Mishin and Barmin, using budget provided by the Ministry of Defence, had designed a lunar base for launch by the N1 in 1969-1974. After the cancellation of the N1, Glushko pleaded with the Military-Industrial Commission for the work to be taken from Barmin and be given to NPO Energia. Glushko's alternative, Vulkan-launched base was elaborated within his bureau. Bushuyev developed spacecraft for the base. Prudnikova developed a modular lunar city, with living modules, factory modules, a nuclear reactor power module, and a lunar crawler with a 200 km radius of action. The project work was only finally cancelled after the Apollo-Soyuz flights.

Glushko proposed a Mars expedition launched by the Vulkan heavy-lift launch vehicle. The concept was treated like a bad allergy by the VPK. He later scaled it down and proposed it for launch by Energia (using 100 tonne modules instead of 230 tonne modules).

As the only remaining contender for the Aelita design competition, Chelomei proposes a Mars flyby using an MK-700 spacecraft. A crew of two would be sent on a two year mission in a single launch of a UR-700M booster. The spacecraft would have a mass of 250 tonnes in low earth orbit and be equipped with an RD-410 nuclear engine.

The last Wing V squadron was turned over to the Strategic Air Command to complete the Wing V integrated program at Francis E. Warren AFB, Wyoming, 20 days ahead of schedule. This program, the greatest single effort in the Minuteman program since the early days when the Minuteman I was placed in operation, included the swap-out of Minuteman I missiles for Minuteman Ills.

HQ USAF issued a Program Management Directive specifying that initial DOD space shuttle mission operations would be planned and controlled by a predominantly NASA team rather than by a DOD team. The Program Management Directive also directed that action be taken to minimize the impact of DOD communications security requirements on shuttle operations.

Grumman completes a study of a lower-cost external tank. It would use a Nomex core, aluminium liner, and E-glass/epoxy exterior. Although lower in cost than the baseline aluminium tank, it would be slightly heavier. Given the critical weight growth problem with the shuttle, it was not proceeded with. In fact, a continuous program of weight reduction for the baseline tank was introduced. Batch 1 External Tanks were already from 500 to 1040 kg lighter than the first tank. Batch 2, set for delivery from June 1982 to Vandenberg AFB for USAF launches, were 2700 kg lighter. The final "lightweight tank" was over 4500 kg lighter. All of these translated into equivalent additional payload for the shuttle.

The first live demonstration flight of a Pedro Recruit sounding rocket occurred at Wallops Island, Virginia. It was a clear air launch of a carbon-phenolic nosetip from an F-4 aircraft. The launch, part of the Fighter Launched Advanced Materials Experiment (FLAME), was successful, but the payload was not recovered. Attempts on 20 September and 9 October to drop an inert Pedro Recruit rocket from an F-4 aircraft had failed. This was a DNA-sponsored experiment.

Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at (GOES W) 115 deg W in 1975-1976; over the Pacific Ocean (GOES W) 135 deg W in 1976-1978; over the Atlantic Ocean (GOES E) 75 deg W in 1979-1981; over the Americas at 106 deg W in 1982 As of 29 August 2001 located at 123.04 deg W drifting at 2.760 deg W per day. As of 2007 Feb 27 located at 127.44E drifting at 2.742W degrees per day.

Examined solar radiation, thermospheric structure. SRATS (Solar and Thermospheric Radiation Satellite) is the third Japanese scientific satellite, to study the intereffects of solar radiation and the thermosphere of the earth. National name: Taiyo. Launch time 0525 GMT.

Carried Oleg Makarov, Vasili Lazarev for rendezvous with Salyut 4; but during second-third stage seperation third stage failed to separate from second stage but still ignited. The crew demanded that the abort procedures be implemented but ground control could not see the launch vehicle gyrations in their telemetry. Soyuz finally was separated from by ground control command at 192 km, and following a 20.6+ G reentry, the capsule landed in the Altai mountains, tumbled down a mountainside, and snagged in some bushes just short of a precipice. The crew was worried that they may have landed in China and would face internment, but after an hour sitting in the cold next to the capsule, they were discovered by locals speaking Russian. Total flight duration was 1574 km and flight time 21 minutes 27 seconds. Lazarev suffered internal injuries from the high-G reentry and tumble down the mountain side and never flew again. Both cosmonauts were denied their 3000 ruble spaceflight bonus pay and had to apeal all the way to Brezhnev before being paid.

Geodynamics Experimental Ocean Satellite. The mission of GEOS 3 (Geodynamics Experimental Ocean Satellite) was to provide the stepping stone between the National Geodetic Satellite Program (NGSP) and the Earth and Ocean Physics Application Program. It provided data to refine the geodetic and geophysical results of the NGSP and served as a test for new systems. A major achievment was the flight of a radar altimeter. Further mission objectives: intercomparison of tracking systems, investigation of solid-earth dynamic phenomena through precision laser tracking, refinement of orbit determination techniques, determination of interdatum ties and gravity models, and support of the calibration and position determination of NASA Spaceflight Tracking and Data Network (STDN) S-band tracking stations.

Space Test Program flight P72-2 was launched; it carried two infrared radiometers and three other payloads. The launch failed when the Atlas F launch vehicle malfunctioned. A lack of deluge water and collection in the flame bucket of a kerosene/liquid oxygen gel led to the explosion of the gel on lift-off, damaging one of the Atlas engines and leading to complete engine failure during the ascent.

In response to the Ministry of Defence's guidelines for third generation launch vehicles, the Ministry of General Machine Building issued instructions for Chelomei to study boosters meeting the military's requirements. These included Lox/Kerosene propellants in place of the toxic N2O4/UDMH favoured previously. Chelomei's competitor in the design, Glushko, was then head of NPO Energia which included Glushko's former OKB-456 engine design bureau. Therefore Chelomei was forced to propose using Kuznetsov Lox/Kerosene engines from the cancelled N1 moon program. The use of existing Proton tankage tooling for the stages and the Kuznetsov engines would allow a high-performance vehicle to be developed at minimum cost. However Chelomei was out of favour, Kuznetsov was discredited after the N1 fiasco, and Glushko was ascendant. The proposal stood no chance. Glushko's Zenit launch vehicle became the accepted solution.

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 104 deg W in 1975-1976; over the Americas at 114 deg W in 1976-1984 As of 4 September 2001 located at 32.38 deg E drifting at 0.812 deg W per day. As of 2007 Mar 9 located at 138.81W drifting at 0.829W degrees per day.

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.

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.

The third pair of Defense Satellite Communications System II satellites was launched; the launch failed due to a malfunction in the Transtage of the Titan IIIC launch vehicle. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

The third pair of Defense Satellite Communications System II satellites was launched; the launch failed due to a malfunction in the Transtage of the Titan IIIC launch vehicle. Unusable orbit. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit over the Indian Ocean at 63 deg E in 1976-1978; over the Atlantic Ocean 17.0 deg W in 1978; over the Atlantic Ocean 18.5 deg W in 1979-1981; over the Pacific Ocean 174 deg E in 1982; over the Atlantic Ocean 53 deg W in 1983-1984; over the Atlantic Ocean 50 deg W in 1984-1987 As of 30 August 2001 located at 111.08 deg W drifting at 3.657 deg W per day. As of 2007 Mar 11 located at 95.13E drifting at 3.657W degrees per day.

Zenit-2M (area survey photo reconnaissance) satellite used for earth resources studies as part of 'Gektor-Priroda' project. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.

SRET 2 technological research and study satellite. Launched from Soviet Union with a Soviet launch vehicle with the Molniya satellite. Mass 30 kg. Study of the behaviour of a passive cryogenic radiation system, study of the aging of thermal casings and pl astic films.

Combined Venus orbiter/lander mission. After separation of the lander, the orbiter spacecraft entered Venus orbit and acted as a communications relay for the lander and explored cloud layers and atmospheric parameters. On October 20, 1975, the Descent Craft was separated from the Orbiter, and landing was made with the sun near zenith at 05:13 GMT on October 22. The Descent Craft included a system of circulating fluid to distribute the heat load. This system, plus precooling prior to entry, permitted operation of the spacecraft for 53 min after landing. The landing was about 2,200 km from the Venera 10 landing site. Preliminary results indicated: (A) clouds 30-40 km thick with bases at 30-35 km altitude, (B) atmospheric constituents including HCl, HF, Br, and I, (C) surface pressure about 90 (earth) atmospheres, (D) surface temperature 485 deg C, (E) light levels comparable to those at earth midlatitudes on a cloudy summer day, and (F) successful TV photography showing shadows, no apparent dust in the air, and a variety of 30-40 cm rocks which were not eroded. Venera 9 and 10 were the first probes to send back black and white pictures from the Venusian surface. They were supposed to make 360 degree panoramic shots, but on both landers one of two camera covers failed to come off, restricting their field of view to 180 degrees. Parameters are for Venus orbit.

Environmental research. The experiments selected for Nimbus-6 were the earth radiation budget (ERB), electrically scanning microwave radiometer (ESMR), high-resolution infrared radiation sounder (HIRS), limb radiance inversion radiometer (LRIR), pressure modulated radiometer (PMR), scanning microwave spectrometer (SCAMS), temperature-humidity infrared radiometer (THIR), tracking and data relay experiment (T+DRE), and the tropical wind energy conversion and reference level experiment (TWERLE). This complement of advanced sensors was capable of mapping tropospheric temperature, water vapor abundance, and cloud water content; providing vertical profiles of temperature, ozone, and water vapor; transmitting real-time data to a geostationary spacecraft (ATS 6); and yielding data on the earth's radiation budget.

The orbiter spacecraft entered Venus orbit and was separated from the lander on October 23, 1975. The lander touched down with the sun near zenith, at 05:17 GMT, on October 25. A system of circulating fluid was used to distribute the heat load. This system, plus precooling prior to entry, permitted operation of the spacecraft for 65 min after landing. During descent, heat dissipation and deceleration were accomplished sequentially by protective hemispheric shells, three parachutes, a disk-shaped drag brake, and a compressible, metal, doughnut-shaped, landing cushion. The landing was about 2,200 km distant from Venera 9. Preliminary results provided: (A) profile of altitude (km)/pressure (earth atmospheres) / temperature (deg C) of 42/3.3/158, 15/37/363, and 0/92/465, (B) successful TV photography showing large pancake rocks with lava or other weathered rocks in between, and (C) surface wind speed of 3.5 m/s. Venera 9 and 10 were the first probes to send back black and white pictures from the Venusian surface. They were supposed to make 360 degree panoramic shots, but on both landers one of two camera covers failed to come off, restricting their field of view to 180 degrees.

Soyuz 19 initial orbital parameters were 220.8 by 185.07 kilometres, at the desired inclination of 51.80°, while the period of the first orbit was 88.6 minutes. On 17 July the two spacecraft docked. The crew members rotated between the two spacecraft and conducted various mainly ceremonial activities. Leonov was on the American side for 5 hours, 43 minutes, while Kubasov spent 4:57 in the command and docking modules.

After being docked for nearly 44 hours, Apollo and Soyuz parted for the first time and were station-keeping at a range of 50 meters. The Apollo crew placed its craft between Soyuz and the sun so that the diameter of the service module formed a disk which blocked out the sun. After this experiment Apollo moved towards Soyuz for the second docking.

Three hours later Apollo and Soyuz undocked for the second and final time. The spacecraft moved to a 40 m station-keeping distance so that an ultraviolet absorption experiment could be performed. With all the joint flight activities completed, the ships went on their separate ways.

This flight marked the culmination of the Apollo-Soyuz Test Project, a post-moon race 'goodwill' flight to test a common docking system for space rescue. 15 July 1975 began with the flawless launch of Soyuz 19. Apollo followed right on schedule. Despite a stowaway - a 'super Florida mosquito' - the crew accomplished a series of rendezvous manoeuvres over the next day resulting in rendezvous with Soyuz 19. At 11:10 on 17 July the two spacecraft docked. The crew members rotated between the two spacecraft and conducted various mainly ceremonial activities. Stafford spent 7 hours, 10 minutes aboard Soyuz, Brand 6:30, and Slayton 1:35. Leonov was on the American side for 5 hours, 43 minutes, while Kubasov spent 4:57 in the command and docking modules.

After being docked for nearly 44 hours, Apollo and Soyuz parted for the first time and were station-keeping at a range of 50 meters. The Apollo crew placed its craft between Soyuz and the sun so that the diameter of the service module formed a disk which blocked out the sun. This artificial solar eclipse, as viewed from Soyuz, permitted photography of the solar corona. After this experiment Apollo moved towards Soyuz for the second docking.

Three hours later Apollo and Soyuz undocked for the second and final time. The spacecraft moved to a 40 m station-keeping distance so that the ultraviolet absorption (UVA MA-059) experiment could be performed. This was an effort to more precisely determine the quantities of atomic oxygen and atomic nitrogen existing at such altitudes. Apollo, flying out of plane around Soyuz, projected monochromatic laser-like beams of light to retro-reflectors mounted on Soyuz. On the 150-meter phase of the experiment, light from a Soyuz port led to a misalignment of the spectrometer, but on the 500-meter pass excellent data were received; on the 1,000-meter pass satisfactory results were also obtained.

With all the joint flight activities completed, the ships went on their separate ways. On 20 July the Apollo crew conducted earth observation, experiments in the multipurpose furnace (MA-010), extreme ultraviolet surveying (MA-083), crystal growth (MA-085), and helium glow (MA-088). On 21 July Soyuz 19 landed safely in Kazakhstan. Apollo continued in orbit on 22-23 July to conduct 23 independent experiments - including a doppler tracking experiment (MA-089) and geodynamics experiment (MA-128) designed to verify which of two techniques would be best suited for studying plate tectonics from earth orbit.

After donning their space suits, the crew vented the command module tunnel and jettisoned the docking module. The docking module would continue on its way until it re-entered the earth's atmosphere and burned up in August 1975.

The crew members take turns visiting each other's capsules, a complicated procedure due to the need to keep both spacecraft manned at all times and for the transfer crews to transition in the docking module between the different Soyuz and Apollo cabin atmospheres. Additional Details: here....

During day five of the flight, the crews concentrated on docking exercises and experiments that involved the two ships in the undocked mode. During the interval between the first undocking and the second docking, the Apollo crew placed its craft between Soyuz and the sun so that the diameter of the service module formed a disk which blocked out the sun. This artificial solar eclipse, as viewed from Soyuz, permitted Leonov and Kubasov to photograph the solar corona. Additional Details: here....

Following a rest period of nearly 10 hours, the Soyuz crewmen advised the ground that they were awake and that all systems were normal. The deorbit burn came exactly on time (5:09 in Houston), and the Soyuz crew landed safely in Kazakhstan. For the remaining three and a half days, Stafford, Slayton, and Brand would concentrate on their experiments, but in many respects the saga of Apollo and Soyuz had come to an end.

Some minor experiment hardware problems developed during the final days of the mission, but for the most part the crew members worked through their flight plan - which included 23 independent experiments - with few difficulties. After a relatively quiet day of work on the 22nd, the major part of the 23rd was devoted to preparing for and conducting the doppler tracking experiment (MA-089). The day was also marked by a press conference from space and jettison of the docking module. Additional Details: here....

Apollo (ASTP) landed at 21:18 GMT, 7.3 km from the recovery ship New Orleans. It was the last splashdown of an American space capsule. However the flight of the last Apollo spacecraft was marred by the fact that the crew almost perished while the capsule was descending under its parachute.

A failure in switchology led the automatic landing sequence to be not armed at the same time the reaction control system was still active. When the Apollo hadn't begun the parachute deployment sequence by 7,000 metres altitude, Brand hit the manual switches for the apex cover and the drogues. The manual deployment of the drogue chutes caused the CM to sway, and the reaction control system thrusters worked vigorously to counteract that motion. When the crew finally armed the automatic ELS 30 seconds later, the thruster action terminated.

During that 30 seconds, the cabin was flooded with a mixture of toxic unignited propellants from the thrusters. Prior to drogue deployment, the cabin pressure relief valve had opened automatically, and in addition to drawing in fresh air it also brought in unwanted gases being expelled from the roll thrusters located about 0.6 meter from the relief valve. Brand manually deployed the main parachutes at about 2,700 meters despite the gas fumes in the cabin.

By the time of splashdown, the crew was nearly unconscious from the fumes, Stafford managed to get an oxygen mask over Brand's face. He then began to come around. When the command module was upright in the water, Stafford opened the vent valve, and with the in-rush of air the remaining fumes disappeared. The crew ended up with a two-week hospital stay in Honolulu. For Slayton, it also meant the discovery of a small lesion on his left lung and an exploratory operation that indicated it was a non-malignant tumour. Additional Details: here....

The final test of the Launch Equipment Room Full-Up Floor Test Program was completed at Vandenberg AFB. This test program began in January 1973 with tests of the complete Wing V upgraded floor shock isolation system with mass-simulated electronics (Block I) and continued with tests of the Wing V upgraded floor with operating electronics (Block II), tests of single isolators (Block III), and tests of a Wing VI upgraded floor with mass-simulated electronics (Block IV). The highly successful program not only qualified the upgraded floor to design criteria, but also demonstrated that the subsystem had inherently harder shock capability than was required.