The 5-2 second aircraft, with rocket engine installed, made its first glide flight.

Launched from Le Cardonnet, France - Latitude: 43.58 N - Longitude: 3.64 E.

Council of Soviet Ministers (SM) Decree 'On approval of work on the R-11FM' was issued.

Symposium on "The Scientific Uses of Earth Satellites" held at the University of Michigan under sponsorship of the Upper Atmosphere Rocket Research Panel, James A. Van Allen of the State University of Iowa, Chairman.

First attempted test flight of USAF Thor IRBM, only 13 months after first production contracts were signed, failed to launch.

NASA completed contract negotiations with McDonnell for the design and development of the Mercury spacecraft. At that time, McDonnell estimated that the first 3 spacecraft could be delivered in 10 months. Spacecraft refinements slipped this estimated goal by only 2 months.

The X-10 was launched with only one electrical generator due to a lack of any remaining spares. As it headed out over the ocean, that generator failed. It lost all electrical power, and crashed into the ocean 105 km downrange.

Successful missile test with capsule. Missed aimpoint by 277 m.

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

Two Atlas ICBMs launched within two hours - one by SAC at VAFB, one by GD/A at AMR; both successful.

Wernher von Braun, Director of Marshall Space Flight Center, proposed that the Saturn C-1 launch vehicle be changed from a three-stage to a two-stage configuration to meet Apollo program schedules. The planned third stage (S-V) would be dropped.

After investigating potential malfunction problems of the modified Titan II/Gemini launch vehicle, Martin-Baltimore prepared a study report with plans to provide the components necessary to ensure flight safety and enhance reliability. Martin defined the malfunction problem quantitatively in terms of the probability of each cause and its characteristic effect on the system and vehicle. Martin intended to keep the launch vehicle as much like the weapon system as possible; thus the data obtained from the Air Force's weapon system development program would be applicable to the launch vehicle. Only minimal modifications to enhance probability of mission success, to increase pilot safety, and to accommodate the Gemini spacecraft as the payload were to be made. These included a malfunction detection system; backup guidance, control, and hydraulic systems; and selective electrical redundancies.

Lunar impact probe; missed the moon by 36,874 km and went into solar orbit. A malfunction in the booster guidance system resulted in excessive spacecraft speed. Reversed command signals caused the telemetry antenna to lose earth acquisition, and mid-course correction was not possible. Some useful data were obtained from the flight. Of four scientific experiments only one was partially completed: gamma-ray readings of the lunar surface. Attempts to relay television pictures of the moon and to bounce radar signals off the moon at close range were unsuccessful.

MSC announced new assignments for the seven original astronauts: L. Gordon Cooper, Jr., and Alan B. Shepard, Jr., would be responsible for the remaining pilot phases of Project Mercury; Virgil I. Grissom would specialize in Project Gemini; John H. Glenn, Jr., would concentrate on Project Apollo; M. Scott Carpenter would cover lunar excursion training; and Walter M. Schirra, Jr., would be responsible for Gemini and Apollo operations and training. As Coordinator for Astronaut Activities, Donald K. Slayton would maintain overall supervision of astronaut duties.

Specialty areas for the second generation were: trainers and simulators, Neil A. Armstrong; boosters, Frank Borman; cockpit layout and systems integration, Charles Conrad, Jr.; recovery system, James A. Lovell, Jr.; guidance and navigation, James A. McDivitt; electrical, sequential, and mission planning, Elliot M. See, Jr.; communications, instrumentation, and range integration, Thomas P. Stafford; flight control systems, Edward H. White II; and environmental control systems, personal equipment, and survival equipment, John W. Young.

Warren J. North, Chairman of the Lunar Landing Research Vehicle (LLRV) Coordination Panel, reported to MSC Director Robert R. Gilruth that the LLRV had been flown 10 times by Flight Research Center pilots - eight times by Joe Walker and twice by Don Mallick. Maximum altitude achieved was 91 m (300 ft) and maximum forward velocity was 12 m (40 ft) per sec. - Additional details.

Launched from Atlantic Ocean Launch Site 6 - Latitude: 35.05 S - Longitude: 35.53 W.

At a NASA Hq briefing, Associate Administrator for Manned Space Flight George E. Mueller stated that NASA planned to form an 'embryonic space station' in 1968-69 by clustering four AAP payloads launched at different times. The first mission would be the launch of a manned spacecraft followed several days later by a spent S-IVB stage converted into an OWS. After the two spacecraft had docked, the crew would enter the Workshop through an airlock. Twenty-eight days later they would passivate the OWS and return to Earth in their spacecraft. In three to six months, a second manned spacecraft would be launched on a 56-day mission to deliver a resupply module to the OWS and to rendezvous with an unmanned ATM, the fourth and last launch of the series. The cluster would be joined together using the multiple docking adapter. Emphasizing the importance of manning the ATM, Mueller said that 'if there is one thing the scientific community is agreed on it is that when you want to have a major telescope instrument in space it needs to be manned.'

Launched from Dumont d'Urville, Terre Adelie - Latitude: 64.67 S - Longitude: 140.02 E.

Replaced ESSA 2. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

The parachute failed to inflate after the capsule separated from the escape tower. The recovery apparatus on both the Soyuz and L1 versions of the capsule continue to perform badly. The soft landing engines have ignited at altitudes of 2000 to 4000 m instead of the 1.2 m required for a soft landing. On the first UR-500K abort the SAS functioned, but the parachute failed to separate after landing, dragging the capsule for 600 m across the steppes. On the second UR-500K abort, there was a premature opening of the parachute, and reaction control system venting led to burn-through of some of the parachute lines.

Maximum Speed - 1443 kph. Maximum Altitude - 26730 m. Flight Time - 411 sec.

Keldysh heads a review of spacecraft environmental control system development. The work of the IMBP is not well organised. They have been developing systems for eight years with no concrete results. G I Voronin is responsible for oxygen regenerator and thermal regulation systems; G I Severin, for space suits; O G Gazenko for biosensors, medicines, and space food. Two problems need to be solved: to understand and counter the effects of zero gravity on the human organism; and to develop a reliable environmental control system with a guaranteed life of two to three years. Keldysh declares that in the next five to ten years the Soviet Union will not fly space stations with artificial gravity. Therefore, due to the inevitable deterioration of the human body in zero gravity, crews will have to be rotated every 30 to 60 days. Development must continue with an eye to supporting eventual lunar bases and manned expeditions to Mars.

Launch vehicle put payload into geosynchronous transfer orbit; the satellite performed the apogee burn and positioned itself in geosynchronous orbit over the Atlantic Ocean at 24.5 deg W. Subsequently at 23 deg W in 1971-1975; over the Atlantic Ocean 1-6 deg W in 1976-1980; over the Atlantic Ocean 0-5 deg E in 1980-1983. As of 3 September 2001 at 31.91 deg E drifting at 5.168 deg W per day. As of 2006 Dec 18 located at 133.93E drifting at 5.166W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

Development of systems for air defence and the control of outer space.

Ames Research Center requested that six R4D rocket engines designed for use in the Apollo program be transferred from MSC to Ames. Possibly the engines would be suitable for the retro-injection function in the Pioneer Venus series of atmospheric probe and orbiter missions. First launch was planned for early 1977.

MSFC Director Eberhard F. M. Rees retired. He had served as Director since 1 March 1970. Rocco A. Petrone, NASA Apollo Program Director, became the new MSFC Director.

Military navigation satellite.

Photo surveillance; film capsule; capsule returned January 30. Second fully successful FSW mission.

International Ultraviolet Explorer. 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 30 deg W in-60 deg W in 1978-1996 As of 3 September 2001 located at 35.66 deg E drifting at 0.773 deg W per day. As of 2007 Mar 8 located at 14.14W drifting at 0.700W degrees per day.

All-sky survey of astronomical IR bodies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

Photo surveillance; returned film capsule.

Radar calibration mission.

Military cartographic satellite; returned film capsule.

Stationed at 53 deg E. Provision of telephone and telegraph radiocommunications and television broadcasting. The Rimsat network was initiated when Gorizont 17 was leased to the corporation and transferred from 53 degrees E (where it was then a backup to Gorizont 27) to 134 degrees E during late-June and July, 1993. At the close of 1994, Gorizont 17 was still on station but nearing the end of its operational life after six years. Positioned in geosynchronous orbit at 53 deg E in 1989-1993; 134 deg E in 1993-1995; 34 deg E in 1995-1997 As of 30 August 2001 located at 22.84 deg W drifting at 4.340 deg W per day. As of 2007 Mar 10 located at 147.41W drifting at 4.350W degrees per day.

Tested spacesuit. Examined exterior of Kvant 2.

Installed solar array supports.

Launched from Mobile launchers in Iraq, western launch area - Latitude: 34.00 N - Longitude: 41.00 E.

Launched from Mobile launchers in Iraq, SE of Basra - Latitude: 30.50 N - Longitude: 48.00 E.

Launched from Mobile launchers in Iraq, SE of Basra - Latitude: 30.50 N - Longitude: 48.00 E.

Covered Oko constellation plane 4 - 34 degree longitude of ascending node.

The EO-10 crew, wearing Orlan spacesuits, first installed a work platform on the exterior of the Zvezda Service Module. Station systems were put on autopilot for the duration of the spacewalk. Atop the platform the astronauts mounted a German experiment, a small remote-controlled manipulator arm, meant to test the operation of lightweight robotic joints in space. They also moved a Japanese micrometeoroid experiment and inspected the station's environmental control system vents for blockages. They completed their work by placing Russian biological experiments on the station exterior.