May 30, 2006 - 35th Anniversary (1971), Mariner 9 Launch (USA Mars Orbiter)
- 40th Anniversary (1966), Surveyor 1 Launch (USA Moon Lander)

My how time flies.
1966 - gas $0.32 - :-)
http://www.1960sflashback.com/1966/Economy.asp
- LRK -

JPL Space Calendar helps with the memories.

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http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1966-045A
Surveyor 1 was the first spacecraft launched in the Surveyor program and the first soft landing on the Moon by the United States.

Launch Date/Time: 1966-05-30 at 14:41:00 UTC On-orbit Dry Mass: 294.3 kg
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http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1971-051A
The Mariner Mars 71 mission was planned to consist of two spacecraft to orbit Mars on complementary missions, but due to the failure of Mariner 8 to launch properly, only one spacecraft was available.

Launch Date/Time: 1971-05-30 at 22:23:00 UTC On-orbit Dry Mass: 558.8 kg Nominal Power Output: 500 W
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Notice the mass of the spacecraft these two early spacecraft compared to the Mars Reconnaissance Orbiter.
- LRK -

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http://en.wikipedia.org/wiki/Mars_Reconnaissance_Orbiter
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The craft's total mass is less than 2,180 kg (4,806 lb) with an unfueled dry mass less than 1,031 kg (2,273 lb)
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http://marsprogram.jpl.nasa.gov/mro/mission/sc.html
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Thanks for looking up with me.

Larry Kellogg

Web Site: http://lkellogg.vttoth.com/LarryRussellKellogg/
BlogSpot: http://kelloggserialreports.blogspot.com/
RSS link: http://kelloggserialreports.blogspot.com/atom.xml
Newsltr.: https://news.altair.com/mailman/listinfo/lunar-update
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http://www2.jpl.nasa.gov/calendar/
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# May 30 - Asteroid 4628 Laplace Closest Approach To Earth (1.577 AU)
http://neo.jpl.nasa.gov/cgi-bin/db_shm?des=4628

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# May 30 - 35th Anniversary (1971), Mariner 9 Launch (USA Mars Orbiter) http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1971-051A
Mariner 9

NSSDC ID: 1971-051A
Image associated with mission
Other Names

* Mariner Mars '71
* Mariner-I
* 05261

Launch Date/Time: 1971-05-30 at 22:23:00 UTC On-orbit Dry Mass: 558.8 kg Nominal Power Output: 500 W Description

The Mariner Mars 71 mission was planned to consist of two spacecraft to orbit Mars on complementary missions, but due to the failure of Mariner 8 to launch properly, only one spacecraft was available. Mariner 9 combined mission objectives of both Mariner 8 (mapping 70 % of the Martian surface) and Mariner 9 (a study of temporal changes in the Martian atmosphere and on the Martian surface). For the survey portion of the mission, the planetary surface was to be mapped with the same resolution as planned for the original mission, although the resolution of pictures of the polar regions would be decreased due to the increased slant range. The variable features experiments were changed from studies of six given areas every 5 days to studies of smaller regions every 17 days. Mariner 9 was the first spacecraft to orbit another planet.

Spacecraft and Subsystems

The Mariner 9 spacecraft was built on an octagonal magnesium frame, 45.7 cm deep and 138.4 cm across a diagonal. Four solar panels, each 215 x 90 cm, extended out from the top of the frame. Each set of two solar panels spanned 6.89 meters from tip to tip. Also mounted on the top of the frame were two propulsion tanks, the maneuver engine, a 1.44 m long low gain antenna mast and a parabolic high gain antenna. A scan platform was mounted on the bottom of the frame, on which were attached the mutually bore-sighted science instruments (wide- and narrow-angle TV cameras, infrared radiometer, ultraviolet spectrometer, and infrared interferometer spectrometer). The overall height of the spacecraft was 2.28 m. The launch mass was 997.9 kg, of which 439.1 kg were expendables. The science instrumentation had a total mass of 63.1 kg. The electronics for communications and command and control were housed within the frame.

Spacecraft power was provided by a total of 14,742 solar cells which made up the 4 solar panels with a total area of 7.7 square meters. The solar panels could produce 800 W at Earth and 500 W at Mars. Power was stored in a 20 amp-hr nickel-cadmium battery. Propulsion was provided by a gimbaled engine capable of 1340 N thrust and up to 5 restarts. The propellant was monomethyl hydrazine and nitrogen tetroxide. Two sets of 6 attitude control nitrogen jets were mounted on the ends of the solar panels. Attitude knowledge was provided by a Sun sensor, a Canopus star tracker, gyroscopes, an inertial reference unit, and an accelerometer. Passive thermal control was achieved through the use of louvers on the eight sides of the frame and thermal blankets.

Spacecraft control was through the central computer and sequencer which had an onboard memory of 512 words. The command system was programmed with 86 direct commands, 4 quantitative commands, and 5 control commands. Data was stored on a digital reel-to-reel tape recorder. The 168 meter 8-track tape could store 180 million bits recorded at 132 kbits/s. Playback could be done at 16, 8, 4, 2, and 1 kbit/s using two tracks at a time.

Telecommunications were via dual S-band 10 W/20 W transmitters and a single receiver through the high gain parabolic antenna, the medium gain horn antenna, or the low gain omnidirectional antenna.

Mission Profile

Mariner 9 was launched on a 398 million km direct ascent trajectory to Mars by an Atlas-Centaur SLV-3C booster (AC-23). Separation from the booster occurred at 22:36 UT (6:36 p.m. EDT), 13 minutes after launch. The four solar panels were deployed at 22:40 UT. The sensors locked onto the Sun at 23:16, shortly after the spacecraft left the Earth's shadow and Canopus acquisition was achieved at 02:26 UT 31 May. A planned midcourse maneuver was executed on 5 June. Mariner 9 arrived at Mars on 14 November 1971 after a 167 day flight. A 15 minute 23 second rocket burn put the spacecraft into Mars orbit, making Mariner 9 the first spacecraft to orbit another planet.

The insertion orbit had a periapsis of 1398 km and a period of 12 hr, 34 min. Two days later a 6 second rocket burn changed the orbital period to just under 12 hours with a periapsis of 1387 km. A correction trim maneuver was made on 30 December on the 94th orbit which raised the periapsis to 1650 km and changed the orbital period to 11:59:28 so that synchronous data transmissions could be made to the Goldstone 64-m DSN antenna.

Imaging of the surface of Mars by Mariner 9 was delayed by a dust storm which started on 22 September 1971 in the Noachis region. The storm quickly grew into one of the largest global storms ever observed on Mars. By the time the spacecraft arrived at Mars no surface details could be seen except the summits of Olympus Mons and the three Tharsis volcanoes. The storm abated through November and December and normal mapping operations began.

The spacecraft gathered data on the atmospheric composition, density, pressure, and temperature and also the surface composition, temperature, gravity, and topography of Mars. A total of 54 billion bits of scientific data were returned, including 7329 images covering the entire planet. After depleting its supply of attitude control gas, the spacecraft was turned off on 27 October 1972. Mariner 9 was left in an orbit which should not decay for at least 50 years, after which the spacecraft will enter the martian atmosphere.

The Mariner 9 mission resulted in a global mapping of the surface of Mars, including the first detailed views of the martian volcanoes, Valles Marineris, the polar caps, and the satellites Phobos and Deimos. It also provided information on global dust storms, the triaxial figure of Mars, and the rugged gravity field as well as evidence for surface aeolian activity.

Total research, development, launch, and support costs for the Mariner series of spacecraft (Mariners 1 through 10) was approximately $554 million.


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# May 30 - 40th Anniversary (1966), Surveyor 1 Launch (USA Moon Lander) http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=1966-045A

Surveyor 1

NSSDC ID: 1966-045A
Image associated with mission
Other Names

* Surveyor I
* Surveyor-A
* 02185

Launch Date/Time: 1966-05-30 at 14:41:00 UTC On-orbit Dry Mass: 294.3 kg Description

Surveyor 1 was the first spacecraft launched in the Surveyor program and the first soft landing on the Moon by the United States. The mission was considered a complete success and demonstrated the technology necessary to achieve landing and operations on the lunar surface. The primary objectives of the Surveyor program, a series of seven robotic lunar softlanding flights, were to support the coming crewed Apollo landings by: (1) developing and validating the technology for landing softly on the Moon; (2) providing data on the compatibility of the Apollo design with conditions encountered on the lunar surface; and (3) adding to the scientific knowledge of the Moon.

The specific primary objectives for this mission were to: (1) demonstrate the capability of the Surveyor spacecraft to perform successful midcourse and terminal maneuvers, and to achieve a soft landing on the Moon; (2) demonstrate the capability of the Surveyor communications system and Deep Space Network to maintain communications with the spacecraft during its flight and after a soft landing; and (3) demonstrate the capability of the Atlas/Centaur launch vehicle to inject the Surveyor spacecraft on a lunar intercept trajectory. Secondary objectives were to obtain engineering data on spacecraft subsystems used during cruise, descent and after landing.

Tertiary objectives were to obtain postlanding TV pictures of a spacecraft footpad, the surface material immediately surrounding it and the lunar topography, and to obtain data on radar reflectivity and bearing strength of the lunar surface and on spacecraft temperatures.

Spacecraft and Subsystems

The basic Surveyor spacecraft structure consisted of a tripod of thin-walled aluminum tubing and interconnecting braces providing mounting surfaces and attachments for the power, communications, propulsion, flight control, and payload systems. A central mast extended about one meter above the apex of the tripod. Three hinged landing legs were attached to the lower corners of the structure. The legs held shock absorbers, crushable, honeycomb aluminum blocks, and the deployment locking mechanism and terminated in footpads with crushable bottoms. The three footpads extended out 4.3 meters from the center of the Surveyor. The spacecraft was about 3 meters tall. The legs folded to fit into a nose shroud for launch.

A 0.855 square meter array of 792 solar cells was mounted on a positioner on top of the mast and generated up to 85 Watts of power which was stored in rechargeable silver-zinc batteries.? Communications were achieved via a movable large planar array high gain antenna mounted near the top of the central mast to transmit television images, two omnidirectional conical antennas mounted on the ends of folding booms for uplink and downlink, two receivers and two transmitters. Thermal control was achieved by a combination of white paint, high IR-emittance thermal finish, polished aluminum underside. Two thermally controlled compartments, equipped with superinsulating blankets, conductive heat paths, thermal switches and small electric heaters, were mounted on the spacecraft structure. One compartment, held at 5 - 50 degrees C, housed communications and power supply electronics. The other, held between -20 and 50 degrees C, housed the command and signal processing components. The TV survey camera was mounted near the top of the tripod and strain gauges, temperature sensors, and other engineering instruments are incorporated throughout the spacecraft. One photometric targets was mounted near the end of a landing leg and one on a short boom extending from the bottom of the structure. Other payload packages, which differed from mission to mission, were mounted on various parts of the structure depending on their function.

A Sun sensor, Canopus tracker and rate gyros on three axes provided attitude knowledge. Propulsion and attitude control were provided by cold-gas (nitrogen) attitude control jets during cruise phases, three throttlable vernier rocket engines during powered phases, including the landing, and the solid-propellant retrorocket engine during terminal descent. The retrorocket was a spherical steel case mounted in the bottom center of the spacecraft.

The vernier engines used monomethyl hydrazine hydrate fuel and MON-10 (90% N2O2, 10% NO) oxidizer. Each thrust chamber could produce 130 N to 460 N of thrust on cammand, one engine could swivel for roll control. The fuel was stored in spherical tanks mounted to the tripod structure. For the landing sequence, an altitude marking radar initiated the firing of the main retrorocket for primary braking. After firing was complete, the retrorocket and radar were jettisoned and the doppler and altimeter radars were activated. These provided information to the autopilot which controlled the vernier propulsion system to touchdown.

No instrumentation was carried specifically for scientific experiments, but considerable scientific information was obtained. Surveyor 1 carried two television cameras - one mounted on the bottom of the frame for approach photography, which was not used, and the survey television camera. Over 100 engineering sensors were on board. Surveyor 1 had a mass of 995.2 kg at launch and 294.3 kg at landing.

Mission Profile

Surveyor 1 was launched on 30 May 1966 at 14:41:00 UT (9:41 EST) on an Atlas/Centaur from Complex 36-A of the Eastern Test Range directly into a lunar impact trajectory. After a midcourse correction at 06:45 UT on 31 May the spacecraft reached the Moon about 63 hours after launch. At an altitude of 75.3 km and a velocity of 2612 m/s the main retrorocket, signaled by the altitude marking radar, ignited for a 40 second burn and was jettisoned at an altitude of roughly 11 km having slowed the spacecraft to 110 m/s.

Descent continued with the vernier engines under control of the altimeter and doppler radars. Engines were turned off at a height of 3.4 m above the lunar surface and the spacecraft fell freely from this height. Surveyor 1 landed on the lunar surface on 2 June 1966 at 6:17:36 UT (1:17:36 a.m. EST) at about 3 m/s. The landing site was at 2.45 S, 316.79 E (selenographic) on a flat area inside a 100 km crater north of Flamsteed Crater in southwest Oceanus Procellarum.

Surveyor 1's first hour on the Moon was spent performing engineering tests.
Photography sessions were then initiated throughout the remainder of the lunar day. The television system transmitted pictures of the spacecraft footpad and surrounding lunar terrain and surface materials. Some 10,338 photos were returned prior to nightfall on June 14. The spacecraft also acquired data on the radar reflectivity of the lunar surface, bearing strength of the lunar surface, and spacecraft temperatures for use in the analysis of the lunar surface temperatures. Surveyor 1 was able to withstand the first lunar night and near high noon on its second lunar day, July 7, photos again were returned. On 13 July at 7:30 UT (2:30 a.m. EST), after a total of 11,240 pictures had been transmitted, Surveyor 1's mission was terminated due to a dramatic drop in battery voltage just after sunset.

Engineering interrogations continued until January 7, 1967. All mission objectives were accomplished. The Surveyor program involved building and launching 7 Surveyor spacecraft to the Moon at a total cost of $469 million.

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WHAT THE MIND CAN CONCEIVE, AND BELIEVE, IT WILL ACHIEVE - LRK

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