Launched 09:06 local time. Reached 103.7 km. Carried composition, photography experiments for Signal Corps Engineering Lab, University of Michigan. V-2 number 58 never launched.

Sky brightness, day airglow research. Launched at 0704 local time. Reached 114.3 km.

Council of Soviet Ministers (SM) Decree 956-4088s 'On approval of work on the R-7 ICBM, R-5R, and M5RD missiles' was issued. References: 474 .

Council of Soviet Ministers (SM) Decree 957-409 'On transfer of intercontinental cruise missile work to the Ministry of Aviation Industry' was issued. Korolev had to place the highest priority on development of the R-7 ICBM. Therefore the final government decree authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles. Both missiles would use ramjet engines by Bondaryuk, astronavigation systems by R Chachikyan, inertial navigation systems by G Tolstoysov, and aerodynamics developed by TsAGI (Central Hydrodynamics Institute). Lavochkin's Burya would use rocket booster engines built by Glushko, while Myasishchev's Buran would use Isayev engines. Both missiles were to deliver a nuclear warhead over an 8,500 km range. But the warhead design specified for the Lavochkin missile had a total mass of 2,100 kg, while that for the Myasishchev missile weighed 3,500 kg. References: 474 .

The Generator-S radiological warhead for the R-5 was developed in the early 1950's. In order to handle the warhead OKBT Kirov Factory built the shielded manipulator vehicle Objekt 805, which had a total mass of 72 tonnes. Following the demonstration the system was accepted by the military in 1955.

The National Advisory Committee for Aeronautics (NACA) and the Air Force signed a Memorandum of Understanding concerning the principles in the development and testing of the Air Force's Hypersonic Boost Glide Vehicle (Dyna Soar I). The following principles would apply to the project: (1) The project would be conducted as a joint Air Force-NACA project. (2) Overall technical control of the project would rest with the Air Force, acting with the advice and assistance of NACA. (3) Financing of the design, construction, and Air Force test of the vehicles would be borne by the Air Force. (4) Management of the project would be conducted by an Air Force project office within the Directorate of Systems Management, Headquarters, Air Research and Development Command. NACA would provide liaison representation in the project office and provide the chairman of the technical team responsible for data transmission and research instrumentation. (5) Design and construction of the system would be conducted through a negotiated prime contractor. (6) Flight tests of the vehicle and related equipment would be accomplished by NACA, the USAF, and the prime contractor in a combined test program, under the overall control of a joint NACA-USAF committee chaired by the Air Force.

NACA-USAF Memorandum of Understanding signed, "Principles for Participation of NACA in Development and Testing of the Air Force System 464L Hypersonic Boost Glide Vehicle (Dyna-Soar I)." References: 17 .

Suborbital. References: 5 .

Atlas ICBM fired 9,040 statute miles from AMR to Indian Ocean, longest known flight of an ICBM to date. Missile attained an apogee of about 1,000 miles. References: 17 , 278 .

Defense Meteorological Satellite Program. References: 1 , 2 , 5 , 6 .

MSC notified NASA Hq. that - with the changes defined for the Block II spacecraft following the January 27 Apollo 204 fire and with CSM delivery schedules now reestablished - it was necessary to complete a contract for three additional CSMs requested in 1966. North American Aviation had responded September 15, 1966, to MSC's February 28 request for a proposal, but action on a contract had been suspended because of the AS-204 accident. NASA Hq. on June 27, 1967, authorized MSC to proceed. References: 16 .

Maximum Speed - 959 kph. Maximum Altitude - 14970 m. Flight Time - 414 sec. References: 49 , 97 .

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

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

Radar monitoring; may or may not have existed!!!. References: 1 , 2 , 5 , 6 , 172 .

KH-4B. The overall image quality is less than that provided by recent missions and 2,000 feet of S0-349 References: 1 , 2 , 5 , 6 .

Not listed as failure by Martin but did not reach orbit. Possible spaceplane test? References: 5 .

Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 .

Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 .

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

The Pioneer Venus Orbiter was inserted into an elliptical orbit around Venus on December 4, 1978. After entering orbit around Venus in 1978, the spacecraft returned global maps of the planet's clouds, atmosphere and ionosphere, measurements of the atmosphere-solar wind interaction, and radar maps of 93 percent of the planet's surface. Additionally, the vehicle made use of several opportunities to make systematic UV observations of several comets. From Venus orbit insertion to July 1980, periapsis was held between 142 and 253 km (at 17 degrees north latitude) to facilitate radar and ionospheric measurements. The spacecraft was in a 24 hour orbit with an apoapsis of 66,900 km. Thereafter, the periapsis was allowed to rise (to 2290 km at maximum) and then fall, to conserve fuel. In 1991 the Radar Mapper was reactivated to investigate previously inaccessible southern portions of the planet. In May 1992 Pioneer Venus began the final phase of its mission, in which the periapsis was held between 150 and 250 km until the fuel ran out and atmospheric entry destroyed the spacecraft. With a planned primary mission duration of only eight months, the spacecraft remained in operation until October 8, 1992 when it finally burned up in Venus' atmosphere after running out of propellant. References: 1 , 2 , 5 , 6 , 278 , 296 .

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

Covered Oko constellation plane 1 - 276 degree longitude of ascending node. References: 1 , 2 , 5 , 6 , 100 .

Stretched Rohini Satellite Series; carried gamma-ray detector, ionosphere monitor. SROSS-C satellite carries two scientific payloads: 1) Retarding Potential Analyser (RPA), consisting of two planar detectors to measure plasma parameters and investigate energetics of the equatorial ionosphere. (2) Gamma Ray Burst (GRB) detectors, consist ing of two scintillation detectors to study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV. Launch vehicle: Augmented Satellite Launch Vehicle. References: 1 , 2 , 5 , 6 .

Stationed at 142.5 deg E. 'Rimsat-2' - Leased to Rimsat Corp. Communications satellite. Intended for use under commercial conditions. References: 1 , 2 , 5 , 6 , 67 , 111 , 274 .

MIR experiment module. Docked to Mir Jun 1
Officially: Docked to Mir Jun 1 References: 2 , 5 , 6 , 67 , 274 .

Installed MCSA solar array. References: 66 .

Telesat Canada's Nimiq television broadcasting satellite was placed into a 7050 km x 35790 km x 15.9 degree transfer orbit. The Nimiq was to use its liquid apogee engine (Royal Ordnance Leros 1) to reach geosynchronous orbit. Telesat Canada also operated the Anik Canadian domestic communications satellites, the first of which was launched in 1972.