orbiter was a later outgrowth of this proposal and resulted in the launching of Explorer I on January 31, 1958.

1954 August 15 - Von Braun proposes launch of US satellite. Spacecraft: Explorer A. Von Braun report 'A Minimum Satellite Vehicle Based on Components Available from Developments of the Army Ordnance Corps' in response to June Pentagon meeting proposes $ 100,000 to launch satellite by Redstone.

1954 August 18 - 14:04 GMT - Cape Canaveral LC4. Redstone RS-4 FAILURE: Steam generator regulator malfunction caused drop in combustion pressure. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 19,200 m.

1954 September 29 - Redstone contract awarded. Army Ordnance awarded contract for Redstone missile to Chrysler Corp.

1954 November 17 - 18:12 GMT - Cape Canaveral LC4. Redstone RS-6 FAILURE: Ground programmed yaw maneuver caused missile control loss at 80 sec causing power plant erratic behavior. Human error in selection of yaw maneuver impulse. Agency: USA. Apogee: 0 km ( mi). Missile test failure. Missed aimpoint by 166,300 m.

1954 December 31 - Hermes program terminated. Army Ordnance terminated the Hermes project, during which development of high-performance liquid-fuel rocket and first stabilized platform inertial guidance equipment had been accomplished.

1955 February 9 - 20:15 GMT - Cape Canaveral LC4. Redstone RS-8 FAILURE: Separation bolt No. 3 failure. Inverter frequency shift. Agency: USA. Apogee: 0 km ( mi). Missile test failure. Missed aimpoint by 23,400 m.

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

1955 May 23 - Cape Canaveral -. Project Orbiter plans. Project Orbiter Conference was held at Redstone Arsenal and at Cape Canaveral.

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

1955 June 15 - First Redstone production contract. Chrysler Corporation received the first industrial contract for the Redstone.

1955 August 24 - Redstone recommended as satellite launcher. Spacecraft: Explorer A. Research and development Policy Council (DOD) unanimously recommended that the time-risk factor in the scientific satellite program be brought to the attention of the Secretary of the Defense for determination as to whether a Redstone backup program was indicated.

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

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

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

1956 February 1 - ABMA established. Army activated the Army Ballistic Missile Agency (ABMA) at Redstone Arsenal, Huntsville, Ala., to weaponize the Redstone and to develop the Jupiter IRBM.

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

1956 April 15 - First Redstone batallion formed. The first Redstone missile battalion, the 217th Field Artillery Missile Battalion, was formally activated at Redstone Arsenal.

1956 April 23 - Army proposes Redstone satellite launch. Army informed the OSD that a Jupiter missile could be fired in an effort to orbit a small satellite in January 1957.

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

1956 July 19 - 08:45 GMT - Cape Canaveral LC5. Jupiter A CC-13 FAILURE: ST-80 malfunction at theta switch operation - 310 sec. Jupiter A Agency: USA. Apogee: 90 km (55 mi). CC-13 was launched at 0345 hours EST from AMR. The flight was successful. The actual range was 142.457 nm; .780 nm over the intended impact point. This was the first Chrysler fabricated and assembled missile. Missed aimpoint by 1,071 m.

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

1956 September 20 - 06:45 GMT - Cape Canaveral LC5. Jupiter C RS-27 FAILURE: Early cut-off due to human error in tanking . Jupiter C re-entry vehicle test flight Agency: USA. Apogee: 1,097 km (681 mi). First Jupiter C (a three-stage ABMA-JPL Redstone missile) was launched at Cape Canaveral, Fla., attained an altitude of 1096 km and traveled 5,300 km downrange. The first three-stage re-entry missile, was fired at 0145 hours EST from AMR. This missile attained an estimated range of 3,335 ST miles, an altitude of 682 ST miles, and reached Mach 18 velocity. The primary objective of the firing was the propulsion and separation tart of a multi-stage vehicle. The missile was a four-stage configuration with the last stage inactive. The first stage was an elongated Redstone missile, the second and third stages were up of 11 and 3 six-inch scaled SERGEANT rockets, respectively. The payload consisted of approximately 20 pounds of instrumentation attached to the inactive fourth stage. The flight was successful and the sequence of operations occurred as programmed. This vehicle could have obtained sufficient velocity to place it in orbit, if the last stage had been activated. First deep penetration of space. Serial number coding for early Redstones and related vehicles used the following substitution cipher: 1234567890 = HUNTSVILLEX

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

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

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

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

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

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

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

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

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

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

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

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

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

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

1957 September 9 - First US Army heavy missile group. The 40th Field Artillery Missile Group, the first heavy missile group organized in the U.S. Army, was transferred from Fort Carson, Colorado, to Redstone Arsenal.

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

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

1957 October 5 - Von Braun promises first US satellite in 60 days. Spacecraft: Explorer A. Von Braun briefs Secretary of Defence McElroy on Jupiter-C/Redstone for immediate US satellite launch. Promises launch in 60 days. Medaris says 90.

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

1957 November 7 - Eisenhower enunciates science policy. President Eisenhower in major address on science and security announced that scientists had solved the problem of ballistic missile reentry and showed the nose cone of an Army Jupiter-C missile which was intact after a flight through space. He announced the creation of the office of Special Assistant to the President for Science and Technology and the appointment of James R. Killian, president of the Massachusetts Institute of Technology, to the new post.

1957 November 8 - Von Braun ordered to launch satellite. Secretary of Defense Neil McElroy directed the Army to proceed with the launching of the Explorer earth satellites. This order, in effect, resumed the Orbiter project that had been eliminated from the IGY satellite planning program on September 9, 1955. Von Braun was to modify two Jupiter-C missiles (modified Redstones) and attempt to place an artificial earth satellite in orbit by March 58.

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

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

1958 February 1 - 03:47 GMT - Cape Canaveral LC26A. Jupiter C/Juno I RS-29 Explorer 1 Mass: 5.00 kg (11.00 lb). Spacecraft: Explorer A. Agency: U.S. Army. Perigee: 347 km (215 mi). Apogee: 1,859 km (1,155 mi). Inclination: 33.20 deg. Period: 107.20 min. Explorer I, the first U.S. earth satellite, was launched by a modified Army Ballistic Missile Agency Jupiter-C. Explorer I, developed by the Jet Propulsion Laboratory, carried the U.S.-IGY (International Geophysical Year) experiment of James A. Van Allen and resulted in the discovery of the radiation belt around the earth.

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

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

1958 March 5 - 18:27 GMT - Cape Canaveral LC26A. Jupiter C/Juno I RS/CC-26 FAILURE: Fourth Stage failed to ignite. Explorer 2 Mass: 5.00 kg (11.00 lb). Spacecraft: Explorer A. Agency: U.S. Army.

1958 March 26 - 17:38 GMT - Cape Canaveral LC5. Jupiter C/Juno I RS-24 Explorer 3 Mass: 5.00 kg (11.00 lb). Spacecraft: Explorer A. Agency: U.S. Army. Perigee: 186 km (115 mi). Apogee: 2,799 km (1,739 mi). Inclination: 33.40 deg. Period: 115.70 min. Radiation, micrometeoroid data.

1958 March 27 - ARPA assigned space project role. President Eisenhower gave his approval to the plans for outer space exploration announced by Secretary of Defense Neil H. McElroy. The Advanced Research Projects Agency (ARPA) was to undertake several space projects including the launching of certain earth satellites and five space probes as a part of this country's contribution to the IGY program. The Air Force Ballistic Missile Division was authorized by ARPA to carry out three lunar probes with a Thor-Vanguard system, and lunar probes utilizing the Jupiter-C rocket were assigned to the Army Ballistic Missile Agency.

1958 May 17 - 00:05 GMT - Cape Canaveral LC5. Redstone RS-1002 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 578 m.

1958 June 1 - First Redstone deployment to Europe. The Redstone became the first large U.S. ballistic missile to be deployed overseas, joining the NATO Shield Force.

1958 June 3 - 04:50 GMT - White Sands LC36. Redstone CC-1004 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 409 m.

1958 June 12 - 01:59 GMT - Cape Canaveral LC6. Jupiter A CC-54 Test mission Agency: USA. Apogee: 90 km (55 mi).

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

1958 July 26 - 15:00 GMT - Cape Canaveral LC5. Jupiter C/Juno I RS/CC-44 Explorer 4 Mass: 8.00 kg (17.60 lb). Spacecraft: Explorer B. Agency: DARPA. Perigee: 257 km (159 mi). Apogee: 1,352 km (840 mi). Inclination: 50.20 deg. Period: 100.90 min. Mapped project Argus radiation.

1958 August 1 - 09:47 GMT - Johnston Island LC1. Redstone CC-50 FAILURE: Failure of tilt program device at lift-off causing vertical night flight did not preclude subsequent system operations and successful mission accomplishment. Hardtack Teak Nuclear test Agency: USA. Apogee: 76 km (47 mi). Teak was a rocket-launched test of a live W-39 nuclear warhead. Purpose was to measure the effects of high altitude nuclear explosions in order to design warheads for the Nike-Zeus anti-ballistic missile system. The Hardtack Configuration Redstone shot the 3.8 megaton warhead to an altitude of 77.8 km. This was the first rocket-launched nuclear test by the United States.

1958 August 12 - 09:27 GMT - Johnston Island LC2. Redstone CC-51 FAILURE: Guidance system malfunction at 70 seconds which did not preclude subsequent system operations and successful mission accomplishment. Hardtack Orange Nuclear test Agency: USA. Apogee: 41 km (25 mi). Orange was a rocket-launched test of the W-39 warhead. Purpose was to measure the effects of high altitude nuclear explosions in order to design warheads for Nike-Zeus anti-ballistic missile system. The Hardtack Configuration Redstone shot the 3.8 megaton warhead to an altitude of 43 km.

1958 August 24 - 06:17 GMT - Cape Canaveral LC5. Jupiter C/Juno I RS/CC-47 FAILURE: First Stage collided with upper stages. Second Stage ignited in wrong direction. Explorer 5 Mass: 17 kg (37 lb). Spacecraft: Explorer C. Agency: DARPA.

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

1958 October 6 - Negotiations for Redstone and Jupiter launch vehicles for Mercury project. Personnel from the Langley Research Center visited the Army Ballistic Missile Agency to open negotiations for procuring Redstone and Jupiter launch vehicles for manned satellite projects.

1958 October 23 - 03:21 GMT - Cape Canaveral LC5. Jupiter C/Juno I RS/CC-49 FAILURE: Upper stages separated prior to burnout. Structural failure after 149 sec due to vibration disturbances generated by the spinning payload. Beacon 1 Mass: 4.00 kg (8.80 lb). Spacecraft: Beacon 1. Agency: NASA. NASA¾with the Army as executive agent¾attempted to launch a 12-foot-diameter inflatable satellite of micro-thin plastic covered with aluminum foil known as BEACON. Launched from AMR by a Juno I¾a modified Redstone, the payload prematurely separated prior to booster burnout.

1958 October 24 - Redstone static firing at White Sands. The Redstone underwent static firing at White Sands Missile Range, the first time such a test had been conducted there.

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

1958 December 2 - Redstone and Jupiter launch vehicle use on Mercury discussed. Space Task Group officials visited the Army Ballistic Missile Agency to determine the feasibility of using the Jupiter launch vehicle for the intermediate phase of Project Mercury, to discuss the Redstone program, and to discuss the cost for Redstone and Jupiter launch vehicles.

1959 January 8 - Redstones ordered for Mercury suborbital launches. NASA requested eight Redstone-type launch vehicles from the Army to be used in Project Mercury development flights.

1959 January 16 - Eight Redstone and two Jupiter launch vehicles for Mercury NASA requested the Army Ordnance Missile Command, Huntsville, Alabama, to construct and launch eight Redstone launch vehicles and two Jupiter launch vehicles in support of Project Mercury manned and unmanned flights.

1959 January 19 - White Sands LC36. Redstone 1010 FAILURE: Human error in connecting separation system. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 1,189 m.

1959 February 11 - Redstone and Jupiter flight phases of Project Mercury. Spacecraft: Mercury. Space Task Group and Army Ballistic Missile Agency personnel met at Huntsville, Alabama, to discuss Redstone and Jupiter flight phases of Project Mercury. During the course of the meeting the following points became firm: (1) Space Task Group was the overall manager and technical director of this phase of the program, (2) ABMA was responsible for the launch vehicle until spacecraft separation, (3) ABMA was responsible for the Redstone launch vehicle recovery (this phase of the program was later eliminated since benefits from recovering the launch vehicle would have been insignificant), (4) Space Task Group was responsible for the spacecraft flight after separation, (5) McDonnell was responsible for the adapters for the Mercury-Redstone configuration, and (6) ABMA would build adapters for the Mercury-Jupiter configuration. Because many points could only be settled by detailed design studies, it was decided to establish several working panels for later meetings.

1959 February 16 - White Sands LC36. Redstone 1011 FAILURE: Improper setting of thrust controller and malfunction of tilt program at 17 sec. Agency: USA. Apogee: 10 km (6 mi). Missile test failure. Missed aimpoint by 17,942 m.

1959 February 24 - Mercury-Redstone-Jupiter trajectory, aerodynamics, and flight loads Spacecraft: Mercury. Mercury-Redstone-Jupiter Study Panel Number IV (choice of trajectory, aerodynamics, and flight loads) met at Redstone Arsenal. Subjects studied included pilot safety, simulation of entry from orbit, length of zero-g time, missile stability and aerodynamics, ascent accelerations, and range. This group reconvened on March 13, 1959.

1959 February 26 - Integration of the Mercury spacecraft with the Redstone and Jupiter launch vehicles. Spacecraft: Mercury. Panel Number I (Design Subcommittee) met at Redstone Arsenal for the first time to discuss integration requirements for the Mercury spacecraft with the Redstone and Jupiter launch vehicles.

1959 March 10 - White Sands LC36. Redstone 1016 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Army Redstone ejected miniature TV camera which transmitted pictures of its target impact area. Missed aimpoint by 144 m.

1959 March 20 - Mercury-Redstone and Mercury-Jupiter test objectives. Spacecraft: Mercury. Mercury-Redstone and Mercury-Jupiter test objectives were discussed in a meeting at Langley between Space Task Group and Army Ballistic Missile Agency personnel. At that time it was decided that the first flights of both the Redstone and Jupiter would be unmanned. The second flights would be 'manned' with primates, and the Jupiter phase would end at that point. The six remaining Redstones would be used in manned flights for astronaut training.

1959 May 12 - White Sands LC36. Redstone 1013 FAILURE: Known initial laying error of approximately 26 min. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 1,091 m.

1959 May 22 - Negotiations on the cost of Redstone and Jupiter boosters for Project Mercury. The Space Task Group, in the process of negotiations with the Army Ordnance Missile Command on the cost of Redstone and Jupiter boosters in support of Project Mercury, received revised funding estimates for study covering Contract HS-44 (Redstone) and HS-54 (Jupiter).

1959 June 5 - Mercury-Redstone inflight abort sensing system. The Army Ballistic Missile Agency submitted a proposal (Report No. DG-TR-7-59) for a Mercury-Redstone inflight abort sensing system. This system would monitor performance of the control system (attitude and angular velocity), electrical power supply, and launch vehicle propulsion. If operational limits were exceeded, the spacecraft would be ejected from the launch vehicle and recovered by parachute.

1959 June 24 - Eight Mercury Redstone launch vehicles final cost $20.1 million. Against an original estimated cost of $15.5 million for eight Redstone launch vehicles in support of Project Mercury, the final negotiated figure was $20.1 million.

1959 July 22 - 04:02 GMT - Cape Canaveral LC26A. Redstone CC-2003 FAILURE: Control system malfunction during re-entry at 380 sec. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 684 m.

1959 August 5 - 02:05 GMT - Cape Canaveral LC26A. Redstone CC-2004 FAILURE: Pre-launch tanking error caused early cut-off by fuel depletion. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 2,707 m.

1959 September 18 - White Sands LC36. Redstone 1018 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 228 m.

1959 November 20 - Open-circuit television system in the Mercury-Redstone MR-2 and MR-3 flights Spacecraft: Mercury. Flight: Mercury MR-3. At the fifth Mercury Coordination Meeting, the Army Ballistic Missile Agency proposed the installation of an open-circuit television system in the Mercury-Redstone second and third flights (MR-2 and MR-3). The purpose of the system was to observe and relay launch vehicle and spacecraft separation data.

1959 December 22 - Redstone for Mercury MR-1 installed on the interim test stand. The Redstone launch vehicle for the first Mercury-Redstone mission (MR-1) was installed on the interim test stand at the Army Ballistic Missile Agency for static testing.

1960 January 18 - Mercury-Redstone Coordination Committee Walter C. Williams proposed the establishment of a Mercury-Redstone Coordination Committee to monitor and coordinate activities related to Mercury-Redstone flight tests.

1960 January 26 - White Sands LC36. Redstone 2011 Capsule operational test launch Agency: USA. Apogee: 90 km (55 mi). Successful missile test with capsule. Missed aimpoint by 277 m.

1960 January 31 - Six chimpanzees ready for Mercury missions. Six chimpanzees were rated as being trained and ready to support Mercury-Redstone or Mercury-Atlas missions. Other chimpanzees were being shipped from Africa to enter the animal training program.

1960 February 8 - Tests started for the mission abort sensing program for Mercury-Redstone Tests were started by the Army Ballistic Missile Agency for the mission abort sensing program to be integrated in the Mercury-Redstone phase of Project Mercury.

1960 March 15 - White Sands LC36. Redstone 2014 T-1 Capsule operational test launch Agency: USA. Apogee: 90 km (55 mi). Successful missile test with T-1 Capsule. Missed aimpoint by 295 m.

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

1960 April 15 - White Sands LC36. Redstone 2021 T-1 Capsule Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 17 m.

1960 June 2 - White Sands LC36. Redstone 2022 Agency: USA. Apogee: 75 km (46 mi). Successful missile test. Missed aimpoint by 336 m.

1960 July 6 - Fort Wingate -. Redstone 1019 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 176 m.

1960 July 7 - Reporting plan for Mercury-Atlas and Mercury-Redstone missions A reporting plan for Mercury-Atlas and Mercury-Redstone missions was issued. This document was amended on February 17, 1961, and April 10, 1961.

1960 July 23 - Mercury spacecraft No. 2 delivered to Cape Canaveral Spacecraft: Mercury. Mercury spacecraft No. 2 was delivered to Cape Canaveral for the Mercury-Redstone 1-A (MR-1A) mission.

1960 August 1 - Final Trajectory for Mercury MR-1 Marshall Space Flight Center published the 'Final Standard Trajectory for MR-1 (Mercury-Redstone).'

1960 August 3 - Redstone launch vehicle No. 1 was delivered to Cape Canaveral for the MR-1 (Mercury-Redstone).

1960 August 10 - 01:31 GMT - Cape Canaveral LC6. Redstone 2023 FAILURE: Erroneously destroyed during boost by range personnel. Agency: USA. Apogee: 10 km (6 mi). Missile test failure.

1960 September 19 - Format of first Mercury-Redstone postlaunch report The format of subject matter coverage for the first Mercury-Redstone postlaunch (MR-1) report was issued. This report, covering a full range of topics related to the mission, was to be submitted within 5 days after the launch.

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

1960 October 18 - Mission rules for Mercury-Redstone 1 (MR-1) issued. A revision was published on Nov. 1, 1960.

1960 November 21 - An attempt was made to launch Mercury-Redstone 1 (MR-1) from Cape Canaveral. Spacecraft: Mercury. This unmanned mission was unsuccessful because premature cut-off of the launch vehicle engines activated the emergency escape system when the vehicle was only about 1 inch off the pad. Engine cut-off was caused by premature loss of electrical ground power to the booster. The launch vehicle settled back on the pad with only slight damage. Since the spacecraft received a cut-off signal, the escape tower and recovery sequence was initiated. The undamaged spacecraft was recovered for reuse.

1960 November 21 - 14:00 GMT - Cape Canaveral LC5. Redstone MRLV-1 FAILURE: Engine cut off after 1 sec, vehicle fell back to the pad from a few centimeters height, but did not explode. This faulty ground-support circuitry had not been noted on some 60 previous Redstone firings. Mercury MR-1 Agency: NASA. Apogee: 0 km ( mi). Suborbital launch attempt. After a four- or five-inch liftoff, MR-1 launched its escape tower but not the capsule. The undamaged spacecraft was recovered for reuse.

1960 December 3 - Mercury Redstone launch vehicle No. 3 shipped to Cape Canaveral Spacecraft: Mercury. Redstone launch vehicle No. 3 was shipped to Cape Canaveral for the Mercury-Redstone 1A (MR-1A) mission.

1960 December 9 - Mercury spacecraft No. 7 delivered to Cape Canaveral Spacecraft: Mercury. Flight: Mercury MR-3. Spacecraft No. 7 was delivered to Cape Canaveral for the Mercury-Redstone 3 (MR-3) manned ballistic mission (Shepard).

1960 December 19 - 16:15 GMT - Cape Canaveral LC5. Redstone MRLV-3 Mercury MR-1A Agency: NASA. Apogee: 210 km (130 mi). Mercury-Redstone 1A (MR-1A) was launched from Cape Canaveral in a repeat of the November 21, 1960, mission and was completely successful. This was the third attempt to accomplish the objectives established for this flight. The first attempt on November 7, 1960, was canceled as a result of a helium leak in the spacecraft reaction control system relief valve, and on November 21, 1960, the mission could not be completed because of premature cut-off of the launch vehicle engines. Objectives of the MR-1A flight were to qualify the spacecraft for space flight and to qualify the flight system for a primate flight scheduled shortly thereafter. Close attention was given to the spacecraft-launch vehicle combination as it went through the various flight sequences: powered flight; acceleration and deceleration; performance of the posigrade rockets; performance of the recovery system; performance of the launch, tracking, and recovery phases of the operation; other events of the flight including retrorocket operation in a space environment; and operation of instrumentation. Except that the launch vehicle cut-off velocity was slightly higher than normal, all flight sequences were satisfactory; tower separation, spacecraft separation, spacecraft turnaround, retrofire, retropackage jettison, and landing system operation occurred or were controlled as planned. The spacecraft reached a maximum altitude of 130.68 statute miles, a range of 234.8 statute miles, and a speed of 4,909.1 miles per hour. Fifteen minutes after landing in the Atlantic Ocean, the recovery helicopter picked up the spacecraft to complete the successful flight mission.

1960 December 20 - Mercury Redstone launch vehicle No. 2 delivered to Cape Canaveral Redstone launch vehicle No. 2 was delivered to Cape Canaveral for the Mercury-Redstone 2 (MR-2) mission (chimpanzee 'Ham' flight).

1961 January 16 - Mercury MR-1A postlaunch system evaluation tests The Mercury-Redstone 1A (MR-1A) postlaunch system evaluation tests were completed at Cape Canaveral. Data disclosed that the instrumentation system, communication system, and other components had operated satisfactorily during the flight mission.

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

1961 January 31 - 16:54 GMT - Cape Canaveral LC5. Redstone MRLV-2 Mercury MR-2 Agency: NASA. Apogee: 251 km (155 mi). Ham, a 37-pound chimpanzee, was aboard the spacecraft. The over-acceleration of the launch vehicle coupled with the velocity of the escape rocket caused the spacecraft to attain a higher altitude and a longer range than planned. In addition, the early depletion of the liquid oxygen caused a signal that separated the spacecraft from the launch vehicle a few seconds early. However spacecraft recovery was effected, although there were some leaks and the spacecraft was taking on water. Ham appeared to be in good physiological condition, but sometime later when he was shown the spacecraft it was visually apparent that he had no further interest in cooperating with the space flight program. Despite the over-acceleration factor, the flight was considered to be successful.

1961 February 10 - Mission rules for the Mercury MR-3 Spacecraft: Mercury. Flight: Mercury MR-3. Mission rules for the Mercury-Redstone 3 (MR-3 - Shepard's flight) were published. Revisions were issued on February 27, and April 28, 1961.

1961 March 7 - Mercury Redstone launch vehicle No. 5 delivered to Cape Canaveral Redstone launch vehicle No. 5 was delivered to Cape Canaveral for the Mercury-Redstone, Booster Development flight (MR-BD).

1961 March 7 - Mercury spacecraft No. 11 delivered to Cape Canaveral Spacecraft: Mercury. Flight: Mercury MR-4. Spacecraft No. 11 was delivered to Cape Canaveral for the Mercury-Redstone 4 (MR-4) ballistic manned (Grissom) flight.

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

1961 March 24 - 17:30 GMT - Cape Canaveral LC5. Redstone MRLV-5 Mercury MR-BD Agency: NASA. Apogee: 181 km (112 mi). Suborbital test of Redstone modifications using a boilerplate Mercury capsule. The test was done at von Braun's insistence against Shepard's wishes, thereby putting the first US manned flight after Gagarin's.

1961 March 30 - Mercury Redstone launch vehicle No. 7 delivered to Cape Canaveral Flight: Mercury MR-3. Redstone launch vehicle No. 7 was delivered to Cape Canaveral for the Mercury-Redstone 3 (MR-3) mission.

1961 April 4 - Glenn, Grissom, and Shepard refresher course on centrifuge for Mercury Glenn, Grissom, and Shepard began refresher course on centrifuge in preparation for the first manned Mercury-Redstone suborbital flight. John Glenn, Virgil Grissom, and Alan Shepard began a refresher course on the Aviation Medical Acceleration Laboratory centrifuge in preparation for the first manned Mercury-Redstone suborbital flight.

1961 April 20 - Mercury-Redstone 3 (MR-3) readiness review. Spacecraft: Mercury. Flight: Mercury MR-3. Spacecraft, mission, and launch vehicle flight safety were reviewed by Space Task Group personnel in preparation for the Mercury-Redstone 3 (MR-3) mission.

1961 April 28 - Simulated countdown for Mercury MR-3 Flight: Mercury MR-3. A simulated countdown for the first Mercury-Redstone manned suborbital flight (MR-3) was successfully completed.

1961 May 1 - Webb warns of Mercury failures. NASA Administrator Webb issued a statement concerning the 2-year Mercury manned space flight program, which said, in part: "NASA has not attempted to encourage press coverage of the first Mercury-Redstone manned flight. It has responded to press and television requests, with the result that over 100 representatives of the press, radio, and TV are now at Cape Canaveral. . . . We must keep the perspective that each flight is but one of the many milestones we must pass. Some will completely succeed in every respect, some partially, and some will fail. From all of them will come mastery of the vast new space environment on which so much of our future depends."

1961 May 2 - Mercury MR-3 postponed. Flight: Mercury MR-3. Manned Mercury-Redstone (MR-3) launch postponed because of rain squalls in the recovery area.

1961 May 5 - 14:34 GMT - Cape Canaveral LC5. Redstone MRLV-7 Mercury MR-3 Agency: NASA. Apogee: 187 km (116 mi). Alan Shepard first American in space, less than a month after Gagarin and only on a 15 minute suborbital flight. Only manned flight with original Mercury capsule design (tiny round porthole and periscope a la Vostok). If NASA had not listened to Von Braun, Shepard would have flown on the MR-BD flight of 24 March, beating Gagarin by three weeks and becoming the first man in space (though not in orbit). Shepard's capsule reached an altitude of 115.696 miles, range of 302 miles,and speed of 5,100 miles per hour. He demonstrated control of a vehicle during weightlessness and high G stresses. Recovery operations were perfect; there was no damage to the spacecraft; and Astronaut Shepard was in excellent condition.

1961 May 9 - Kennedy decision to allow MR-3 flight defended. Flight: Mercury MR-3. Senator Robert S. Kerr, chairman of the Senate Aeronautical and Space Sciences Committee, told a group at the National Radio and Television Convention that President Kennedy accepted the views of NASA and congressional leaders in approving the manned Mercury-Redstone flight of May 5.

1961 May 18 - 02:00 GMT - Cape Canaveral LC6. Redstone 2042 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 304 m.

1961 June 12 - Mercury Redstone launch vehicle No. 8 delivered to Cape Canaveral Flight: Mercury MR-4. Redstone launch vehicle No. 8 was delivered to Cape Canaveral for the Mercury-Redstone 4 (MR-4) suborbital flight mission.

1961 June 22 - Mercury MR-4 recovery requirements Flight: Mercury MR-4. Mercury-Redstone 4 (MR-4) recovery requirements were forwarded by the Space Task Group to the Navy.

1961 June 22 - Redstone for Mercury MR-4 manned suborbital flight erected Flight: Mercury MR-4. The Redstone booster for the Mercury-Redstone 4 (MR-4) manned suborbital flight mission was erected on Pad 5, at Cape Canaveral.

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

1961 July 6 - Fort Wingate -. Redstone 1005 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 266 m.

1961 July 13 - Mercury MR-6 static engine test Flight: Mercury MR-6. Mercury-Redstone 6 was static tested for 30 seconds at Marshall Space Flight Center to ensure satisfactory operation of the turbopump assembly.

1961 July 13 - Mercury-Redstone 4 (MR-4) manned suborbital flight mission rules were published. Flight: Mercury MR-4.

1961 July 19 - Mercury MR-4 launch scrubbed. Spacecraft: Mercury. Flight: Mercury MR-4. Mercury-Redstone (MR-4) with manned Liberty Bell 7 capsule canceled within minutes of launch because of adverse weather.

1961 July 21 - 12:20 GMT - Cape Canaveral LC5. Redstone MRLV-8 Mercury MR-4 Agency: NASA. Apogee: 189 km (117 mi). The Mercury capsule, Liberty Bell 7, manned by Astronaut Virgil I. Grissom, boosted by a Redstone rocket, reached a peak altitude of 190.3 km and a speed of 8,335 km per hour. After a flight of 15 minutes and 37 seconds, the landing was made 487 km downrange from the launch site. The hatch blew while still in water, and the capsule sank; Grissom saved, though his suit was filling up with water through open oxygen inlet lines.

This was the second and final manned suborbital Mercury Redstone flight, and the first flight with trapezoidal window. Further suborbital flights (each astronaut was to make one as a training exercise) were cancelled. An attempt to recover the capsule in very deep water in 1994 not successful. It was finally raised in the summer of 1999.

1961 August 1 - Fort Wingate -. Redstone 1009 FAILURE: Human error in laying launch azimuth. Drop in inter-compartment pressure suspected. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 5,085 m.

1961 August 18 - Further Mercury suborbital flights cancelled. Spacecraft: Mercury. Flight: Mercury MR-5. NASA announced that analysis of Project Mercury suborbital data indicated that all objectives of that phase of the program had been achieved, and that no further Mercury-Redstone flights were planned.

1961 August 30 - Investigation of the Mercury MR-4 explosive egress hatch. Spacecraft: Mercury. Flight: Mercury MR-4. An investigation was conducted as a result of the premature activation of the Mercury-Redstone 4 (MR-4) explosive egress hatch. Tests were initiated in an environment more severe than had been conducted in prelaunch activities and tests, but no premature firings occurred. As a backup, McDonnell was asked to design a mechanical-type hatch. The model weighed some 60 pounds more than the explosive type, so other methods had to be sought to prevent any recurrence of the incident. A procedure was initiated which stipulated that the firing plunger safety pin would be left in place until the helicopter hook was attached to the spacecraft and tension was applied to the recovery cable.

1961 Late summer - Redstone MRLV-4 Mercury MR-5 (cancelled) Spacecraft: Mercury. Crew: Glenn. Flight: Mercury MR-5. The original Mercury project plan envisioned all of the astronauts making an initial suborbital hop aboard a Redstone booster before making an orbital flight aboard an Atlas. But Gherman Titov was launched on a full-day orbital flight in August 1961, making NASA's suborbital hops look pathetic. Further suborbital Mercury flights after that of Grissom were cancelled.

1961 September 1 - Fort Wingate -. Redstone 1006 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 196 m.

1961 October 1 - Fort Wingate -. Redstone 1012 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 197 m.

1961 October 23 - Mercury Freedom 7 presented to the Smithsonian Spacecraft: Mercury. Flight: Mercury MR-3. Freedom 7, the Mercury-Redstone 3 (MR-3) spacecraft, was presented by NASA to the National Air Museum of the Smithsonian Institution.

1961 Autumn - Redstone MRLV-6 Mercury MR-6 (cancelled) Spacecraft: Mercury. Crew: Slayton. Flight: Mercury MR-6. After the Russians began orbiting cosmonauts, NASA cancelled further suborbital flights. The MR-6 mission was cancelled by NASA administrator James Webb at the beginning of July, 1961.

1961 December 15 - Fort Wingate -. Redstone 1008 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 82 m.

1962 June 1 - Fort Wingate -. Redstone 1014 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 378 m.

1962 July 1 - Fort Wingate -. Redstone 1017 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 390 m.

1962 August 1 - Fort Wingate -. Redstone 1007 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 167 m.

1962 August 1 - Fort Wingate -. Redstone 1015 FAILURE: Human error in repair of pitch .potentiometer. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 3,191 m.

1963 August 5 - Fort Wingate -. Redstone 2033 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 216 m.

1963 August 19 - Fort Wingate -. Redstone 2008 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 267 m.

1963 September 10 - Fort Wingate -. Redstone 2015 FAILURE: Control system malfunction immediately prior to impact. Agency: USA. Apogee: 90 km (55 mi). Missile test failure. Missed aimpoint by 4,393 m.

1963 September 23 - Fort Wingate -. Redstone 2044 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 63 m.

1963 October 5 - Fort Wingate -. Redstone 2005 Agency: USA. Apogee: 90 km (55 mi). Successful missile test. Missed aimpoint by 131 m.

1964 June 25 - Redstone obsolete. The Redstone missile was classified as obsolete.

1964 October 30 - Redstone leaves Army service. In a ceremony on the parade field at Redstone Arsenal, the Redstone missile was ceremonially retired.

1964 December 1 - Redstone support contract terminated. The initial Redstone production contract awarded to Chrysler in October 1952 was closed out.

1965 November 29 - San Nicolas -. Project Defender Redstone launch. Redstone launched as ballistic missile target and was successfully intercepted by a US Navy Terrier surface-to-air missile launched from Point Mugu, California.

1965 November 30 - San Nicolas -. DAT-371 Target mission Agency: USA/ARPA. Apogee: 50 km (31 mi). Redstone launched as ballistic missile target for a US Navy Terrier surface-to-air missile launched from Point Mugu, California. It was reported that there were two Redstone launches as part of Project Defender from November 30 to December 13, 1965, but details of the second launch are not known.

1966 November 28 - 12:15 GMT - Woomera LA8. SPARTA ?/SV-1 FAILURE: Failure. Sparta SV-1 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1966 December 13 - 11:50 GMT - Woomera LA8. SPARTA 2034/SV-2 Sparta SV-2 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1967 April 20 - 08:37 GMT - Woomera LA8. SPARTA ?/SV-3 Sparta SV-3 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1967 July 4 - 23:07 GMT - Woomera LA8. SPARTA 2032/SV-4 Sparta SV-4 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1967 July 24 - 16:43 GMT - Woomera LA8. SPARTA 2009/SV-5 Sparta SV-5 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1967 August 17 - 19:46 GMT - Woomera LA8. SPARTA 2039/SV-6 Sparta SV-6 re-entry vehicle test flight Agency: USA. Apogee: 90 km (55 mi).

1967 September 15 - 16:17 GMT - Woomera LA8. SPARTA 2012/SV-7 Sparta SV-7 re-entry vehicle test flight Agency: USA. Apogee: 91 km (56 mi).

1967 October 11 - 16:22 GMT - Woomera LA8. SPARTA 2030/SV-8 Sparta SV-8 re-entry vehicle test flight Agency: USA. Apogee: 137 km (85 mi).

1967 October 31 - 13:14 GMT - Woomera LA8. SPARTA 2041/SV-9 Sparta SV-9 re-entry vehicle test flight Agency: USA. Apogee: 111 km (68 mi).

1967 November 29 - 04:49 GMT - Woomera LA8. SPARTA 2029/SV-10 Wresat 1 Mass: 45 kg (99 lb). Spacecraft: Wresat. Agency: WRE. Perigee: 198 km (123 mi). Apogee: 1,252 km (777 mi). Inclination: 83.30 deg. Period: 99.30 min. Weapons Research Establishment Satellite; solar radiation, upper atmosphere data. WRESAT 1 launched for upper atmosphere and space research at 1419 h central standard time, from Woomera, South Australia. Launch vehicle based on Redstone.