Original design and development of Aerobee sounding rocket begun when contract was given to Aerojet Engineering Corp. References: 17 .

Test of separable warhead. Range achieved 320 km. Ballistic launch. Expected range 210 km. Launched at 0055 local time. References: 283 , 344 .

NACA flight 35. Spanwise pressure distribution, stability and control. Pull-ups and rolls. Mach 1.13 at 12810 m. References: 49 , 97 .

The Langley Research Center was in the process of preparing a one-fourteenth scale model of the Mercury spacecraft for launch from Wallops Island on a five-stage rocket to a speed of mach 18. References: 483 .

Tsybin�s design was called the gliding spacecraft (PKA). The draft project, undertaken in co-operation with Korolev�s OKB-1, was signed by Tsybin on 17 May 1959.The piloted PKA would be inserted into a 300 km altitude orbit by a Vostok launch vehicle. After 24 to 27 hours of flight the spacecraft would brake from orbit, gliding through the dense layers of the earth�s atmosphere. At the beginning of the descent, in the zone of most intense heating, the spacecraft would take advantage of a hull of original shape (called �Lapotok� by Korolev after the Russian wooden shoes that it resembled). After braking to 500 to 600 m/s at an altitude of 20 km, the PKA would glide to a runway landing on deployable wings, which would move to a horizontal position from a stowed vertical position over the back of the spacecraft. Control of the PKA in flight was by rocket jets or aerodynamic surfaces, depending on the phase of flight.

Successful missile test. Missed aimpoint by 304 m. References: 439 .

The Mercury-Atlas 7 (MA-7) manned orbital mission was postponed a second time because of necessary modifications to the altitude-sensing instrumentation in the parachute-deployment system. References: 483 .

Suborbital. References: 5 .

High resolution photo reconnaissance mission. References: 279 .

Maximum Speed - 5112 kph. Maximum Altitude - 21670 m. References: 38 , 49 , 97 .

Fractional Orbital Bombardment system test. Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 .

The E-6LS was a radio-equipped version of the E-6 used to test tracking and communications networks for the Soviet manned lunar program. The payload entered the desired orbit as Kosmos-159. References: 1 , 2 , 5 , 6 , 64 .

Christopher C. Kraft, Jr., MSC Director of Flight Operations, expressed concern to ASPO Manager George M. Low over the escalation of E-mission objectives; the flight now loomed as an extremely complex and ambitious mission. The probability of accomplishing all the objectives set forth for the mission, said Kraft, was very low. He did not propose changing the mission plan, however. "If we are fortunate," he said, "then certainly the quickest way to the moon will be achieved." Kraft did suggest caution in setting mission priorities and in "apply(ing) adjectives to the objectives." Additional Details: Concern over escalation of Apollo E-mission objectives. References: 16 .

Area survey photo reconnaissance satellite; returned film capsule; separated electron flux cosmic ray experiment capsule. References: 1 , 2 , 6 .

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

Ocean surveillance; nuclear powered. References: 1 , 2 , 5 , 6 .

Synchronous Meteorological Satellite. 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 solar ultraviolet rays and X-rays and the earth's upper atmosphere. References: 1 , 2 , 5 , 6 , 99 , 116 .

D5A: Weight 36 kg. Testing in space of a hydrazine catalytic decomposition micropropulsion unit. Responsible organization: Societe Europeene de Propulsion. D5B: Weight 76 kg. Testing in space of the CACTUS accelerometer (ultrasensitive triaxial capacitive accelerometric sensor). Responsible organization: ONERA, Chatillon-sous-Berneux, France. References: 1 , 2 , 5 , 6 .

D5A: Weight 36 kg. Testing in space of a hydrazine catalytic decomposition micropropulsion unit. Responsible organization: Societe Europeene de Propulsion. D5B: Weight 76 kg. Testing in space of the CACTUS accelerometer (ultrasensitive triaxial capacitive accelerometric sensor). Responsible organization: ONERA, Chatillon-sous-Berneux, France. References: 1 , 2 , 5 , 6 .

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

Replaced Cosmos 845. Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 .

Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. References: 1 , 2 , 6 , 103 .

3rd generation, high resolution photo surveillance; film capsule; maneuverable; also performed earth resources tasks. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. References: 1 , 2 , 6 .

Military navigation satellite. Replaced Cosmos 1383. References: 1 , 2 , 5 , 6 .

High resolution 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 , 179 .

12 microgravity experiments

Six satellites launched by a single carrier rocket. References: 1 , 2 , 5 , 6 , 105 .

Began installation of solar array. References: 66 .

Stationed at 53.1 deg W. References: 2 , 5 , 6 .

LEO. Sensor technology tests References: 4 , 6 , 276 .

Plane 1. Ascending node 167.8 degrees.

Plane 1. Ascending node 167.8 degrees.

Plane 1. Ascending node 167.8 degrees.

Plane 1. Ascending node 167.8 degrees.

Plane 1. Ascending node 167.7 degrees. Not in service.