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.

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

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: here....

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.'

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.

In the post-mortems on the N1 after the Apollo 8 mission, MKBS became a key justification for continuing with the N1. MS Ryazanskiy: Our biggest problem - we think only 2 - 3 years ahead. Are we no longer prepared to create a TOS Heavy orbital station? After 7K-VI need to create a large space stations.
VI Shcheulov: Creation of a powerful space station on the basis of N1 would offset, to to some extent, the effect of the United States winning the moon race. MKBS would achieve long-duration through rotation of crews. Modification is necessary in parallel with the existing launch vehicle. We must build two new launch facilities allowing simultaneous launches. (It is necessary to assign the task to develop those launch facilities.) Mishin Diaries 2-159)

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).

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.

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.

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.

The Mir-crew is still struggling along to keep the complex habitable and operational. Recently they had to cope with technical problems with the heating, drinking-water, pressure control and with a leakage of water in the Kristall-module. With the help of advice from experts on earth they solved the problems. On 23.01.1995 during the pass in orbit 51032, 0719- UTC, TsUP gave Viktorenko attitude control data to adjust the attitude of the complex in such a way that the solar panels of the Kristall module could deliver a maximum of energy. Dr. Polyakov continued his medical checks and experiments. On request by experts on earth the crew filmed and observed the areas of Kobe in Japan and Grozny. On 21.01.1995 they transmitted these images to earth. It was not always possible to do this due to clouds and bad weather in the areas of interest. Also on 21.01.1995 Dr. Polyakov gave a lecture for Russian children, members of an organisation for young people interested in spaceflight. During a long TV-session via Altair Polyakov explained how the systems in the base block worked. Extensively he explained all about the production and delivery of oxygen for the complex and the purification of the air on board. He emphasised the necessity of the permanent survey of the life systems and a regular maintenance.

Rendezvous Discovery (STS-63) with Mir: On 2.02.1995 at 0549 UTC STS-63 will be launched for a flight in which the most important operation will be a rendezvous with the Mir-complex. Somewhat earlier, on 4.02.1995 at 1221- UTC Mir and Discovery will be able to establish radio contact. From Discovery cosmonaut Titov and the female astronauts Collins and Voss will speak with the crew of Mir. On 5.02.1995 at 1828 UTC the rendezvous operation will begin and STS-63 will approach Mir in a distance of 10 meters.

Chris v.d. Berg, NL-9165/A-UK3202.

"When Day is Done" by Django Reinhardt and Stephane Grappelli. Dedicated to Dave Brown. Capcom Charlie Hobaugh said,"We're doing great down here, and I feel cultured" Dave replied,"It's about time" Red Team -"Love of My Life" by Queen. Dedicated to Ilan Ramon. A videotape of the wakeup activities survived the accident.

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.

German engineer, V-2 test leader. At end of war headed development of Taifun unguided antiaircraft rocket, characterized as a 'desperation project'. Went to America after the war, working at Fort Bliss. Later returned to Germany and died in Lenningen in 2008.