Sky brightness research. Launched at 0732 local time. Reached 101.4 km.

USAF X-17 flight test program started at Cape Canaveral to study reentry problems by simulating reentry velocities and conditions with three-stage solid-fuel Lockheed X-17. A total of 26 X-17 flights were conducted until March 1957. References: 17 .

Myasishchev OKB-23 sketches first serious manned winged spacecraft design. References: 83 .

Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Creation of pockets With Engines on the Basis of Nuclear Energy Applications--work on a draft project for rockets with nuclear engines' was issued. Competing engine designs were in development by Glushko�s OKB-456 and Bondaryuk�s OKB-670. Both designs used existing available reactors in cyldindrical housings, with the reactors operating at 3000 degrees K. The propellant was heated in the reactor and exhausted through four expansion nozzles. The Glushko engine operated with ammonia, while the Bondaryuk engine used a mixture of ammonia and alcohol. With such propellants a specific impulse of 430 seconds was achieved. References: 474 .

Micrometeorite counter satellite (S-55). References: 5 , 126 .

Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. References: 1 , 2 , 5 , 6 , 99 .

Maximum Speed - 5364 kph. Maximum Altitude - 30358 m. References: 38 , 49 , 97 .

Centaur test. Launch vehicle was to have put payload into geosynchronous transfer orbit References: 5 , 126 , 278 .

Langley Research Center put into operation its 3.5 million Lunar Landing Research Facility. The huge structure (76.2 m (250 ft) high and 121.9 m (400 ft) long) would be used to explore techniques and to forecast various problems of landing on the moon. The facility would enable a test vehicle to be operated under one-sixth g conditions. References: 16 .

The cancellation came only a few months before an orbital 2G-1 could be flown. Martlet 2's were used to conduct extensive research at altitudes of up to 180 km with some 200 flights being conducted between 1963 and 1967. The very low cost per flight, about $3,000, made it ideal for a wide variety of applications.. Typical mission payloads included chemical ejection to produce an observable atmospheric trail and assorted sensors with multi-channel telemetry.

While the next N1, 3L was being built, the 1M1 was moved back to the pad for further ground tests and launch crew training. It remained there until the end of September. References: 96 .

Ministry of General Machine Building (MOM) Decree 232 'On start of work on the UR-700M rocket' was issued. The decree allowed development of an advanced project for a manned Mars expedition using the UR-700M booster and MK-700 spacecraft. The TTZ specification document was written by the TsNIIMASH and NIITI institutes, and the project was given the code name 'Aelita'. References: 474 .

No competing US project any more, huge obstacles in getting Tu-144 SST to fly at Mach 2 sustained let alone Mach 4 sustained for Tupolev's Spiral first stage. References: 83 .

Original planned date for first flight tests of Spiral with rocket first stage. References: 83 .

Continuation of joint studies of the sun's ultra-violet and x-radiation and its effects on the structure of the earth's upper atmosphere. References: 1 , 2 , 5 , 6 , 99 , 116 .

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

Acquisition of meteorological information needed for use by the weather service. References: 1 , 2 , 5 , 6 .

Glushko supports modest project to do subsonic flight tests of Spiral orbiter configuration. References: 83 .

SSME dummy set on dock, Palmdale, Enterprise (OV-101) References: 15 .

Original planned date for flight test of Spiral with airbreathing hypersonic first stage. References: 83 .

Area survey photo reconnaissance satellite; returned film capsule. References: 1 , 2 , 6 .

Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. References: 1 , 2 , 6 , 69 .

Trials of experimental equipment for testing systems to determine the location of vessels and aircraft in distress. References: 1 , 2 , 5 , 6 .

Began repair of TTM telescope. References: 66 .

Unmanned resupply vessel to Mir. An initial docking attempt on 2 Jul 1992 was a failure. Docked with Mir on 4 Jul 1992 16:55:13 GMT. Undocked on 24 Jul 1992 04:14:00 GMT. Destroyed in reentry on 24 Jul 1992 08:03:35 GMT. Total free-flight time 4.17 days. Total docked time 19.47 days. It was docked to Mir for only a few weeks, since on 26 Jul the Soyuz TM-15 was to be launched with a replacement crew and would need to use the same docking port. References: 1 , 2 , 6 , 275 .

No known mission (with the end of SDI and the cold war) - plus the project manager was one of the 1991 coup plotters. Total cost 20 billion rubles at time of cancellation. References: 83 .

The polar orbiting ADEOS spacecraft performed Earth, atmospheric, and oceanographic remote sensing. Initially put on August 20 1996 into a wrong orbit, it achieved an acceptable orbit in September 1996.

First Advanced Tracking and Data Relay Satellite, using a Hughes HS 601 satellite bus. It included an S-band phased array antenna and two Ku/Ka band reflectors 4.6 meters in diameter. The satellite was launched into a a 167 x 577 km x 28.3 deg parking orbit at 13:05 GMT. The Centaur upper stage made a second burn at 13:21 GMT, releasing the satellite into a subsynchronous transfer orbit of 237 x 27,666 km x 27.0 deg. The satellite's own Primex/Marquardt R4D liquid apogee engine would be used to maneuver the satellite into its final geosynchronous orbit. Stationed at 151 deg W.

Digital Audio Radio Satellite, used for transmission of S-band radio broadcasts direct to receivers in cars in the United States. Sirius 1 was inserted into an initial 6,166 x 47110 km x 63.4 deg transfer orbit by the Proton-K's Blok DM3 upper stage. The satellite's R4D liquid apogee engine made several burns to raise the orbit to 24,388 x 47,097 km x 63.3 deg by July 8. This elliptical, inclined 24 hour orbit had a 24 hour period, designed to keep the satellite between longitude 60W and 140W, with apogee over the northern hemisphere. Stationed at 66 deg W.