Engine used 29 lb liquid oxygen; 45 lb gasoline; produced 671 lb of lift for 12 sec, with jet velocity of 4820 ft/sec; oxygen 2.15 lb/sec; gasoline, 2.28 lb/sec; mixture ratio 0.94. Over 24 pump tests were completed by the time of the last run on February 28. References: 482 .

Bell flight 14. Buffet boundary investigation. References: 49 , 97 .

First of a series of two-stage test vehicles (RM-10) to make heat transfer studies at high speed in free flight, was launched from NACA's Pilotless Aircraft Reserach Station at Wallops Island, Va. Vehicle was developed by PARD of Langley Laboratory. References: 17 .

To further the national space effort pending a decision as to permanent organization, the Secretary of Defense created the Advanced Research Projects Agency (ARPA), an organization under consideration since November 15, 1957.. ARPA was authorized to direct or perform advanced projects in the field of research and development. It was also empowered to deal directly with operational elements on all aspects of ARPA projects; for example, to bypass the Army Staff and the Chief of Ordnance in dealing with the Army Ballistic Missile Agency on what was to be the Saturn project. Roy W. Johnson was named ARPA Director. ARPA was to be a centralized group capable of handling direction of both outer space and antimissile-missile projects, whose duties in the space field were to bridge the gap until Congress could consider legislative proposals for the establishment of a National Space Agency. References: 16 .

Ionosphere research. Launched at 1151 local time. Reached 120.4 km.

At the Lovelace Clinic, Albuquerque, New Mexico, the medical tests for the Mercury astronaut selection were started. References: 483 .

The Manned Lunar Landing Task Group (Low Committee) transmitted its final report to NASA Associate Administrator Robert C. Seamans, Jr. The Group found that the manned lunar landing mission could be accomplished during the decade, using either the earth orbit rendezvous or direct ascent technique. Multiple launchings of Saturn C-2 launch vehicles would be necessary in the earth orbital mode, while the direct ascent technique would require the development of a Nova-class vehicle. Information to be obtained through supporting unmanned lunar exploration programs, such as Ranger and Surveyor, was felt to be essential in carrying out the manned lunar mission. Total funding for the program was estimated at just under $7 billion through Fiscal Year 1968. References: 16 .

Meeting of NASA and contractor personnel held at NASA headquarters to review Centaur development program. References: 18 , 278 .

Maximum Speed - 3660 kph. Maximum Altitude - 23820 m. Last XLR-11 flight. References: 38 , 49 , 97 .

On the basis of a study by NAA, a single-engine configuration was chosen as the optimum approach for the service module propulsion subsystem. The results of the study were presented to MSC representatives and NAA was authorized to issue a work statement to begin procurement of an engine for this configuration. Agreement was also reached at this meeting on a vacuum thrust level of 20,000 pounds for the engine. This would maintain a thrust-to-weight ratio of 0.4 and allow a considerable increase in the lunar liftoff weight of the spacecraft. References: 16 .

At his regular press conference, President John F. Kennedy was asked for his "evaluation of our progress in space at this time" and whether the United States had changed its "timetable for landing a man on the moon." He replied: "As I said from the beginning, we have been behind . . . and we are running into the difficulties which came from starting late, We, however, are going to proceed by making a maximum effort. As you know, the expenditures in our space program are enormous . . . the time schedule, at least our hope, has not been changed by the recent setbacks (Ranger failures)." References: 16 .

NASA announced a simplified terminology for the Saturn booster series: Saturn C-1 became "Saturn I," Saturn C-1B became "Saturn IB," and Saturn C-5 became "Saturn V." References: 16 .

After the self-destruction of the first Soyuz 7K-OK on re-entry, and the loss of the second one on the pad fire in December, the state commission ruled that the third 7K-OK model would be flown unpiloted on a solo mission. If this was successful then the fourth and fifth Soyuz would be flown on a manned docking mission. Once in orbit Cosmos 140 experienced attitude control problems due to a faulty star sensor resulting in excessive fuel consumption. The spacecraft couldn't keep the required orientation towards the sun to keep the solar panels illuminated, and the batteries discharged. Despite all of these problems the spacecraft remained controllable. An attempted manoeuvre on the 22nd revolution still showed problems with the control system. It malfunctioned yet again during retrofire, leading to a steeper than planned uncontrolled ballistic re-entry. The re-entry capsule itself had depressurised on separation from the service module due to a fault in the base of the capsule. A 300 mm hole burned through in the heat shield during re-entry. Although such events would have been lethal to any human occupants, the capsule's recovery systems operated and the capsule crashed through the ice of the frozen Aral Sea, 3 km from shore and 500 kilometres short of the intended landing zone. The spacecraft finally sank in 10 meters of water and had to be retrieved by divers. Still, the mission was deemed 'good enough' for the next mission to be a manned two-craft docking and crew transfer space spectacular. Mishin and Kamanin felt that a human crew could have sorted out the problems. They were also under intense pressure to achieve a manned circumlunar flight before the 50th Anniversary of the Soviet Revolution in October. References: 1 , 2 , 6 .

Failed launch of an E-6LS radio-equipped version of the E-6 used to test tracking and communications networks for the Soviet manned lunar program. Suggestions for the abnormal consumption included the seizing up of a pintle valve for controlling fuel supply into the regulator or the seizing up of the fuel inlet control. The upper stages broke up in the atmosphere. References: 5 , 64 , 65 .

Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 , 99 .

Enterprise (OV-101)/shuttle carrier aircraft mate start References: 15 .

Docked with Salyut 5. A busy, successful mission, accomplishing nearly as much as the earlier Soyuz 21's 50 day mission. Recovered February 25, 1977 9:38 GMT. Landed 37 km NE Arkalyk. References: 1 , 2 , 6 , 32 , 33 .

Photo surveillance; returned film capsule. References: 1 , 2 , 6 .

KH-11 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 .

Tested MMU manoeuvring unit in free flight. References: 66 .

Gathering meteorological information and data on penetrating radiation fluxes in circumterrestrial space. References: 1 , 2 , 6 .

Photo/digital surveillance. References: 1 , 2 , 6 .

Military cartographic satellite; returned film capsule. References: 1 , 2 , 6 .

Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT. References: 1 , 2 , 5 , 6 .

Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT. References: 1 , 2 , 5 , 6 .

JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT. References: 1 , 2 , 5 , 6 .

High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. References: 1 , 2 , 6 , 179 .

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1 , 2 , 5 , 6 .

Stardust was to fly within 100 km of comet 81P/Wild-2 in January 2004 and recover cometary material using an aerogel substance. A return capsule would land on a lake bed in Utah in January 2006, returning the material to earth. The launch went as planned. The second stage ignited at 21:08 GMT and its first burn put the vehicle into a 185 km x 185 km x 28 degree parking orbit at 21:14 GMT. The second stage second burn at 21:25 changed the orbit to planned values of 178 km x 7184 km x 28.5 degrees. The Star 37FM solid third stage ignited at 21:29 GMT and placed the spacecraft into a 2 year period solar orbit. The spacecraft separated at 21:31 GMT. Meanwhile, the Delta 266 second stage burned a third time on its own, until its propellants were depleted, entering a final orbit of 294 km x 6818 km x 22.5 degrees.