Flight missions of the Apollo spacecraft were to be numerically identified in the future according to the following scheme :

Pad aborts: PA-1, PA-2, etc.

Missions using Little Joe II launch vehicles: A-001, A-002, etc. Missions using Saturn C-1 launch vehicles: A-101, A-102, etc. Missions using Saturn C-1B launch vehicles: A-201, A-202, etc. Missions using Saturn C-5 launch vehicles: A-501, A-502, etc.

The 'A' denoted Apollo, the first digit stood for launch vehicle type or series, and the last two digits designated the order of Apollo spacecraft flights within a vehicle series.

On the fourth attempt, a Thor IRBM was used to launch a Mk 4 Re-entry Vehicle containing a 186 kg W-50 nuclear warhead of either 200 or 400 kilotons yield. The detonation occurred at an altitude of 50 km, 31 km SSW of Johnston Atoll. A fireball formed, the colourful afterglow continuing for 30 minutes of the explosion. At this altitude the extensive disruption of the ionosphere seen in later explosions did not occur.

Stage I was erected in the complete vehicle erector October 28, stage II in the second stage erector October 29. The two stages were cabled together in the side-by-side configuration required for the Sequence Compatibility Firing scheduled for mid-December. A limited Electronic-Electrical Interference Test was completed November 7, and power was applied to the vehicle November 13.

In an interview for Missiles and Rockets magazine, Associate Administrator Robert C. Seamans, Jr., stated that NASA planned to initiate program definition studies of an Apollo X spacecraft during Fiscal Year 1965. Seamans emphasized that such a long-duration space station program would not receive funding for actual hardware development until the 1970s. He stressed that NASA's Apollo X would not compete with the Manned Orbiting Laboratory program: 'MOL is important for the military as a method of determining what opportunities there are for men in space. It is not suitable to fulfill NASA requirements to gain scientific knowledge.'

Russell L. Schweickart spent eight days in a Gemini space suit to evaluate Gemini biomedical recording instruments. While in the suit, the astronaut flew several zero-g flight profiles, went through a simulated four-day Gemini mission, and experienced several centrifuge runs.

Kamanin notes the aborted first launch attempt of Gemini 6, but expects the Americans to achieve the first space docking, using the crew as pilots to fly the spacecraft. He curses Korolev and Keldysh for wasting three years trying to develop a fully automated system for Soyuz, which has put the Soviet Union well behind the Americans. He does not see any equivalent Soviet achievement until the end of 1966...

Headquarters USAF issued a System Management Directive to add an Airborne Launch Control System (ALCS) for Minuteman I and II systems. SAC would then be able to use its EC-135 airborne command post aircraft to launch Minuteman missiles that were isolated from ground control.

Second manned Soyuz flight. Rendezvoused with the unmanned Soyuz 2 but failed to dock. Complex testing of spaceship systems; development, in joint flight with space ship Soyuz 2 of processes of space ship manoeuvring and docking in artificial earth satellite orbit; development of elements of celestial navigation; conduct of research under space flight conditions. The failed docking was blamed on manual control of the Soyuz by Beregovoi, who repeatedly put the spacecraft in an orientation that nulled the automatic docking system. Beregovoi used nearly all of his orientation fuel in his first attempt to dock - of 80 kg allocated, only 8 to 10 kg was remaining. Additional Details: here....

Statsionar T. Transmission of colour and black-and-white USSR central television programmes to the network of public receiving units located in population centres in Siberia and the Far North. Positioned in geosynchronous orbit over the Indian Ocean at 99 deg E in 1976-1978 As of 29 August 2001 located at 68.75 deg E drifting at 0.171 deg E per day. As of 2007 Mar 11 located at 73.60E drifting at 0.187W degrees per day.

The booster was used to put the twin spacecraft in a 182 km x 403,810 km x 28.5 deg lunar transfer orbit. They would use a series of lunar flybys to eventually place themselves in two different solar orbits: Stereo Ahead in a 0.95 AU x 0.97 AU x 0.12 Deg / 344 day orbit around the Sun leading the Earth, and Stereo Behind in a 0.99 AU x 1.09 AU x 0.03 deg / 389 day orbit trailing the Earth. The satellites were equipped with optical, ultraviolet, radio, and particle sensors that would allow them to form a three-dimensional image of the sun's corona using identical sensors from two vantage points at the same moment.

Communications with the STEREO-B science craft in solar orbit had been lost on 2014 Oct 1 for unknown reasons; by 2016 it was assumed the mission had been lost, but on Aug 21 the big DSS-14 dish at Goldstone picked up a signal from it. This was great news for the heliophysics community, but attempts to recover full communications with the tumbling and underpowered spacecraft have met with mixed success, and as of Oct 11 recovery attempts were scaled back until STEREO-B drifts into a more favorable attitude and orbital position.

The astronauts emerged from the Quest hatch at 10:01 GMT. They moved an antenna from the Z1 truss and stowed it in the payload bay, prepared the P6 truss for separation from Z1, and assisted in installation of the Harmony module, which was unberthed from the shuttle bay by the ISS Canadarm-2 and docked to the Unity module.