Rocket had new timing device for parachute, and cushioned gyro. Day was windy; duration 10 sec; height 120 ft; tipped into wind as it left the tower. References: 482 .

In a meeting, Dr. Wernher von Braun, Frederick C. Durant III, Alexander Satin, David Young, Dr. Fred L. Whipple, Dr. S. Fred Singer, and Commander George W. Hoover agreed that a Redstone rocket with a Loki cluster as the second stage could launch a satellite into a 200-mile orbit without major new developments. This became a joint Army-Navy study project after meeting at Redstone Arsenal on August 3. Project Orbiter was a later outgrowth of this proposal and resulted in the launching of Explorer I on January 31, 1958. References: 483 .

Ionosphere research. Launched at 0707 local time. Reached 202 km.

In a US Air Force briefing a preliminary astronaut selection for the Man-In-Space Soonest project is made. The list consisted of USAF test pilots Robert Walker, Scott Crossfield, Neil Armstrong, Robert Rushworth, William Bridgeman, Alvin White, Iven Kincheloe, Robert White, and Jack McKay. References: 491 .

Navy surface vessels and aircraft were used in a recovery operation after an airdrop of a spacecraft off the coast from Jacksonville, Florida. The spacecraft was purposely dropped 40 miles away from the predicted impact point and 45 miles away from the nearest ship. Recovery was effected in 2 and one half hours. References: 483 .

KH-1; 1st generation low resolution photo surveillance. Failed to achieve orbit. References: 5 , 126 .

Maximum Speed - 6293 kph. Maximum Altitude - 34080 m. References: 38 , 49 , 97 .

The Redstone missile was classified as obsolete.

Maximum Speed - 4994 kph. Maximum Altitude - 25390 m. First flight of X-15 No. 2 in X-15A-2 configuration, but without drop tanks. References: 38 , 49 , 97 .

Environmental Sciences Research Satellite. References: 5 , 126 .

NASA announced negotiations with Douglas Aircraft Company for nine additional S-IVB stages to be used as the third stage of the Saturn V launch vehicle being developed at Marshall Space Flight Center. Work was to include related spares and launch support services. The S-IVB contract, presently valued at $312 million, would be increased by $150 million for the additional work. References: 16 .

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

Radar monitoring. References: 1 , 2 , 5 , 6 , 172 , 278 .

KH-7 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 , 278 .

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

KH-8 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 .

Photo surveillance mission. References: 279 .

First successful Almaz military manned space station flight. Following the successful Soyuz 14 and unsuccessful Soyuz 15 missions, on 23 September 1974 the station ejected a film return capsule, which was successfully recovered. On 25 January 1975 it fired its manoeuvring engines for the last time and braked itself from orbit over the Pacific Ocean.
Maneuver Summary:
208km X 240km orbit to 213km X 253km orbit. Delta V: 4 m/s
213km X 252km orbit to 251km X 268km orbit. Delta V: 15 m/s
250km X 266km orbit to 265km X 271km orbit. Delta V: 5 m/s
266km X 267km orbit to 268km X 272km orbit. Delta V: 1 m/s
265km X 269km orbit to 265km X 273km orbit. Delta V: 1 m/s
261km X 266km orbit to 258km X 262km orbit. Delta V: 1 m/s
258km X 261km orbit to 258km X 286km orbit. Delta V: 7 m/s
235km X 259km orbit to 261km X 285km orbit. Delta V: 14 m/s
261km X 285km orbit to 255km X 294km orbit. Delta V: 3 m/s
218km X 229km orbit to 0km X 218km orbit. Delta V: 68 m/s
Total Delta V: 51/119 m/s.
Officially: Futher testing of improved station design, on-board systems and equipment; conduct of scientific and technical research and experiments in space flight. Futher testing of improved station design, on-board systems and equipment; conduct of scientific and technical research and experiments in space flight. References: 1 , 2 , 5 , 6 , 67 , 274 .

Maximum Speed - 1427 kph. Maximum Altitude - 17680 m. Flight Time - 426 sec. References: 49 , 97 .

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

Replaced Cosmos 1223. Covered Oko constellation plane 7 - 154 degree longitude of ascending node. References: 1 , 2 , 5 , 6 , 100 .

Radar monitoring. References: 1 , 2 , 5 , 6 , 172 .

KH-9 type satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1 , 2 , 5 , 6 .

Time 19 minutes. References: 81 .

Replaced Kurs docking system antenna. References: 66 .

Released 25 Romb radar calibration subsatellites.

Carried United States Microgravity Laboratory. First extended-duration mission. Payloads: United States Microgravity Laboratory (USML)-1; Orbital Acceleration Research Experiment (OARE); Investigations Into Polymer Membrane Processing (IPMP), Shuttle Amateur Radio Experiment (SAREX)-ll; Ultraviolet Plume Instrument (UVPl) . Additional Details: STS-50. References: 1 , 2 , 5 , 6 , 7 .

Latched Eureca antenna. Conducted tests to refine procedures for servicing of the Hubble Space Telescope and construction of the International Space Station References: 66 .

Geostationary at 99 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1 , 2 , 5 , 6 .

Investigation of the natural resources of the Earth in the interests of various branches of the national economy; solution of problems relating to ecology and international cooperation. References: 1 , 2 , 5 , 6 .

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

Geosynchronous. Stationed over 174.1E References: 4 .

Photo/digital surveillance. Entered an initial 170 x 290 km x 64.9 deg initial orbit. It manoeuvred to its operational orbit of 240 x 302 km x 64.9 deg on June 27.

Second Fengyun-2 weather satellite, replacing the first FY-2 (retired in April after a three year service life). The spin-stabilised FY-2 fired its solid apogee motor early on Jun 26. By July 3, it was in a 35,791 x 35,804 km x 1.1 deg orbit drifting over the Pacific. Stationed at 104 deg E.