The American Interplanetary Society, later the American Rocket Society (ARS), founded in New York City by David Lasser, G. Edward Pendray, Fletcher Pratt, and nine others, for the "promotion of interst in and experimentation toward interplanetary expeditions and travel." References: 17 .

AF flight 6. Date estimated. References: 49 , 97 .

Establishment of the U.S. Naval Missile Facility at Point Arguello, the southern portion of former Camp Cooke (facility formally commissioned on 10 May). References: 88 .

Development of the RT-2 ICBM was authorised by a decree of 4 April 1961 in parallel with the RT-1.

Three astronauts selected for Mercury-Redstone flight (MR-3) were ordered to take refresher course in Navy centrifuge at Johnsville, Pa. References: 18 .

A mockup of the Apollo command module, built by the Space and Information Systems Division of NAA, was made public for the first time during a visit to NAA by news media representatives. References: 16 .

Area survey photo reconnaissance satellite. References: 1 , 2 , 5 , 6 , 93 .

Area survey photo reconnaissance satellite. Program partially completed. Failure of primary SA-20 camera. References: 1 , 2 , 5 , 6 , 93 .

Maximum Speed - 5808 kph. Maximum Altitude - 57150 m. References: 38 , 49 , 97 .

Apollo 6 (AS-502) was launched from Complex 39A at Kennedy Space Center. The space vehicle consisted of a Saturn V launch vehicle with an unmanned, modified Block I command and service module (CSM 020) and a lunar module test article (LTA-2R).

Liftoff at 7:00 a.m. EST was normal but, during the first-stage (S-IC) boost phase, oscillations and abrupt measurement changes were observed. During the second-stage (S-II) boost phase, two of the J-2 engines shut down early and the remaining three were extended approximately one minute to compensate. The third stage (S-IVB) firing was also longer than planned and at termination of thrust the orbit was 177.7 x 362.9 kilometers rather than the 160.9-kilometer near-circular orbit planned. The attempt to reignite the S-IVB engine for the translunar injection was unsuccessful. Reentry speed was 10 kilometers per second rather than the planned 11.1, and the spacecraft landed 90.7 kilometers uprange of the targeted landing point.

The most significant spacecraft anomaly occurred at about 2 minutes 13 seconds after liftoff, when abrupt changes were indicated by strain, vibration, and acceleration measurements in the S-IVB, instrument unit, adapter, lunar module test article, and CSM. Apparently oscillations induced by the launch vehicle exceeded the spacecraft design criteria.

The second-stage (S-II) burn was normal until about 4 minutes 38 seconds after liftoff; then difficulties were recorded. Engine 2 cutoff was recorded about 6 minutes 53 seconds into the flight and engine 3 cutoff less than 3 seconds later. The remaining second-stage engines shut down at 9 minutes 36 seconds - 58 seconds later than planned.

The S-IVB engine during its first burn, which was normal, operated 29 seconds longer than programmed. After two revolutions in a parking orbit, during which the systems were checked, operational tests performed, and several attitude maneuvers made, preparations were completed for the S-IVB engine restart. The firing was scheduled to occur on the Cape Kennedy pass at the end of the second revolution, but could not be accomplished. A ground command was sent to the CSM to carry out a planned alternate mission, and the CSM separated from the S-IVB stage.

A service propulsion system (SPS) engine firing sequence resulted in a 442-second burn and an accompanying free-return orbit of 22,259.1 x 33.3 kilometers. Since the SPS was used to attain the desired high apogee, there was insufficient propellant left to gain the high-velocity increase desired for the entry. For this reason, a complete firing sequence was performed except that the thrust was inhibited.

Parachute deployment was normal and the spacecraft landed about 9 hours 50 minutes after liftoff, in the mid-Pacific, 90.7 kilometers uprange from the predicted landing area (27.40 N 157.59 W). A normal retrieval was made by the U.S.S. Okinawa, with waves of 2.1 to 2.4 meters.

The spacecraft was in good condition, including the unified crew hatch, flown for the first time. Charring of the thermal protection was about the same as that experienced on the Apollo 4 spacecraft (CM 017).

Of the five primary objectives, three - demonstrating separation of launch vehicle stages, performance of the emergency detection system (EDS) in a close-loop mode, and mission support facilities and operations - were achieved. Only partially achieved were the objectives of confirming structure and thermal integrity, compatibility of launch vehicle and spacecraft, and launch loads and dynamic characteristics; and of verifying operation of launch vehicle propulsion, guidance and control, and electrical systems. Apollo 6, therefore, was officially judged in December as "not a success in accordance with . . . NASA mission objectives." References: 1 , 2 , 5 , 6 , 16 , 26 , 27 .

High resolution photo reconnaissance satellite; returned film capsule References: 1 , 2 , 6 .

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

ASAT interceptor. Conducted an extended test flight to shake out homing system and engine function. Tested new redundant ranging systems. Tested effectiveness of new approach trajectory to target, whereby target was approached from above rather than below. Following completion of tests and verification of system functions via telemetry, spacecraft was commanded to a destructive reentry over the Pacific Ocean. References: 1 , 2 , 5 , 6 , 272 .

Operation of the long-range telephone and telegraph radiocommunications system in the USSR; transmission of television programmes to stations in the Orbita network. References: 1 , 2 , 5 , 6 .

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

High resolution photo reconnaissance satellite; returned film capsule; maneuverable. References: 1 , 2 , 6 .

Manned precursor. Recovered April 15, 1978 12:02 GMT. Unsuccessful mission. Soyuz T test -failure.
Maneuver Summary:
202 km X 231 km orbit to 195 km X 291 km orbit. Delta V: 19 m/s
195 km X 291 km orbit to 306 km X 322 km orbit. Delta V: 40 m/s
306 km X 322 km orbit to 308 km X 318 km orbit. Delta V: 1 m/s
Total Delta V: 60 m/s.
Officially: Investigation of the upper atmosphere and outer space. References: 1 , 2 , 6 .

Manned four crew. First flight of space shuttle Challenger; deployed TDRSS. Payloads: Deployment of Tracking and Data Relay Satellite (TDRS)-A with Inertial Upper Stage (lUS)-2, Continuous Flow Electrophoresis System (CFES), Monodisperse Latex Reactor (MLR), Night/Day Optical Survey of Lightning (NOSL) experiment, three getaway specials (GAS). Additional Details: STS-6. References: 1 , 2 , 5 , 6 , 7 , 33 .

Element of satellite communications network, deployed from STS-6 4/5/83. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1 , 2 , 5 , 6 .

Replaced Cosmos 1382. Covered Oko constellation plane 7 - 154 degree longitude of ascending node. References: 1 , 2 , 5 , 6 , 100 .

Stationed at 13.5 deg W. Continuation of the investigation of outer space; experimental retransmission of telephone and telegraph data in the centimetre band. References: 1 , 2 , 5 , 6 , 67 , 112 , 274 .

Military navigation satellite. References: 1 , 2 , 5 , 6 .

Glonass. Testing of components and apparatus of the Glonass global space navigation system being set up to determine the position of the Soviet Union's civil aircraft and vessels in its merchant marine and fishing fleet. References: 1 , 2 , 5 , 6 , 67 , 274 .

Glonass. Testing of components and apparatus of the Glonass global space navigation system being set up to determine the position of the Soviet Union's civil aircraft and vessels in its merchant marine and fishing fleet. References: 1 , 2 , 5 , 6 , 67 , 274 .

Glonass. Testing of components and apparatus of the Glonass global space navigation system being set up to determine the position of the Soviet Union's civil aircraft and vessels in its merchant marine and fishing fleet. References: 1 , 2 , 5 , 6 , 67 , 274 .

Canadian communications; 107.3 deg W. References: 1 , 2 , 5 , 6 .

Remained attached to OV-102 References: 4 , 276 .

The launch of STS-83, the first Microgravity Science Laboratory (MSL-1) mission, was postponed for a day to replace some insulation around a water coolant line in Columbia's payload bay. Liftoff was further delayed 20 minutes due to anomalous oxygen readings in the orbiter's payload bay. STS-83 was cut short due to a problem with one of the three fuel cells that provide electricity and water to Columbia (flight rules required that all three must be operating). At 14:30 GMT on April 6 the crew were ordered to begin a Minimum Duration Flight (MDF). On April 8 the OMS engines ignited at 17:30 GMT for the deorbit burn, and Columbia landed on Runway 33 at Kennedy Space Center at 18:33 GMT.

With delays in International Space Station construction leaving ample room in the shuttle schedule, NASA made the unique decision to leave the equipment installed in Columbia and refly this mission with the same crew later in 1997 as STS-94. Additional Details: STS-83. References: 4 , 7 , 276 .

Soyuz TM-30 docked with Mir's forward (-X) port on April 6 at 0631 GMT. Zalyotin and Kaleri reactivated Mir and using Progress M1-1 and M1-2 resupplied the station and raised the orbit to 360 x 378 km x 51.6 deg. The orbital plane of Mir was then around 120 degrees away from that of ISS (making transport between the stations impossible, as desired by NASA). Soyuz TM-30 undocked from Mir on June 15 21:24 GMT. Retrofire came at 23:52 GMT, followed by a safe landing at June 16, 00:44 GMT near Arkalyk in Kazakkstan.