Mariner 7

Launch data: Designation 03837 / 69030A Launch date 27 Mar 1969 - 22:22:01 UT Launch site CC, LC-36A Launch vehicle Atlas-SLV3C Centaur-D (AC-19) Satellite type Mission Mars probe Heliocentric orbit Perihelion x Aphelion 0.971 x 1.568 A.U. Eccentricity  0.235 Inclination 1.60 deg Period 522 days Orbit after Mars fly-by Perihelion x Aphelion 1.118 x 1.670 A.U. Eccentricity  0.198 Inclination 1.82 deg Period 609 days

Specifications:

Descriptions:

• Mariner 6 and 7 comprised a dual-spacecraft mission to Mars. The primary objectives of the missions were to study the surface and atmosphere of Mars during close flybys to establish the basis for future investigations, particularly those relevant to the search for extraterrestrial life, and to demonstrate and develop technologies required for future Mars missions and other long-duration missions far from the Sun. Each spacecraft carried a wide- and narrow-angle television camera, an infrared spectroscope, an infrared radiometer, and an ultraviolet spectroscope. The spacecraft were oriented entirely to planetary data acquisition, and no data were obtained during the trip to Mars or beyond Mars. Mariners 6 and 7 were designed to fly over the equator and southern hemisphere of Mars. Mariner 6 encountered Mars on July 31,1969 and was quickly followed by Mariner 7 on August 4, 1969. The two spacecraft returned a combined total of 143 approach pictures of the planet and 55 close-up pictures. These images, from the vehicles' television cameras, included pictures of the northern and southern polar caps as well as Phobos, one of Mars' two moons. The spacecraft also studied the Martian atmosphere and profiled its chemical composition. Closest approach to Mars for both spacecraft was approximately 3,550 kilometres. The cost of the two missions was $148 million.
• Spacecraft and Subsystems:
  The Mariner 6 and 7 spacecraft were identical, consisting of an octagonal magnesium frame base, 138.4 cm diagonally and 45.7 cm deep. A conical superstructure mounted on top of the frame held the high-gain 1 meter diameter parabolic antenna and four solar panels, each measuring 215 x 90 cm, were affixed to the top corners of the frame. The tip-to-tip span of the deployed solar panels was 5.79 m. A low-gain omnidirectional antenna was mounted on a 2.23 m high mast next to the high-gain antenna. Underneath the octagonal frame was a two-axis scan platform which held scientific instruments. Overall science instrument mass was 57.6 kg. The total height of the spacecraft was 3.35 m.
• The spacecraft was attitude stabilized in three axes (referenced to the sun and the star, Canopus) through the use of 3 gyros, 2 sets of 6 nitrogen jets mounted on the ends of the solar panels, a Canopus tracker, and two primary and four secondary sun sensors. Propulsion was provided by a 223 N rocket motor mounted within the frame which used monopropellant hydrazine. The nozzle with 4-jet vane vector control protruded from one wall of the octagonal structure. Power was supplied by 17,472 photovoltaic cells covering an area of 7.7 square meters on the four solar panels. These could provide 800 W of power near Earth and 449 W at Mars. The maximum power requirement was 380 W at Mars encounter. A 1200 W-hr rechargeable silver-zinc battery was used to provide backup power. Thermal control was achieved through the use of adjustable louvers on the sides of the main compartment.
• Three telemetry channels were available for telecommunications. Channel A carried engineering data at 8 1/3 or 33 1/3 bps, channel B carried scientific data at 66 2/3 or 270 bps and channel C carried science data at 16,200 bps. Communications were accomplished via the high- and low-gain antennas via dual S-band travelling wave tube 10/20 W amplifiers for transmission and a single receiver. An analog tape recorder with a capacity of 195 million bits could store television images for subsequent transmission. Other science data was stored on a digital recorder. The command system, consisting of a central computer and sequencer (CC&S), was designed to actuate specific events at precise times. The CC&S was programmed with a standard mission and a conservative backup mission befire launch, but could be commanded and reprogrammed in flight. It could perform 53 direct commands, 5 control commands, and 4 quantitative commands.
• Payload:
  The planetary experiments (59 kg) included two television cameras, an infrared radiometer, an infrared spectrometer, and an ultraviolet spectrometer. These sensors took TV pictures of Mars and measured the ratio of refractivity and UV and IR emissions of the atmosphere.

Mission details:

• Mariner 7 was launched on a direct-ascent trajectory to Mars 31 days after Mariner 6. On 8 April 1969 a midcourse correction was made by firing the hydrazine moter for 7.6 seconds. On 8 May Mariner 7 was put on gyro control to avoid attitude control problems which were affecting Mariner 6. On 31 July telemetry from Mariner 7 was suddenly lost and the spacecraft was commanded to switch to the low-gain antenna. It was later successfully switched back to the high-gain antenna. It was thought that leaking gases, perhaps from the battery which later failed a few days before encounter, had caused the anomaly.
• At 09:32:33 GMT on 2 August 1969 Mariner 7 bagan the far-encounter sequence involving imaging of Mars with the narrow angle camera. Over the next 57 hours, ending about 5 hours before closest approach, 93 images of Mars were taken and transmitted. The spacecraft was reprogrammed as a result of analysis of Mariner 6 images. The new sequence called for the spacecraft to go further south than originally planned, take more near-encounter pictures, and collect more scientific data on the lighted side of Mars. Data from the dark side of Mars were to be transmitted directly back to Earth but there would be no room on the digital recorder for backup due to the added dayside data. At closest approach, 05:00:49 GMT on 5 August, Mariner 7 was 3430 km above the martian surface. Over this period, 33 near-encounter images were taken. About 19 minutes after the flyby, the spacecraft went behind Mars and emerged roughly 30 minutes later. X-band occultation data were taken during the entrance and exit phases. Science and imaging data were played back and transmitted over the next few days. The spacecraft was then returned to cruise mode which included engineering and communications tests, star photography TV tests, and UV scans of the Milky Way and an area containing comet 1969-B. Periodic tracking of the spacecraft in its heliocentric orbit was also done.
• Science Results:
  The total data return for Mariners 6 and 7 was 800 million bits. Mariner 7 returned 93 far and 33 near encounter images. Close-ups from the near encounter phases covered 20% of the surface. The spacecraft instruments measured UV and IR emissions and radio refractivity of the Martian atmosphere. Images showed the surface of Mars to be very different from that of the Moon, in some contrast to the results from Mariner 4. The south polar cap was identified as being composed predominantly of carbon dioxide. Atmospheric surface pressure was estimated at between 6 and 7 mb. Radio science refined estimates of the mass, radius and shape of Mars.