Bell flight 11. Accelerated stalls. Partial power due to engine igniters. Mach 0.75.

AF flight 19. Pressure distribution survey. Mach 1.1.

Robert J. Woods of the Bell Aircraft Company recommended to the Committee on Aerodynamics of the National Advisory Committee for Aeronautics (NACA) that a small study group be formed to investigate the problems of space flight. On June 24, the NACA Committee adopted a resolution (1) that NACA research effort on problems of manned and unmanned flight in the upper stratosphere at altitudes between 12 and 50 miles and at Mach numbers between 4 and 10 be increased, and (2) that NACA devote a modest effort to problems associated with manned and unmanned flight at altitudes from 50 miles to infinity and at speeds from Mach 10 to the velocity of escape from earth's gravity. - Additional details.

An NACA report was issued covering several projects and proposals for the flight of manned and unmanned vehicles to altitudes above the earth where atmospheric density was very low. The substance of these reports was presented at the June 24, 1952, meeting of the Committee on Aerodynamics. After the presentation, committee member Robert J. Woods recommended that basic research be initiated on the problems of space flight and stated that the NACA was the logical organization to carry on this work. To accomplish this task, a small working group was established to analyze the available information on the subject of space flight. The objective of this group was to arrive at a concept of a suitable manned test vehicle that could be constructed within 2 years.

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

Ionosphere research. Launched at 1345 local time. Failure.

Central Committee of the Communist Party and Council of Soviet Ministers Decree 149882 'On creation of the Object D artificial satellite' was issued.

Design work starts on the Zenit, the first military photo-reconnaisance satellite. The necessary subsystems were defined incrementally throughout 1956 in a series of specification documents. In April the specifications for a redundant restartable engine and appropriate satellite guidance and control systems were released. In May the technical requirements document was issued for a satellite that could be oriented in orbit. In July tests began of appropriate heat shield materials.

Admiral Arleigh Burke, Chief of Naval Operations, advised Dr. T. Keith Glennan that Navy candidates for Project Mercury had started in the first selection process.

Conference of 12 European nations held at Strasbourg to discuss a British and French proposal for a European satellite launcher development program.

President John F. Kennedy announced that he was nominating James E. Webb as Administrator of the National Aeronautics and Space Administration and Hugh L. Dryden as Deputy Administrator, Senate confirmation followed on February 9 and they were sworn in on February 14.

The Mercury-Atlas 6 (MA-6) mission was postponed because of technical difficulties with the launch vehicle.

Grumman and NASA announced the selection of four companies as major LEM subcontractors:

1. Rocketdyne for the descent engine
2. Bell Aerosystems Company for the ascent engine
3. The Marquardt Corporation for the reaction control system
4. Hamilton Standard for the environmental control system

Studied inner Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.

Studied outer Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.

Impacted Moon but TV camera malfunctioned. A midcourse trajectory correction was accomplished early in the flight by ground control. On February 2, 1964, 65.5 hours after launch, Ranger 6 impacted the Moon on the eastern edge of Mare Tranquillitatis (Sea of Tranquility). No camera data were obtained, probably because of failure due to an arc-over in the TV power system when it inadvertently turned on during the period of booster-engine separation.

Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

The Volchka L1 trainer, M-220 computer, centrifuge, L1 cabin, and instructor control station are in place. But many critical equipment items have not yet been installed, including essential cabin instruments and flight indicators.

Mishin agrees with Tyulin that he will fly to Tyuratam on 3 February to supervise launch of the Ye-8 on 18 February and the first N1 on 21 February.

Ionospheric measurements; data correlated with measurements from Alouette 1. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

First test of prototype DF-3 (perhaps same configuration as CZ-1); not deployed.

Operational radar target for the ABM forces.

The TsPK is visited by participants in a meeting of the Warsaw Pact General Staff. This amounts to 29 generals, 2 to 3 from each country of the pact.

High resolution photo reconnaissance satellite; returned film capsule; maneuverable.

Covered Oko constellation planes 7/8 - 182 degree longitude of ascending node.

Start orbiter/ET/SRB burnout mated vertical ground vibration test, MSFC

High resolution photo reconnaissance satellite; returned film capsule; maneuverable.

Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.

Replaced Molniya 1-41. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of the long-range telephone and telegraph radiocommunications system in the USSR; transmission of television programmes to stations in the Orbita network.

Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission.

Geosynchronous ballistic missile early warning satellite. Launch vehicle failure; left in unusable orbit. Investigation of the upper atmosphere and outer space.

Gathering meteorological information and data on penetrating radiation fluxes in circumterrestrial space.

Investigation of outer space.

STS-42 landed at 16:07 GMT.

Geosynchronous. Stationed over 84.9W Positioned in geosynchronous orbit at 85 deg W in 1997-1999 As of 5 September 2001 located at 84.89 deg W drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 85.05W drifting at 0.004W degrees per day.

Geosynchronous. Stationed over 71.8W Positioned in geosynchronous orbit at 72 deg W in 1997-1999 As of 3 September 2001 located at 71.82 deg W drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 71.83W drifting at 0.002W degrees per day.

GPS Block IIR production no. SV 14. Placed in Plane E Slot 4 of the constellation.

The platform was designed to survive such an explosion, but the flame deflector was blown off and the blast doors unhinged. The launch platform was towed back to Long Beach for repairs. The time required to repair the platform and the investigation to determine and fix the cause would certainly impact the 2007 Zenit-3SL and Zenit-2 launch schedules, probably forcing customers to be diverted to other boosters. NSS-8 was to have been placed at a 57º East orbital position to satisfy demand in the Indian Ocean region with 56 C-band and 36 Ku-band transponders. NSS-703, with an expected end-of-life in 2009, would have to continue in service until a replacement was built and launched.