Rb-Sr and Sm-Nd chronology and genealogy of mare basalts from the Sea of Tranquility

NASA Technical Reports Server (NTRS)

Papanastassiou, D. A.; Depaolo, D. J.; Wasserburg, G. J.

1977-01-01

Rb-Sr and Sm-Nd ages of two Apollo 11 mare basalts, high-K basalt 10072 and low-K basalt 10062, are reported. Rb-Sr, Sm-Nd, and Ar-40-Ar-39 ages are in good agreement and indicate an extensive time interval for filling of the Sea of Tranquility, presumably by thin lava flows, in agreement with similar observations for the Ocean of Storms. Initial Sr and Nd isotopic compositions on Apollo 11 basalts reveal at least two parent sources producing basalts. The Sm-Nd isotopic data demonstrate that low-K and high-Ti basalts from Apollo 11 and 17 derived from distinct reservoirs, while low-Ti Apollo 15 mare basalt sources have Sm/Nd similar to the sources of Apollo 11 basalts. Groupings of mare basalt based on Ti content and on isotopic data do not coincide.

Exploiting Secondary Sources for Unsupervised Record Linkage

DTIC Science & Technology

2004-01-01

paper, we present an extension to Apollo’s active learning component to Report Documentation Page Form ApprovedOMB No. 0704-0188 Public reporting...Sources address the issue of user involvement. Using secondary sources, a system can autonomously answer questions posed by its active learning component...over, we present how Apollo utilizes the identified sec- ondary sources in an unsupervised active learning pro- cess. Apollo’s learning algorithm

Mobility performance of the lunar roving vehicle: Terrestrial studies: Apollo 15 results

NASA Technical Reports Server (NTRS)

Costes, N. C.; Farmer, J. E.; George, E. B.

1972-01-01

The constriants of the Apollo 15 mission dictated that the average and limiting performance capabilities of the first manned lunar roving vehicle be known or estimated within narrow margins. Extensive studies were conducted and are compared with the actual performance of the lunar roving vehicle during the Apollo 15 mission. From this comparison, conclusions are drawn relating to the capabilities and limitation of current terrestrial methodology in predicting the mobility performance of lunar roving vehicles under in-situ environmental conditions, and recommendations are offered concerning the performance of surface vehicles on future missions related to lunar or planetary exploration.

ALSEP termination report

NASA Technical Reports Server (NTRS)

Bates, J. R.; Lauderdale, W. W.; Kernaghan, H.

1979-01-01

The Apollo Lunar Surface Experiments Package (ALSEP) final report was prepared when support operations were terminated September 30, 1977, and NASA discontinued the receiving and processing of scientific data transmitted from equipment deployed on the lunar surface. The ALSEP experiments (Apollo 11 to Apollo 17) are described and pertinent operational history is given for each experiment. The ALSEP data processing and distribution are described together with an extensive discussion on archiving. Engineering closeout tests and results are given, and the status and configuration of the experiments at termination are documented. Significant science findings are summarized by selected investigators. Significant operational data and recommendations are also included.

ASCANS Saturn V & LCC Tour

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – NASA astronaut candidates Anne McClain, from left, Andrew Morgan, Nicole Mann, Victor Glover, Christina Hammock and Josh Cassada observe the Apollo 14 command module which carried astronauts Alan Shepard, Stu Roosa and Edgar Mitchell on their lunar landing mission in 1971.The astronauts toured the Apollo Saturn V Center at Kennedy Space Center in Florida during a daylong set of briefings and tours of different facilities at NASA's primary launch center. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Kim Shiflett

KSC-2011-5964

NASA Image and Video Library

2011-07-25

CAPE CANAVERAL, Fla. -- The Apollo/Saturn V Center at NASA's Kennedy Space Center in Florida hosted a celebration on the 40th anniversary of NASA's Apollo 15 mission. Apollo 15 Commander Dave Scott and Command Module Pilot Al Worden and an elite gathering of Apollo-era astronauts were on hand for the event and panel discussion. Here, Al Worden with microphone in hand, speaks to the invited guests. Worden circled the moon while Scott and the late Jim Irwin, the Lunar Module commander, made history when they became the first humans to drive a vehicle on the surface of the moon. They also provided extensive descriptions and photographic documentation of geologic features in the vicinity of the Hadley Rille landing site during their three days on the lunar surface. Photo credit: NASA/Kim Shiflett

CSM digital autopilot testing in support of ASTP experiments control requirements

NASA Technical Reports Server (NTRS)

Rue, D. L.

1975-01-01

Results are presented of CSM digital autopilot (DAP) testing. The testing was performed to demonstrate and evaluate control modes which are currently planned or could be considered for use in support of experiments on the ASTP mission. The testing was performed on the Lockheed Guidance, Navigation, and Control System Functional Simulator (GNCFS). This simulator, which was designed to test the Apollo and Skylab DAP control system, has been used extensively and is a proven tool for CSM DAP analysis.

R&D 100 Awards | NREL

Science.gov Websites

a cost of about $.50/watt. Learn more HP Apollo 8000 System HP Apollo 8000 System Uses component Award - HP Apollo 8000 System - Steve Hammond and Team 2008 Editor's Choice Award - Hybrid CIGS (copper

Apollo experience report: Television system

NASA Technical Reports Server (NTRS)

Coan, P. P.

1973-01-01

The progress of the Apollo television systems from the early definition of requirements through the development and inflight use of color television hardware is presented. Television systems that have been used during the Apollo Program are discussed, beginning with a description of the specifications for each system. The document describes the technical approach taken for the development of each system and discusses the prototype and engineering hardware built to test the system itself and to perform the testing to verify compatibility with the spacecraft systems. Problems that occurred during the design and development phase are described. Finally, the flight hardware, operational characteristics, and performance during several Apollo missions are described, and specific recommendations for the remaining Apollo flights and future space missions are made.

Flight feeding systems design and evaluation. [the Apollo inflight menu design

NASA Technical Reports Server (NTRS)

Huber, C. S.

1973-01-01

The Apollo flight menu design is fully recounted for Apollo missions 7 through 17, to show modifications that were introduced to the Apollo food system, to document the range of menus and nutritional quality, and to describe packaging and preparation procedures for each class of food item. Papers concerning the Apollo 14 food system, and nutrition systems for pressure suits are included, and the following special topics are treated in depth: (1) food handling procedures; (2) modification of the physical properties of freeze dried rice; (3) stabilization of aerospace food waste; and (4) identification and quantitation of hexadecanal and octadecanal in broiler muscle phospholipids.

Large-Print Computers: An Evaluation of Their Features.

ERIC Educational Resources Information Center

Morrissette, Diane L.

1984-01-01

Three large-print computers for visually handicapped users are evaluated: the Apollo Computer Terminal System, Viewscan Text System, and Visualtek Large Print Display Processor. The Apollo Professional Typing System, an option with the Apollo Terminal System, is also reviewed. Advantages and disadvantages are explored. (Author/CL)

Precision Selenodesy via Differential Very-Long-Baseline Interferometry. Ph.D. Thesis; [Apollo lunar surface experiments package

NASA Technical Reports Server (NTRS)

King, R. W., Jr.

1975-01-01

The technique of differential very-long baseline interferometry was used to measure the relative positions of the ALSEP transmitters at the Apollo 12, 14, 15, 16, and 17 lunar landing sites with uncertainties less than 0.005 of geocentric arc. These measurements yielded improved determinations of the selenodetic coordinates of the Apollo landing sites, and of the physical libration of the moon. By means of a new device, the differential Doppler receiver (DDR), instrumental errors were reduced to less than the equivalent of 0.001. DDRs were installed in six stations of the NASA spaceflight tracking and data network and used in an extensive program of observations beginning in March 1973.

Significant results from Apollo 14 lunar orbital photography.

NASA Technical Reports Server (NTRS)

El-Baz, F.; Roosa, S. A.

1972-01-01

Apollo 14 obtained 950 photographs from lunar orbit using the Hasselblad and Hycon cameras. The photographs reveal a number of new geologic features as well as previously unrecognized details of the morphology, structure, and stratigraphy of lunar surface units. The primary result is the verification of the extensive role of volcanism in the formation and modification of the lunar highlands, especially on the far side. Terra volcanism appears to be manifest in the formation of (1) constructional units of hilly and furrowed materials of regional extent as in the Kant Plateau in the central near-side highlands and northwest of the crater Pasteur near the eastern limb of the moon; (2) somewhat viscous lava flows and pools associated with fracture systems and/or what appear to be volcanic craters; (3) craters, crater chains, and irregular depressions, particularly on the lunar far side. The first photographs of a flow channel, a leveed sinuous rille that apparently originated by lava flowage on the surface, were obtained by Apollo 14. Another first is a high-resolution photograph of the interior of what appears to be the youngest lunar crater yet photographed in the 20- 40-km size range.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned Program manager, welcomes participants to the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo Telescope Mount (ATM) gimballed star tracker. [developed for the Skylab program

NASA Technical Reports Server (NTRS)

Lana, J. D.

1974-01-01

Design and development of six gimballed star trackers for Skylab's Apollo Telescope Mount, which performed successfully on all three manned Skylab missions and accumulated a total usage time of approximately 3,500 hours, is described in terms of configurations, materials and construction, qualification testing, performance, and reliability characteristics. A brief program history and design changes incorporated during the life of the program are also discussed. Extensive drawings, block diagrams, and photographs are provided.

Apollo experience report: Guidance and control systems. Mission control programmer for unmanned missions AS-202, Apollo 4, and Apollo 6

NASA Technical Reports Server (NTRS)

Holloway, G. F.

1975-01-01

An unmanned test flight program required to evaluate the command module heat shield and the structural integrity of the command and service module/Saturn launch vehicle is described. The mission control programer was developed to provide the unmanned interface between the guidance and navigation computer and the other spacecraft systems for mission event sequencing and real-time ground control during missions AS-202, Apollo 4, and Apollo 6. The development of this unmanned programer is traced from the initial concept through the flight test phase. Detailed discussions of hardware development problems are given with the resulting solutions. The mission control programer functioned correctly without any flight anomalies for all missions. The Apollo 4 mission control programer was reused for the Apollo 6 flight, thus being one of the first subsystems to be reflown on an Apollo space flight.

Apollo 8 Astronaut Anders Suits Up For Countdown Demonstration Test

NASA Technical Reports Server (NTRS)

1968-01-01

Apollo 8 astronaut William Anders, Lunar Module (LM) pilot, is suited up for the Apollo 8 mission countdown demonstration test. The first manned Apollo mission launched aboard the Saturn V and first manned Apollo craft to enter lunar orbit, the SA-503, Apollo 8 mission lift off occurred on December 21, 1968 and returned safely to Earth on December 27, 1968. Aboard were Anders and fellow astronauts James Lovell, Command Module (CM) pilot; and Frank Borman, commander. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team, speaks to participants during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Other guest panelists included Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Orbital evolution studies of planet-crossing asteroids

NASA Astrophysics Data System (ADS)

Hahn, Gerhard; Lagerkvist, Claes-Ingvar

The orbits of 26 planet-crossing Aten-Apollo-Amor asteroids are predicted on the basis of numerical integrations covering 33,000 or 100,000 yrs; the values reported supplement the preliminary findings of Hahn and Lagerkvist (1987). A solar-system dynamics model accounting for the effects of all planets from Venus to Neptune is employed, along with the 15th-order integration algorithm RADAU (Everhart, 1985). The results are presented in extensive tables and graphs and discussed in detail.

Impacting Innovation and Commercialization: NREL's Partnering Facilities

Science.gov Websites

Apollo 8000 System based on the ESIF's Peregrine supercomputer. The system uses component-level warm advantage." "NREL is the partner we needed and wanted for the first-born in the Apollo family ," said Nic Dubé, Peregrine's system architect and HP's technical lead for Apollo. "From the

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Kennedy Space Center Director Bob Cabana welcomes participants to the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

ART CONCEPTS - APOLLO IX

NASA Image and Video Library

1969-02-20

S69-19794 (February 1969) --- Composite of two artist's concepts illustrating key events, tasks and activities on the third day of the Apollo 9 mission, including crew transfer and Lunar Module system evaluation. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

Apollo experience report: Problem reporting and corrective action system

NASA Technical Reports Server (NTRS)

Adams, T. J.

1974-01-01

The Apollo spacecraft Problem Reporting and Corrective Action System is presented. The evolution from the early system to the present day system is described. The deficiencies and the actions taken to correct them are noted, as are management controls for both the contractor and NASA. Significant experience gained from the Apollo Problem Reporting and Corrective Action System that may be applicable to future manned spacecraft is presented.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned Program manager, far right, is pictured with panelists from the Apollo 1 Lessons Learned event in the Training Auditorium at NASA's Kennedy Space Center in Florida. In the center, are Ernie Reyes, retired, former Apollo 1 senior operations manager; and John Tribe, retired, former Apollo 1 Reaction and Control System lead engineer. At far left is Zulie Cipo, the Apollo, Challenger, Columbia Lessons Learned Program event support team lead. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Suzy Cunningham, with the Communication and Public Engagement Directorate, sings the National Anthem before the start of the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The program's theme was "To There and Back Again." Guest panelists included Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team; Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

A model for calculating expected performance of the Apollo unified S-band (USB) communication system

NASA Technical Reports Server (NTRS)

Schroeder, N. W.

1971-01-01

A model for calculating the expected performance of the Apollo unified S-band (USB) communication system is presented. The general organization of the Apollo USB is described. The mathematical model is reviewed and the computer program for implementation of the calculations is included.

Apollo food technology

NASA Technical Reports Server (NTRS)

Smith, M. C., Jr.; Heidelbaugh, N. D.; Rambaut, P. C.; Rapp, R. M.; Wheeler, H. O.; Huber, C. S.; Bourland, C. T.

1975-01-01

Large improvements and advances in space food systems achieved during the Apollo food program are discussed. Modifications of the Apollo food system were directed primarily toward improving delivery of adequate nutrition to the astronaut. Individual food items and flight menus were modified as nutritional countermeasures to the effects of weightlessness. Unique food items were developed, including some that provided nutritional completeness, high acceptability, and ready-to-eat, shelf-stable convenience. Specialized food packages were also developed. The Apollo program experience clearly showed that future space food systems will require well-directed efforts to achieve the optimum potential of food systems in support of the physiological and psychological well-being of astronauts and crews.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, at left, the Apollo, Challenger, Columbia Lessons Learned Program manager, presents a certificate to John Tribe, retired, Apollo 1 Reaction and Control System lead engineer, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Remembering Apollo 11: The 30th Anniversary Data Archive CD-ROM

NASA Technical Reports Server (NTRS)

Cortright, Edgar M. (Editor)

1999-01-01

On July 20, 1969, the human race accomplished its single greatest technological achievement of all time when a human first set foot on another celestial body. Six hours after landing at 4:17 p.m. Eastern Standard Time (with less than thirty seconds of fuel remaining), Neil A. Armstrong took the "small step" into our greater future when he stepped off the Lunar Module, named Eagle, onto the surface of the Moon, from which he could look up and see Earth in the heavens as no one had done before him. He was shortly joined by Edwin "Buzz" Aldrin, and the two astronauts spent twenty-one hours on the lunar surface and returned forty-six pounds of lunar rocks. After their historic walks on the Moon, they successfully docked with Michael Collins, patiently orbiting the cold but no longer lifeless Moon alone in the Command module Columbia. This CR-ROM is intended as a collection of hard to find technical data and other interesting information about the Apollo 11 mission, as well as the apollo program in general. It includes basic overviews, such as a retrospective analysis, an annotated bibliography, and history of the lunar-orbit rendezvous concept. It also contains technical data, such as mission operations reports, press kits, and news references for all of the Apollo missions, the Apollo spacecraft, and the Saturn V launch vehicle. Rounding out this CD-ROM are extensive histories of the lunar Orbiter program (the robotic predecessor to Apollo, biographies of the Apollo astronauts and other key individuals, and interesting audio-visual materials, such as video and audio clips, photo galleries, and blueprint-like diagrams of the Apollo spacecraft.

Complex Indigenous Organic Matter Embedded in Apollo 17 Volcanic Black Glass Surface Deposits

NASA Technical Reports Server (NTRS)

Thomas-Keprta, Kathie L.; Clemett, S. J.; Ross, D. K.; Le, L.; Rahman, Z.; Gonzalez, C.; McKay, D. S.; Gibson, E. K.

2013-01-01

Papers presented at the first Lunar Science Conference [1] and those published in the subsequent Science Moon Issue [2] reported the C content of Apollo II soils, breccias, and igneous rocks as rang-ing from approx.50 to 250 parts per million (ppm). Later Fegley & Swindle [3] summarized the C content of bulk soils from all the Apollo missions as ranging from 2.5 (Apollo 15) to 280 ppm (Apollo 16) with an overall average of 124+/- 45 ppm. These values are unexpectedly low given that multiple processes should have contributed (and in some cases continue to contribute) to the lunar C inventory. These include exogenous accretion of cometary and asteroidal dust, solar wind implantation, and synthesis of C-bearing species during early lunar volcanism. We estimate the contribution of C from exogenous sources alone is approx.500 ppm, which is approx.4x greater than the reported average. While the assessm ent of indigenous organic matter (OM) in returned lunar samples was one of the primary scientific goals of the Apollo program, extensive analysis of Apollo samples yielded no evidence of any significant indigenous organic species. Furthermore, with such low concentrations of OM reported, the importance of discriminating indigenous OM from terrestrial contamination (e.g., lunar module exhaust, sample processing and handling) became a formidable task. After more than 40 years, with the exception of CH4 [5-7], the presence of indigenous lunar organics still remains a subject of considerable debate. We report for the first time the identification of arguably indigenous OM present within surface deposits of black glass grains collected on the rim of Shorty crater during the Apollo 17 mission by astronauts Eugene Cernan and Harrison Schmitt.

Geology of Lunar Landing Sites and Origin of Basin Ejecta from a Clementine Perspective

NASA Technical Reports Server (NTRS)

Jolliff, Bradley L.; Haskin, Larry A.

1998-01-01

The goals of this research were to examine Clementine multispectral data covering the Apollo landing sites in order to: (1) provide ground truth for the remotely sensed observations, (2) extend our understanding of the Apollo landing sites to the surrounding regions using the empirically calibrated Clementine data, and (3) investigate the composition and distribution of impact-basin ejecta using constraints based upon the remotely sensed data and the Apollo samples. Our initial efforts (in collaboration with P. Lucey and coworkers) to use the Apollo soil compositions to "calibrate" information derived from the remotely sensed data resulted in two extremely useful algorithms for computing estimates of the concentrations of FeO and TiO2 from the UV-VIS 5-band data. In this effort, we used the average surface soil compositions from 37 individual Apollo and 3 Luna sample stations that could be resolved using the Clementine data. We followed this work with a detailed investigation of the Apollo 17 landing site, where the sampling traverses were extensive and the spectral and compositional contrast between different soils covers a wide range. We have begun to investigate the nature and composition of basin ejecta by comparing the thick deposits on the rim of Imbrium in the vicinity of the Apollo 15 site and those occurring southeast of the Serenitatis basin, in the Apollo 17 region. We continue this work under NAG5-6784, "Composition, Lithology, and Heterogeneity of the lunar crust using remote sensing of impact-basin uplift structures and ejecta as probes. The main results of our work are given in the following brief summaries of major tasks. Detailed accounts of these results are given in the attached papers, manuscripts, and extended abstracts.

Apollo experience report: Protection against radiation

NASA Technical Reports Server (NTRS)

English, R. A.; Benson, R. E.; Bailey, J. V.; Barnes, C. M.

1973-01-01

Radiation protection problems on earth and in space are discussed. Flight through the Van Allen belts and into space beyond the geomagnetic shielding was recognized as hazardous before the advent of manned space flight. Specialized dosimetry systems were developed for use on the Apollo spacecraft, and systems for solar-particle-event warning and dose projection were devised. Radiation sources of manmade origin on board the Apollo spacecraft present additional problems. Methods applied to evaluate and control or avoid the various Apollo radiation hazards are discussed.

Apollo experience report: S-band system signal design and analysis

NASA Technical Reports Server (NTRS)

Rosenberg, H. R. (Editor)

1972-01-01

A description is given of the Apollo communications-system engineering-analysis effort that ensured the adequacy, performance, and interface compatibility of the unified S-band system elements for a successful lunar-landing mission. The evolution and conceptual design of the unified S-band system are briefly reviewed from a historical viewpoint. A comprehensive discussion of the unified S-band elements includes the salient design features of the system and serves as a basis for a better understanding of the design decisions and analyses. The significant design decisions concerning the Apollo communications-system signal design are discussed providing an insight into the role of systems analysis in arriving at the current configuration of the Apollo communications system. Analyses are presented concerning performance estimation (mathematical-model development through real-time mission support) and system deficiencies, modifications, and improvements.

A study of the role of pyrotechnic systems on the space shuttle program

NASA Technical Reports Server (NTRS)

Lake, E. R.; Thompson, S. J.; Drexelius, V. W.

1973-01-01

Pyrotechnic systems, high burn rate propellant and explosive-actuated mechanisms, have been used extensively in aerospace vehicles to perform a variety of work functions, including crew escape, staging, deployment and destruction. Pyrotechnic system principles are described in this report along with their applications on typical military fighter aircraft, Mercury, Gemini, Apollo, and a representative unmanned spacecraft. To consider the possible pyrotechnic applications on the space shuttle the mechanical functions on a large commercial aircraft, similar in scale to the shuttle orbiter, were reviewed. Many potential applications exist for pyrotechnic system on the space shuttle, both in conventional short-duration functions and in longer duration and/or repetitive type gas generators.

MIT's role in project Apollo. Volume 2: Optical, radar, and candidate subsystems

NASA Technical Reports Server (NTRS)

1972-01-01

The development of optical, radar, and candidate subsystems for Project Apollo is discussed. The design and development of the optical subsystems for both the Apollo command and lunar spacecraft are described. Design approaches, problems, and solutions are presented. The evolution of radar interfaces with the GN&C system is discussed; these interfaces involved both hardware and software in a relatively complex interrelationship. The design and development of three candidate subsystems are also described. The systems were considered for use in Apollo, but were not incorporated into the final GN&C system. The three subsystems discussed are the star tracker-horizon photometer, the map and data viewer and the lunar module optical rendezvous system.

Saturn Apollo Program

NASA Image and Video Library

1976-06-01

This illustration depicts the launch configuration of the Apollo spacecraft for the Apollo-Soyuz Test Project (ASTP). The ASTP was the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. A joint engineering team from the two countries met to develop a docking system that permitted the two spacecraft to link in space and allowed the two crews to travel from one spacecraft to the other. This system entailed developing a large habitable Docking Module (DM) to be carried on the Apollo spacecraft to facilitate the joining of two dissimilar spacecraft. The Marshall Space Flight Center was responsible for development and sustaining engineering of the Saturn IB launch vehicle during the mission.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

John Tribe, retired, Apollo 1 Reaction and Control System lead engineer, answers questions during the Apollo 1 Lessons Learned event in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The theme of the presentation was "To There and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Saturn Apollo Program

NASA Image and Video Library

1968-01-22

The Saturn IB launch vehicle (SA204) for the Apollo 5 mission lifted off on January 22, 1968. The unmarned Apollo 5 mission verified the ascent and descent stage propulsion systems, including restart and throttle operations of the Lunar Module.

Apollo experience report: Real-time auxiliary computing facility development

NASA Technical Reports Server (NTRS)

Allday, C. E.

1972-01-01

The Apollo real time auxiliary computing function and facility were an extension of the facility used during the Gemini Program. The facility was expanded to include support of all areas of flight control, and computer programs were developed for mission and mission-simulation support. The scope of the function was expanded to include prime mission support functions in addition to engineering evaluations, and the facility became a mandatory mission support facility. The facility functioned as a full scale mission support activity until after the first manned lunar landing mission. After the Apollo 11 mission, the function and facility gradually reverted to a nonmandatory, offline, on-call operation because the real time program flexibility was increased and verified sufficiently to eliminate the need for redundant computations. The evaluation of the facility and function and recommendations for future programs are discussed in this report.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

NASA Kennedy Space Center Director Bob Cabana, at left, moderates a panel discussion during the Apollo 1 Lessons Learned event in the Training Auditorium at NASA’s Kennedy Space Center in Florida. The theme of the presentation was "To There and Back Again." Answering questions are Ernie Reyes, retired, Apollo 1 senior operations engineer; and John Tribe, retired, Apollo 1 Reaction and Control System lead engineer. The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Apollo/Saturn 5 consolidated instrumentation plan for AS-511 (Apollo 16)

NASA Technical Reports Server (NTRS)

Clark, D. E.

1972-01-01

The consolidated instrumentation plan, for employing optical and electronic data acquisition systems to monitor the performance and trajectory of Apollo Saturn 5 vehicle 511 during the launch phase of the mission (prelaunch, liftoff to insertion), is presented. Telemetry, optical, and electronic tracking equipment on board the vehicle and data acquisition systems monitoring the flight are discussed. Flight safety instrumentation, vehicle data transmission systems, and geophysical instrumentation are also described.

Flight feeding systems design and evaluation. Supplement 1: Production guides. [for the Apollo food system

NASA Technical Reports Server (NTRS)

1973-01-01

The requirements for processing, packaging, testing, and shipment of foods selected for use in the Apollo food system are presented. Specific foodstuffs chosen from the following categories are discussed: (1) soups; (2) juices; (3) breads; (4) meat and poultry products; (5) fruits and nuts; (6) desserts; and (7) beverages. Food procurement for the mobile quarantine facility and for Apollo preflight and postflight activities is also discussed.

ART CONCEPTS - APOLLO IX

NASA Image and Video Library

1969-02-20

S69-19796 (February 1969) --- Composite of six artist's concepts illustrating key events, tasks and activities on the fifth day of the Apollo 9 mission, including vehicles undocked, Lunar Module burns for rendezvous, maximum separation, ascent propulsion system burn, formation flying and docking, and Lunar Module jettison ascent burn. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

Lunar highlands volcanism implications from Luna 20 and Apollo 16

USGS Publications Warehouse

Wilshire, H.G.; Wilhelms, D.E.; Howard, K.A.

1974-01-01

Highlands materials sampled at the Apollo 16 and Luna 20 sites represent units of distinctive morphology that are widespread on the lunar nearside. Samples from the Apollo 16 site represent hilly and furrowed materials of the Descartes highlands and Cayley Formation. Materials were collected by Luna 20 from terrain resembling the Descartes terrain. Most photogeologic interpretations of these units favored volcanic origins, but the samples fail to support this interpretation. Luna 20 soil fragments are mainly glassy microbreccia with lithic inclusions of fine-grained hornfels; less than 3 percent of the fragments have textures of volcanic rocks, and most of these are likely crystalline products of impact melting. Apollo 16 soils formed on ejecta derived from a plutonic anorthosite-norite-troctolite suite. The similarity of Luna 20 soils indicates that these too formed as regolith on ejecta of anorthosite-norite-troctolitc composition. Interpretation of the samples from the two locations now suggests that hilly and furrowed terrains, previously thought to be of volcanic origin, are impact ejecta; in view of the plutonic nature of the source rocks and their extensive fusion and metamorphism, it is likely that the ejecta were derived from multiring basins. At one point, the Apollo 16 site, the Cayley Formation is composed of basin ejecta.

Regional chemical setting of the Apollo 16 landing site and the importance of the Kant Plateau

NASA Technical Reports Server (NTRS)

Andre, C. G.; El-Baz, F.

1982-01-01

Orbital X-ray data from the Apollo 16 region indicate that physiographic units identified before the lunar mission can be classified as chemical units as well. The Descartes Mountains, however, appear to be an extension of the Kant Plateau composition that is unusually anorthositic and resembles farside terra. The Cayley Plains have closer affinities to basaltic materials than terra materials, physically, spectrally and chemically. The Theophilus impact, 330 km east of the landing site, excavated magnesium-rich basalts from below less-magnesian flows in Mare Nectaris; but, mafic ejecta was substantially blocked from the Apollo 16 site by the Kant Plateau that rises 5 km above the level of the mare. Apollo 16 soil samples from stations selected to collect either Descartes Mountains material or Cayley Plains material were surprisingly similar. However, they do, indeed, show the chemical trends indicative of the two units as defined by the orbiting geochemistry detectors. The Kant Plateau and Descartes Mountains material may be among the rare nearside examples of a plagioclase-rich cumulate of the primordial magma ocean.

Particle Ejection and Levitation Technology (PELT)

NASA Technical Reports Server (NTRS)

2008-01-01

Each of the six Apollo landers touched down at unique sites on the lunar surface. Aside from the Apollo 12 landing site located 180 meters from the Surveyor III lander, plume impingement effects on ground hardware during the landings were not a problem. The planned return to the Moon requires numerous landings at the same site. Since the top few centimeters of lunar soil are loosely packed regolith, plume impingement from the lander will eject the granular material at high velocities. A picture shows what the astronauts viewed from the window of the Apollo 14 lander. There was tremendous dust excavation beneath the vehicle. With high-vacuum conditions on the Moon (10 (exp -14) to 10 (exp -12) torr), motion of all particles is completely ballistic. Estimates derived from damage to Surveyor III caused by the Apollo 12 lander show that the speed of the ejected regolith particles varies from 100 m/s to 2,000 m/s. It is imperative to understand the physics of plume impingement to safely design landing sites for future Moon missions. Aerospace scientists and engineers have examined and analyzed images from Apollo video extensively in an effort to determine the theoretical effects of rocket exhaust impingement. KSC has joined the University of Central Florida (UCF) to develop an instrument that will measure the 3-D vector of dust flow caused by plume impingement during descent of landers. The data collected from the instrument will augment the theoretical studies and analysis of the Apollo videos.

Apollo 9 Mission image - Earth Observation - Anticyclonic cloud pattern

NASA Image and Video Library

1969-03-03

AS09-23-3592 (3-13 March 1969) --- Cyclonic storm system, located 1,200 miles north of Hawaii, as photographed from the Apollo 9 spacecraft during its 10-day, Earth-orbital space mission. This picture was made on the 124th revolution of Apollo 9. This cyclonic storm system can also be seen in the ESSA-7 photograph taken on March 11, 1969.

Performance analysis of the ascent propulsion system of the Apollo spacecraft

NASA Technical Reports Server (NTRS)

Hooper, J. C., III

1973-01-01

Activities involved in the performance analysis of the Apollo lunar module ascent propulsion system are discussed. A description of the ascent propulsion system, including hardware, instrumentation, and system characteristics, is included. The methods used to predict the inflight performance and to establish performance uncertainties of the ascent propulsion system are discussed. The techniques of processing the telemetered flight data and performing postflight performance reconstruction to determine actual inflight performance are discussed. Problems that have been encountered and results from the analysis of the ascent propulsion system performance during the Apollo 9, 10, and 11 missions are presented.

Apollo experience report: Command and service module environmental control system

NASA Technical Reports Server (NTRS)

Samonski, F. H., Jr.; Tucker, E. M.

1972-01-01

A comprehensive review is presented of the design philosophy of the Apollo environmental control system together with the development history of the total system and of selected components within the system. In particular, discussions are presented relative to the development history and to the problems associated with the equipment cooling coldplates, the evaporator and its electronic control system, and the space radiator system used for rejection of the spacecraft thermal loads. Apollo flight experience and operational difficulties associated with the spacecraft water system and the waste management system are discussed in detail to provide definition of the problem and the corrective action taken when applicable.

Apollo 7 - Press Kit

NASA Technical Reports Server (NTRS)

1968-01-01

Contents include the following: General release. Mission objectives. Mission description. Flight plan. Alternate missions. Experiments. Abort model. Spacecraft structure system. The Saturn 1B launch vehicle. Flight sequence. Launch preparations. Mission control center-Houston. Manned space flight network. Photographic equipment. Apollo 7 crew. Apollo 7 test program.

Apollo Lunar Module Electrical Power System Overview

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

Objectives include: a) Describe LM Electrical System original specifications; b) Describe the decision to change from fuel cells to batteries and other changes; c) Describe the Electrical system; and d) Describe the Apollo 13 failure from the LM perspective.

Cosmonaut Aleksey Leonov briefed on Apollo Communications test system console

NASA Image and Video Library

1974-04-23

S74-20807 (23 April 1974) --- Cosmonaut Aleksey A. Leonov (foreground) is briefed on the Apollo communications test system console in the Building 440 laboratory during the joint U.S.-USSR Apollo-Soyuz Test Project training activity at the Johnson Space Center. Leonov is the commander of the Soviet ASTP crew. Leonov is being briefed by astronaut Thomas P. Stafford, commander of the American ASTP crew.

Space food systems - Mercury through Apollo.

NASA Technical Reports Server (NTRS)

Roth, N. G.; Smith, M. C.

1972-01-01

Major achievements which characterized the development of food systems used by American astronauts in manned space flight are reviewed throughout a period spanning the Mercury, Gemini, and Apollo programs up to and including the Apollo 11 lunar landing mission. Lists of food types are accompanied by information on packaging, storage, preparation, consumption, and quality of particular products. Experience gained from development efforts for the Manned Orbiting Laboratory Program is also discussed.

The Apollo Lightcraft Project

NASA Technical Reports Server (NTRS)

1988-01-01

The overall goal for this NASA/USRA-sponsored 'Apollo Lightcraft Project' is to develop a revolutionary launch vehicle technology that can reduce payload transport costs by a factor of 1000 below the Space Shuttle Orbiter. The RPI design team proposes to utilize advanced, highly energetic, beamed-energy sources (laser, microwave) and innovative combined-cycle (airbreathing/rocket) engines to accomplish this goal. This second year focused on systems integration and analysis of the 'Apollo Lightcraft'. This beam-powered, single-stage-to-orbit vehicle is envisioned as the globe-trotting family shuttlecraft of the 21st century. Detailed investigations of the Apollo Lightcraft Project during the second year of study helped evolve the propulsion system design, while focusing on the following areas: (1) man/machine interface; (2) flight control systems; (3) power beaming system architecture; (4) reentry aerodynamics; (5) shroud structural dynamics; and (6) optimal trajectory analysis.

An Apollo 15 Mare Basalt Fragment and Lunar Mare Provinces

NASA Technical Reports Server (NTRS)

Ryder, Graham; Burling, Trina Cox

1996-01-01

Lunar sample 15474,4 is a tiny fragment of olivine-augite vitrophyre that is a mare basalt. Although petroraphically distinct from all other Apollo 15 samples, it has been ignored since its first brief description. Our new petrographic and mineral chemical data show that the olivines and pyroxenes are distinct from those in other basalts. The basalt cooled and solidified extremely rapidly; some of the olivine might be cumulate or crystallized prior to extrusion. Bulk-chemical data show that the sample is probably similar to an evolved Apollo 15 olivine-normative basalt in major elements but is distinct in its rare earth element pattern. Its chemical composition and petrography both show that 15474,4 cannot be derived from other Apollo 15 mare basalts by shallow-level crystal fractionation. It represents a distinct extrusion of magma. Nonetheless, the chemical features that 15474,4 has in common with other Apollo 15 mare basalts, including the high FeO/Sc, the general similarity of the rare earth element pattern, and the common (and chondritic) TiO2/Sm ratio, emphasize the concept of a geochemical province at the Apollo 15 site that is distinct from basalts and provinces elsewhere. In making a consistent picture for the derivation of all of the Apollo 15 basalts, both the commonalities and the differences among the basalts must be explained. The Apollo 15 commonalities and differences suggest that the sources must have consisted of major silicate phases with the same composition but with varied amounts of a magma trapped from a contemporary magma ocean. They probably had a high olivine/pyroxene ratio and underwent small and reasonably consistent degrees of partial melting to produce the basalts. These inferences may be inconsistent with models that suggest greatly different depths of melting among basalts, primitive sources for the green glasses, or extensive olivine fractionation during ascent. An integrated approach to lunar mare provinces, of which the Apollo 15 mare basalts constitute only one, offers advances in our understanding of the physical and chemical processes of source formation and mare production but has so far not been utilized.

Apollo experience report: Power generation system

NASA Technical Reports Server (NTRS)

Bell, D., III; Plauche, F. M.

1973-01-01

A comprehensive review of the design philosophy and experience of the Apollo electrical power generation system is presented. The review of the system covers a period of 8 years, from conception through the Apollo 12 lunar-landing mission. The program progressed from the definition phase to hardware design, system development and qualification, and, ultimately, to the flight phase. Several problems were encountered; however, a technology evolved that enabled resolution of the problems and resulted in a fully manrated power generation system. These problems are defined and examined, and the corrective action taken is discussed. Several recommendations are made to preclude similar occurrences and to provide a more reliable fuel-cell power system.

Saturn Apollo Program

NASA Image and Video Library

1968-01-01

AS-204, the fourth Saturn IB launch vehicle, developed by the Marshall Space Flight Center (MSFC), awaits its January 22, 1968 liftoff from Cape Canaveral, Florida for the unmarned Apollo 5 mission. Primary mission objectives included the verification of the Apollo Lunar Module's (LM) ascent and descent propulsion systems and an evaluation of the S-IVB stage instrument unit performance. In all, nine Saturn IB flights were made, ending with the Apollo-Soyuz Test Project in July 1975.

Flame Retardant Fibers for Human Space Exploration - Past, Present, and Future

NASA Technical Reports Server (NTRS)

Orndoff, Evelyne

2017-01-01

The National Aeronautics and Space Administration (NASA) has led in the development of unique flame retardant fibers for human spaceflight since the beginning of the Apollo program. After the Apollo 1 fire which killed Command Pilot Virgil I 'Gus' Grissom, Senior Pilot Edward H. White II, and Pilot Roger B. Chaffee from cardiac arrest on January 27, 1967, the accident investigators found severe third degree burns and melted spacesuits on the astronauts bodies. NASA immediately initiated an extensive research program aimed at developing flame retardant and flame resistant fibers for the enriched oxygen atmosphere of the Apollo crew cabin. Fibers are flame retardant when they have been modified by chemical and thermal treatments. Fibers are flame resistant when they are made of inherently flame resistant materials (i.e. glass, ceramic, highly aromatic polymers). Immediately after this tragic accident, NASA funded extensive research in specifically developing flame retardant fibers and fabrics. The early developmental efforts for human spaceflight were for the outer layer of the Apollo spacesuit. It was imperative that non-flammable fabrics be used in a 100% oxygen environment. Owens-Corning thus developed the Beta fiber that was immediately used in the Apollo program and later in the Space Shuttle program. Aside from the urgent need for protective fabrics for the spacesuit, NASA also needed flame retardant fabrics for both clothing and equipment inside the spacecraft. From the mid-1960s to the early 1980's, NASA contracted with many companies to develop inherently flame retardant fibers and flame retardant finishes for existing fibers. Fluorocarbons and aromatic polyamides were the polymers of great interest for the development of new inherently flame retardant fibers for enriched oxygen environments. These enriched environments varied for different space programs. For example, the Apollo program requirements were for materials that would not support combustion in a 70%/30% oxygen/nitrogen environment at 6.3 pounds per square inch (psi). The Skylab program flammability requirements were set at 80%/20% oxygen/nitrogen ratios at 5 psi. While many fibers produced under several NASA contracts were never used, a few have become commercial products. The intent of this paper is to present the developmental history of some of these new or modified textile fibers. These developmental efforts are presented at various levels of details depending on the source of the historical records.

The Importance of Apollo to Solar-System Science and Future Human Exploration

NASA Astrophysics Data System (ADS)

Neal, C. R.; Shearer, C. K.

2012-12-01

December 14, 2012 marks 40 years since humans walked on the Moon, and the demise of the Apollo program. Apollo will be remembered for America's response to the President's ambitious plan to go to the Moon that was fueled by cold-war "competition". However, the importance of Apollo goes far beyond that because it represents an achievement that spacefaring nations, including the USA, still aspire to. This presentation focuses on the Apollo influence on our understanding of the Moon and the Solar-System, as well as future human exploration activities. Apollo gave 2 things that continue to yield surprises and (re)shape our thinking about the Moon: ALSEP data sets and the Apollo lunar sample collection. The ALSEPs gave us data on the radiation and dust environment, as the nature of the lunar interior, and how the Moon interacts with the solar wind and Earth's magnetotail. Many of ALSEP datasets are STILL not available in the Planetary Data System, but those that are yield surprises, such as the direct detection of the Moon's core from Apollo seismic data (Weber et al., 2011, Science 331, 309). This is now possible because of the more sophisticated computing systems that are available. Apollo samples have shown the unequivocal presence of indigenous lunar water (Saal et al., 2008, Nature 454, 192). ALSEP data, Apollo samples, and the Apollo experience itself are still critical in shaping human space exploration, and showing the knowledge gaps that need to be filled to facilitate long-term human lunar exploration and beyond. ALSEP data are the only data we have regarding dust activity on the lunar surface. This coupled with the Apollo astronaut experience shows that systems (e.g., space suits) need to be engineered differently if a permanent human lunar presence is ever to be established. Seismic data show the magnitude of some moonquakes exceed 5 on the Richter scale and the maximum ground movement lasts several minutes and takes over an hour to dissipate. Any habitat should not be constructed where such an epicenter could be located. In addition, there are lunar samples that have remained unopened since there were collected, which could inform us about the volatile content and potential toxicity of the lunar regolith, as well as the technologies needed to collect, preserve and return volatile-rich samples from many planetary environments. With regard to science, Apollo allowed an absolute chronology to be developed for the impact history of the inner Solar-System. This was achieved by the return of impact melts, but their recognition within the collection initially proved difficult and detection requires destruction of a large amount of precious sample. A new, non-destructive method for identifying impact melts is presented that demonstrates Apollo samples are "the gift that keeps on giving". This involves quantitative petrography through the determination of plagioclase crystal size distributions and the relationship between the slopes and population density intercepts. Data from a study of mare basalt and impact melt crystal size distributions over several years shows lunar impact melts are distinct from mare basalts. Such a non-destructive identification of impact melt is critical for a future sample return from South Pole-Aitken Basin where impact melt is required to date the impact basin and test the late heavy bombardment hypothesis.

ART CONCEPTS - APOLLO IX

NASA Image and Video Library

1969-02-20

S69-19798 (February 1969) --- Composite of three artist's concepts illustrating key events, tasks and activities on the tenth day of the Apollo 9 mission, including Command Module and Service Modules separation, re-entry, and Atlantic splashdown. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

Apollo 40th Anniversary History Panel

NASA Image and Video Library

2009-07-15

Cristina Guidi, deputy director, Constellation Systems Division, Exploration Systems Mission Directorate, NASA Headquarters, speaks during an Apollo History and Legacy roundtable discussion, Thursday, July 16, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Apollo experience report: Communications system flight evaluation and verification

NASA Technical Reports Server (NTRS)

Travis, D.; Royston, C. L., Jr.

1972-01-01

Flight tests of the synergetic operation of the spacecraft and earth based communications equipment were accomplished during Apollo missions AS-202 through Apollo 12. The primary goals of these tests were to verify that the communications system would adequately support lunar landing missions and to establish the inflight communications system performance characteristics. To attain these goals, a communications system flight verification and evaluation team was established. The concept of the team operations, the evolution of the evaluation processes, synopses of the team activities associated with each mission, and major conclusions and recommendations resulting from the performance evaluation are represented.

Apollo Command and Service Module Propulsion Systems Overview

NASA Technical Reports Server (NTRS)

Interbartolo, Michael A.

2009-01-01

An overview of the Apollo Command and Service Module (CSM) propulsion systems is provided. The systems for CSM propulsion and control are defined, the times during the mission when each system is used are listed, and, the basic components and operation of the service propulsion system, SM reaction control system and CM reaction control system are described.

KSC-04pd0611

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Like a dinosaur crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0611

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Like a dinosaur crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Multipurpose electric furnace system. [for use in Apollo-Soyuz Test Program

NASA Technical Reports Server (NTRS)

Mazelsky, R.; Duncan, C. S.; Seidensticker, R. G.; Johnson, R. A.; Mchugh, J. P.; Foust, H. C.; Piotrowski, P. A.

1974-01-01

A multipurpose electric furnace system of advanced design for space applications was developed and tested. This system is intended for use in the Apollo-Soyuz Test Program. It consists of the furnace, control package and a helium package for rapid cooldown.

Apollo 8 Commander Frank Borman Receives Presidential Call

NASA Technical Reports Server (NTRS)

1968-01-01

Apollo 8 Astronaut Frank Borman, commander of the first manned Saturn V space flight into Lunar orbit, accepted a phone call from the U.S. President Lyndon B. Johnson prior to launch. Borman, along with astronauts William Anders, Lunar Module (LM) pilot, and James Lovell, Command Module (CM) pilot, launched aboard the Apollo 8 mission on December 21, 1968 and returned safely to Earth on December 27, 1968. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

Apollo 8 Astronaut James Lovell On Phone With President Johnson

NASA Technical Reports Server (NTRS)

1968-01-01

Apollo 8 Astronaut James Lovell, Command Module (CM) pilot of the first manned Saturn V space flight into Lunar orbit, accepted a phone call from the U.S. President Lyndon B. Johnson prior to launch. Lovell, along with astronauts William Anders, Lunar Module (LM) pilot, and Frank Borman, commander, launched aboard the Apollo 8 mission on December 21, 1968 and returned safely to Earth on December 27, 1968. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

Apollo 8 Astronaut William Anders On Phone With President Johnson

NASA Technical Reports Server (NTRS)

1968-01-01

Apollo 8 Astronaut William Anders, Lunar Module (LM) pilot of the first manned Saturn V space flight into Lunar orbit, accepted a phone call from the U.S. President Lyndon B. Johnson prior to launch. Anders, along with astronauts James Lovell, Command Module (CM) pilot, and Frank Borman, commander, launched aboard the Apollo 8 mission on December 21, 1968 and returned safely to Earth on December 27, 1968. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

Apollo Lesson Sampler: Apollo 13 Lessons Learned

NASA Technical Reports Server (NTRS)

Interbartolo, Michael A.

2008-01-01

This CD-ROM contains a two-part case study of the Apollo 13 accident. The first lesson contains an overview of the electrical system hardware on the Apollo spacecraft, providing a context for the details of the oxygen tank explosion, and the failure chain reconstruction that led to the conditions present at the time of the accident. Given this background, the lesson then covers the tank explosion and immediate damage to the spacecraft, and the immediate response of Mission Control to what they saw. Part 2 of the lesson picks up shortly after the explosion of the oxygen tank on Apollo 13, and discusses how Mission Control gained insight to and understanding of the damage in the aftermath. Impacts to various spacecraft systems are presented, along with Mission Control's reactions and plans for in-flight recovery leading to a successful entry. Finally, post-flight vehicle changes are presented along with the lessons learned.

Saturn Apollo Program

NASA Image and Video Library

1968-12-19

Pictured from left to right, the Apollo 9 astronauts, James A. McDivitt, David R. Scott, and Russell L. Schweickart, pause in front of the Apollo/Saturn V space vehicle that would launch the Apollo 8 crew. The launch of the Apollo 9 (Saturn V launch vehicle, SA-504) took place on March 3, 1968. The Apollo 9 spacecraft, in the lunar mission configuration, was tested in Earth orbit. The mission was designed to rehearse all the steps and reproduce all the events of the Apollo 11 mission with the exception of the lunar touchdown, stay, and liftoff. The command and service modules, and the lunar module were used in flight procedures identical to those that would later take similar vehicles to the Moon, and a landing. The flight mechanics, mission support systems, communications, and recording of data were tested in a final round of verification. Astronauts Scott and Schweickart conducted Extravehicular Activity during this mission.

Moon Technology For A New Artform

NASA Technical Reports Server (NTRS)

1979-01-01

The keystone of the density slicing process is an instrument called a densitometer, which can "see" many subtle gradations not visible to the human eye. This instrument was integrated into a computerized system which analyzed the tonal density of a moon photo, assigned a color code to each of the various shades, and created on a video monitor a new picture in which each color represented a particular measurement, such as height or depth. Density slicing, applied to telescopic photos and later to close-up views acquired by unmanned spacecraft, provided the foundation for NASA's extensive study and selection of safe Apollo landing sites.

ASCANS Saturn V & LCC Tour

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – NASA astronaut candidates Victor Glover, from left, Andrew Morgan and Jessica Meir tour the Apollo Saturn V Center at Kennedy Space Center in Florida during a daylong set of briefings and tours of different facilities at NASA's primary launch center. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Kim Shiflett

Review of measurements of dust movements on the Moon during Apollo

NASA Astrophysics Data System (ADS)

O'Brien, Brian J.

2011-11-01

This is the first review of 3 Apollo experiments, which made the only direct measurements of dust on the lunar surface: (i) minimalist matchbox-sized 270 g Dust Detector Experiments (DDEs) of Apollo 11, 12, 14 and 15, produced 30 million Lunar Day measurements 21 July 1969-30 September, 1977; (ii) Thermal Degradation Samples (TDS) of Apollo 14, sprinkled with dust, photographed, taken back to Earth into quarantine and lost; and (iii) the 7.5 kg Lunar Ejecta and Meteoroids (LEAM) experiment of Apollo 17, whose original tapes and plots are lost. LEAM, designed to measure rare impacts of cosmic dust, registered scores of events each lunation most frequently around sunrise and sunset. LEAM data are accepted as caused by heavily-charged particles of lunar dust at speeds of <100 m/s, stimulating theoretical models of transporting lunar dust and adding significant motivation for returning to the Moon. New analyses here show some raw data are sporadic bursts of 1, 2, 3 or more events within time bubbles smaller than 0.6 s, not predicted by theoretical dust models but consistent with noise bits caused by electromagnetic interference (EMI) from switching of large currents in the Apollo 17 Lunar Surface Experiment Package (ALSEP), as occurred in pre-flight LEAM-acceptance tests. On the Moon switching is most common around sunrise and sunset in a dozen heavy-duty heaters essential for operational survival during 350 h of lunar night temperatures of minus 170 °C. Another four otherwise unexplained features of LEAM data are consistent with the "noise bits" hypothesis. Discoveries with DDE and TDS reported in 1970 and 1971, though overlooked, and extensive DDE discoveries in 2009 revealed strengths of adhesive and cohesive forces of lunar dust. Rocket exhaust gases during Lunar Module (LM) ascent caused dust and debris to (i) contaminate instruments 17 m distant (Apollo 11) as expected, and (ii) unexpectedly cleanse Apollo hardware 130 m (Apollo 12) and 180 m (Apollo 14) from LM. TDS photos uniquely document in situ cohesion of dust particles and their adhesion to 12 different test surfaces. This review finds the entire TDS experiment was contaminated, being inside the aura of outgassing from astronaut Alan Shepard's spacesuit, and applies an unprecedented caveat to all TDS discoveries. Published and further analyses of Apollo DDE, TDS and LEAM measurements can provide evidence-based guidance to theoretical analyses and to management and mitigation of major problems from sticky dust, and thus help optimise future lunar and asteroid missions, manned and robotic.

Apollo Expeditions to the Moon

NASA Technical Reports Server (NTRS)

Cortright, E. M. (Editor)

1975-01-01

The Apollo program is described from the planning stages through Apollo 17. The organization of the program is discussed along with the development of the spacecraft and related technology. The objectives and accomplishments of each mission are emphasized along with personal accounts of the major figures involved. Other topics discussed include: ground support systems and astronaut selection.

KSC-04PD-0606

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0605

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0609

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0609

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0606

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0605

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

LAUNCH - APOLLO 9 - CAPE

NASA Image and Video Library

1969-03-03

S69-25861 (3 March 1969) --- The Apollo 9 (Spacecraft 104/Lunar Module 3/ Saturn 504) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC) at 11 a.m. (EST), March 3, 1969. Aboard the spacecraft are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 is the second manned Saturn V mission.

APOLLO IX - ART CONCEPTS - EXTRAVEHICULAR ACTIVITY (EVA)

NASA Image and Video Library

1969-02-06

S69-18546 (February 1969) --- North American Rockwell artist's concept illustrating the docking of the Lunar Module ascent stage with the Command and Service Modules during the Apollo 9 mission. The two figures in the Lunar Module represent astronauts James A. McDivitt, Apollo 9 commander; and Russell L. Schweickart, lunar module pilot. The figure in the Command Module represents astronaut David R. Scott, command module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

Postflight Analysis of the Apollo 14 Cryogenic Oxygen System

NASA Technical Reports Server (NTRS)

Rule, D. D.

1972-01-01

A postflight analysis of the Apollo 14 cryogenic oxygen system is presented. The subjects discussed are: (1) methods of analysis, (2) stratification and heat transfer, (3) flight analysis, (4) postflight analysis, and (5) determination of model parameters.

The Violent Early Solar System, as Told by Sample Geochronology

NASA Technical Reports Server (NTRS)

Cohen, Barbara

2013-01-01

One of the legacies of the samples collected by the Apollo and Luna missions is the link forged between radiometric ages of rocks and relative ages according to stratigraphic relationships and impact crater size-frequency distributions. Our current understanding of the history of the inner solar system is based on the relative chronology of individual planets, tied to the absolute geochronology of the Moon via these important samples. Sample ages have enabled us to infer that impact-melt breccias from Apollo 14 and 15 record the formation of the Imbrium Basin, those from the highland massifs at Apollo 17 record the age of Serenitatis, those from the KREEP-poor Apollo 16 site record the age of Nectaris, and materials from Luna 24 record the age of Crisium. Ejecta from smaller and younger craters Copernicus and Tycho were sampled at Apollo 12 and 17, respectively, and local craters such as Cone at Apollo 14, and North Ray and South Ray at Apollo 16 were also sampled and ages determined for those events. Much of what we understand about the lunar impact flux is based on these ages. Samples from these nearside locations reveal a preponderance of impact-disturbed or recrystallized ages between 3.75 and 3.95 billion years. Argon and lead loss (and correlated disturbances in the Rb-Sr system) have been attributed to metamorphism of the lunar crust by an enormous number of impacts in a brief pulse of time, called the Lunar Cataclysm or Late Heavy Bombardment. Subsequent high-precision geochronometric analyses of Apollo samples and lunar highlands meteorites show a wider range of ages, but very few older than 4 Ga. The paucity of ancient impact melt rocks has been interpreted to mean that either that most impact basins formed at this time, or that ejecta from the large, near-side, young basins dominates the Apollo samples.

Engineering aspects of the experiment and results of animal tests. [Apollo 17 Biological Cosmic Ray Experiment

NASA Technical Reports Server (NTRS)

Look, B. C.; Tremor, J. W.; Barrows, W. F.; Zabower, H. R.; Suri, K.; Park, E. G., Jr.; Durso, J. A.; Leon, H. A.; Haymaker, W.; Lindberg, R. G.

1975-01-01

A closed passive system independent of support from the spacecraft or its crew was developed to house five pocket mice for their flight on Apollo XVII. The reaction of potassium superoxide with carbon dioxide and water vapor to produce oxygen provided a habitable atmosphere within the experiment package. The performance of the system and the ability of the mice to survive the key preflight tests gave reasonable assurance that the mice would also withstand the Apollo flight.-

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Greene, WIlliam

2007-01-01

The United States (U.S.) Vision for Space Exploration has directed NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020 by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage (EDS). This decision was reached during the Exploration Systems Architecture Study and confirmed after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by testing existing engine hardware and designs; building on the Apollo Program (1961 to 1975), the Space Shuttle Program (1972 to 2010); and consulting with Apollo era experts to derive other lessons learned to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Greene, William D.; Snoddy, Jim

2007-01-01

The United States (U.S.) Vision for Space Exploration has directed NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020, by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage. This decision was reached during the Exploration Systems Architecture Study and confirmed after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by testing existing engine hardware and designs; building on the Apollo Program (1961 to 1975), the Space Shuttle Program (1972 to 2010); and consulting with Apollo-era experts to derive other lessons lived to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Apollo 16 Mission Report

NASA Technical Reports Server (NTRS)

1972-01-01

Information is provided on the operational and engineering aspects of the Apollo 16 mission. Customary units of measurement are used in those sections of the report pertaining to spacecraft systems and trajectories. The International System of Units is used in sections pertaining to science activities.

Engineering study for pallet adapting the Apollo laser altimeter and photographic camera system for the Lidar Test Experiment on orbital flight tests 2 and 4

NASA Technical Reports Server (NTRS)

Kuebert, E. J.

1977-01-01

A Laser Altimeter and Mapping Camera System was included in the Apollo Lunar Orbital Experiment Missions. The backup system, never used in the Apollo Program, is available for use in the Lidar Test Experiments on the STS Orbital Flight Tests 2 and 4. Studies were performed to assess the problem associated with installation and operation of the Mapping Camera System in the STS. They were conducted on the photographic capabilities of the Mapping Camera System, its mechanical and electrical interface with the STS, documentation, operation and survivability in the expected environments, ground support equipment, test and field support.

Testing gravity with Lunar Laser Ranging: An update on the APOLLO experiment

NASA Astrophysics Data System (ADS)

Battat, James; Colmenares, Nick; Davis, Rodney; Ruixue, Louisa Huang; Murphy, Thomas W., Jr.; Apollo Collaboration

2017-01-01

The mystery of dark energy and the incompatibility of quantum mechanics and General Relativity indicate the need for precision experimental probes of gravitational physics. The Earth-Moon-Sun system is a fertile laboratory for such tests. The Apache Point Observatory Lunar Laser-ranging Operation (APOLLO) makes optical range measurements to retro-reflectors on the Moon with one millimeter precision. These measurements of the lunar orbit enable incisive constraints on gravitational phenomena such as the Strong Equivalence Principle and dG / dt (among others). Until now, the APOLLO team had not been able to assess the accuracy of our data, in large part because known limitations to lunar range models ensure data-model residuals at the centimeter scale. To directly measure the APOLLO system timing accuracy, we have built an Absolute timing Calibration System (ACS) that delivers photons to our detector at known, stable time intervals using a pulsed fiber laser locked to a cesium frequency standard. This scheme provides real-time calibration of the APOLLO system timing, synchronous with the range measurements. We installed the calibration system in August, 2016. In this talk, we will describe the ACS design, and present present preliminary results from the ACS calibration campaign. We acknowledge the support of both NSF and NASA

Biomedical Results of Apollo

NASA Technical Reports Server (NTRS)

Johnston, R. S. (Editor); Dietlein, L. F. (Editor); Berry, C. A. (Editor); Parker, James F. (Compiler); West, Vita (Compiler)

1975-01-01

The biomedical program developed for Apollo is described in detail. The findings are listed of those investigations which are conducted to assess the effects of space flight on man's physiological and functional capacities, and significant medical events in Apollo are documented. Topics discussed include crew health and inflight monitoring, preflight and postflight medical testing, inflight experiments, quarantine, and life support systems.

Saturn Apollo Program

NASA Image and Video Library

1974-06-01

This illustration shows the docking configuration of the Apollo-Soyuz Test Project (ASTP). The ASTP was the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. A joint engineering team from the two countries met to develop a docking system that permitted the two spacecraft to link in space and allowed the two crews to travel from one spacecraft to the other. This system entailed developing a large habitable Docking Module (DM) to be carried on the Apollo spacecraft to facilitate the joining of two dissimilar spacecraft. The Marshall Space Flight Center was responsible for development and sustaining engineering of the Saturn IB launch vehicle during the mission. The ASTP marked the last use of the Saturn Launch Vehicle.

The Lunar Landing Research Vehicle; Prelude to the Arrival at Tranquility Base

NASA Technical Reports Server (NTRS)

Gelzer, Christian

2006-01-01

The flight of Apollo 11 was the end of a decade-long race to reach the moon, a race between the US and Soviet Union, but also a race with time, for we as a nation only had the 1960s to reach our objective. Most of us remember that particular day, July 20, 1969, but the further we are from any date the harder it is to recall details. It s easy to forget, for instance, how close together the Apollo flights came to each other as the lunar flight date approached. Apollo 7 circled Earth for almost 11 days testing the systems of the spacecraft in October 1968; Apollo 8 gave us the first glimpse of our entire planet while circling the moon during Christmas of 1968. Apollo 9 lifted off on March 3 of 1969, and Apollo 10 returned to Earth on May 26 of that year. Less than two months later, on 16 July, Apollo 11 lifted off on its mission of landing on the moon. That s five Apollo launches in ten months, three of which went to the moon.

Saturn Apollo Program

NASA Image and Video Library

1967-01-01

This cutaway illustration shows the Apollo Spacecraft with callouts of the major components. The spacecraft consisted of the lunar module, the service module, the command module, and the launch escape system.

View of White Room atop Pad A during Apollo 9 Countdown Demonstration Test

NASA Image and Video Library

1969-02-23

S69-25884 (23 Feb. 1969) --- Interior view of the white room atop Pad A, Launch Complex 39, Kennedy Space Center, during Apollo 9 Countdown Demonstration Test activity. Standing next to spacecraft hatch is astronaut James A. McDivitt, commander. Also, taking part in the training exercise were astronauts David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 will be the second manned Saturn V mission.

KSC-04PD-0610

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0612

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with the Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0604

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1), stored in the Industrial Area of KSC, is being demolished using a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear being used for demolition is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0607

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0608

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

LAUNCH - APOLLO 9 - CAPE

NASA Image and Video Library

1969-03-03

S69-25862 (3 March 1969) --- Framed by palm trees in the foreground, the Apollo 9 (Spacecraft 104/Lunar Module 3/ Saturn 504) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC) at 11 a.m. (EST), March 3, 1969. Aboard the spacecraft are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 is the second manned Saturn V mission.

Saturn Apollo Program

NASA Image and Video Library

1973-01-01

This illustration depicts a configuration of the Soyuz spacecraft for the Apollo-Soyuz Test Project (ASTP). The ASTP was the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. For this project, the Soviets built another in their continuing series of Soyuz space capsules. The U.S. used the Saturn IB Apollo capsule. A joint engineering team from the two countries met to develop a docking system that permitted the two spacecraft to link in space and allowed the crews to travel from one spacecraft to the other.

PDS Lunar Data Node Restoration of Apollo In-Situ Surface Data

NASA Technical Reports Server (NTRS)

Williams, David R.; Hills, H. Kent; Guinness, Edward A.; Lowman, Paul D.; Taylor, Patrick T.

2010-01-01

The Apollo missions between 1969 and 1972 deployed scientific instruments on the Moon's surface which made in-situ measurements of the lunar environment. Apollo II had the short-term Early Apollo Surface Experiments Package (EASEP) and Apollos 12, 14, 15, 16, and 17 each set up an Apollo Lunar Surface Experiments Package (ALSEP). Each ALSEP package contained a different suite of instruments which took measurements and radioed the results back to Earth over periods from 5 to 7 years until they were turned off on 30 September 1977. To this day the ALSEP data remain the only long-term in-situ information on the Moon's surface environment. The Lunar Data Node (LDN) has been formed under the auspices of the Planetary Data System (PDS) Geosciences Node to put relevant, scientifically important Apollo data into accessible digital form for use by researchers and mission planners. We will report on progress made since last year and plans for future data restorations.

APOLLO clock performance and normal point corrections

NASA Astrophysics Data System (ADS)

Liang, Y.; Murphy, T. W., Jr.; Colmenares, N. R.; Battat, J. B. R.

2017-12-01

The Apache point observatory lunar laser-ranging operation (APOLLO) has produced a large volume of high-quality lunar laser ranging (LLR) data since it began operating in 2006. For most of this period, APOLLO has relied on a GPS-disciplined, high-stability quartz oscillator as its frequency and time standard. The recent addition of a cesium clock as part of a timing calibration system initiated a comparison campaign between the two clocks. This has allowed correction of APOLLO range measurements—called normal points—during the overlap period, but also revealed a mechanism to correct for systematic range offsets due to clock errors in historical APOLLO data. Drift of the GPS clock on  ∼1000 s timescales contributed typically 2.5 mm of range error to APOLLO measurements, and we find that this may be reduced to  ∼1.6 mm on average. We present here a characterization of APOLLO clock errors, the method by which we correct historical data, and the resulting statistics.

Potable water supply

NASA Technical Reports Server (NTRS)

Sauer, R. L.; Calley, D. J.

1975-01-01

The history and evolution of the Apollo potable water system is reviewed. Its operation in the space environment and in the spacecraft is described. Its performance is evaluated. The Apollo potable water system satisfied the dual purpose of providing metabolic water for the crewmen and water for spacecraft cooling.

Apollo Experiment Report: Lunar-Sample Processing in the Lunar Receiving Laboratory High-Vacuum Complex

NASA Technical Reports Server (NTRS)

White, D. R.

1976-01-01

A high-vacuum complex composed of an atmospheric decontamination system, sample-processing chambers, storage chambers, and a transfer system was built to process and examine lunar material while maintaining quarantine status. Problems identified, equipment modifications, and procedure changes made for Apollo 11 and 12 sample processing are presented. The sample processing experiences indicate that only a few operating personnel are required to process the sample efficiently, safely, and rapidly in the high-vacuum complex. The high-vacuum complex was designed to handle the many contingencies, both quarantine and scientific, associated with handling an unknown entity such as the lunar sample. Lunar sample handling necessitated a complex system that could not respond rapidly to changing scientific requirements as the characteristics of the lunar sample were better defined. Although the complex successfully handled the processing of Apollo 11 and 12 lunar samples, the scientific requirement for vacuum samples was deleted after the Apollo 12 mission just as the vacuum system was reaching its full potential.

ART CONCEPTS - ASTP

NASA Image and Video Library

1975-04-01

S75-27289 (May 1975) --- An artist?s concept depicting the American Apollo spacecraft docked with a Soviet Soyuz spacecraft in Earth orbit. During the joint U.S.-USSR Apollo-Soyuz Test Project mission, scheduled for July 1975, the American and Soviet crews will visit one another?s spacecraft while the Soyuz and Apollo are docked for a maximum period of two days. The mission is designed to test equipment and techniques that will establish international crew rescue capability in space, as well as permit future cooperative scientific missions. Each nation has developed separately docking systems based on a mutually agreeable single set of interface design specifications. The major new U.S. program elements are the docking module and docking system necessary to achieve compatibility of rendezvous and docking systems with the USSR-developed hardware to be used on the Soyuz spacecraft. The DM and docking system together with an Apollo Command/Service Module will be launched by a Saturn 1B launch vehicle. This artwork is by Paul Fjeld.

An absolute calibration system for millimeter-accuracy APOLLO measurements

NASA Astrophysics Data System (ADS)

Adelberger, E. G.; Battat, J. B. R.; Birkmeier, K. J.; Colmenares, N. R.; Davis, R.; Hoyle, C. D.; Huang, L. R.; McMillan, R. J.; Murphy, T. W., Jr.; Schlerman, E.; Skrobol, C.; Stubbs, C. W.; Zach, A.

2017-12-01

Lunar laser ranging provides a number of leading experimental tests of gravitation—important in our quest to unify general relativity and the standard model of physics. The apache point observatory lunar laser-ranging operation (APOLLO) has for years achieved median range precision at the  ∼2 mm level. Yet residuals in model-measurement comparisons are an order-of-magnitude larger, raising the question of whether the ranging data are not nearly as accurate as they are precise, or if the models are incomplete or ill-conditioned. This paper describes a new absolute calibration system (ACS) intended both as a tool for exposing and eliminating sources of systematic error, and also as a means to directly calibrate ranging data in situ. The system consists of a high-repetition-rate (80 MHz) laser emitting short (< 10 ps) pulses that are locked to a cesium clock. In essence, the ACS delivers photons to the APOLLO detector at exquisitely well-defined time intervals as a ‘truth’ input against which APOLLO’s timing performance may be judged and corrected. Preliminary analysis indicates no inaccuracies in APOLLO data beyond the  ∼3 mm level, suggesting that historical APOLLO data are of high quality and motivating continued work on model capabilities. The ACS provides the means to deliver APOLLO data both accurate and precise below the 2 mm level.

Minimally invasive evacuation of parenchymal and ventricular hemorrhage using the Apollo system with simultaneous neuronavigation, neuroendoscopy and active monitoring with cone beam CT.

PubMed

Fiorella, David; Gutman, Fredrick; Woo, Henry; Arthur, Adam; Aranguren, Ricardo; Davis, Raphael

2015-10-01

The Apollo system is a low profile irrigation-aspiration system which can be used for the evacuation of intracranial hemorrhage. We demonstrate the feasibility of using Apollo to evacuate intracranial hemorrhage in a series of three patients with combined neuronavigation, neuroendoscopy, and cone beam CT (CB-CT). Access to the hematoma was planned using neuronavigation software. Parietal (n=2) or frontal (1) burr holes were created and a 19 F endoscopic sheath was placed under neuronavigation guidance into the distal aspect of the hematoma along its longest accessible axis. The 2.6 mm Apollo wand was then directed through the working channel of a neuroendoscope and used to aspirate the blood products under direct visualization, working from distal to proximal. After a pass through the hematoma, the sheath, neuroendoscope, and Apollo system were removed. CB-CT was then used to evaluate for residual hematoma. When required, the CB-CT data could then be directly uploaded into the neuronavigation system and a new trajectory planned to approach the residual hematoma. Three patients with parenchymal (n=2) and mixed parenchymal-intraventricular (n=1) hematomas underwent minimally invasive evacuation with the Apollo system. The isolated parenchymal hematomas measured 93.4 and 15.6 mL and were reduced to 11.2 (two passes) and 0.9 mL (single pass), respectively. The entire parenchymal component of the mixed hemorrhage was evacuated, as was the intraventricular component within the right frontal horn (single pass). No complications were experienced. All patients showed clinical improvement after the procedure. The average presenting National Institutes of Health Stroke Scale was 19.0, which had improved to 5.7 within an average of 4.7 days after the procedure. The Apollo system can be used within the neuroangiography suite for the minimally invasive evacuation of intracranial hemorrhage using simultaneous neuronavigation for planning and intraprocedural guidance, direct visualization with neuroendoscopy, and real time monitoring of progress with CB-CT. Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://group.bmj.com/group/rights-licensing/permissions.

Dynamic analysis of Apollo-Salyut/Soyuz docking

NASA Technical Reports Server (NTRS)

Schliesing, J. A.

1972-01-01

The use of a docking-system computer program in analyzing the dynamic environment produced by two impacting spacecraft and the attitude control systems is discussed. Performance studies were conducted to determine the mechanism load and capture sensitivity to parametric changes in the initial impact conditions. As indicated by the studies, capture latching is most sensitive to vehicle angular-alinement errors and is least sensitive to lateral-miss error. As proved by load-sensitivity studies, peak loads acting on the Apollo spacecraft are considerably lower than the Apollo design-limit loads.

Prospects for Dating the South Pole-Aitken Basin through Impact-Melt Rock Samples

NASA Technical Reports Server (NTRS)

Cohen, B. A.; Coker, R. F.; Petro, N. E.

2016-01-01

Much of the present debate about the ages of the nearside basins arises because of the difficulty in understanding the relationship of recovered samples to their parent basin. The Apollo breccias are from basin ejecta formations, which are ballistically-emplaced distal deposits that have mixed provenances. The Nectaris, Imbrium, and Serenitatis basins all have mare-basalt fill obscuring their original melt sheets, so geochemical ties are indirect. Though the geological processes acting to vertically and laterally mix materials into regolith are the same as at the Apollo sites, the SPA interior is a fundamentally different geologic setting than the Apollo sites. The South Pole-Aitken basin was likely filled by a large impact melt sheet, possibly differentiated into cumulate horizons. It is on this distinctive melt sheet that the regolith has formed, somewhat diluting but not erasing the prominent geochemical signature seen from orbital assets. By analogy to the Apollo 16 site, a zeroth-order expectation is that bulk samples taken from regolith within SPA will contain abundant samples gardened from the SPA melt sheet. However, questions persist as to whether the SPA melt sheet has been so extensively contaminated with foreign ejecta that a simple robotic scoop sample of such regolith would be unlikely to yield the age of the basin.

Mobility systems activity for lunar rovers at MSFC

NASA Technical Reports Server (NTRS)

Jones, C. S., Jr.; Nola, F. J.

1971-01-01

The Apollo Lunar Roving Vehicle (LRV) mobility system is described. Special emphasis is given to the redundancy aspects and to the selection of the drive motors. A summary chart of the performance on the lunar surface during the Apollo 15 flight is included. An appendix gives details on some development work on high efficiency drive systems and compares these systems to the selected system.

Design development of the Apollo command and service module thrust vector attitude control systems

NASA Technical Reports Server (NTRS)

Peters, W. H.

1978-01-01

Development of the Apollo thrust vector control digital autopilot (TVC DAP) was summarized. This is the control system that provided pitch and yaw attitude control during velocity change maneuvers using the main rocket engine on the Apollo service module. A list of ten primary functional requirements for this control system are presented, each being subordinate to a more general requirement appearing earlier on the list. Development process functions were then identified and the essential information flow paths were explored. This provided some visibility into the particular NASA/contractor interface, as well as relationships between the many individual activities.

Saturn Apollo Program

NASA Image and Video Library

1974-01-01

This illustration depicts a comparison of two space vehicles, the U.S.'s Saturn IB launch vehicle and the U.S.S.R.'s Soyuz launch vehicle, for the Apollo-Soyuz Test Project. The ASTP was the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. A joint engineering team from the two countries met to develop a docking system that permitted the two spacecraft to link in space and allowed the two crews to travel from one spacecraft to the other. This system entailed developing a large habitable Docking Module (DM) to be carried on the Apollo spacecraft to facilitate the joining of two dissimilar spacecraft. The Marshall Space Flight Center was responsible for development and sustaining engineering of the Saturn IB launch vehicle during the mission.

The telomeric protein SNM1B/Apollo is required for normal cell proliferation and embryonic development

PubMed Central

Akhter, Shamima; Lam, Yung C.; Chang, Sandy; Legerski, Randy J.

2013-01-01

Summary Conserved metallo β-Lactamase and β-CASP (CPSF-Artemis-Snm1-Pso2) domain nuclease family member SNM1B/Apollo is a shelterin-associated protein that localizes to telomeres through its interaction with TRF2. To study its in vivo role, we generated a knockout of SNM1B/Apollo in a mouse model. Snm1B/Apollo homozygous null mice die at birth with developmental delay and defects in multiple organ systems. Cell proliferation defects were observed in Snm1B/Apollo mutant mouse embryonic fibroblasts (MEFs) owing to high levels of telomeric end-to-end fusions. Deficiency of the nonhomologous end-joining (NHEJ) factor Ku70, but not p53, rescued the developmental defects and lethality observed in Snm1B/Apollo mutant mice as well as the impaired proliferation of Snm1B/Apollo-deficient MEFs. These findings demonstrate that SNM1B/Apollo is required to protect telomeres against NHEJ-mediated repair, which results in genomic instability and the consequent multi-organ developmental failure. Although Snm1B/Apollo-deficient MEFs exhibited high levels of apoptosis, abrogation of p53-dependent programmed cell death did not rescue the multi-organ developmental failure in the mice. PMID:20854421

Lunar orbital mass spectrometer experiment

NASA Technical Reports Server (NTRS)

Lord, W. P.

1971-01-01

The design, development, manufacture, test and calibration of five lunar orbital mass spectrometers with the four associated ground support equipment test sets are discussed. A mass spectrometer was installed in the Apollo 15 and one in the Apollo 16 Scientific Instrument Module within the Service Module. The Apollo 15 mass spectrometer was operated with collection of 38 hours of mass spectra data during lunar orbit and 50 hours of data were collected during transearth coast. The Apollo 16 mass spectrometer was operated with collection of 76 hours of mass spectra data during lunar orbit. However, the Apollo 16 mass spectrometer was ejected into lunar orbit upon malfunction of spacecraft boom system just prior to transearth insection and no transearth coast data was possible.

Apollo experience report: The cryogenic storage system

NASA Technical Reports Server (NTRS)

Chandler, W. A.; Rice, R. R.; Allgeier, R. K., Jr.

1973-01-01

A review of the design, development, and flight history of the Apollo cryogenic storage system and of selected components within the system is presented. Discussions are presented on the development history of the pressure vessels, heaters, insulation, and selected components. Flight experience and operational difficulties are reported in detail to provide definition of the problems and applicable corrective actions.

Apollo Missions to the Lunar Surface

NASA Technical Reports Server (NTRS)

Graff, Paige V.

2018-01-01

Six Apollo missions to the Moon, from 1969-1972, enabled astronauts to collect and bring lunar rocks and materials from the lunar surface to Earth. Apollo lunar samples are curated by NASA Astromaterials at the NASA Johnson Space Center in Houston, TX. Samples continue to be studied and provide clues about our early Solar System. Learn more and view collected samples at: https://curator.jsc.nasa.gov/lunar.

Calculations of reliability predictions for the Apollo spacecraft

NASA Technical Reports Server (NTRS)

Amstadter, B. L.

1966-01-01

A new method of reliability prediction for complex systems is defined. Calculation of both upper and lower bounds are involved, and a procedure for combining the two to yield an approximately true prediction value is presented. Both mission success and crew safety predictions can be calculated, and success probabilities can be obtained for individual mission phases or subsystems. Primary consideration is given to evaluating cases involving zero or one failure per subsystem, and the results of these evaluations are then used for analyzing multiple failure cases. Extensive development is provided for the overall mission success and crew safety equations for both the upper and lower bounds.

ASCANS Saturn V & LCC Tour

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – NASA astronaut candidates Andrew Morgan, from left, Victor Glover, Josh Cassada, Anne McClain and Jessica Meir tour the Apollo Saturn V Center at Kennedy Space Center in Florida during a daylong set of briefings and tours of different facilities at NASA's primary launch center. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Kim Shiflett

Interviews with Apollo Lunar Surface Astronauts in Support of EVA Systems Design

NASA Technical Reports Server (NTRS)

Eppler, Dean

2010-01-01

A 3-person team interviewed 8 of the 11 surviving Apollo crewmembers in a series of focused interviews to discuss their experiences on the lunar surface. Eppler presented the results of these interviews, along with recommendations for the design of future lunar surface systems.

The Violent Early Solar System, as Told by Lunar Sample Geochronology

NASA Astrophysics Data System (ADS)

Cohen, B. A.

2012-12-01

One of the legacies of the samples collected by the Apollo and Luna missions is the link forged between radiometric ages of rocks and relative ages according to stratigraphic relationships and impact crater size-frequency distributions. Our current understanding of the history of the inner solar system is based on the relative chronology of individual planets, tied to the absolute geochronology of the Moon via these important samples. Sample ages have enabled us to infer that impact-melt breccias from Apollo 14 and 15 record the formation of the Imbrium Basin, those from the highland massifs at Apollo 17 record the age of Serenitatis, those from the KREEP-poor Apollo 16 site record the age of Nectaris, and materials from Luna 24 record the age of Crisium. Ejecta from smaller and younger craters Copernicus and Tycho were sampled at Apollo 12 and 17, respectively, and local craters such as Cone at Apollo 14, and North Ray and South Ray at Apollo 16 were also sampled and ages determined for those events. Much of what we understand about the lunar impact flux is based on these ages. Samples from these nearside locations reveal a preponderance of impact-disturbed or recrystallized ages between 3.75 and 3.95 billion years. Argon and lead loss (and correlated disturbances in the Rb-Sr system) have been attributed to metamorphism of the lunar crust by an enormous number of impacts in a brief pulse of time, called the Lunar Cataclysm or Late Heavy Bombardment. Subsequent high-precision geochronometric analyses of Apollo samples and lunar highlands meteorites show a wider range of ages, but very few older than 4 Ga. The paucity of ancient impact melt rocks has been interpreted to mean that either that most impact basins formed at this time, or that ejecta from the large, near-side, young basins dominates the Apollo samples. The impact history of the Moon has significant implications because the lunar bombardment history mirrors that of the Earth. During the cataclysm, 80% of the lunar surface was resurfaced; on Earth, this would scale to ~23,000 large impacts in a brief time. Impact ages in ordinary chondrites, HED meteorites, and the Martian meteorite ALH 84001 suggest that this early bombardment event affected the entire inner solar system. If true, the late heavy bombardment may have directly affected the evolution of life on Earth and our understanding of "habitable" planets. Lunar sample ages have also been used to drive large-scale dynamical modeling of solar system formation. These new models of planetary dynamics show a violent beginning to our solar system, where the late formation or outward migration of the gas giant planets destabilizes the Kuiper belt and main-belt asteroids, sending a cascade of impactors into the Moon and all the inner planets. The existence of an early bombardment has even been postulated in extrasolar planetary systems. Even after 40+ years of study, the provenance of returned lunar samples and ages of key events continue to be a focus of research and a topic of debate. One of the most important lessons learned from Apollo missions is that small samples yield a wealth of information and are gifts that keep on giving. The legacy of Apollo samples serves as a model and impetus for future sample return missions from the Moon, Mars, and asteroids.

Evidence for high-temperature fractionation of lithium isotopes during differentiation of the Moon

NASA Astrophysics Data System (ADS)

Day, James M. D.; Qiu, Lin; Ash, Richard D.; McDonough, William F.; Teng, Fang-Zhen; Rudnick, Roberta L.; Taylor, Lawrence A.

2016-06-01

Lithium isotope and abundance data are reported for Apollo 15 and 17 mare basalts and the LaPaz low-Ti mare basalt meteorites, along with lithium isotope data for carbonaceous, ordinary, and enstatite chondrites, and chondrules from the Allende CV3 meteorite. Apollo 15 low-Ti mare basalts have lower Li contents and lower δ7Li (3.8 ± 1.2‰; all uncertainties are 2 standard deviations) than Apollo 17 high-Ti mare basalts (δ7Li = 5.2 ± 1.2‰), with evolved LaPaz mare basalts having high Li contents, but similar low δ7Li (3.7 ± 0.5‰) to Apollo 15 mare basalts. In low-Ti mare basalt 15555, the highest concentrations of Li occur in late-stage tridymite (>20 ppm) and plagioclase (11 ± 3 ppm), with olivine (6.1 ± 3.8 ppm), pyroxene (4.2 ± 1.6 ppm), and ilmenite (0.8 ± 0.7 ppm) having lower Li concentrations. Values of δ7Li in low- and high-Ti mare basalt sources broadly correlate negatively with 18O/16O and positively with 56Fe/54Fe (low-Ti: δ7Li ≤4‰; δ56Fe ≤0.04‰; δ18O ≥5.7‰; high-Ti: δ7Li >6‰ δ56Fe >0.18‰ δ18O <5.4‰). Lithium does not appear to have acted as a volatile element during planetary formation, with subequal Li contents in mare basalts compared with terrestrial, martian, or vestan basaltic rocks. Observed Li isotopic fractionations in mare basalts can potentially be explained through large-degree, high-temperature igneous differentiation of their source regions. Progressive magma ocean crystallization led to enrichment in Li and δ7Li in late-stage liquids, probably as a consequence of preferential retention of 7Li and Li in the melt relative to crystallizing solids. Lithium isotopic fractionation has not been observed during extensive differentiation in terrestrial magmatic systems and may only be recognizable during extensive planetary magmatic differentiation under volatile-poor conditions, as expected for the lunar magma ocean. Our new analyses of chondrites show that they have δ7Li ranging between -2.5‰ and 4‰. The higher δ7Li in planetary basalts than in the compilation of chondrites (2.1 ± 1.3‰) demonstrates that differentiated planetary basalts are, on average, isotopically heavier than most chondrites.

Saturn Apollo Program

NASA Image and Video Library

1968-12-17

Apollo 8 crew members paused before the mission simulator during training for the first manned lunar orbital mission. Frank Borman, commander; James Lovell, Command Module (CM) pilot; and William Anders, Lunar Module (LM) pilot , were also the first humans to launch aboard the massive Saturn V space vehicle. Lift off occurred on December 21, 1968 and returned safely to Earth on December 27, 1968. The mission achieved operational experience and tested the Apollo command module systems, including communications, tracking, and life-support, in cis-lunar space and lunar orbit, and allowed evaluation of crew performance on a lunar orbiting mission. The crew photographed the lunar surface, both far side and near side, obtaining information on topography and landmarks as well as other scientific information necessary for future Apollo landings. All systems operated within allowable parameters and all objectives of the mission were achieved.

Impact of workstations on criticality analyses at ABB combustion engineering

DOE Office of Scientific and Technical Information (OSTI.GOV)

Tarko, L.B.; Freeman, R.S.; O'Donnell, P.F.

1993-01-01

During 1991, ABB Combustion Engineering (ABB C-E) made the transition from a CDC Cyber 990 mainframe for nuclear criticality safety analyses to Hewlett Packard (HP)/Apollo workstations. The primary motivation for this change was improved economics of the workstation and maintaining state-of-the-art technology. The Cyber 990 utilized the NOS operating system with a 60-bit word size. The CPU memory size was limited to 131 100 words of directly addressable memory with an extended 250000 words available. The Apollo workstation environment at ABB consists of HP/Apollo-9000/400 series desktop units used by most application engineers, networked with HP/Apollo DN10000 platforms that use 32-bitmore » word size and function as the computer servers and network administrative CPUS, providing a virtual memory system.« less

Apollo experience report: Crew station integration. Volume 2: Crew station displays and controls

NASA Technical Reports Server (NTRS)

Langdoc, W. A.; Nassman, D. A.

1975-01-01

The functional requirements for the Apollo displays and controls system are presented. The configuration of the displays, controls, and panels for both the command module and the lunar module are described, and the design development and operational experience of the displays and controls system are discussed. Pertinent recommendations for future displays and controls system design efforts are made.

Crew Training - Apollo 9 - Grumman Aircraft Eng. Corp. (GAEC)

NASA Image and Video Library

1969-01-25

S69-17615 (25 Jan. 1969) --- Astronaut Russell L. Schweickart, lunar module pilot of the Apollo 9 prime crew, participates in a press conference at the Grumman Aircraft Engineering Corporation. Grumman is the contractor to NASA for the Lunar Module. Schweickart is holding a model of a docked Lunar Module/Command and Service Modules. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight.

The telomeric protein SNM1B/Apollo is required for normal cell proliferation and embryonic development.

PubMed

Akhter, Shamima; Lam, Yung C; Chang, Sandy; Legerski, Randy J

2010-12-01

Conserved metallo β-Lactamase and β-CASP (CPSF-Artemis-Snm1-Pso2) domain nuclease family member SNM1B/Apollo is a shelterin-associated protein that localizes to telomeres through its interaction with TRF2. To study its in vivo role, we generated a knockout of SNM1B/Apollo in a mouse model. Snm1B/Apollo homozygous null mice die at birth with developmental delay and defects in multiple organ systems. Cell proliferation defects were observed in Snm1B/Apollo mutant mouse embryonic fibroblasts (MEFs) owing to high levels of telomeric end-to-end fusions. Deficiency of the nonhomologous end-joining (NHEJ) factor Ku70, but not p53, rescued the developmental defects and lethality observed in Snm1B/Apollo mutant mice as well as the impaired proliferation of Snm1B/Apollo-deficient MEFs. These findings demonstrate that SNM1B/Apollo is required to protect telomeres against NHEJ-mediated repair, which results in genomic instability and the consequent multi-organ developmental failure. Although Snm1B/Apollo-deficient MEFs exhibited high levels of apoptosis, abrogation of p53-dependent programmed cell death did not rescue the multi-organ developmental failure in the mice. © 2010 The Authors. Aging Cell © 2010 Blackwell Publishing Ltd/Anatomical Society of Great Britain and Ireland.

Verification test results of Apollo stabilization and control systems during undocked operations

NASA Technical Reports Server (NTRS)

Copeland, E. L.; Haken, R. L.

1974-01-01

The results are presented of analysis and simulation testing of both the Skylark 1 reaction control system digital autopilot (RCS DAP) and the thrust vector control (TVC) autopilot for use during the undocked portions of the Apollo/Soyuz Test Project Mission. The RCS DAP testing was performed using the Skylab Functional Simulator (SLFS), a digital computer program capable of simulating the Apollo and Skylab autopilots along with vehicle dynamics including bending and sloshing. The model is used to simulate three-axis automatic maneuvers along with pilot controlled manual maneuvers using the RCS DAP. The TVC autopilot was tested in two parts. A classical stability analysis was performed on the vehicle considering the effects of structural bending and sloshing when under control of the TVC autopilot. The time response of the TVC autopilot was tested using the SLFS. Results indicate that adequate performance stability margins can be expected for the CSM/DM configuration when under the control of the Apollo control systems tested.

Power supply sharing in the Apollo telescope mount electrical power system

NASA Technical Reports Server (NTRS)

Lanier, R., Jr.; Kapustka, R.

1977-01-01

A modular dc power supply power sharing technique was developed for the Apollo telescope mount electrical power sytem on Skylab. The advantages and disadvantages of various techniques used are reviewed and compared. The new technique design is discussed, and results of its implementation in the power system are reviewed.

Apollo experience report: Earth landing system

NASA Technical Reports Server (NTRS)

West, R. B.

1973-01-01

A brief discussion of the development of the Apollo earth landing system and a functional description of the system are presented in this report. The more significant problems that were encountered during the program, the solutions, and, in general, the knowledge that was gained are discussed in detail. Two appendixes presenting a detailed description of the various system components and a summary of the development and the qualification test programs are included.

Apollo Soyuz Mission: 5-Day Report

NASA Technical Reports Server (NTRS)

1975-01-01

The Apollo Soyuz Test Project mission objectives and technical investigations are summarized. Topics discussed include: spacecraft and crew systems performance; joint flight activities; scientific and applications experiments; in-flight demonstrations; biomedical considerations; and mission support performance.

Emblem - Apollo 9 Space Mission

NASA Image and Video Library

1969-02-06

S69-18569 (February 1969) --- The insignia of the Apollo 9 space mission. The crew consist of astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. The NASA insignia design for Apollo flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the form of illustrations by the various news media. When and if there is any change in this policy, which we do not anticipate, it will be publicly announced.

Apollo experience report: Command module uprighting system

NASA Technical Reports Server (NTRS)

White, R. D.

1973-01-01

A water-landing requirement and two stable flotation attitudes required that a system be developed to ensure that the Apollo command module would always assume an upright flotation attitude. The resolution to the flotation problem and the uprighting concepts, design selection, design changes, development program, qualification, and mission performance are discussed for the uprighting system, which is composed of inflatable bags, compressors, valves, and associated tubing.

Guidance, navigation, and control systems performance analysis: Apollo 13 mission report

NASA Technical Reports Server (NTRS)

1970-01-01

The conclusions of the analyses of the inflight performance of the Apollo 13 spacecraft guidance, navigation, and control equipment are presented. The subjects discussed are: (1) the command module systems, (2) the lunar module inertial measurement unit, (3) the lunar module digital autopilot, (4) the lunar module abort guidance system, (5) lunar module optical alignment checks, and (6) spacecraft component separation procedures.

The NASA teleconferencing system: An evaluation

NASA Technical Reports Server (NTRS)

Connors, M. M.; Lindsey, G.; Miller, R. H.

1976-01-01

The communication requirements of the Apollo project led to the development of a teleconferencing network which linked together, in an audio-fax mode, the several NASA centers and supporting contractors of the Apollo project. The usefulness of this communication linkage for the Apollo project suggested that the system might be extended to include all NASA centers, enabling them to conduct their in-house business more efficiently than by traveling to other centers. A pilot project was run in which seventeen NASA center and subcenters, some with multiple facilities, were connected into the NASA teleconferencing network. During that year, costs were charted and, at the end of the year, an evaluation was made to determine how the system had been used and with what results. The year-end evaluation of the use of NASA teleconferencing system is summarized.

Test and Evaluation of the Surveyor 3 Television Camera Returned from the Moon by Apollo 12. Volume 1

NASA Technical Reports Server (NTRS)

1970-01-01

Results are presented of engineering tests of the Surveyor III television camera, which resided on the moon for 2 and 1/2 years before being brought back to earth by the Apollo XII astronauts. Electric circuits, electrical, mechanical, and optical components and subsystems, the vidicon tube, and a variety of internal materials and surface coatings were examined to determine the effects of lunar exposure. Anomalies and failures uncovered were analyzed. For the most part, the camera parts withstood the extreme environment exceedingly well except where degradation of obsolete parts or suspect components had been anticipated. No significant evidence of cold welding was observed, and the anomalies were largely attributable to causes other than lunar exposure. Very little evidence of micrometeoroid impact was noted. Discoloration of material surfaces -- one of the major effects noted--was found to be due to lunar dust contamination and radiation damage. The extensive test data contained in this report are supplemented by results of tests of other Surveyor parts retrieved by the Apollo XII astronauts, which are contained in a companion report.

JPEG2000 still image coding quality.

PubMed

Chen, Tzong-Jer; Lin, Sheng-Chieh; Lin, You-Chen; Cheng, Ren-Gui; Lin, Li-Hui; Wu, Wei

2013-10-01

This work demonstrates the image qualities between two popular JPEG2000 programs. Two medical image compression algorithms are both coded using JPEG2000, but they are different regarding the interface, convenience, speed of computation, and their characteristic options influenced by the encoder, quantization, tiling, etc. The differences in image quality and compression ratio are also affected by the modality and compression algorithm implementation. Do they provide the same quality? The qualities of compressed medical images from two image compression programs named Apollo and JJ2000 were evaluated extensively using objective metrics. These algorithms were applied to three medical image modalities at various compression ratios ranging from 10:1 to 100:1. Following that, the quality of the reconstructed images was evaluated using five objective metrics. The Spearman rank correlation coefficients were measured under every metric in the two programs. We found that JJ2000 and Apollo exhibited indistinguishable image quality for all images evaluated using the above five metrics (r > 0.98, p < 0.001). It can be concluded that the image quality of the JJ2000 and Apollo algorithms is statistically equivalent for medical image compression.

Telomeric 3' overhangs derive from resection by Exo1 and Apollo and fill-in by POT1b-associated CST.

PubMed

Wu, Peng; Takai, Hiroyuki; de Lange, Titia

2012-07-06

A 3' overhang is critical for the protection and maintenance of mammalian telomeres, but its synthesis must be regulated to avoid excessive resection of the 5' end, which could cause telomere shortening. How this balance is achieved in mammals has not been resolved. Here, we determine the mechanism for 3' overhang synthesis in mouse cells by evaluating changes in telomeric overhangs throughout the cell cycle and at leading- and lagging-end telomeres. Apollo, a nuclease bound to the shelterin subunit TRF2, initiates formation of the 3' overhang at leading-, but not lagging-end telomeres. Hyperresection by Apollo is blocked at both ends by the shelterin protein POT1b. Exo1 extensively resects both telomere ends, generating transient long 3' overhangs in S/G2. CST/AAF, a DNA polα.primase accessory factor, binds POT1b and shortens the extended overhangs produced by Exo1, likely through fill-in synthesis. 3' overhang formation is thus a multistep, shelterin-controlled process, ensuring functional telomeric overhangs at chromosome ends. Copyright © 2012 Elsevier Inc. All rights reserved.

On the Application of a Response Surface Technique to Analyze Roll-over Stability of Capsules with Airbags Using LS-Dyna

NASA Technical Reports Server (NTRS)

Horta, Lucas G.; Reaves, Mercedes C.

2008-01-01

As NASA moves towards developing technologies needed to implement its new Exploration program, studies conducted for Apollo in the 1960's to understand the rollover stability of capsules landing are being revisited. Although rigid body kinematics analyses of the roll-over behavior of capsules on impact provided critical insight to the Apollo problem, extensive ground test programs were also used. For the new Orion spacecraft being developed to implement today's Exploration program, new air-bag designs have improved sufficiently for NASA to consider their use to mitigate landing loads to ensure crew safety and to enable re-usability of the capsule. Simple kinematics models provide only limited understanding of the behavior of these air bag systems, and more sophisticated tools must be used. In particular, NASA and its contractors are using the LS-Dyna nonlinear simulation code for impact response predictions of the full Orion vehicle with air bags by leveraging the extensive air bag prediction work previously done by the automotive industry. However, even in today's computational environment, these analyses are still high-dimensional, time consuming, and computationally intensive. To alleviate the computational burden, this paper presents an approach that uses deterministic sampling techniques and an adaptive response surface method to not only use existing LS-Dyna solutions but also to interpolate from LS-Dyna solutions to predict the stability boundaries for a capsule on airbags. Results for the stability boundary in terms of impact velocities, capsule attitude, impact plane orientation, and impact surface friction are discussed.

Review of Vedder pool development, Kern River field, Kern County, California

DOE Office of Scientific and Technical Information (OSTI.GOV)

Condon, M.W.

1986-07-01

The Kern River field is located on the east side of the San Joaquin Valley, just north of Bakersfield, California. Since its discovery in 1899, the field has produced over 1 billion bbl of heavy oil from the Kern River Formation. It was not until 1981 that light oil was discovered from a deeper zone, the Vedder formation. The discovery well, Getty Oil Company WD-1 Apollo, encountered 40 ft of net oil sand within the third Vedder sand and was completed on pump for an initial production of 100 bbl of 40.5/sup 0/ API oil and 200 MCDGD. As suggestedmore » by its name, WD-1 Apollo was drilled as a water-water injection wells. However, a detailed subsurface study of the field suggested the possibility of a trap within the Vedder formation. The originally proposed location of WD-1 Apollo was then moved to test the proposal. The trap is a series of intersecting, up-to-the-basin normal faults trending west and northwest. These faults have dropped impermeable silty zones within the Vedder formation against the productive Vedder sands. Since the completion of WD-1 Apollo, nine other wells have been drilled within this pool, extending production over 1 mi to the southeast. One of the first of the extension wells, Getty Oil Company 73X Central Point, located approximately 600 ft southeast of WD-1 Apollo, established production from the second Vedder sand. This well was completed flowing 300 b/d of 32/sup 0/ API oil and 1000 MCFGD through a 16/64-in. choke. Through December 1985, Texaco (Getty Oil) produced more than 250,000 bbl of oil and 350,000 mcf of gas combined from the second and third Vedder sands from 2.5 net wells. Although attempts to find other such Vedder pools have met with limited success, there is still the potential for many to exist, given proper structural closure, as seen in the Apollo pool.« less

Apollo Spacecraft and Saturn V Launch Vehicle Pyrotechnics/Explosive Devices

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

The Apollo Mission employs more than 210 pyrotechnic devices per mission.These devices are either automatic of commanded from the Apollo spacecraft systems. All devices require high reliability and safety and most are classified as either crew safety critical or mission critical. Pyrotechnic devices have a wide variety of applications including: launch escape tower separation, separation rocket ignition, parachute deployment and release and electrical circuit opening and closing. This viewgraph presentation identifies critical performance, design requirements and safety measures used to ensure quality, reliability and performance of Apollo pyrotechnic/explosive devices. The major components and functions of a typical Apollo pyrotechnic/explosive device are listed and described (initiators, cartridge assemblies, detonators, core charges). The presentation also identifies the major locations and uses for the devices on: the Command and Service Module, Lunar Module and all stages of the launch vehicle.

Apollo Portable Life Support System

NASA Image and Video Library

1968-06-11

S68-34580 (1968) --- With its exterior removed, the Apollo portable life support system (PLSS) can be easily studied. The PLSS is worn as a backpack over the Extravehicular Mobility Unit (EMU), a multi-layered spacesuit used for outside-the-spacecraft activity. JSC photographic frame no. S68-34582 is a close-up view of the working parts of the PLSS.

Apollo experience report: Guidance and control systems. Engineering simulation program

NASA Technical Reports Server (NTRS)

Gilbert, D. W.

1973-01-01

The Apollo Program experience from early 1962 to July 1969 with respect to the engineering-simulation support and the problems encountered is summarized in this report. Engineering simulation in support of the Apollo guidance and control system is discussed in terms of design analysis and verification, certification of hardware in closed-loop operation, verification of hardware/software compatibility, and verification of both software and procedures for each mission. The magnitude, time, and cost of the engineering simulations are described with respect to hardware availability, NASA and contractor facilities (for verification of the command module, the lunar module, and the primary guidance, navigation, and control system), and scheduling and planning considerations. Recommendations are made regarding implementation of similar, large-scale simulations for future programs.

Apollo 16 mission Report. Supplement 1: Apollo 16 guidance, navigation, and control system performance analysis report

NASA Technical Reports Server (NTRS)

1972-01-01

The results are reported of additional studies which were conducted to supplement conclusions drawn in the MSC Mission Report and analyses which were not completed in time to meet the Mission Report dealine. A detailed evaluation of the Abort Guidance System sensor assembly and results from the investigation of the X gyro loop anomaly are included. Further evidence is presented substantiating the excellent LM IMU performance obtained from preliminary indications. A detailed study is presented of the procedural changes implemented on Apollo 16 to diminish the number and duration of interruptions to the CSM DAP attitude maneuver during P20 Option 5 operations.

Multispectral studies of western limb and farside maria from Galileo Earth-Moon Encounter 1

NASA Astrophysics Data System (ADS)

Williams, David A.; Greeley, Ronald; Neukum, Gerhard; Wagner, Roland; Kadel, Steven D.

1995-11-01

New visible and near-infrared multispectral images of the Moon obtained by the Galileo solid-state imaging system, along with lunar orbiter images (for crater counts), and spectral mixing analyses were used to characterize western limb and eastern farside maria and determine compositional and age relationships in selected regions. Results indicate that (1) western limb mare deposits have less variability in titanium content (<2-7 wt% TiO2) and age (2.79-3.86 Ga) than areally extensive maria on the nearside; (2) areally extensive basin-filling maria generally have higher titanium contents than smaller, crater-filling mare patches and ponds; (3) ancient maria covered by highland material (cryptomaria) may be present in the Mendel-Rydberg and South Pole-Aitken basins; and (4) maria with compositional and age variations occur in the Grimaldi, Crüger, Mendel-Rydberg, and Apollo regions. No extensive high-titanium (>6 wt% TiO2) mare basalts were observed on the western limb and farside, which may reflect the inability of such denser magmas to penetrate the thicker farside crust.

A review of cryogenic testing performed by the thermochemical test branch, Manned Spacecraft Center in support of Apollo 13 and14

NASA Technical Reports Server (NTRS)

Propp, C. E.; Mcgee, J. M.

1971-01-01

The Apollo 13 anomaly provided considerable impetus for a variety of types of cryogenic and ignition tests. The logic of the various test program designs, the test techniques, and their final impact upon the investigation findings are described. In addition, several test programs initiated to determine the thermal performance and general performance characteristics of the redesigned Apollo 14 cryogenic storage system are presented.

A thermal scale modeling study for Apollo and Apollo applications, volume 2

NASA Technical Reports Server (NTRS)

Shannon, R. L.

1972-01-01

The development and demonstration of practical thermal scale modeling techniques applicable to systems involving radiation, conduction, and convection with emphasis on cabin atmosphere/cabin wall thermal interface are discussed. The Apollo spacecraft environment is used as the model. Four possible scaling techniques were considered: (1) modified material preservation, (2) temperature preservation, (3) scaling compromises, and Nusselt number preservation. A thermal mathematical model was developed for use with the Nusselt number preservation technique.

Autonomous Navigation Error Propagation Assessment for Lunar Surface Mobility Applications

NASA Technical Reports Server (NTRS)

Welch, Bryan W.; Connolly, Joseph W.

2006-01-01

The NASA Vision for Space Exploration is focused on the return of astronauts to the Moon. While navigation systems have already been proven in the Apollo missions to the moon, the current exploration campaign will involve more extensive and extended missions requiring new concepts for lunar navigation. In this document, the results of an autonomous navigation error propagation assessment are provided. The analysis is intended to be the baseline error propagation analysis for which Earth-based and Lunar-based radiometric data are added to compare these different architecture schemes, and quantify the benefits of an integrated approach, in how they can handle lunar surface mobility applications when near the Lunar South pole or on the Lunar Farside.

Energy Expenditure During Extravehicular Activity: Apollo Skylab Through STS-135

NASA Technical Reports Server (NTRS)

Paul, Heather L.

2011-01-01

The importance of real-time metabolic rate monitoring during extravehicular activities (EVAs) came into question during the Gemini missions, when the energy expenditure required to conduct an EVA over-tasked the crewmember and exceeded the capabilities of vehicle and space suit life support systems. Energy expenditure was closely evaluated through the Apollo lunar surface EVAs, resulting in modifications to space suit design and EVA operations. After the Apollo lunar surface missions were completed, the United States shifted its focus to long duration human space flight, to study the human response to living and working in a microgravity environment. This paper summarizes the energy expenditure during EVA from Apollo Skylab through STS-135.

KSC-2015-1180

NASA Image and Video Library

2015-01-27

CAPE CANAVERAL, Fla. – The past intersects with the future on Cape Canaveral Air Force Station in Florida. In the foreground is what remains of historic Launch Pad 34 in the distance behind it is Space Launch Complex 37 whence NASA's Orion spacecraft made its first flight test. On this day in 1967, a fire erupted on the Pad 34 during a preflight test, taking the lives of the Apollo 1 crew, NASA astronauts Virgil Grissom, Edward White and Roger Chaffee. To learn more about Apollo 1 and the crew, visit http://www.nasa.gov/mission_pages/apollo/missions/apollo1.html. To learn more about Orion, visit http://www.nasa.gov/exploration/systems/orion/. Photo credit: NASA/Ben Smegelsky

KSC-2015-1181

NASA Image and Video Library

2015-01-27

CAPE CANAVERAL, Fla. – The past intersects with the future on Cape Canaveral Air Force Station in Florida. In the foreground is what remains of historic Launch Pad 34 in the distance behind it is Space Launch Complex 37 whence NASA's Orion spacecraft made its first flight test. On this day in 1967, a fire erupted on the Pad 34 during a preflight test, taking the lives of the Apollo 1 crew, NASA astronauts Virgil Grissom, Edward White and Roger Chaffee. To learn more about Apollo 1 and the crew, visit http://www.nasa.gov/mission_pages/apollo/missions/apollo1.html. To learn more about Orion, visit http://www.nasa.gov/exploration/systems/orion/. Photo credit: NASA/Ben Smegelsky

Intra-Extra Vehicular Activity Apollo Spacesuits

NASA Technical Reports Server (NTRS)

Thomas, Kenneth S.

2016-01-01

Kenneth Thomas will discuss the Apollo Intra-Extra Vehicular Activity (IEVA) spacesuits, which supported launch and reentry and extra-vehicular activity. This program was NASA's first attempt to develop a new suit design from requirements and concepts. Mr. Thomas will chronicle the challenges, developments, struggles, and solutions that culminated in the system that allowed the first human exploration of the Moon and deep space (outside low-Earth orbit). Apollo pressure suit designs allowed the heroic repair of the Skylab space station and supported the first U.S. and Russian spacecraft docking during the Apollo Soyuz Test Project. Mr. Thomas will also discuss the IEVA suits' successes and challenges associated with the IEVA developments of the 1960s.

Apollo 8 Mission Report

NASA Technical Reports Server (NTRS)

1969-01-01

Postflight analysis of Apollo 8 mission. Apollo 8 was the second manned flight in the program and the first manned lunar orbit mission. The crew were Frank Borman, Commander; James A. Lovell, Command Module Pilot; and William A. Anders, Lunar Module Pilot. The Apollo 8 space vehicle was launched on time from Kennedy Space Center, Florida, at 7:51:00 AM, EST, on December 21, 1968. Following a nominal boost phase, the spacecraft and S-IVB combination was inserted - into a parking orbit of 98 by 103 nautical miles. After a post-insertion checkout of spacecraft systems, the 319-second translunar injection maneuver was initiated at 2:50:37 by reignition of the S-IVB engine.

Apollo management: A key to the solution of the social-economical dilemma - The transferability of space-travel managerial techniques to the civil sector

NASA Technical Reports Server (NTRS)

Puttkamer, J. V.

1973-01-01

An analysis has been conducted to find out whether the management techniques developed in connection with the Apollo project could be used for dealing with such urgent problems of modern society as the crisis of the cities, the increasing environmental pollution, and the steadily growing traffic. Basic concepts and definitions of program and system management are discussed together with details regarding the employment of these concepts in connection with the solution of the problems of the Apollo program. Principles and significance of a systems approach are considered, giving attention to planning, system analysis, system integration, and project management. An application of the methods of project management to the problems of the civil sector is possible if the special characteristics of each particular case are taken into account.

Apollo Soyuz, mission evaluation report

NASA Technical Reports Server (NTRS)

1975-01-01

The Apollo Soyuz mission was the first manned space flight to be conducted jointly by two nations - the United States and the Union of Soviet Socialist Republics. The primary purpose of the mission was to test systems for rendezvous and docking of manned spacecraft that would be suitable for use as a standard international system, and to demonstrate crew transfer between spacecraft. The secondary purpose was to conduct a program of scientific and applications experimentation. With minor modifications, the Apollo and Soyuz spacecraft were like those flown on previous missions. However, a new module was built specifically for this mission - the docking module. It served as an airlock for crew transfer and as a structural base for the docking mechanism that interfaced with a similar mechanism on the Soyuz orbital module. The postflight evaluation of the performance of the docking system and docking module, as well as the overall performance of the Apollo spacecraft and experiments is presented. In addition, the mission is evaluated from the viewpoints of the flight crew, ground support operations, and biomedical operations. Descriptions of the docking mechanism, docking module, crew equipment and experiment hardware are given.

Reliability history of the Apollo guidance computer

NASA Technical Reports Server (NTRS)

Hall, E. C.

1972-01-01

The Apollo guidance computer was designed to provide the computation necessary for guidance, navigation and control of the command module and the lunar landing module of the Apollo spacecraft. The computer was designed using the technology of the early 1960's and the production was completed by 1969. During the development, production, and operational phase of the program, the computer has accumulated a very interesting history which is valuable for evaluating the technology, production methods, system integration, and the reliability of the hardware. The operational experience in the Apollo guidance systems includes 17 computers which flew missions and another 26 flight type computers which are still in various phases of prelaunch activity including storage, system checkout, prelaunch spacecraft checkout, etc. These computers were manufactured and maintained under very strict quality control procedures with requirements for reporting and analyzing all indications of failure. Probably no other computer or electronic equipment with equivalent complexity has been as well documented and monitored. Since it has demonstrated a unique reliability history, it is important to evaluate the techniques and methods which have contributed to the high reliability of this computer.

Fly-by-Wire Systems Enable Safer, More Efficient Flight

NASA Technical Reports Server (NTRS)

2012-01-01

Using the ultra-reliable Apollo Guidance Computer that enabled the Apollo Moon missions, Dryden Flight Research Center engineers, in partnership with industry leaders such as Cambridge, Massachusetts-based Draper Laboratory, demonstrated that digital computers could be used to fly aircraft. Digital fly-by-wire systems have since been incorporated into large airliners, military jets, revolutionary new aircraft, and even cars and submarines.

Apollo Portable Life Support System

NASA Image and Video Library

1968-06-11

S68-34582 (1968) --- With its exterior removed, the Apollo portable life support system (PLSS) can be easily studied. The PLSS is worn as a backpack over the Extravehicular Mobility Unit (EMU) a multi-layered spacesuit used for outside-the-spacecraft activity. JSC photographic frame no. S68-34582 is a wider view of the exposed interior working parts of the PLSS and its removed cover.

STS-32 view of the moon setting over the Earth's limb

NASA Image and Video Library

1990-01-20

STS-32 crew took this view of the moon setting over the Earth's limb. Near the center is a semi-vortex in the clouds - a storm system in the early stages of formation. The moon's image is distorted due to refraction through the Earth's atmosphere. The near side of the moon is visible showing the vast area of the moon's western seas (Mare Occidental), Apollo landing sites: Apollo 14 at Fra Mauro and Apollo 16 at Central Highlands near Descartes.

STS-32 view of the moon setting over the Earth's limb

NASA Technical Reports Server (NTRS)

1990-01-01

STS-32 crew took this view of the moon setting over the Earth's limb. Near the center is a semi-vortex in the clouds - a storm system in the early stages of formation. The moon's image is distorted due to refraction through the Earth's atmosphere. The near side of the moon is visible showing the vast area of the moon's western seas (Mare Occidental), Apollo landing sites: Apollo 14 at Fra Mauro and Apollo 16 at Central Highlands near Descartes.

Distribution of inert gases in fines from the Cayley-Descartes region

NASA Technical Reports Server (NTRS)

Walton, J. R.; Lakatos, S.; Heymann, D.

1973-01-01

The inert gases in 14 different fines and in one sample of 2 to 4 mm fines from Apollo 16 were measured by mass spectroscopy with respect to trapped solar wind gases, cosmogenic gases, and 'parentless' Ar-40. Such studies are helpful for the understanding of regolith evolution, of transport of regolith fines, and of the lunar atmosphere. The Apollo 16 soils are unique because they represent, after Luna 20, the second and much more extensive record from the lunar highlands. The landing site presents the problem of materials from the Cayley Formation vs those from the Descartes Formation. There are two large, relatively fresh craters in the area, North Ray and South Ray, whose ejecta patterns may be recognized in the inert-gas record.

Some thoughts on the origin of lunar ANT-KREEP and mare basalts

NASA Technical Reports Server (NTRS)

Wakita, H.; Laul, J. C.; Schmitt, R. A.

1975-01-01

It is suggested that a series of ANT (anorthosite-norite-troctolite)-KREEP type rocks and the source material for mare basalts sampled by Apollo 11, 12, 15, and 17 may have been derived from a common magmatic differentiation. This differentiation is studied on the basis of a model which proposes that, in the early history of the moon, extensive melting occurred in the outer lunar shell and a magma layer of 100-200 km was formed. The presence of a residual liquid which has not yet been sampled is suspected between high-K KREEP and the Apollo 11 basalt materials. This residual liquid would have a FeO/MgO ratio greater than one and would be significantly enriched in apatite, zircon, K-feldspar, and ilmenite minerals.

Saturn Apollo Program

NASA Image and Video Library

1967-03-01

The Saturn V configuration is shown in inches and meters as illustrated by the Boeing Company. The Saturn V vehicle consisted of three stages: the S-IC (first) stage powered by five F-1 engines, the S-II (second) stage powered by five J-2 engines, the S-IVB (third) stage powered by one J-2 engine. A top for the first three stages was designed to contain the instrument unit, the guidance system, the Apollo spacecraft, and the escape system. The Apollo spacecraft consisted of the lunar module, the service module, and the command module. The Saturn V was designed perform lunar and planetary missions and it was capable of placing 280,000 pounds into Earth orbit.

Apollo experience report: Launch escape propulsion subsystem

NASA Technical Reports Server (NTRS)

Townsend, N. A.

1973-01-01

The Apollo launch escape propulsion subsystem contained three solid rocket motors. The general design, development, and qualification of the solid-propellant pitch-control, tower-jettison, and launch-escape motors of the Apollo launch escape propulsion subsystem were completed during years 1961 to 1966. The launch escape system components are described in general terms, and the sequence of events through the ground-based test programs and flight-test programs is discussed. The initial ground rules established for this system were that it should use existing technology and designs as much as possible. The practicality of this decision is proved by the minimum number of problems that were encountered during the development and qualification program.

Spacecraft Conceptual Design Compared to the Apollo Lunar Lander

NASA Technical Reports Server (NTRS)

Young, C.; Bowie, J.; Rust, R.; Lenius, J.; Anderson, M.; Connolly, J.

2011-01-01

Future human exploration of the Moon will require an optimized spacecraft design with each sub-system achieving the required minimum capability and maintaining high reliability. The objective of this study was to trade capability with reliability and minimize mass for the lunar lander spacecraft. The NASA parametric concept for a 3-person vehicle to the lunar surface with a 30% mass margin totaled was considerably heavier than the Apollo 15 Lunar Module "as flown" mass of 16.4 metric tons. The additional mass was attributed to mission requirements and system design choices that were made to meet the realities of modern spaceflight. The parametric tool used to size the current concept, Envision, accounts for primary and secondary mass requirements. For example, adding an astronaut increases the mass requirements for suits, water, food, oxygen, as well as, the increase in volume. The environmental control sub-systems becomes heavier with the increased requirements and more structure was needed to support the additional mass. There was also an increase in propellant usage. For comparison, an "Apollo-like" vehicle was created by removing these additional requirements. Utilizing the Envision parametric mass calculation tool and a quantitative reliability estimation tool designed by Valador Inc., it was determined that with today?s current technology a Lunar Module (LM) with Apollo capability could be built with less mass and similar reliability. The reliability of this new lander was compared to Apollo Lunar Module utilizing the same methodology, adjusting for mission timeline changes as well as component differences. Interestingly, the parametric concept's overall estimated risk for loss of mission (LOM) and loss of crew (LOC) did not significantly improve when compared to Apollo.

Apollo 15 mission report, supplement 4: Descent propulsion system final flight evaluation

NASA Technical Reports Server (NTRS)

Avvenire, A. T.; Wood, S. C.

1972-01-01

The results of a postflight analysis of the LM-10 Descent Propulsion System (DPS) during the Apollo 15 Mission are reported. The analysis determined the steady state performance of the DPS during the descent phase of the manned lunar landing. Flight measurement discrepancies are discussed. Simulated throttle performance results are cited along with overall performance results. Evaluations of the propellant quantity gaging system, propellant loading, pressurization system, and engine are reported. Graphic illustrations of the evaluations are included.

Analysis of the Apollo spacecraft operational data management system. Executive summary

NASA Technical Reports Server (NTRS)

1971-01-01

A study was made of Apollo, Skylab, and several other data management systems to determine those techniques which could be applied to the management of operational data for future manned spacecraft programs. The results of the study are presented and include: (1) an analysis of present data management systems, (2) a list of requirements for future operational data management systems, (3) an evaluation of automated data management techniques, and (4) a plan for data management applicable to future space programs.

Restoration and Reexamination of Apollo Lunar Dust Detector Data from Original Telemetry Files

NASA Technical Reports Server (NTRS)

McBride, M. J.; Williams, David R.; Hills, H. Kent

2012-01-01

We are recovering the original telemetry (Figure I) from the Apollo Dust, Thermal, Radiation Environment Monitor (DTREM) experiment, more commonly known as the Dust Detector, and producing full time resolution (54 second) data sets for release through the Planetary Data System (PDS). The primary objective of the experiment was to evaluate the effect of dust deposition, temperature, and radiation damage on solar cells on the lunar surface. The monitor was a small box consisting of three solar cells and thermistors mounted on the ALSEP (Apollo Lunar Surface Experiments Package) central station. The Dust Detector was carried on Apollo's 11, 12, 14 and 15. The Apollo 11 DTREM was powered by solar cells and only operated for a few months as planned. The Apollo 12, 14, and 15 detectors operated for 5 to 7 years, returning data every 54 seconds, consisting of voltage outputs from the three solar cells and temperatures measured by the three thermistors. The telemetry was received at ground stations and held on the Apollo Housekeeping (known as "Word 33") tapes. made available to the National Space Science Data Center (NSSDC) by Yosio Nakamura (University of Texas Institute for Geophysics). We have converted selected parts of the telemetry into uncalibrated and calibrated output voltages and temperatures.

Revolution in Field Science: Apollo Approach to Inaccessible Surface Exploration

NASA Astrophysics Data System (ADS)

Clark, P. E.

2010-07-01

The extraordinary challenge mission designers, scientists, and engineers, faced in planning the first human expeditions to the surface of another solar system body led to the development of a distinctive and even revolutionary approach to field work. Not only were those involved required to deal effectively with the extreme limitation in resources available for and access to a target as remote as the lunar surface; they were required to developed a rigorous approach to science activities ranging from geological field work to deploying field instruments. Principal aspects and keys to the success of the field work are discussed here, including the highly integrated, intensive, and lengthy science planning, simulation, and astronaut training; the development of a systematic scheme for description and documentation of geological sites and samples; and a flexible yet disciplined methodology for site documentation and sample collection. The capability for constant communication with a ‘backroom’ of geological experts who make requests and weigh in on surface operations was innovative and very useful in encouraging rapid dissemination of information to the greater community in general. An extensive archive of the Apollo era science activity related documents provides evidence of the principal aspects and keys to the success of the field work. The Apollo Surface Journal allows analysis of the astronaut’s performance in terms of capability for traveling on foot, documentation and sampling of field stations, and manual operation of tools and instruments, all as a function of time. The application of these analysis as ‘lessons learned’ for planning the next generation of human or robotic field science activities on the Moon and elsewhere are considered here as well.

Liftoff of the Apollo 11 lunar landing mission

NASA Image and Video Library

1969-07-16

S69-39958 (16 July 1969) --- A 70mm Airborne Lightweight Optical Tracking System (ALOTS) camera, mounted in a pod on a cargo door of a U.S. Air Force EC-135N aircraft, photographed this event in the early moments of the Apollo 11 launch. The mated Apollo spacecraft and Saturn V second (S-II) and third (S-IVB) stages pull away from the expended first (S-1C) stage. Separation occurred at an altitude of about 38 miles, some 55 miles downrange from Cape Kennedy. The aircraft's pod is 20 feet long and 5 feet in diameter. The crew of the Apollo 11 lunar landing mission are astronauts Neil A. Armstrong, Michael Collins, and Edwin E. Aldrin Jr.

Apollo Medical Operations Project: Recommendations for EVA and Lunar Surface Operations

NASA Technical Reports Server (NTRS)

Scheuring, R. A.; Davis, J. R.; Duncan, J. M.; Polk, J. D.; Jones, J. A.; Gillis, D. B.; Novak, J.

2013-01-01

The potential risk of injury to crewmembers is inherent in aggressive surface activities, whether they be Moon-, Mars-, or asteroid-based. In December 2005, the Space Medicine Division at JSC requested a study to identify Apollo mission issues that had an impact to crew health or performance or both. This talk focused on the Apollo EVA suit and lunar surface operations concerning crew health and performance. There were roughly 20 recommendations from this study of Apollo for improving these two areas for future exploration missions, a few of which were incorporated into the Human Systems Integration Requirements (HSIR). Dr. Richard Scheuring covered these topics along with some of the analog work that has been done regarding surface operations and medical contingencies.

Saturn Apollo Program

NASA Image and Video Library

1968-03-03

The launch of the Apollo 9 (Saturn V launch vehicle, SA-504), with astronauts James A. McDivitt, David R. Scott, and Russell L. Schweickart, took place on March 3, 1968. The Apollo 9 spacecraft, in the lunar mission configuration, was tested in Earth orbit. The mission was designed to rehearse all the steps and reproduce all the events of the Apollo 11 mission with the exception of the lunar touchdown, stay, and liftoff. The command and service modules, and the lunar module were used in flight procedures identical to those that would later take similar vehicles to the Moon, and a landing. The flight mechanics, mission support systems, communications, and recording of data were tested in a final round of verification. Astronauts Scott and Schweickart conducted Extravehicular Activity during this mission.

Apollo experience report: Apollo lunar surface experiments package data processing system

NASA Technical Reports Server (NTRS)

Eason, R. L.

1974-01-01

Apollo Program experience in the processing of scientific data from the Apollo lunar surface experiments package, in which computers and associated hardware and software were used, is summarized. The facility developed for the preprocessing of the lunar science data is described, as are several computer facilities and programs used by the Principal Investigators. The handling, processing, and analyzing of lunar science data and the interface with the Principal Investigators are discussed. Pertinent problems that arose in the development of the data processing schemes are discussed so that future programs may benefit from the solutions to the problems. The evolution of the data processing techniques for lunar science data related to recommendations for future programs of this type.

Magnesian anorthosites and a deep crustal rock from the farside crust of the moon

NASA Astrophysics Data System (ADS)

Takeda, Hiroshi; Yamaguchi, A.; Bogard, D. D.; Karouji, Y.; Ebihara, M.; Ohtake, M.; Saiki, K.; Arai, T.

2006-07-01

Among over thirty lunar meteorites recovered from the hot deserts and Antarctica, Dhofar 489 is the most depleted in thorium (0.05 ppm), FeO, and rare earth elements (REE). Dhofar 489 is a crystalline matrix anorthositic breccia and includes clasts of magnesian anorthosites and a spinel troctolite. The Mg / (Mg + Fe) mol% (Mg numbers = 75-85) of olivine and pyroxene grains in this meteorite are higher than those of the Apollo ferroan anorthosites. Such materials were not recovered by the Apollo and Luna missions. However, remote sensing data suggest that the estimated concentrations of Th and FeO are consistent with the presence of such samples on the farside of the Moon. The differentiation trend deduced from the mineralogy of the anorthositic clasts define a magnesian extension of the ferroan anorthosite (FAN) trend constructed from the Apollo samples. The presence of magnesian anorthositic clasts in Dhofar 489 still offers a possibility that the farside trend with magnesian compositions is more primitive than the FAN trend, and may require a revision of this classical differentiation trend. The Ar-Ar age of Dhofar 489 is 4.23 ± 0.034 Gyr, which is older than most Ar ages reported for highland rocks returned by Apollo. The old Ar-Ar age of impact formation of this breccia and the presence of a fragment of spinel troctolite of deep crustal origin suggest that a basin forming event on the farside excavated the deep crust and magnesian anorthosites before formation of Imbrium.

Launch Vehicle Flight Report - Nasa Project Apollo Little Joe 2 Qualification Test Vehicle 12-50-1

NASA Technical Reports Server (NTRS)

1963-01-01

The Little Joe II Qualification Test Vehicle, Model 12-50-1, was launched from Army Launch Area 3 {ALA-3) at White Sands Missile Range, New Mexico, on 28 August 1963. This was the first launch of this class of boosters. The Little Joe II Launch Vehicle was designed as a test vehicle for boosting payloads into flight. For the Apollo Program, its mission is to serve as a launch vehicle for flight testing of the Apollo spacecraft. Accomplishment of this mission requires that the vehicle be capable of boosting the Apollo payload to parameters ranging from high dynamic pressures at low altitude to very high altitude flight. The fixed-fin 12-50 version was designed to accomplish the low-altitude parameter. The 12-51 version incorporates an attitude control system to accomplish the high altitude mission. This launch was designed to demonstrate the Little Joe II capability of meeting the high dynamic pressure parameter for the Apollo Program. For this test, a boiler-plate version of the Apollo capsule, service module and escape tower were attached to the launch vehicle to simulate weight, center of gravity and aerodynamic shape of the Apollo configuration. No attempt was made to separate the payload in flight. The test was conducted in compliance with Project Apollo Flight Mission Directive for QTV-1, NASA-MSC, dated 3 June 1963, under authority of NASA Contract NAS 9-492,

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Apollo astronauts from left, Walt Cunningham (Apollo 17), James Lovell (Apollo 8 Apollo 13), David Scott (Apollo 9 Apollo 15), Buzz Aldrin (Apollo 11), Charles Duke (Apollo 16), Thomas Stafford (Apollo 10) and Eugene Cernan (Apollo 17) are seen during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Apollo experience report: Real-time display system

NASA Technical Reports Server (NTRS)

Sullivan, C. J.; Burbank, L. W.

1976-01-01

The real time display system used in the Apollo Program is described; the systematic organization of the system, which resulted from hardware/software trade-offs and the establishment of system criteria, is emphasized. Each basic requirement of the real time display system was met by a separate subsystem. The computer input multiplexer subsystem, the plotting display subsystem, the digital display subsystem, and the digital television subsystem are described. Also described are the automated display design and the generation of precision photographic reference slides required for the three display subsystems.

International, private-public, multi-mission, next-generation Lunar/Martian laser retroreflectors

NASA Astrophysics Data System (ADS)

Dellagnello, S.

2017-09-01

We describe an international, private-public, multi-mission effort to deploy on the Moon next-generation lunar laser retroreflectors to extend (also to the far side) the existing passive Lunar Geophysical Network (LNG) consisting of the three Apollo and the two Lunokhod payloads. We also describe important applications and extension of this program to Mars Geophysical Network (MGN).

Apollo 16 Mission: Oxidizer Deservicing Tank Failure. No. 1; Anomaly Report

NASA Technical Reports Server (NTRS)

1972-01-01

An explosive failure of a ground support equipment decontamination unit tank occurred during the postflight deactivation of the oxidizer (nitrogen tetroxide) portion of the Apollo 16 command module reaction control system. A discussion of the significant aspects of the incident and conclusions are included.

Apollo: Changing the Way We Work.

ERIC Educational Resources Information Center

Schroeder, John R.; Bleed, Ron

In January 1994, Arizona's Maricopa Community College District issued a request for proposals to develop new administrative software applications to solve problems related to high maintenance costs for existing systems and difficulties in updating software. The result was the Apollo Project, in which the District contracted with Oracle Corporation…

A gas flow indicator for portable life support systems

NASA Technical Reports Server (NTRS)

Bass, R. L., III; Schroeder, E. C.

1975-01-01

A three-part program was conducted to develop a gas flow indicator (GFI) to monitor ventilation flow in a portable life support system. The first program phase identified concepts which could potentially meet the GFI requirements. In the second phase, a working breadboard GFI, based on the concept of a pressure sensing diaphragm-aneroid assembly connected to a venturi, was constructed and tested. Extensive testing of the breadboard GFI indicated that the design would meet all NASA requirements including eliminating problems experienced with the ventilation flow sensor used in the Apollo program. In the third program phase, an optimized GFI was designed by utilizing test data obtained on the breadboard unit. A prototype unit was constructed using prototype materials and fabrication techniques, and performance tests indicated that the prototype GFI met or exceeded all requirements.

NASA's J-2X Engine Builds on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Snoddy, Jimmy R.

2006-01-01

In January 2006, NASA streamlined its U.S. Vision for Space Exploration hardware development approach for replacing the Space Shuttle after it is retired in 2010. The revised CLV upper stage will use the J-2X engine, a derivative of NASA s Apollo Program Saturn V s S-II and S-IVB main propulsion, which will also serve as the Earth Departure Stage (EDS) engine. This paper gives details of how the J- 2X engine effort mitigates risk by building on the Apollo Program and other lessons learned to deliver a human-rated engine that is on an aggressive development schedule, with first demonstration flight in 2010 and human test flights in 2012. It is well documented that propulsion is historically a high-risk area. NASA s risk reduction strategy for the J-2X engine design, development, test, and evaluation is to build upon heritage hardware and apply valuable experience gained from past development efforts. In addition, NASA and its industry partner, Rocketdyne, which originally built the J-2, have tapped into their extensive databases and are applying lessons conveyed firsthand by Apollo-era veterans of America s first round of Moon missions in the 1960s and 1970s. NASA s development approach for the J-2X engine includes early requirements definition and management; designing-in lessons learned from the 5-2 heritage programs; initiating long-lead procurement items before Preliminary Desi& Review; incorporating design features for anticipated EDS requirements; identifying facilities for sea-level and altitude testing; and starting ground support equipment and logistics planning at an early stage. Other risk reduction strategies include utilizing a proven gas generator cycle with recent development experience; utilizing existing turbomachinery ; applying current and recent main combustion chamber (Integrated Powerhead Demonstrator) and channel wall nozzle (COBRA) advances; and performing rigorous development, qualification, and certification testing of the engine system, with a philosophy of "test what you fly, and fly what you test". These and other active risk management strategies are in place to deliver the J-2X engine for LEO and lunar return missions as outlined in the U.S. Vision for Space Exploration.

Advances in Astromaterials Curation: Supporting Future Sample Return Missions

NASA Technical Reports Server (NTRS)

Evans, C. A.; Zeigler, R. A.; Fries, M. D..; Righter, K.; Allton, J. H.; Zolensky, M. E.; Calaway, M. J.; Bell, M. S.

2015-01-01

NASA's Astromaterials, curated at the Johnson Space Center in Houston, are the most extensive, best-documented, and leastcontaminated extraterrestrial samples that are provided to the worldwide research community. These samples include lunar samples from the Apollo missions, meteorites collected over nearly 40 years of expeditions to Antarctica (providing samples of dozens of asteroid bodies, the Moon, and Mars), Genesis solar wind samples, cosmic dust collected by NASA's high altitude airplanes, Comet Wild 2 and interstellar dust samples from the Stardust mission, and asteroid samples from JAXA's Hayabusa mission. A full account of NASA's curation efforts for these collections is provided by Allen, et al [1]. On average, we annually allocate about 1500 individual samples from NASA's astromaterials collections to hundreds of researchers from around the world, including graduate students and post-doctoral scientists; our allocation rate has roughly doubled over the past 10 years. The curation protocols developed for the lunar samples returned from the Apollo missions remain relevant and are adapted to new and future missions. Several lessons from the Apollo missions, including the need for early involvement of curation scientists in mission planning [1], have been applied to all subsequent sample return campaigns. From the 2013 National Academy of Sciences report [2]: "Curation is the critical interface between sample return missions and laboratory research. Proper curation has maintained the scientific integrity and utility of the Apollo, Antarctic meteorite, and cosmic dust collections for decades. Each of these collections continues to yield important new science. In the past decade, new state-of-the-art curatorial facilities for the Genesis and Stardust missions were key to the scientific breakthroughs provided by these missions." The results speak for themselves: research on NASA's astromaterials result in hundreds of papers annually, yield fundamental discoveries about the evolution of the solar system (e.g. [3] and references contained therein), and serve the global scientific community as ground truth for current and planned missions such as NASA's Dawn mission to Vesta and Ceres, and the future OSIRIS REx mission to asteroid Bennu [1,3

Petrologic comparisons of Cayley and Descartes on the basis of Apollo 16 soils from stations 4 and 11

NASA Technical Reports Server (NTRS)

Basu, A.; Mckay, D. S.

1984-01-01

Petrologic aspects of the Cayley and Descartes formations are reviewed in the light of new data on Apollo 16 soils. Specific comparison of the modal abundances of lithic fragments in drive tube sample 64001/2 from the slopes of Stone Mountain (station 4) and in soil 67941 from the North Ray Crater rim (station 11) shows that melt rocks, especially poikilitic rocks, are more abundant at station 4 than at station 11; the reverse is true for fragmental breccias. Such lithologic differences suggest that stations 4 and 11 do not belong to the same geologic formation. Metamorphosed breccias are pervasive in both the formations and may represent a local component that has been reworked and diluted as fresh materials were added. Lithologic compositions inferred from the study of soil samples are different from lithologic compositions inferred from the study of rake samples or breccia clasts. This difference may be related to a mixing of material of different grain size distributions. The petrology of soils at the Apollo 16 site may not accurately reflect original material associated with either the Descartes or the Cayley formation because of extensive mixing with local material.

Telomeric 3′ overhangs derive from resection by Exo1 and Apollo and fill-in by POT1b-associated CST

PubMed Central

Wu, Peng; Takai, Hiroyuki; de Lange, Titia

2012-01-01

SUMMARY A 3′ overhang is critical for the protection and maintenance of mammalian telomeres. How these overhangs are generated and whether different processing steps modify telomeres synthesized by leading- and lagging-strand DNA replication was not known. Here we evaluate changes in the telomeric overhangs through the cell cycle and at leading- and lagging-end telomeres in mouse cells lacking relevant genes. Apollo, a nuclease bound to the shelterin subunit TRF2, initiated formation of the 3′ overhang at leading-, but not lagging-end telomeres. Hyper-resection by Apollo was blocked at both ends by the shelterin protein POT1b. Exo1 extensively resected both telomere ends, generating long 3′ overhangs that transiently occurred in S/G2. CST/AAF, a DNA polymeraseα. primase accessory factor related to yeast CST, bound POT1b and shortened the extended overhangs produced by Exo1, most likely through fill-in synthesis. The results establish 3′ overhang formation as a multi-step, shelterin-controlled process that ensures functional telomeric overhangs at all chromosome ends. PMID:22748632

Quantitative determination of zero-gravity effects on electronic materials processing germanium crystal growth with simultaneous interface demarcation experiment MA-060, section 5

NASA Technical Reports Server (NTRS)

Gatos, H. C.; Witt, A. F.; Lichtensteiger, M.; Herman, C. J.

1982-01-01

The crystal growth and segregation characteristics of a melt in a directional solidification configuration under near zero g conditions were investigated. The germanium (doped with gallium) system was selected because it was extensively studied on Earth and because it lends itself to a very detailed macroscopic and microscopic characterization. An extensive study was performed of the germanium crystals grown during the Apollo-Soyuz Test Project mission. It was found that single crystal growth was achieved and that the interface demarcation functioned successfully. On the basis of the results obtained to date, there is no indication that convection driven by thermal or surface tension gradients was present in the melt. The gallium segregation, in the absence of gravity, was found to be fundamentally different in its initial and its subsequent stages from that of the ground based tests. None of the existing theoretical models for growth and segregation can account for the observed segregation behavior in the absence of gravity.

Mercury, Skylab, Spacehab, International Space Station: A Continuum

NASA Technical Reports Server (NTRS)

Walker, Charles; Crouch, Roger K.; Binnenbruck, Horsta; Nagaoka, Shunji; Riesselmann, Werner

2000-01-01

We have conducted real research in space. Virtually all that we conducted in the first decade and a half of the space age was government funded and basic research like the carrier vehicles we call satellites and Sputniki, but direction human interaction began with Project Mercury. When the Apollo program ended with success, we got back to research again. Skylab was using Apollo hardware, using Apollo systems in a manner that offered spacious accomodations for researchers. Education began to move into space. This document describes Skylab's role in spaceborne experiments.

View of damaged Apollo 13 Service Module from the Lunar/Command Modules

NASA Image and Video Library

1970-04-17

AS13-58-8464 (17 April 1970) --- This view of the severely damaged Apollo 13 Service Module (SM) was photographed from the Lunar Module/Command Module (LM/CM) following SM jettisoning. Nearest the camera is the Service Propulsion System (SPS) engine and nozzle. An entire SM panel was blown away by the apparent explosion of oxygen tank number two located in Sector 4 of the SM. The apparent rupture of the oxygen tank caused the Apollo 13 crew men to use the Lunar Module (LM) as a "lifeboat".

Apollo experience report: Development of the extravehicular mobility unit

NASA Technical Reports Server (NTRS)

Lutz, C. C.; Stutesman, H. L.; Carson, M. A.; Mcbarron, J. W., II

1975-01-01

The development and performance history of the Apollo extravehicular mobility unit and its major subsystems is described. The three major subsystems, the pressure garment assembly, the portable life-support system, and the oxygen purge system, are defined and described in detail as is the evolutionary process that culminated in each major subsystem component. Descriptions of ground-support equipment and the qualification testing process for component hardware are also presented.

Apollo-Soyuz test project

NASA Technical Reports Server (NTRS)

1975-01-01

Experiments proposed for the Apollo-Soyuz space mission are discussed. Data focus of space processing and manufacturing, earth surveys, and life sciences. Special efforts were made to test the compatibility of the rendezvous and docking systems for manned spacecraft. Mission planning programs, personnel training, and spacecraft modifications for both spacecraft are included.

Capacitance discharge system for ignition of Single Bridge Apollo Standard Initiators (SBASI)

NASA Technical Reports Server (NTRS)

Ward, R. D.

1974-01-01

The design support data developed during the single bridge Apollo standard initiator (SBASI) program are presented. A circuit was designed and bread-board tested to verify operational capabilities of the circuit. Test data, design criteria, weight, and reliability trade-off considerations, and final design recommendations are reported.

Apollo 16 mission report. Supplement 2: Service Propulsion system final flight evaluation

NASA Technical Reports Server (NTRS)

Smith, R. J.; Wood, S. C.

1974-01-01

The Apollo 16 Mission was the sixteenth in a series of flights using Apollo flight hardware and included the fifth lunar landing of the Apollo Program. The Apollo 16 Mission utilized CSM 113 which was equipped with SPS Engine S/N 66 (Injector S/N 137). The engine configuration and expected performance characteristics are presented. Since previous flight results of the SPS have consistently shown the existence of a negative mixture ratio shift, SPS Engine S/N 66 was reorificed to increase the mixture ratio for this mission. The propellant unbalance for the two major engine firings is compared with the predicted unbalance. Although the unbalance at the end of the TEI burn is significantly different than the predicted unbalance, the propellant mixture ratio was well within limits. The SPS performed six burns during the mission, with a total burn duration of 575.3 seconds. The ignition time, burn duration and velocity gain for each of the six SPS burns are reported.

Radiation protection and instrumentation

NASA Technical Reports Server (NTRS)

Bailey, J. V.

1975-01-01

Radiation was found not to be an operational problem during the Apollo program. Doses received by the crewmen of Apollo missions 7 through 17 were small because no major solar-particle events occurred during those missions. One small event was detected by a radiation sensor outside the Apollo 12 spacecraft, but no increase in radiation dose to the crewmen inside the spacecraft was detected. Radiation protection for the Apollo program was focused on both the peculiarities of the natural space radiation environment and the increased prevalence of manmade radiation sources on the ground and onboard the spacecraft. Radiation-exposure risks to crewmen were assessed and balanced against mission gain to determine mission constraints. Operational radiation evaluation required specially designed radiation detection systems onboard the spacecraft in addition to the use of satellite data, solar observatory support, and other liaison. Control and management of radioactive sources and radiation-generating equipment was important in minimizing radiation exposure of ground-support personnel, researchers, and the Apollo flight and backup crewmen.

PDS Archive Release of Apollo 11, Apollo 12, and Apollo 17 Lunar Rock Sample Images

NASA Technical Reports Server (NTRS)

Garcia, P. A.; Stefanov, W. L.; Lofgren, G. E.; Todd, N. S.; Gaddis, L. R.

2013-01-01

Scientists at the Johnson Space Center (JSC) Lunar Sample Laboratory, Information Resources Directorate, and Image Science & Analysis Laboratory have been working to digitize (scan) the original film negatives of Apollo Lunar Rock Sample photographs [1, 2]. The rock samples, and associated regolith and lunar core samples, were obtained during the Apollo 11, 12, 14, 15, 16 and 17 missions. The images allow scientists to view the individual rock samples in their original or subdivided state prior to requesting physical samples for their research. In cases where access to the actual physical samples is not practical, the images provide an alternate mechanism for study of the subject samples. As the negatives are being scanned, they have been formatted and documented for permanent archive in the NASA Planetary Data System (PDS). The Astromaterials Research and Exploration Science Directorate (which includes the Lunar Sample Laboratory and Image Science & Analysis Laboratory) at JSC is working collaboratively with the Imaging Node of the PDS on the archiving of these valuable data. The PDS Imaging Node is now pleased to announce the release of the image archives for Apollo missions 11, 12, and 17.

Lunar Dust on Heat Rejection System Surfaces: Problems and Prospects

NASA Technical Reports Server (NTRS)

Gaier, James R.; Jaworske, Donald A.

2007-01-01

Heat rejection from power systems will be necessary for human and robotic activity on the lunar surface. Functional operation of such heat rejection systems is at risk of degradation as a consequence of dust accumulation. The Apollo astronauts encountered marked degradation of performance in heat rejection systems for the lunar roving vehicle, science packages, and other components. Although ground testing of dust mitigation concepts in support of the Apollo mission identified mitigation tools, the brush concept adopted by the Apollo astronauts proved essentially ineffective. A better understanding of the issues associated with the impact of lunar dust on the functional performance of heat rejection systems and its removal is needed as planning gets underway for human and robotic missions to the Moon. Renewed emphasis must also be placed on ground testing of pristine and dust-covered heat rejection system surfaces to quantify degradation and address mitigation concepts. This paper presents a review of the degradation in performance of heat rejection systems encountered on the lunar surface to-date, and will discuss current activities underway to evaluate the durability of candidate heat rejection system surfaces and current dust mitigation concepts.

LRO Finds Apollo 16 Booster Rocket Impact Site

NASA Image and Video Library

2017-12-08

After decades of uncertainty, the Apollo 16 S-IVB impact site on the lunar surface has been identified. S-IVBs were portions of the Saturn V rockets that brought astronauts to the moon. The site was identified in imagery from the high-resolution LROC Narrow Angle Camera aboard NASA's Lunar Reconnaissance Orbiter. Beginning with Apollo 13, the S-IVB rocket stages were deliberately impacted on the lunar surface after they were used. Seismometers placed on the moon by earlier Apollo astronauts measured the energy of these impacts to shed light on the internal lunar structure. Locations of the craters that the boosters left behind were estimated from tracking data collected just prior to the impacts. Earlier in the LRO mission, the Apollo 13, 14, 15 and 17 impact sites were successfully identified, but Apollo 16's remained elusive. In the case of Apollo 16, radio contact with the booster was lost before the impact, so the location was only poorly known. Positive identification of the Apollo 16 S-IVB site took more time than the other four impact craters because the location ended up differing by about 30 km (about 19 miles) from the Apollo-era tracking estimate. (For comparison, the other four S-IVB craters were all within 7 km -- about four miles -- of their estimated locations.) Apollo 16's S-IVB stage is on Mare Insularum, about 160 miles southwest of Copernicus Crater (more precisely: 1.921 degrees north, 335.377 degrees east, minus 1,104 meters elevation). Credit: NASA/Goddard/Arizona State University NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Spacecraft cryogenic gas storage systems

NASA Technical Reports Server (NTRS)

Rysavy, G.

1971-01-01

Cryogenic gas storage systems were developed for the liquid storage of oxygen, hydrogen, nitrogen, and helium. Cryogenic storage is attractive because of the high liquid density and low storage pressure of cryogens. This situation results in smaller container sizes, reduced container-strength levels, and lower tankage weights. The Gemini and Apollo spacecraft used cryogenic gas storage systems as standard spacecraft equipment. In addition to the Gemini and Apollo cryogenic gas storage systems, other systems were developed and tested in the course of advancing the state of the art. All of the cryogenic storage systems used, developed, and tested to date for manned-spacecraft applications are described.

Apollo experience report guidance and control systems: Primary guidance, navigation, and control system development

NASA Technical Reports Server (NTRS)

Holley, M. D.; Swingle, W. L.; Bachman, S. L.; Leblanc, C. J.; Howard, H. T.; Biggs, H. M.

1976-01-01

The primary guidance, navigation, and control systems for both the lunar module and the command module are described. Development of the Apollo primary guidance systems is traced from adaptation of the Polaris Mark II system through evolution from Block I to Block II configurations; the discussion includes design concepts used, test and qualification programs performed, and major problems encountered. The major subsystems (inertial, computer, and optical) are covered. Separate sections on the inertial components (gyroscopes and accelerometers) are presented because these components represent a major contribution to the success of the primary guidance, navigation, and control system.

Lunar Dust Effects on Spacesuit Systems: Insights from the Apollo Spacesuits

NASA Technical Reports Server (NTRS)

Christoffersen, Roy; Lindsay, John R.; Noble, Sarah K.; Meador, Mary Ann; Kosmo, Joseph J.; Lawrence, J. Anneliese; Brostoff, Lynn; Young, Amanda; McCue, Terry

2008-01-01

Systems and components of selected Apollo A7L/A7LB flight-article spacesuits that were worn on the lunar surface have been studied to determine the degree to which they suffered contamination, abrasion and wear or loss of function due to effects from lunar soil particles. Filter materials from the lithium hydroxide (LiOH) canisters from the Apollo Command Module were also studied to determine the amount and type of any lunar dust particles they may have captured from the spacecraft atmosphere. The specific spacesuit study materials include the outermost soft fabric layers on Apollo 12 and 17 integrated thermal micrometeorite garment assemblies and outermost fabrics on Apollo 17 extravehicular pressure gloves. In addition, the degree of surface wear in the sealed wrist rotation bearing from Apollo 16 extravehicular and intravehicular pressure gloves was evaluated and compared. Scanning electron microscope examination of the Apollo 12 T-164 woven TeflonO fabric confirms the presence of lunar soil particles and the ability of these particles to cause separation and fraying of the Teflon fibers. Optical imaging, chemical analysis and particle sampling applied to the outer fabric of the Apollo 17 spacesuit has identified Ti as a potentially useful chemical marker for comparing the amount of lunar soil retained on different areas of the spacesuit outer fabric. High-yield particle sampling from the Apollo 17 fabric surfaces using adhesive tape found 80% of particles on the fabric are lunar soil particles averaging 10.5 m in diameter, with the rest being intrinsic fabric materials or environmental contaminants. Analysis of the mineralogical composition of the lunar particles found that on a grain-count basis the particle population is dominated by plagioclase feldspar and various types of glassy particles derived mostly from soil agglutinates, with a subordinate amount of pyroxene. On a grain size basis, however, the pyroxene grains are generally a factor of 2 larger than glass and plagioclase, so conversion of the data to a modal (volume %) basis results in pyroxene becoming the modally dominant particle type with glass and plagioclase significantly less abundant. When comparisons are made to the modal composition of lunar soil at the Apollo 17 landing site, the results suggest that pyroxene particles have overall better retention on the spacesuit outer fabric compared to plagioclase and especially glass. Scanning electron microscopy revealed no measureable difference in the amount of wear and abrasion in the wrist rotation bearing of an Apollo 16 pressure glove worn only in the spacecraft and one worn only for extravehicular activity on the lunar surface. The results suggest either that the bearing prevented entry of lunar dust, or that dust was not sufficiently abrasive to damage the bearing, or both.

Apollo 10 and 11 crews photographed during Apollo 10 debriefing

NASA Image and Video Library

1969-06-03

S69-35504 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left foreground, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

Apollo 10 and 11 crews photographed during Apollo 10 debriefing

NASA Image and Video Library

1969-06-03

S69-35507 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

Apollo experience report: Guidance and control systems. Lunar module stabilization and control system

NASA Technical Reports Server (NTRS)

Shelton, D. H.

1975-01-01

A brief functional description of the Apollo lunar module stabilization and control subsystem is presented. Subsystem requirements definition, design, development, test results, and flight experiences are discussed. Detailed discussions are presented of problems encountered and the resulting corrective actions taken during the course of assembly-level testing, integrated vehicle checkout and test, and mission operations. Although the main experiences described are problem oriented, the subsystem has performed satisfactorily in flight.

Apollo Lightcraft Project

NASA Technical Reports Server (NTRS)

Myrabo, Leik N.; Smith, Wayne L. (Editor); Decusatis, Casimer; Frazier, Scott R.; Garrison, James L., Jr.; Meltzer, Jonathan S.; Minucci, Marco A.; Moder, Jeffrey P.; Morales, Ciro; Mueller, Mark T.

1988-01-01

This second year of the NASA/USRA-sponsored Advanced Aeronautical Design effort focused on systems integration and analysis of the Apollo Lightcraft. This beam-powered, single-stage-to-orbit vehicle is envisioned as the shuttlecraft of the 21st century. The five person vehicle was inspired largely by the Apollo Command Module, then reconfigured to include a new front seat with dual cockpit controls for the pilot and co-pilot, while still retaining the 3-abreast crew accommodations in the rear seat. The gross liftoff mass is 5550 kg, of which 500 kg is the payload and 300 kg is the LH2 propellant. The round trip cost to orbit is projected to be three orders of magnitude lower than the current space shuttle orbiter. The advanced laser-driven 5-speed combined-cycle engine has shiftpoints at Mach 1, 5, 11 and 25+. The Apollo Lightcraft can climb into low Earth orbit in three minutes, or fly to any spot on the globe in less than 45 minutes. Detailed investigations of the Apollo Lightcraft Project this second year further evolved the propulsion system design, while focusing on the following areas: (1) man/machine interface; (2) flight control systems; (3) power beaming system architecture; (4) re-entry aerodynamics; (5) shroud structural dynamics; and (6) optimal trajectory analysis. The principal new findings are documented. Advanced design efforts for the next academic year (1988/1989) will center on a one meter+ diameter spacecraft: the Lightcraft Technology Demonstrator (LTD). Detailed engineering design and analyses, as well as critical proof-of-concept experiments, will be carried out on this small, near-term machine. As presently conceived, the LTD could be constructed using state of the art components derived from existing liquid chemical rocket engine technology, advanced composite materials, and high power laser optics.

APOLLO X - CREW

NASA Image and Video Library

1969-06-03

S69-35505 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left foreground, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

Dynamical evidence regarding the relationship between asteroids and meteorites

NASA Technical Reports Server (NTRS)

Wetherill, G. W.

1978-01-01

Meteorites are fragments of small solar system bodies transferring into the vicinity of earth from the inner edge of the asteroid belt. Photometric measurements support an association between Apollo objects and chondritic meteorites. Dynamical arguments indicate that most Apollo objects are devolatilized comet residues, however; petrographic and cosmogonical reasons argue against this conclusion.

Apollo experience report: Command and service module sequential events control subsystem

NASA Technical Reports Server (NTRS)

Johnson, G. W.

1975-01-01

The Apollo command and service module sequential events control subsystem is described, with particular emphasis on the major systems and component problems and solutions. The subsystem requirements, design, and development and the test and flight history of the hardware are discussed. Recommendations to avoid similar problems on future programs are outlined.

Apollo lunar surface experiments package

NASA Technical Reports Server (NTRS)

1972-01-01

The ALSEP program status and monthly progress are reported. Environmental and quality control tests and test results are described. Details are given on the Apollo 17 Array E, and the lunar seismic profiling, ejecta and meteorites, mass spectrometer, surface gravimeter, and heat flow experiments. Monitoring of the four ALSEP systems on the moon is also described.

13 Things That Saved Apollo 13

NASA Technical Reports Server (NTRS)

Woodfill, Jared

2012-01-01

Perhaps, the most exciting rescue, terrestrial or extra-terrestrial, is the successful return of the Apollo 13 crew to Earth in April of 1970. The mission s warning system engineer, Jerry Woodfill, who remains a NASA employee after 47 years of government service has examined facets of the rescue for the past 42 years. He will present "13 Things That Saved Apollo 13" from the perspective of his real time experience as well as two score years of study. Many are recent discoveries never before published in mission reports, popular books or documentary and Hollywood movies depicting the rescue.

Early Impacts on the Moon: Crystallization Ages of Apollo 16 Melt Breccias

NASA Technical Reports Server (NTRS)

Norman, M. D.; Shih, C.-Y.; Nyquist, L. E.; Bogard, D. D.; Taylor, L. A.

2007-01-01

A better understanding of the early impact history of the terrestrial planets has been identified one of the highest priority science goals for solar system exploration. Crystallization ages of impact melt breccias from the Apollo 16 site in the central nearside lunar highlands show a pronounced clustering of ages from 3.75-3.95 Ga, with several impact events being recognized by the association of textural groups and distinct ages. Here we present new geochemical and petrologic data for Apollo 16 crystalline breccia 67955 that document a much older impact event with an age of 4.2 Ga.

The Apollo experiment for document delivery via satellite communication

NASA Astrophysics Data System (ADS)

1985-03-01

Dutch participation possibilities in the Apollo document delivery project, wishes and idea's of potential user and tender groups, and plans and activities of Dutch institutes and companies, are surveyed. The Apollo storage and transport system, demand and administration network, potential markets, and subject areas of the documents are investigated. Utilization areas (scientific, technical, administration, and business information) are listed. High tariffs and the lack of necessary provision make a direct participation strategy impossible. However, in the experimental phase, Dutch companies must be allowed to contribute in technical developments and availability of organizational and technical facilities must be stimulated.

Liftoff of the Apollo 11 lunar landing mission

NASA Image and Video Library

1969-07-16

S69-39957 (16 July 1969) --- A 70mm Airborne Lightweight Optical Tracking System (ALOTS) took this picture. ALOTS tracking camera mounted on an Air Force EC-135 aircraft flying at about 40,000 feet altitude photographed this event in the early moments of the Apollo 11 launch. The 7.6 million-pound thrust Saturn V (S-1C) first stage boosts the space vehicle to an altitude of 36.3 nautical miles at 50.6 nautical miles downrange in 2 minutes 40.8 seconds. The S-1C stage separates at 2 minutes 41.6 seconds after liftoff. The crew of the Apollo 11 NASA's first lunar landing mission are astronauts Neil A. Armstrong, Michael Collins, and Edwin E. Aldrin Jr. The Apollo 11 launch was at 9:32 a.m. (EDT), July 16, 1969.

Saturn Apollo Program

NASA Image and Video Library

1970-04-01

Apollo 13 onboard photo: This view of the severely damaged Apollo 13 Service Module was photographed from the Lunar Module/Command Module following the jettison of the Service Module. As seen here, an entire panel of the Service Module was blown away by the apparent explosion of oxygen tank number two located in Sector 4 of the Service Module. Two of the three fuel cells are visible just forward (above) the heavily damaged area. Three fuel cells, two oxygen tanks, and two hydrogen tanks, are located in Sector 4. The damaged area is located above the S-band high gain anterna. Nearest the camera is the Service Propulsion System (SPS) engine and nozzle. The damage to the Service Module caused the Apollo 13 crewmen to use the Lunar Module as a lifeboat. The Lunar Module was jettisoned by the Command Module just prior to Earth re-entry.

3D-Laser-Scanning Technique Applied to Bulk Density Measurements of Apollo Lunar Samples

NASA Technical Reports Server (NTRS)

Macke, R. J.; Kent, J. J.; Kiefer, W. S.; Britt, D. T.

2015-01-01

In order to better interpret gravimetric data from orbiters such as GRAIL and LRO to understand the subsurface composition and structure of the lunar crust, it is import to have a reliable database of the density and porosity of lunar materials. To this end, we have been surveying these physical properties in both lunar meteorites and Apollo lunar samples. To measure porosity, both grain density and bulk density are required. For bulk density, our group has historically utilized sub-mm bead immersion techniques extensively, though several factors have made this technique problematic for our work with Apollo samples. Samples allocated for measurement are often smaller than optimal for the technique, leading to large error bars. Also, for some samples we were required to use pure alumina beads instead of our usual glass beads. The alumina beads were subject to undesirable static effects, producing unreliable results. Other investigators have tested the use of 3d laser scanners on meteorites for measuring bulk volumes. Early work, though promising, was plagued with difficulties including poor response on dark or reflective surfaces, difficulty reproducing sharp edges, and large processing time for producing shape models. Due to progress in technology, however, laser scanners have improved considerably in recent years. We tested this technique on 27 lunar samples in the Apollo collection using a scanner at NASA Johnson Space Center. We found it to be reliable and more precise than beads, with the added benefit that it involves no direct contact with the sample, enabling the study of particularly friable samples for which bead immersion is not possible

Apollo experience report: Very high frequency ranging system

NASA Technical Reports Server (NTRS)

Panter, W. C.; Shores, P. W.

1972-01-01

The history of the Apollo very-high-frequency ranging system development program is presented from the program-planning stage through the final-test and flight-evaluation stages. Block diagrams of the equipment are presented, and a description of the theory of operation is outlined. A sample of the distribution of errors measured in the aircraft-flight test program is included. The report is concluded with guidelines or recommendations for the management of development programs having the same general constraints.

Apollo telescope mount thermal systems unit thermal vacuum test

NASA Technical Reports Server (NTRS)

Trucks, H. F.; Hueter, U.; Wise, J. H.; Bachtel, F. D.

1971-01-01

The Apollo Telescope Mount's thermal systems unit was utilized to conduct a full-scale thermal vacuum test to verify the thermal design and the analytical techniques used to develop the thermal mathematical models. Thermal vacuum test philosophy, test objectives configuration, test monitoring, environment simulation, vehicle test performance, and data correlation are discussed. Emphasis is placed on planning and execution of the thermal vacuum test with particular attention on problems encountered in conducting a test of this maguitude.

Apollo Soyuz Test Project Weights and Mass Properties Operational Management System

NASA Technical Reports Server (NTRS)

Collins, M. A., Jr.; Hischke, E. R.

1975-01-01

The Apollo Soyuz Test Project (ASTP) Weights and Mass Properties Operational Management System was established to assure a timely and authoritative method of acquiring, controlling, generating, and disseminating an official set of vehicle weights and mass properties data. This paper provides an overview of the system and its interaction with the various aspects of vehicle and component design, mission planning, hardware and software simulations and verification, and real-time mission support activities. The effect of vehicle configuration, design maturity, and consumables updates is discussed in the context of weight control.

Report of Apollo 204 Review Board to the Administrator, National Aeronautics and Space Administration . Appendix F ; Schedule of Physical Evidence

NASA Technical Reports Server (NTRS)

1967-01-01

Immediately following the Apollo 204 accident of January 27, 1961. all associated equipment and material were impounded. Release of this equipment and material for normal use was under the close control of the Apollo 204 Review Board. Apollo Review Board Administrative Procedure No. 11, February 11, 1961, established the Apollo 204 Review Board Material Release Record (MRR). This MRR was the official form used to release material from full impoundment and was valid only after being approved by the Board and signed by a Member. The form was used as the authority to place any impounded item into one of the three Categories defined in Administrative Procedure No. 11. This appendix contains all of the authorized MRR's. Each item submitted on an MRR was given a control number; a description, including the part number and serial number; the relevance and location to the accident; any constraints before release; and the control category. The categories placed on the equipment were as follows: Category A - Items which may have a significant influence or bearing on the results or findings of the Apollo 204 Review Board; Category B - All material other than Category A which is considered relevant to the Apollo 204 Review Board investigation; Category C - Material released from Board jurisdiction. Several classes of equipment were released by special Board action prior to the establishment of the MRR system. The operating procedure for release of these classes is Enclosure F-l to this appendix.

Artificial lunar impact craters: Four new identifications, part I

NASA Technical Reports Server (NTRS)

Whitaker, E. A.

1972-01-01

The Apollo 16 panoramic camera photographed the impact locations of the Ranger 7 and 9 spacecraft and the S-4B stage of the Apollo 14 Saturn launch vehicle. Identification of the Ranger craters was very simple because each photographed its target point before impact. Identification of the S-4B impact crater proved to be a simple matter because the impact location, as derived from earth-based tracking, displayed a prominent and unique system of mixed light and dark rays. By using the criterion of a dark ray pattern, a reexamination of the Apollo 14 500 mm Hasselblad sequence taken of the Apollo 13 S-4B impact area was made. This examination quickly led to the discovery of the ray system and the impact crater. The study of artificial lunar impact craters, ejecta blankets, and ray systems provides the long-needed link between the various experimental terrestrial impact and explosion craters, and the naturally occurring impact craters on the moon. This elementary study shows that lunar impact crater diameters are closely predictable from a knowledge of the energies involved, at least in the size range considered, and suggests that parameters, such as velocity, may have a profound effect on crater morphology and ejecta blanket albedo.

Project: Apollo 15

NASA Technical Reports Server (NTRS)

1971-01-01

The 12-day Apollo 15 mission, scheduled for launch on July 26 to carry out the fourth United States manned exploration of the Moon, will: Double the time and extend tenfold the range of lunar surface exploration as compared with earlier missions; Deploy the third in a network of automatic scientific stations; Conduct a new group of experiments in lunar orbit; and Return to Earth a variety of lunar rock and soil samples. Scientists expect the results will greatly increase man's knowledge both of the Moon's history and composition and of the evolution and dynamic interaction of the Sun-Earth system. This is so because the dry, airless, lifeless Moon still bears records of solar radiation and the early years of solar system history that have been erased from Earth. Observations of current lunar events also may increase understanding of similar processes on Earth, such as earthquakes. The Apollo 15 Lunar module will make its descent over the Apennine peaks, one of the highest mountain ranges on the Moon, to land near the rim of the canyon-like Hadley Rille. From this Hadley-Apennine lunar base, between the mountain range and the rille, Commander David R. Scott and Lunar Module Pilot James B. Irwin will explore several kilometers from the lunar module, driving an electric-powered lunar roving vehicle for the first time on the Moon. Scott and Irwin will leave the lunar module for three exploration periods to emplace scientific experiments on the lunar surface and to make detailed geologic investigations of formations in the Apennine foothills, along the Hadley Rille rim, and to other geologic structures. The three previous manned landings were made by Apollo 11 at Tranquillity Base, Apollo 12 in the Ocean of Storms and Apollo 14 at Fra Mauro.

Six Apollo astronauts in front of Saturn V at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts pose in front of an Apollo Command and Service Module during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The astronauts are (from left): Apollo 14 Lunar Module Pilot Edgar D. Mitchell; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr.; Apollo 10 Commander Thomas P. Stafford; Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; and Apollo 9 Lunar Module Pilot Russell L. Schweikart. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Lunar Module Communications

NASA Technical Reports Server (NTRS)

Interbartolo, Michael A.

2009-01-01

This slide presentation reviews the Apollo lunar module communications. It describes several changes in terminology from the Apollo era to more recent terms. It reviews: (1) Lunar Module Antennas and Functions (2). Earth Line of Sight Communications Links (3) No Earth Line of Sight Communications Links (4) Lunar Surface Communications Links (5) Signal-Processing Assembly (6) Instrumentation System (7) Some Communications Problems Encountered

Apollo experience report: Development flight instrumentation. [telemetry equipment for space flight test program

NASA Technical Reports Server (NTRS)

Farmer, N. B.

1974-01-01

Development flight instrumentation was delivered for 25 Apollo vehicles as Government-furnished equipment. The problems and philosophies of an activity that was concerned with supplying telemetry equipment to a space-flight test program are discussed. Equipment delivery dates, system-design details, and flight-performance information for each mission also are included.

Using Apollo sites and soils to compositionally ground truth Diviner Lunar Radiometer observations

NASA Astrophysics Data System (ADS)

Greenhagen, B. T.; Lucey, P. G.; Song, E.; Thomas, I. R.; Bowles, N. E.; Donaldson Hanna, K. L.; Foote, E. J.; Paige, D. A.; Allen, C.

2012-12-01

Apollo landing sites and returned soils afford us a unique opportunity to "ground truth" Diviner Lunar Radiometer compositional observations, which are the first global, high resolution, thermal infrared measurements of an airless body. The Moon is the most accessible member of the most abundant class of solar system objects, which includes Mercury, asteroids, and icy satellites. And the Apollo samples returned from the Moon are the only extraterrestrial samples with known spatial context. Here we compare Diviner observations of Apollo landing sites and compositional and spectral laboratory measurements of returned Apollo soils. Diviner, onboard NASA's Lunar Reconnaissance Orbiter, has three spectral channels near 8 μm that were designed to characterize the mid-infrared emissivity maximum known as the Christiansen feature (CF), a well-studied indicator of silicate mineralogy. It has been observed that thermal infrared spectra measured in simulated lunar environment (SLE) are significantly altered from spectra measured under terrestrial or martian conditions, with enhanced CF contrast and shifted CF position relative to other spectral features. Therefore only thermal emission experiments conducted in SLE are directly comparable to Diviner data. With known compositions, Apollo landing sites and soils are important calibration points for the Diviner dataset, which includes all six Apollo sites at approximately 200 m spatial resolution. Differences in measured CFs caused by composition and space weathering are apparent in Diviner data. Analyses of Diviner observations and SLE measurements for a range of Apollo soils show good agreement, while comparisons to thermal reflectance measurements under ambient conditions do not agree well, which underscores the need for SLE measurements and validates our measurement technique. Diviner observations of Apollo landing sites are also correlated with geochemical measurements of Apollo soils from the Lunar Sample Compendium. In particular, the correlations between CF and FeO and Al2O3 are very strong, owing to the dependence on the feldspar-mafic ratio. Our analyses suggest that Diviner data may offer an independent measure of soil iron content from the existing optical and gamma-ray spectrometer datasets.

Using Apollo Sites and Soils to Compositionally Ground Truth Diviner Lunar Radiometer Observations

NASA Technical Reports Server (NTRS)

Greenhagen, Benjamin T.; Lucey, P. G.; Song, E.; Thomas, I R.; Bowles, N. E.; DonaldsonHanna, K. L.; Allen, C.; Foote, E. J.; Paige, D .A.

2012-01-01

Apollo landing sites and returned soils afford us a unique opportunity to "ground truth" Diviner Lunar Radiometer compositional observations, which are the first global, high resolution , thermal infrared measurements of an airless body. The Moon is the most accessible member of the most abundant class of solar system objects, which includes Mercury, asteroids, and icy satellites. And the Apollo samples returned from the Moon are the only extraterrestrial samples with known spatial context. Here we compare Diviner observations of Apollo landing sites and compositional and spectral laboratory measurements of returned Apollo soils. Diviner, onboard NASA's Lunar Reconnaissance Orbiter, has three spectral channels near 8 micron that were designed to characterize the mid-infrared emissivity maximum known as the Christiansen feature (CF), a well-studied indicator of silicate mineralogy. It has been observed that thermal infrared spectra measured in simulated lunar environment (SLE) are significantly altered from spectra measured under terrestrial or martian conditions, with enhanced CF contrast and shifted CF position relative to other spectral features. Therefore only thermal emission experiments conducted in SLE are directly comparable to Diviner data. With known compositions, Apollo landing sites and soils are important calibration points for the Diviner dataset, which includes all six Apollo sites at approximately 200 m spatial resolution. Differences in measured CFs caused by composition and space weathering are apparent in Diviner data. Analyses of Diviner observations and SLE measurements for a range of Apollo soils show good agreement, while comparisons to thermal reflectance measurements under ambient conditions do not agree well, which underscores the need for SLE measurements and validates our measurement technique. Diviner observations of Apollo landing sites are also correlated with geochemical measurements of Apollo soils from the Lunar Sample Compendium. In particular, the correlations between CF and FeO and AI203 are very strong, owing to the dependence on the feldspar-mafic ratio. Our analyses suggest that Diviner data may offer an independent measure of soil iron content from the existing optical and gamma-ray spectrometer datasets.

Apollo experience report: Command and service module electrical power distribution on subsystem

NASA Technical Reports Server (NTRS)

Munford, R. E.; Hendrix, B.

1974-01-01

A review of the design philosophy and development of the Apollo command and service modules electrical power distribution subsystem, a brief history of the evolution of the total system, and some of the more significant components within the system are discussed. The electrical power distribution primarily consisted of individual control units, interconnecting units, and associated protective devices. Because each unit within the system operated more or less independently of other units, the discussion of the subsystem proceeds generally in descending order of complexity; the discussion begins with the total system, progresses to the individual units of the system, and concludes with the components within the units.

Geohazards on the Moon and the Importance of the International Lunar Network

NASA Technical Reports Server (NTRS)

Cohen, Barbara A.

2009-01-01

Seven of the 28 shallow seismic events recorded by the Apollo passive seismic experiment (PSE) network released energy equivalent to earthquakes with magnitudes of 5 or greater. On Earth, such quakes can cause extensive damage to structures near the epicenter. Unexpected structural damage to a lunar habitat could have devastating results and thus, lunar seismicity may present a significant geohazard to long-term human habitation.

The Effects of Lunar Dust on EVA Systems During the Apollo Missions

NASA Technical Reports Server (NTRS)

Gaier, James R.

2005-01-01

Mission documents from the six Apollo missions that landed on the lunar surface have been studied in order to catalog the effects of lunar dust on Extra-Vehicular Activity (EVA) systems, primarily the Apollo surface space suit. It was found that the effects could be sorted into nine categories: vision obscuration, false instrument readings, dust coating and contamination, loss of traction, clogging of mechanisms, abrasion, thermal control problems, seal failures, and inhalation and irritation. Although simple dust mitigation measures were sufficient to mitigate some of the problems (i.e., loss of traction) it was found that these measures were ineffective to mitigate many of the more serious problems (i.e., clogging, abrasion, diminished heat rejection). The severity of the dust problems were consistently underestimated by ground tests, indicating a need to develop better simulation facilities and procedures.

The Effects of Lunar Dust on EVA Systems During the Apollo Missions

NASA Technical Reports Server (NTRS)

Gaier, James R.

2007-01-01

Mission documents from the six Apollo missions that landed on the lunar surface have been studied in order to catalog the effects of lunar dust on Extra-Vehicular Activity (EVA) systems, primarily the Apollo surface space suit. It was found that the effects could be sorted into nine categories: vision obscuration, false instrument readings, dust coating and contamination, loss of traction, clogging of mechanisms, abrasion, thermal control problems, seal failures, and inhalation and irritation. Although simple dust mitigation measures were sufficient to mitigate some of the problems (i.e., loss of traction) it was found that these measures were ineffective to mitigate many of the more serious problems (i.e., clogging, abrasion, diminished heat rejection). The severity of the dust problems were consistently underestimated by ground tests, indicating a need to develop better simulation facilities and procedures.

Location of Microbial Ecology Evaluation Device in Apollo Command Module

NASA Technical Reports Server (NTRS)

1971-01-01

The location of the Microbial Ecology Evaluation Device (MEED) installed on the open hatch of the Apollo Command Module is illustrated in this photograph. The MEED, equipment of the Microbial Response in Space Environment experiment, will house a selection of microbial systems. The MEED will be deployed during the extravehicular activity on the transearth coast phase of the Aopllo 16 lunar landing mission. The purpose of the experiment will be to measure the effects of certain space environmental parameters on the microbial test systems.

Apollo Recovery Operations

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

Objectives include: a) Describe the organization of recovery force command and control and landing areas; b) Describe the function and timeline use of the Earth Landing System (ELS); c) Describe Stable 1 vs Stable 2 landing configurations and the function of the Command Module Uprighting System; d) Explain the activities of the helicopter and swimmer teams in egress and recovery of the crew; e)Explain the activities of the swimmer teams and primary recovery ship in recovery of the Command Module; and f) Describe several landing incidents that occurred during Apollo.

Apollo experience report: Guidance and control systems - Digital autopilot design development

NASA Technical Reports Server (NTRS)

Peters, W. H.; Cox, K. J.

1973-01-01

The development of the Apollo digital autopilots (the primary attitude control systems that were used for all phases of the lunar landing mission) is summarized. This report includes design requirements, design constraints, and design philosophy. The development-process functions and the essential information flow paths are identified. Specific problem areas that existed during the development are included. A discussion is also presented on the benefits inherent in mechanizing attitude-controller logic and dynamic compensation in a digital computer.

An analysis of cryotrap heat exchanger performance test data (400 area) and recommendations for a system to handle Apollo RCS engines

NASA Technical Reports Server (NTRS)

Rakow, A.

1983-01-01

The current arrangement of a Platecoil heat exchanger which uses LN2 on the inside of parallel tubes, in counter flow to the test cell engine exhaust gases which are drawn through a box surrounding the plates by the existing vacuum blowers is examined. As a result of inadequate performance and special test data it was decided to redesign the system to accommodate an Apollo RCS engine.

AFTER: Batch jobs on the Apollo ring

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hofstadler, P.

1987-07-01

This document describes AFTER, a system that allows users of an Apollo ring to submit batch jobs to run without leaving themselves logged in to the ring. Jobs may be submitted to run at a later time or on a different node. Results from the batch job are mailed to the user through some designated mail system. AFTER features an understandable user interface, good on line help, and site customization. This manual serves primarily as a user's guide to AFTER although administration and installation are covered for completeness.

Analysis of the ultrafine fraction of the Apollo 14 regolith

NASA Technical Reports Server (NTRS)

Finkelman, R. B.

1973-01-01

Analyses were obtained on more than 2400 randomly selected particles from the sub-37 micron (ultrafine) fraction of ten Apollo 14 regolith samples. The analyses were conducted with an energy dispersive electron microprobe system. The semiquantitative data were used to group the particles into ten categories. The pyroxene/plagioclase and olivine/plagioclase ratios are inconsistent with those ratios in the Apollo 14 breccias and rocks. The data suggest that fragmented basalts similar to Apollo 12 olivine basalts may have made significant contributions to the ultrafine fraction of the Fra Mauro regolith. Among a number of unusual particles encountered are brown, birefringent lath-shaped grains with 60 wt % SiO2 and 34 wt % FeO(FeSi2O5) and a glass with 20 to 25 wt % CaO, 0 to 8 wt % MgO, 40 to 45 wt % Al2O3 and approximately 30 wt % SiO2.

Lunar Data Node: Apollo Data Restoration and Archiving Update

NASA Technical Reports Server (NTRS)

Williams, David R.; Hills, Howard K.; Guiness, Edward A.; Taylor, Patrick T.; McBride, Marie Julia

2013-01-01

The Lunar Data Node (LDN) of the Planetary Data System (PDS) is responsible for the restoration and archiving of Apollo data. The LDN is located at the National Space Science Data Center (NSSDC), which holds much of the extant Apollo data on microfilm, microfiche, hard-copy documents, and magnetic tapes in older formats. The goal of the restoration effort is to convert the data into user-accessible PDS formats, create a full set of explanatory supporting data (metadata), archive the full data sets through PDS, and post the data online at the PDS Geosciences Node. This will both enable easy use of the data by current researchers and ensure that the data and metadata are securely preserved for future use. We are also attempting to locate and preserve Apollo data which were never archived at NSSDC. We will give a progress report on the data sets we have been restoring and future work.

Restoration of APOLLO Data by the NSSDC and PDS Lunar Data Node

NASA Technical Reports Server (NTRS)

Williams, David R.; Hills, H. Kent; Guinness, Edward A.; Taylor, Patrick T.; McBride, Marie J.

2012-01-01

The Apollo Lunar Surface Experiment Packages (ALSEPs), suites of instruments deployed by the Apollo 12. 14, 15, 16 and 17 astronauts on the lunar surface, still represent the only in-situ measurements of the Moon's environment taken over long time periods, Much of these data are housed at the National Space Science Data Center (NSSDC) at Goddard Space Flight Center but are in forms that are not readily usable, such as microfilm, hardcopy, and magnetic tapes with older, obsolete formats. The Lunar Data Node (LDN) has been formed under the auspices of the Planetary Data System (PDS) Geosciences Node to put relevant, scientifically important Apollo data into accessible digital form for use by researchers and mission planners. The LDN has prioritized the restoration of these data based on their scientific and engineering value and the level of effort required. We will report on progress made and plans for future data restorations.

Minimally invasive cone beam CT-guided evacuation of parenchymal and ventricular hemorrhage using the Apollo system: proof of concept in a cadaver model.

PubMed

Fiorella, David; Arthur, Adam; Schafer, Sebastian

2015-08-01

The Apollo system (Penumbra Inc, Alameda, California, USA) is a low profile irrigation-aspiration system designed for the evacuation of intracranial hemorrhage. To demonstrate the feasibility of using Apollo in combination with cone beam CT guidance. Parenchymal (n=1) and mixed parenchymal-intraventricular hematomas (n=1) were created in cadaver heads using a transvascular (n=1) or transcranial (n=1) approach. Hematomas were then imaged with cone beam CT (CB-CT), and the long axis of the hematoma defined. The CB-CT data were then used to guide transcranial access to the hematoma-defining the location of the burr hole and the path to the leading edge of the hematoma. An 8F vascular sheath was then placed under live fluoroscopic guidance into the hematoma. A second CB-CT was performed to confirm localization of the sheath. The hematoma was then demarcated on the CB-CT and the Apollo wand was introduced through the 8F sheath and irrigation-aspiration was performed under (periodic) live fluoroscopic guidance. The operators manipulated the wand within the visible boundaries of the hematoma. After irrigation-aspiration, a control CB-CT was performed to document reduction in hematoma volume. Transvascular and transcranial techniques were both successful in creating intracranial hematomas. Hematomas could be defined with conspicuity sufficient for localization and volumetric measurement using CB-CT. Live fluoroscopic guidance was effective in navigating a sheath into the leading aspect of a parenchymal hematoma and guiding irrigation-aspiration with the Apollo system. Irrigation-aspiration reduced the parenchymal hemorrhage volume from 14.8 to 1.7 cc in 189 s in the first case (parenchymal hemorrhage) and from 26.4 to 4.1 cc in 300 s in the second case (parenchymal and intraventricular hemorrhage). The cadaver model described is a useful means of studying interventional techniques for intracranial hemorrhage. It seems feasible to use CB-CT to guide the evacuation of intraparenchymal and intraventricular hemorrhage using the Apollo system through a minimally invasive transcranial access. Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://group.bmj.com/group/rights-licensing/permissions.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Astronaut James Lovell (Apollo 8 Apollo 13), center, flanked by Walt Cunningham (Apollo 7), left, and David Scott (Apollo 9 Apollo 15) responds during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

The role of toxicology in the Apollo space program

NASA Technical Reports Server (NTRS)

Rippstein, W. J., Jr.

1975-01-01

Some of the major considerations are presented which governed the formation and application of the toxicology program employed in support of the Apollo program. The overriding concern of the program was the safety of crews exposed to trace contaminant gases for extended periods of time. The materials screening program employed, in conjunction with a well designed spacecraft environmental control system, helped to attain the goals set forth for the Apollo program. The knowledge gained from working with the toxicity problems and the identification of compounds in the space cabin atmosphere are of importance for continued efforts in manned space flight. Tabular data of spacecraft contaminants are presented.

American-built hardware for ASPT undergoes pre-delivery preparations

NASA Image and Video Library

1974-09-11

S74-28295 (September 1974) --- American-built hardware for the joint U.S.-USSR Apollo-Soyuz Test Project mission undergoes pre-delivery preparations in the giant clean room at Rockwell International Corporation?s Space Division at Downey, California. The U.S. portion of the ASTP docking system is in the right foreground. In the right background is the cylindrical-shaped docking module, which is designed to link the Apollo and Soyuz spacecraft when they dock in Earth orbit next summer. In the left background is the Apollo Command Module which they will carry the three American astronauts into Earth orbit. Photo credit: NASA

Apollo experience report: Crew station integration. Volume 1: Crew station design and development

NASA Technical Reports Server (NTRS)

Allen, L. D.; Nussman, D. A.

1976-01-01

An overview of the evolution of the design and development of the Apollo command module and lunar module crew stations is given, with emphasis placed on the period from 1964 to 1969. The organizational planning, engineering techniques, and documentation involved are described, and a detailed chronology of the meetings, reviews, and exercises is presented. Crew station anomalies for the Apollo 7 to 11 missions are discussed, and recommendations for the solution of recurring problems of crew station acoustics, instrument glass failure, and caution and warning system performance are presented. Photographs of the various crew station configurations are also provided.

Apollo/Skylab suit program management systems study. Volume 2: Cost analysis

NASA Technical Reports Server (NTRS)

1974-01-01

The business management methods employed in the performance of the Apollo-Skylab Suit Program are studied. The data accumulated over the span of the contract as well as the methods used to accumulate the data are examined. Management methods associated with the monitoring and control of resources applied towards the performance of the contract are also studied and recommended upon. The primary objective is the compilation, analysis, and presentation of historical cost performance criteria. Cost data are depicted for all phases of the Apollo-Skylab program in common, meaningful terms, whereby the data may be applicable to future suit program planning efforts.

ArcGIS Digitization of Apollo Surface Traverses

NASA Technical Reports Server (NTRS)

Petro, N. E.; Bleacher, J. E.; Gladdis, L. R.; Garry, W. B.; Lam, F.; Mest, S. C.

2012-01-01

The Apollo surface activities were documented in extraordinary detail, with every action performed by the astronauts while on the surface recorded either in photo, audio, film, or by written testimony [1]. The samples and in situ measurements the astronauts collected while on the lunar surface have shaped our understanding of the geologic history of the Moon, and the earliest history and evolution of the inner Solar System. As part of an ongoing LASERfunded effort, we are digitizing and georeferencing data from astronaut traverses and spatially associating them to available, co-registered remote sensing data. Here we introduce the products produced so far for Apollo 15, 16, and 17 missions.

Lunar Regolith Simulant Materials: Recommendations for Standardization, Production, and Usage

NASA Technical Reports Server (NTRS)

Sibille, L.; Carpenter, P.; Schlagheck, R.; French, R. A.

2006-01-01

Experience gained during the Apollo program demonstrated the need for extensive testing of surface systems in relevant environments, including regolith materials similar to those encountered on the lunar surface. As NASA embarks on a return to the Moon, it is clear that the current lunar sample inventory is not only insufficient to support lunar surface technology and system development, but its scientific value is too great to be consumed by destructive studies. Every effort must be made to utilize standard simulant materials, which will allow developers to reduce the cost, development, and operational risks to surface systems. The Lunar Regolith Simulant Materials Workshop held in Huntsville, AL, on January 24 26, 2005, identified the need for widely accepted standard reference lunar simulant materials to perform research and development of technologies required for lunar operations. The workshop also established a need for a common, traceable, and repeatable process regarding the standardization, characterization, and distribution of lunar simulants. This document presents recommendations for the standardization, production and usage of lunar regolith simulant materials.

APOLLO: a general code for transport, slowing-down and thermalization calculations in heterogeneous media

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kavenoky, A.

1973-01-01

From national topical meeting on mathematical models and computational techniques for analysis of nuclear systems; Ann Arbor, Michigan, USA (8 Apr 1973). In mathematical models and computational techniques for analysis of nuclear systems. APOLLO calculates the space-and-energy-dependent flux for a one dimensional medium, in the multigroup approximation of the transport equation. For a one dimensional medium, refined collision probabilities have been developed for the resolution of the integral form of the transport equation; these collision probabilities increase accuracy and save computing time. The interaction between a few cells can also be treated by the multicell option of APOLLO. The diffusionmore » coefficient and the material buckling can be computed in the various B and P approximations with a linearly anisotropic scattering law, even in the thermal range of the spectrum. Eventually this coefficient is corrected for streaming by use of Benoist's theory. The self-shielding of the heavy isotopes is treated by a new and accurate technique which preserves the reaction rates of the fundamental fine structure flux. APOLLO can perform a depletion calculation for one cell, a group of cells or a complete reactor. The results of an APOLLO calculation are the space-and-energy-dependent flux, the material buckling or any reaction rate; these results can also be macroscopic cross sections used as input data for a 2D or 3D depletion and diffusion code in reactor geometry. 10 references. (auth)« less

Online plasma calculator

NASA Astrophysics Data System (ADS)

Wisniewski, H.; Gourdain, P.-A.

2017-10-01

APOLLO is an online, Linux based plasma calculator. Users can input variables that correspond to their specific plasma, such as ion and electron densities, temperatures, and external magnetic fields. The system is based on a webserver where a FastCGI protocol computes key plasma parameters including frequencies, lengths, velocities, and dimensionless numbers. FastCGI was chosen to overcome security problems caused by JAVA-based plugins. The FastCGI also speeds up calculations over PHP based systems. APOLLO is built upon the WT library, which turns any web browser into a versatile, fast graphic user interface. All values with units are expressed in SI units except temperature, which is in electron-volts. SI units were chosen over cgs units because of the gradual shift to using SI units within the plasma community. APOLLO is intended to be a fast calculator that also provides the user with the proper equations used to calculate the plasma parameters. This system is intended to be used by undergraduates taking plasma courses as well as graduate students and researchers who need a quick reference calculation.

a 3d Based Approach to the Architectural Study of the Roman Bath at the Sanctuary of Apollo Hylates (kourion, Cyprus).

NASA Astrophysics Data System (ADS)

Faka, M.; Christodoulou, S.; Abate, D.; Ioannou, C.; Hermon, S.

2017-08-01

Roman baths represented a popular social practice of everyday life, cited in numerous literary sources and testified by ample archaeological remains all over the Roman Empire. Although regional studies have contributed extensively to our knowledge about how baths functioned and what was their social role in various regions of the Mediterranean, their study in Cyprus is yet to be developed. Moreover, despite the increasing availability of devices and techniques for 3D documentation, various characteristics, especially in relation to the heating and water supply system of the baths, were omitted and were not properly and accurately documented. The pilot case study outlined in this paper presents the 3D documentation of the Roman bath, excavated in the 1950s, within the area of the Sanctuary of Apollo Hylates at Kourion (Limassol district). The creation of an accurate 3D model of the documented area through image and range based techniques combined with topographic data, allows the detailed analysis of architectural elements and their decorative features. At the same time, it enables accurate measurements of the site, which are used as input for the archaeological interpretation and virtual reconstruction of the original shape of the bath. In addition, this project aims to answer a number of archaeological research questions related to Roman baths such as their architectural features, function mode, and technological elements related to heating techniques.

KSC-2014-3196

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At the Kennedy Space Center in Florida, NASA officials and Apollo astronauts visiting Launch Pad 39B with their families and friends take a moment to enjoy the view. From left are Apollo astronaut Jim Lovell, Center Director Bob Cabana, Apollo 11 command module pilot Mike Collins, and Apollo 11 moonwalker Buzz Aldrin's son Andy Aldrin. The group is at Kennedy for a ceremony renaming the Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. The pad is being modified to support the agency's new Orion spacecraft which will lift off atop the Space Launch System rocket. Orion is designed to take humans farther than they’ve ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Neil Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Michael Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

Apollo Soyuz test project. USA-USSR, fact sheet

NASA Technical Reports Server (NTRS)

1974-01-01

The Apollo Soyuz Test Project (ASTP) is discussed. The United States and the Soviet Union have agreed to develop compatible rendezvous and docking systems which will provide a basis for docking and rescue on future spacecraft of both nations. The ASTP mission will include testing the rendezvous system in orbit, verifying techniques for transfer of astronauts and cosmonauts, and conducting experiments while docked and undocked. Diagrams of the spacecraft and systems involved in the tests are presented. The prime contractors for the equipment are identified. Biographical data on the astronauts participating in the program are provided.

Interviews with the Apollo lunar surface astronauts in support of planning for EVA systems design

NASA Technical Reports Server (NTRS)

Connors, Mary M.; Eppler, Dean B.; Morrow, Daniel G.

1994-01-01

Focused interviews were conducted with the Apollo astronauts who landed on the moon. The purpose of these interviews was to help define extravehicular activity (EVA) system requirements for future lunar and planetary missions. Information from the interviews was examined with particular attention to identifying areas of consensus, since some commonality of experience is necessary to aid in the design of advanced systems. Results are presented under the following categories: mission approach; mission structure; suits; portable life support systems; dust control; gloves; automation; information, displays, and controls; rovers and remotes; tools; operations; training; and general comments. Research recommendations are offered, along with supporting information.

Apollo experience report: Electronic systems test program accomplishments and results

NASA Technical Reports Server (NTRS)

Ohnesorge, T. E.

1972-01-01

A chronological record is presented of the Electronic Systems Test Program from its conception in May 1963 to December 1969. The original concept of the program, which was primarily a spacecraft/Manned Space Flight Network communications system compatibility and performance evaluation, is described. The evolution of these concepts to include various levels of test detail, as well as systems level design verification testing, is discussed. Actual implementation of these concepts is presented, and the facility to support the program is described. Test results are given, and significant contributions to the lunar landing mission are underlined. Plans for modifying the facility and the concepts, based on Apollo experience, are proposed.

On the X-34 FASTRAC-Memorandums of Misunderstanding

NASA Technical Reports Server (NTRS)

Hawkins, Lakiesha V.; Turner, Jim E.

2015-01-01

Engineers at MSFC designed, developed, and tested propulsion systems that helped launch Saturn I, IB, and V boosters for the Apollo missions. After the Apollo program, Marshall was responsible for the design and development of the propulsion elements for the Shuttle launch vehicle, including the solid rocket boosters, external tank and main engines. Each of these systems offered new propulsion technological challenges that pushed engineers and administrators beyond Saturn. The technical challenges presented by the development of each of these propulsion systems helped to establish and sustain a culture of engineering conservatism and was often accompanied by a deep level of penetration into contractors that worked on these systems.

The triumph and decline of the "squares": Grumman Aerospace engineers and production workers in the Apollo era, 1957--1973

NASA Astrophysics Data System (ADS)

Onkst, David Hugh

This dissertation is a social, cultural, and economic history of the men and women of the Grumman Aerospace Company of Bethpage, New York from 1957 through 1973. These "Grummanites" were the engineers and production workers who designed and built the Apollo Lunar Modules that allowed humans to land on the Moon. This study provides unique insights into the impact that the Apollo Program---a large state-initiated and -supported program---had on those "squares," people whom many contemporaries saw as a vital part of mainstream 1960s American society. By the beginning of the Space Age in 1957, Grumman, Long Island's single largest employer, had firmly established a workplace culture of paternalism that Grummanites largely embraced. Company officials believed strongly in worker retention and had established a policy of providing every sort of benefit their employees seemingly desired, including a highly personal and participatory form of management. Many Grummanites had joined the firm during the early years of the Apollo Program because they believed in the promise of permanent employment on exciting projects that would explore the endless frontier of space. But, as many of these mainly self-reliant, individualistic "squares" would bitterly discover, their dedication to Grumman did little to secure their livelihoods during the aerospace industry's early 1970s downsizing; their individual successes were too largely tied to federal spending and declined when Americans grew disenchanted with space exploration. This dissertation demonstrates how the cultural bond of paternalism between aerospace workers and their company unraveled in the 1960s, and then ended in the early 1970s, because of forces within the company, the economy, and the American state. The word "triumph" in this study's title not only applies to Grummanites' triumphs with the Lunar Modules, but also their individual socioeconomic victories. The term "decline" refers to the early 1970s downsizing of more than a third of the Apollo workforce that had made that program a reality. By relying on a wide-range of archival research (including corporate records) and extensive surveys and interviews with Grummanites, this dissertation provides an overview of how Apollo era aerospace workers interacted with the Cold War American state.

Apollo Contour Rocket Nozzle in the Propulsion Systems Laboratory

NASA Image and Video Library

1964-07-21

Bill Harrison and Bud Meilander check the setup of an Apollo Contour rocket nozzle in the Propulsion Systems Laboratory at the National Aeronautics and Space Administration (NASA) Lewis Research Center. The Propulsion Systems Laboratory contained two 14-foot diameter test chambers that could simulate conditions found at very high altitudes. The facility was used in the 1960s to study complex rocket engines such as the Pratt and Whitney RL-10 and rocket components such as the Apollo Contour nozzle, seen here. Meilander oversaw the facility’s mechanics and the installation of test articles into the chambers. Harrison was head of the Supersonic Tunnels Branch in the Test Installations Division. Researchers sought to determine the impulse value of the storable propellant mix, classify and improve the internal engine performance, and compare the results with analytical tools. A special setup was installed in the chamber that included a device to measure the thrust load and a calibration stand. Both cylindrical and conical combustion chambers were examined with the conical large area ratio nozzles. In addition, two contour nozzles were tested, one based on the Apollo Service Propulsion System and the other on the Air Force’s Titan transtage engine. Three types of injectors were investigated, including a Lewis-designed model that produced 98-percent efficiency. It was determined that combustion instability did not affect the nozzle performance. Although much valuable information was obtained during the tests, attempts to improve the engine performance were not successful.

Five Apollo astronauts with Lunar Module at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts observe a Lunar Module and Moon mockup during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Some of the visiting astonauts were (from left): Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 9 Lunar Module Pilot Russell L. Schweikart; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; Apollo 10 Commander Thomas P. Stafford; and Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Four Apollo astronauts with Command and Service Module at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts admire an Apollo Command and Service Module during a tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The astronauts are (from left): Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young;. Apollo 11 Lunar Module Pilot Edwin E. 'Buzz' Aldrin, Jr.; Apollo 17 Commander Eugene A. Cernan; and Apollo 10 Commander Thomas P. Stafford. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Engle, Cernan, Young, and Stafford under Saturn V at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts recall the past as they tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Standing underneath the KSC Apollo/Saturn V inside the building are (from left): Apollo 14 Back-up Lunar Module Pilot Joe H. Engle; Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Command Module Pilot and Apollo 16 Commander John W. Young; and Apollo 10 Commander Thomas P. Stafford. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Initial multicenter technical experience with the Apollo device for minimally invasive intracerebral hematoma evacuation.

PubMed

Spiotta, Alejandro M; Fiorella, David; Vargas, Jan; Khalessi, Alexander; Hoit, Dan; Arthur, Adam; Lena, Jonathan; Turk, Aquilla S; Chaudry, M Imran; Gutman, Frederick; Davis, Raphael; Chesler, David A; Turner, Raymond D

2015-06-01

No conventional surgical intervention has been shown to improve outcomes for patients with spontaneous intracerebral hemorrhage (ICH) compared with medical management. We report the initial multicenter experience with a novel technique for the minimally invasive evacuation of ICH using the Penumbra Apollo system (Penumbra Inc, Alameda, California). Institutional databases were queried to perform a retrospective analysis of all patients who underwent ICH evacuation with the Apollo system from May 2014 to September 2014 at 4 centers (Medical University of South Carolina, Stony Brook University, University of California at San Diego, and Semmes-Murphy Clinic). Cases were performed either in the neurointerventional suite, operating room, or in a hybrid operating room/angiography suite. Twenty-nine patients (15 female; mean age, 62 ± 12.6 years) underwent the minimally invasive evacuation of ICH. Six of these parenchymal hemorrhages had an additional intraventricular hemorrhage component. The mean volume of ICH was 45.4 ± 30.8 mL, which decreased to 21.8 ± 23.6 mL after evacuation (mean, 54.1 ± 39.1% reduction; P < .001). Two complications directly attributed to the evacuation attempt were encountered (6.9%). The mortality rate was 13.8% (n = 4). Minimally invasive evacuation of ICH and intraventricular hemorrhage can be achieved with the Apollo system. Future work will be required to determine which subset of patients are most likely to benefit from this promising technology.

KSC-2014-3231

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At the Kennedy Space Center in Florida, Apollo astronauts tour the refurbished Operations and Checkout Building, newly named for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Viewing the Orion crew module stacked on top of the service module from left, are Apollo 11 astronaut Michael Collins, Apollo astronaut Jim Lovell, and Apollo 11 astronaut Buzz Aldrin. The building's high bay is being used to support the agency's new Orion spacecraft, which will lift off atop the Space Launch System. Orion is designed to take humans farther than they've ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the moon landing. As the world watched, Neil Armstrong and Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

Flight Operations reunion for the Apollo 11 20th anniversary of the first manned lunar landing

NASA Technical Reports Server (NTRS)

1989-01-01

The following major areas are presented: (1) the Apollo years; (2) official flight control manning list for Apollo 11; (3) original mission control emblem; (4) foundations of flight control; (5) Apollo-11 20th anniversary program and events; (6) Apollo 11 mission operations team certificate; (7) Apollo 11 mission summary (timeline); and (8) Apollo flight control team photographs and biographies.

The Age of the Moon

NASA Astrophysics Data System (ADS)

Barboni, M.; Boehnke, P.; Keller, C. B.; Kohl, I. E.; McKeegan, K. D.; Schoene, B.; Young, E. D.

2016-12-01

Knowledge of the age of the Moon is important for understanding the early evolution of the solar system, including the timing of the hypothesized Giant Impact (GI). There have been many attempts to determine the Moon's age, but significant disagreement remains with some authors favoring an early formation and others arguing for a relatively young Moon formed at 4.4 Ga. Attempts to date the GI indirectly through its effects on the asteroid belt are problematic as there is no way to uniquely ascertain the cause of the observed disturbances (e.g., GI or meteorite parent body breakup). Determining the timing of the Lunar Magma Ocean (LMO) crystallization provides a more direct constraint on the age of the Moon, but interpreting the chronologic significance of LMO products is complicated by the fact that the only rock samples available are breccias. A better approach is to construct a model age for the fractional crystallization of the LMO since this should provide a global signature. Zircons from the Apollo samples are ancient, robust against later disturbances, and amenable to precise U-Pb geochronology and Hf isotope analyses that can be used to construct Lu-Hf model ages for the silicate differentiation of the Moon. Previous isotopic studies of Apollo zircons yielded artificially young Hf model ages because of the (then unknown) effect of neutron capture on Hf isotopic ratios generated by long exposure to cosmic radiation, and were unable to determine whether or not the U-Pb dates were concordant due to insufficient precision of in situ dating techniques. We have addressed these issues by carrying out CA-ID-TIMS U-Pb geochronology on Apollo 14 zircon fragments, followed by Hf isotope determination by solution MC-ICP-MS on the same volume of zircon. By constructing Hf model ages from zircons that are concordant to the sub-permil level, we show that the minimum age for the end of differentiation of the LMO, and by extension, the formation of the Moon, is 4.52 ± 0.01 Ga.

Apollo experience report: Guidance and control systems: Command and service module entry monitor subsystem

NASA Technical Reports Server (NTRS)

Reina, B., Jr.; Patterson, H. G.

1975-01-01

The conceptual aspects of the command and service module entry monitor subsystem, together with an interpretation of the displays and their associated relationship to entry trajectory control, are presented. The entry monitor subsystem is described, and the problems encountered during the developmental phase and the first five manned Apollo flights are discussed in conjunction with the design improvements implemented.

Apollo 15 mission main parachute failure

NASA Technical Reports Server (NTRS)

1971-01-01

The failure of one of the three main parachutes of the Apollo 15 spacecraft was investigated by studying malfunctions in the forward heat shield, broken riser, and firing the fuel expelled from the command module reaction control system. It is concluded that the most probable cause was the burning of raw fuel being expelled during the latter portion of depletion firing. Recommended corrective actions are included.

Astronauts Young and Duke participate in training with Lunar Roving Vehicle

NASA Technical Reports Server (NTRS)

1972-01-01

Astronauts John W. Young (right) and Charles M. Duke Jr., participate in simulation training with the Lunar Roving Vehicle (LRV) during Apollo 16 pre-launch activity at the Kennedy Space Center. All systems on the LRV-2 were activated and checked for trouble-free operation during the simulations. Young is the Apollo 16 commander; and Duke is the lunar module pilot.

Mission Architecture Comparison for Human Lunar Exploration

NASA Technical Reports Server (NTRS)

Geffre, Jim; Robertson, Ed; Lenius, Jon

2006-01-01

The Vision for Space Exploration outlines a bold new national space exploration policy that holds as one of its primary objectives the extension of human presence outward into the Solar System, starting with a return to the Moon in preparation for the future exploration of Mars and beyond. The National Aeronautics and Space Administration is currently engaged in several preliminary analysis efforts in order to develop the requirements necessary for implementing this objective in a manner that is both sustainable and affordable. Such analyses investigate various operational concepts, or mission architectures , by which humans can best travel to the lunar surface, live and work there for increasing lengths of time, and then return to Earth. This paper reports on a trade study conducted in support of NASA s Exploration Systems Mission Directorate investigating the relative merits of three alternative lunar mission architecture strategies. The three architectures use for reference a lunar exploration campaign consisting of multiple 90-day expeditions to the Moon s polar regions, a strategy which was selected for its high perceived scientific and operational value. The first architecture discussed incorporates the lunar orbit rendezvous approach employed by the Apollo lunar exploration program. This concept has been adapted from Apollo to meet the particular demands of a long-stay polar exploration campaign while assuring the safe return of crew to Earth. Lunar orbit rendezvous is also used as the baseline against which the other alternate concepts are measured. The first such alternative, libration point rendezvous, utilizes the unique characteristics of the cislunar libration point instead of a low altitude lunar parking orbit as a rendezvous and staging node. Finally, a mission strategy which does not incorporate rendezvous after the crew ascends from the Moon is also studied. In this mission strategy, the crew returns directly to Earth from the lunar surface, and is thus referred to as direct return. Figures of merit in the areas of safety and mission success, mission effectiveness, extensibility, and affordability are used to evaluate and compare the lunar orbit rendezvous, libration point rendezvous, and direct return architectures, and this paper summarizes the results of those assessments.

Description of the docking module ECS for the Apollo-Soyuz Test Project.

NASA Technical Reports Server (NTRS)

Guy, W. W.; Jaax, J. R.

1973-01-01

The role of the Docking Module ECS (Environmental Control System) to be used on the Apollo-Soyuz Test mission is to provide a means for crewmen to transfer safely between the Apollo and Soyuz vehicles in a shirtsleeve environment. This paper describes the Docking Module ECS and includes the philosophy and rationale used in evaluating and selecting the capabilities that are required to satisfy the Docking Module's airlock function: (1) adjusting the pressure and composition of the atmosphere to effect crew transfer and (2) providing a shirtsleeve environment during transfer operations. An analytical evaluation is given of the environmental parameters (including CO2 level, humidity, and temperature) during a normal transfer timeline.

A rocket spectroscopic payload in support of the Apollo Telescope Mount experiments

NASA Technical Reports Server (NTRS)

Rugge, H. R.

1974-01-01

The scientific instrumentation and other payload systems of a solar rocket experiment are described in detail. The objectives of the rocket payload were: (1) to carry out high-spectral-resolution measurements of a coronal active region in the X-ray and extreme ultraviolet regions at the same time as high-spatial-resolution measurements were being made of the same active region by the Apollo Telescope Mount experiments flown on Skylab; and (2) to derive a physical model of the conditions in the coronal active regions, which dominate the X-ray spectrum of the nonflaring active sun, on the basis of data obtained from both the rocket instrumentation and several of the Apollo Telescope Mount experiments.

Dallas-Fort Worth, Texas as seen from the Apollo 6 unmanned spacecraft

NASA Image and Video Library

1968-04-06

AS06-02-1462 (4 April 1968) --- View of the Dallas-Fort Worth, Texas, area as photographed from the unmanned Apollo 6 (Spacecraft 020/Saturn 502) space mission. The highway and expressway system in and around both cities is clearly visible. North is toward left side of picture. Grapevine Reservoir and Garza-Little Elm Reservoir are to the north-west of Dallas. The city of Denton can be seen in left center of picture at conjunction of highways leading to both Fort Worth and Dallas. The Brazos River is in lower right corner. This photograph was made three hours and nine minutes after liftoff of the Apollo 6 space flight.

Saturn Apollo Program

NASA Image and Video Library

1972-04-01

The Lunar Roving Vehicle (LRV) was designed to transport astronauts and materials on the Moon. An LRV was used on each of the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17, in 1971 and 1972, to permit the crew to travel several miles from the lunar landing site. This photograph was taken during the Apollo 16 mission.

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Apollo2Go: a web service adapter for the Apollo genome viewer to enable distributed genome annotation.

PubMed

Klee, Kathrin; Ernst, Rebecca; Spannagl, Manuel; Mayer, Klaus F X

2007-08-30

Apollo, a genome annotation viewer and editor, has become a widely used genome annotation and visualization tool for distributed genome annotation projects. When using Apollo for annotation, database updates are carried out by uploading intermediate annotation files into the respective database. This non-direct database upload is laborious and evokes problems of data synchronicity. To overcome these limitations we extended the Apollo data adapter with a generic, configurable web service client that is able to retrieve annotation data in a GAME-XML-formatted string and pass it on to Apollo's internal input routine. This Apollo web service adapter, Apollo2Go, simplifies the data exchange in distributed projects and aims to render the annotation process more comfortable. The Apollo2Go software is freely available from ftp://ftpmips.gsf.de/plants/apollo_webservice.

Recommendations for Exploration Space Medicine from the Apollo Medical Operations Project

NASA Technical Reports Server (NTRS)

Scheuring, R. a.; Davis, J. R.; Duncan, J. M.; Polk, J. D.; Jones, J. A.; Gillis, D. B.

2007-01-01

Introduction: A study was requested in December, 2005 by the Space Medicine Division at the NASA-Johnson Space Center (JSC) to identify Apollo mission issues relevant to medical operations that had impact to crew health and/or performance. The objective was to use this new information to develop medical requirements for the future Crew Exploration Vehicle (CEV), Lunar Surface Access Module (LSAM), Lunar Habitat, and Advanced Extravehicular Activity (EVA) suits that are currently being developed within the exploration architecture. Methods: Available resources pertaining to medical operations on the Apollo 7 through 17 missions were reviewed. Ten categories of hardware, systems, or crew factors were identified in the background research, generating 655 data records in a database. A review of the records resulted in 280 questions that were then posed to surviving Apollo crewmembers by mail, face-to-face meetings, or online interaction. Response analysis to these questions formed the basis of recommendations to items in each of the categories. Results: Thirteen of 22 surviving Apollo astronauts (59%) participated in the project. Approximately 236 pages of responses to the questions were captured, resulting in 107 recommendations offered for medical consideration in the design of future vehicles and EVA suits based on the Apollo experience. Discussion: The goals of this project included: 1) Develop or modify medical requirements for new vehicles; 2) create a centralized database for future access; and 3) take this new knowledge and educate the various directorates at NASA-JSC who are participating in the exploration effort. To date, the Apollo Medical Operations recommendations are being incorporated into the exploration mission architecture at various levels and a centralized database has been developed. The Apollo crewmembers input has proved to be an invaluable resource, prompting ongoing collaboration as the requirements for the future exploration missions continue to evolve and be refined.

Restoration and Reexamination of Data from the Apollo 11, 12, 14, and 15 Dust, Thermal and Radiation Engineering Measurements Experiments

NASA Technical Reports Server (NTRS)

McBride, Marie J.; Williams, David R.; Kent, H.; Turner, Niescja

2012-01-01

As part of an effort by the Lunar Data Node (LDN) we are restoring data returned by the Apollo Dust, Thermal, and Radiation Engineering Measurements (DTREM) packages emplaced on the lunar surface by the crews of Apollo 11, 12, 14, and 15. Also commonly known as the Dust Detector experiments, the DTREM packages measured the outputs of exposed solar cells and thermistors over time. They operated on the surface for up to nearly 8 years, returning data every 54 seconds. The Apollo 11 DTREM was part of the Early Apollo Surface Experiments Package (EASEP), and operated for a few months as planned following emplacement in July 1969. The Apollo 12, 14, and 15 DTREMs were mounted on the central station as part of the Apollo Lunar Surface Experiments Package (ALSEP) and operated from deployment until ALSEP shutdown in September 1977. The objective of the DTREM experiments was to determine the effects of lunar and meteoric dust, thermal stresses, and radiation exposure on solar cells. The LDN, part of the Geosciences Node of the Planetary Data System (PDS), operates out of the National Space Science Data Center (NSSDC) at Goddard Space Flight Center. The goal of the LDN is to extract lunar data stored on older media and/or in obsolete formats, restore the data into a usable digital format, and archive the data with PDS and NSSDC. For the DTREM data we plan to recover the raw telemetry, translate the raw counts into appropriate output units, and then apply calibrations. The final archived data will include the raw, translated, and calibrated data and the associated conversion tables produced from the microfilm, as well as ancillary supporting data (metadata) packaged in PDS format.

Restoration of Apollo Data for Future Lunar Exploration

NASA Astrophysics Data System (ADS)

Schultz, Alfred B.; Williams, D. R.; Hills, H. K.

2007-10-01

The Lunar Data Project (LDP) at NASA's National Space Science Data Center (NSSDC) is retrieving and restoring relevant, scientifically important Apollo data into accessible digital form for use by researchers and mission planners. Much of the Apollo data housed at the NSSDC are in forms which are not readily usable, such as microfilm, hardcopy, and magnetic tapes written using machine representations of computers no longer in use. The LDP has prioritized these data based on scientific and engineering value and level of effort required and is in the process of restoring these data collections. In association with the Planetary Data System (PDS), the restored data are converted into standard format and subject to a data peer review before ingestion into PDS. The Apollo 12 and 15 Solar Wind Spectrometer data have been restored and are awaiting data review. The Apollo 14 and 15 ALSEP Cold Cathode Ion Gage data have been scanned, the Apollo 14 Dust, Thermal, and Radiation Engineering Measurements data are in the process of being scanned, and the Apollo 14 Charged Particle Lunar Environment Experiment data have been retrieved from magnetic tape. An optical character recognition software to produce digital tables of the scanned data, where appropriate, is under development. These data represent some of the only long-term lunar surface environment information that exists. We will report on our progress. Metadata, ancillary information to aid in the use and understanding of the data, will be included in these online data collections. These cover complete descriptions of the data sets, formats, processing history, relevant references and contacts, and instrument descriptions. Restored data and associated metadata are posted online and easily accessible to interested users. The data sets and more information on the LDP can be found at nssdc.gsfc.nasa.gov/planetary/lunar/lunar_data/

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Using Technology to Better Characterize the Apollo Sample Suite: A Retroactive PET Analysis and Potential Model for Future Sample Return Missions

NASA Technical Reports Server (NTRS)

Zeigler, R. A.

2015-01-01

From 1969-1972 the Apollo missions collected 382 kg of lunar samples from six distinct locations on the Moon. Studies of the Apollo sample suite have shaped our understanding of the formation and early evolution of the Earth-Moon system, and have had important implications for studies of the other terrestrial planets (e.g., through the calibration of the crater counting record) and even the outer planets (e.g., the Nice model of the dynamical evolution of the Solar System). Despite nearly 50 years of detailed research on Apollo samples, scientists are still developing new theories about the origin and evolution of the Moon. Three areas of active research are: (1) the abundance of water (and other volatiles) in the lunar mantle, (2) the timing of the formation of the Moon and the duration of lunar magma ocean crystallization, (3) the formation of evolved lunar lithologies (e.g., granites) and implications for tertiary crustal processes on the Moon. In order to fully understand these (and many other) theories about the Moon, scientists need access to "new" lunar samples, particularly new plutonic samples. Over 100 lunar meteorites have been identified over the past 30 years, and the study of these samples has greatly aided in our understanding of the Moon. However, terrestrial alteration and the lack of geologic context limit what can be learned from the lunar meteorites. Although no "new" large plutonic samples (i.e., hand-samples) remain to be discovered in the Apollo sample collection, there are many large polymict breccias in the Apollo collection containing relatively large (approximately 1 cm or larger) previously identified plutonic clasts, as well as a large number of unclassified lithic clasts. In addition, new, previously unidentified plutonic clasts are potentially discoverable within these breccias. The question becomes how to non-destructively locate and identify new lithic clasts of interest while minimizing the contamination and physical degradation of the samples.

NASA Crew and Cargo Launch Vehicle Development Approach Builds on Lessons from Past and Present Missions

NASA Technical Reports Server (NTRS)

Dumbacher, Daniel L.

2006-01-01

The United States (US) Vision for Space Exploration, announced in January 2004, outlines the National Aeronautics and Space Administration's (NASA) strategic goals and objectives, including retiring the Space Shuttle and replacing it with new space transportation systems for missions to the Moon, Mars, and beyond. The Crew Exploration Vehicle (CEV) that the new human-rated Crew Launch Vehicle (CLV) lofts into space early next decade will initially ferry astronauts to the International Space Station (ISS) Toward the end of the next decade, a heavy-lift Cargo Launch Vehicle (CaLV) will deliver the Earth Departure Stage (EDS) carrying the Lunar Surface Access Module (LSAM) to low-Earth orbit (LEO), where it will rendezvous with the CEV launched on the CLV and return astronauts to the Moon for the first time in over 30 years. This paper outlines how NASA is building these new space transportation systems on a foundation of legacy technical and management knowledge, using extensive experience gained from past and ongoing launch vehicle programs to maximize its design and development approach, with the objective of reducing total life cycle costs through operational efficiencies such as hardware commonality. For example, the CLV in-line configuration is composed of a 5-segment Reusable Solid Rocket Booster (RSRB), which is an upgrade of the current Space Shuttle 4- segment RSRB, and a new upper stage powered by the liquid oxygen/liquid hydrogen (LOX/LH2) J-2X engine, which is an evolution of the J-2 engine that powered the Apollo Program s Saturn V second and third stages in the 1960s and 1970s. The CaLV configuration consists of a propulsion system composed of two 5-segment RSRBs and a 33- foot core stage that will provide the LOX/LED needed for five commercially available RS-68 main engines. The J-2X also will power the EDS. The Exploration Launch Projects, managed by the Exploration Launch Office located at NASA's Marshall Space Flight Center, is leading the design, development, testing, and operations planning for these new space transportation systems. Utilizing a foundation of heritage hardware and management lessons learned mitigates both technical and programmatic risk. Project engineers and managers work closely with the Space Shuttle Program to transition hardware, infrastructure, and workforce assets to the new launch systems, leveraging a wealth of knowledge from Shuffle operations. In addition, NASA and its industry partners have tapped into valuable Apollo databases and are applying corporate wisdom conveyed firsthand by Apollo-era veterans of America s original Moon missions. Learning from its successes and failures, NASA employs rigorous systems engineering and systems management processes and principles in a disciplined, integrated fashion to further improve the probability of mission success.

PISCES: An environment for parallel scientific computation

NASA Technical Reports Server (NTRS)

Pratt, T. W.

1985-01-01

The parallel implementation of scientific computing environment (PISCES) is a project to provide high-level programming environments for parallel MIMD computers. Pisces 1, the first of these environments, is a FORTRAN 77 based environment which runs under the UNIX operating system. The Pisces 1 user programs in Pisces FORTRAN, an extension of FORTRAN 77 for parallel processing. The major emphasis in the Pisces 1 design is in providing a carefully specified virtual machine that defines the run-time environment within which Pisces FORTRAN programs are executed. Each implementation then provides the same virtual machine, regardless of differences in the underlying architecture. The design is intended to be portable to a variety of architectures. Currently Pisces 1 is implemented on a network of Apollo workstations and on a DEC VAX uniprocessor via simulation of the task level parallelism. An implementation for the Flexible Computing Corp. FLEX/32 is under construction. An introduction to the Pisces 1 virtual computer and the FORTRAN 77 extensions is presented. An example of an algorithm for the iterative solution of a system of equations is given. The most notable features of the design are the provision for several granularities of parallelism in programs and the provision of a window mechanism for distributed access to large arrays of data.

Rocketdyne - SE-7 and SE-8 Engines. Chapter 4, Appendix F

NASA Technical Reports Server (NTRS)

Harmon, Tim

2009-01-01

The 70-pound SE-7 engine is very similar with its two valves, ablative material, a silicon carbide liner, a silicon carbide throat, and overall configuration. There were different wraps. One had a ninety-degree ablative material orientation. That is important because it caused problems with the SE-8, but not for this application. It was not overly stressed. It was a validation of the off-the-shelf application approach. There were two SE-7 engines located on the stage near the bottom. They had their own propellant tanks. That was the application. All it did was give a little bit of gravity by firing to push the propellants to the bottom of the tanks for start or restart. It was not a particularly complicated setup. (See Slides 6 and 7, Appendix F) What had we learned? This was a proven engine in a space environment. There weren't any development issues. Off-the-shelf seemed to work. There were no operational issues, which made the SE-7 very cost-effective. Besides NASA, the customer for this application was the Douglas Aircraft Company. Douglas decided the off-the-shelf idea was cost-effective. With the Gemini Program, the company was McDonnell Aircraft Corporation, which was part of the reason the off-the-shelf idea was applied to the Apollo. (See Slide 8, Appendix F) However, here are some differences between Apollo and Gemini vehicles. For one thing, the Apollo vehicle was really moving at high speed when it re-entered the atmosphere. Instead of a mere 17,000 miles per hour, it was going 24,000 miles per hour. That meant the heat load was four times as high on the Apollo vehicle as on the Gemini craft. Things were vibrating a little more. We had two redundant systems. Apollo was redundant where it could be as much as possible. That was really a keystone or maybe an anchor point for Apollo. We decided to pursue the off-the-shelf approach. However, the prime contractor was a different entity - the North American Space Division. They thought they ought to tune up this off-the-shelf setup. It was a similar off-the-shelf application, but at a higher speed. They wanted to improve it. What they wanted to improve was the material performance of silicon carbide. They were uncomfortable with the cracks they were seeing. They were uncomfortable with the cracks in the throat, and feeling that the environment was a little tougher, that maybe it was going to rattle, perhaps something would fall out, and they would have a problem. They wanted to eliminate the ceramic liner, and they wanted a different throat material. (See Slides 9 and 10, Appendix F) The Rocketdyne solutions were to replace silicon carbide material with a more forgiving ceramic material. Also, due to the multiple locations within the vehicle, the shape of the nozzles varied. Some nozzles were long, and some nozzles were short. We came up with a single engine design with variable nozzle extensions and configurations to fit particular vehicle locations. (See Slides 10 and 11, Appendix F)

KSC-2014-3190

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At the Kennedy Space Center in Florida, NASA officials and Apollo astronauts visiting Launch Pad 39B with their families and friends preserve the moment with a group portrait. The group was at Kennedy for a ceremony renaming the Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. From left are NASA Administrator Charles Bolden, Apollo astronaut Jim Lovell, Neil's son Mark Armstrong, Neil's granddaughter Lily Armstrong, Neil's son Rick Armstrong, Neil's grandson Bryce Armstrong, Neil's former wife Janet Armstrong, Apollo 11 moonwalker Buzz Aldrin, and Apollo 11 command module pilot Michael Collins. The pad is being modified to support the agency's new Orion spacecraft which will lift off atop the Space Launch System rocket. Orion is designed to take humans farther than they’ve ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Neil Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Michael Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

Growth-rate periodicity of Streptomyces levoris during space flight.

PubMed

Rogers, T D; Brower, M E; Taylor, G R

1977-01-01

Streptomyces levoris Kras was used is an experimental test micro-organism during the Apollo Soyuz Test Project to study alternating vegetative mycelial and spore ring periodicity during space flight. Four cultures were launched in each of the spacecrafts (Apollo and Soyuz). During the joint space-flight activities, two cultures from each spacecraft were exchanged. Selected duplicate cultures were maintained as controls in both the USA and the USSR. Spore ring morphology was periodically documented by photographing the specimens at approximately 12-hr intervals during the pre-, in-, and post-flight periods of the experiment. A decreased growth-rate periodicity in all but one of the eight space-flight cultures was in part attributed to the reduced temperature in the spacecraft. One of the eight cultures grew at a faster rate in the reduced temperature environment of Apollo than did the ground controls. Three of the space-flight cultures developed double spore rings during the immediate post-flight period. This anomaly was attributed to re-entry into the earth's gravity. The absence of spores in portions of one ring formed during space flight may have been caused by nutritional defects or media abnormality. Extensive studies will be required to elucidate the cause of this detect with certainty. There was no visible evidence of wedges in the cultures which would suggest naturally occurring or radiation-induced mutagenic alteration during space flight.

Development and application of nonflammable, high-temperature beta fibers

NASA Technical Reports Server (NTRS)

Dawn, Frederic S.

1989-01-01

Recent advances in fiber technology have contributed to the success of the U.S. space program. The inorganic fiber Beta, developed as a result of efforts begun in the early 1960's and heightened following the January 27, 1967 Apollo fire is unique among inorganic and organic fibers. It has been developed into woven, nonwoven, knitted, braided, coated and printed structures. All of these were used extensively for the Apollo, Skylab, Apollo-Soyuz test project, space shuttle, Spacelab, and satellite programs. In addition to being used successfully in the space program, Beta fibers are being used commercially as firesafe fabrics in homes, hospitals, institutions, public buildings, aircraft, and public transportation, wherever total nonflammability is required. One of the most unique applications of the Beta composite structure is the roofing material for the 80,000-seat Detroit Lion's Silverdome and 5 square miles of the Jeddah International Airport in Saudi Arabia. This fiber has been successfully incorporated into 165 major public construction projects around the globe. The United States alone has used more than 12 million square yards of the material. Beta fiber has been used successfully to date and has a promising future with unlimited potential for both space and commercial application. Efforts are currently underway to improve Beta fiber to meet the requirements of extended service life for the Space Station Freedom, lunar outpost, and Mars exploration missions.

Apollo 16, LM-11 descent propulsion system final flight evaluation

NASA Technical Reports Server (NTRS)

Avvenire, A. T.

1974-01-01

The performance of the LM-11 descent propulsion system during the Apollo 16 missions was evaluated and found satisfactory. The average engine effective specific impulse was 0.1 second higher than predicted, but well within the predicted one sigma uncertainty of 0.2 seconds. Several flight measurement discrepancies existed during the flight as follows: (1) the chamber pressure transducer had a noticeable drift, exhibiting a maximum error of about 1.5 psi at approximately 130 seconds after engine ignition, (2) the fuel and oxidizer interface pressure measurements appeared to be low during the entire flight, and (3) the fuel propellant quantity gaging system did not perform within expected accuracies.

Micropaleontological studies of lunar and terrestrial precambrian materials

NASA Technical Reports Server (NTRS)

Schope, J. W.

1974-01-01

Optical microscopic and scanning electron microscopic studies of rock chips and dust returned by Apollo 14, 15, 16, and 17 are analyzed along with optical microscopic studies of petrographic thin sections of breccias and basalts returned by Apollo 14, 15, and 16. Results show no evidence of modern or fossil lunar organisms. The lunar surface is now, and apparently has been throughout the geologic past, inimical to known biologic systems.

Photogrammetry of Apollo 15 photography, part C

NASA Technical Reports Server (NTRS)

Wu, S. S. C.; Schafer, F. J.; Jordan, R.; Nakata, G. M.; Derick, J. L.

1972-01-01

In the Apollo 15 mission, a mapping camera system and a 61 cm optical bar, high resolution panoramic camera, as well as a laser altimeter were used. The panoramic camera is described, having several distortion sources, such as cylindrical shape of the negative film surface, the scanning action of the lens, the image motion compensator, and the spacecraft motion. Film products were processed on a specifically designed analytical plotter.

Saturn Apollo Program

NASA Image and Video Library

1967-11-07

A technician checks the systems of the Saturn V instrument unit in a test facility in Huntsville. This instrument unit was flown aboard Apollo 4 on November 7, 1967, which was the first test flight of the Saturn V. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

The Origin of Apollo Objects

DOE Office of Scientific and Technical Information (OSTI.GOV)

Perlmutter, Saul

1984-03-29

The source of the Earth-orbit-crossing asteroids has been much debated. (This class of asteroidal bodies includes the Apollo, Aten, and some Amor objects, each with its own orbital characteristics; we shall use the term Apollo objects to mean all Earth-crossers.) It is difficult to find a mechanism which would create new Apollo objects at a sufficient rate to balance the loss due to collision with planets and ejection from the solar system, and thus explain the estimated steady-state number. A likely source is the main asteroid belt, since it has similar photometric characteristics. There are gaps in the main beltmore » which correspond to orbits resonant with the orbits of Jupiter and Saturn, and it has been shown that the resonances can perturb a body into an Earth-crossing orbit. Apollo objects could thus be generated when random collisions between asteroids in the main belt sent fragments into these resonant orbits. Calculations of the creation rate from these random collisions, however, yielcl numbers too low by a factor of four. This rate could be significantly lower given the uncertainty in the efficiency of the resonance mechanism. As an alternative, it was suggested that the evaporation of a comet's volatile mantle as it passes near the sun could provide enough non-gravitational force to move the comet into an orbit with aphelion inside of Jupiter's orbit, and thus safe from ejection from the solar system. The probability of such an event occurring is unknown, although the recent discovery of the 'asteroid' 1983 TB, with an orbit matching that of the Geminid meteor shower, suggests that such a mechanism has occurred at least once. New evidence from paleontology and geophysics, however, suggests a better solution to the problem of the source of the Apollos. M. Davis, P. Hut, and R. A. Muller recently proposed that an unseen companion to the sun passes through the Oort cloud every 28 million years, sending a shower of comets to the Earth; this provides an explanation for the periodicity of the fossil record of extinctions found by D. M. Raup and J. J. Sepkoski. W. Alvarez and R. A. Muller have shown that the craters on the earth have an age distribution with a periodicity and phase consistent with this hypothesis. These periodic comet showers would of course pass through the entire solar system, colliding with other bodies besides the earth. When the target is the asteroid belt, many small comets will have sufficient kinetic energy to disrupt large asteroids. This will generate many more fragments in the resonant orbits than would be generated by random collisions of asteroids with each other, and hence more Apollo objects. In this report, we shall calculate approximately (A) the number of comets per shower which cross the asteroid belt, (B) the probability of collisions with a single asteroid per shower, (C) the number of fragments with radius > 0.5 km which reach Apollo orbits, and (D) the current expected number of Apollos derived from comet/asteroid collisions. Given conservative assumptions, the calculated number is in agreement with observations.« less

View of the orange soil which Apollo 17 crewmen found at Station 4 during EVA

NASA Image and Video Library

1972-12-12

AS17-137-20989 (12 Dec. 1972) --- A close-up view of the much-publicized orange soil which the Apollo 17 crewmen found at Station 4 (Shorty Crater) during the second Apollo 17 extravehicular activity (EVA) at the Taurus-Littrow landing site. The orange soil was first spotted by scientist-astronaut Harrison H. Schmitt. While astronauts Schmitt and Eugene A. Cernan descended in the Lunar Module (LM) "Challenger" to explore the lunar surface, astronaut Ronald E. Evans remained with the Apollo 17 Command and Service Modules (CSM) in lunar orbit. The orange soil was never seen by the crewmen of the other lunar landing missions - Apollo 11 (Sea of Tranquility); Apollo 12 (Ocean of Storms); Apollo 14 (Fra Mauro); Apollo 15 (Hadley-Apennines); and Apollo 16 (Descartes).

KSC-99pp0877

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- During an anniversary banquet honoring the Apollo program team, the people who made the entire lunar landing program possible, former Apollo astronaut Gene Cernan relates a humorous comment while Wally Schirra (background) gestures behind him. Cernan, who flew on Apollo 10 and 17, was the last man to walk on the moon; Schirra flew on Apollo 7. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Other guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing, and Walt Cunningham, who also flew on Apollo 7

Cernan, Stafford, and Young talk at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Discussing old times beneath the KSC Apollo/Saturn V rocket inside the building are (from left) Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Commander Thomas P. Stafford and Apollo 16 Commander John W. Young. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/ Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is photographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is phtographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

The fuel cell in space: Yesterday, today and tomorrow

NASA Technical Reports Server (NTRS)

Warshay, Marvin; Prokopius, Paul R.

1989-01-01

The past, present, and future of space fuel cell power systems is reviewed, starting with the first practical fuel cell by F.T. Bacon which led to the 1.5 kW Apollo alkaline fuel cell. However, the first fuel cell to be used for space power was the Gemini 1.0 kW Acid IEM fuel cell. The successor to the Apollo fuel cell is today's 12 kW Orbiter alkaline fuel cell whose technology is considerably different and considerably better than that of its ancestor, the Bacon cell. And in terms of specific weight there has been a steady improvement from the past to the present, from the close to 200 lb/kW of Apollo to the 20 lb/kW of the orbiter. For NASA future Lunar and Martian surface power requirements the regenerative fuel cell (RFC) energy storage system is enabling technology, with the alkaline and the PEM the leading RFC candidate systems. The U.S. Air Force continues to support fuel cell high power density technology development for its future short duration applications.

Apollo 13 Emblem

NASA Image and Video Library

1969-12-01

S69-60662 (December 1969) --- This is the insignia of the Apollo 13 lunar landing mission. The Apollo 13 prime crew will be astronauts James A. Lovell Jr., commander; Thomas K. Mattingly II, command module pilot; and Fred W. Haise Jr., lunar module pilot. Represented in the Apollo 13 emblem is Apollo, the sun god of Greek mythology, symbolizing how the Apollo flights have extended the light of knowledge to all mankind. The Latin phrase Ex Luna, Scientia means "From the Moon, Knowledge." Apollo 13 will be the National Aeronautics and Space Administration's (NASA) third lunar landing mission.

Apollo 14 regolith breccias - Different glass populations and their potential for charting space time variations

NASA Technical Reports Server (NTRS)

Delano, John W.

1988-01-01

Apollo 14 regolith breccias (14313, 14307, 14301, 14049, 14047) have been found to have different populations of nonagglutinitic, mare-derived glasses. These variations appear to not only reflect different source regoliths but also different closure ages for these breccias. Based upon these different glass populations, 14301 is inferred to have a closure age sometime during the epoch of mare volcanism. All of the other four breccias were formed after the termination of mare volcanism with a possible age sequence from old to young of the following: 14307, 14313, 14049, 14047. Due to the relative simplicity of acquiring high-quality chemical data on large numbers of glasses by electron microprobe, mare glass populations allow: (1) classification of regolith breccias with respect to provenance and (2) estimation of their relative and absolute closure ages. The determination of (Ar-40)-(Ar-39) ages on individual glass spherules within breccias using the laser probe should in the future prove to be a promising extension of the present study.

Apollo Saturn 511 effluent measurements from the Apollo 16 launch operations: An experiment

NASA Technical Reports Server (NTRS)

Gregory, G. L.; Hulten, W. C.; Wornom, D. E.

1974-01-01

An experiment was performed in conjunction with the Apollo 16 launch to define operational and instrumentational problems associated with launch-vehicle exhaust effluent monitoring. Ground and airborne sampling were performed for CO, CO2, hydrocarbons, and particulates. Sampling systems included filter pads and photometers for particulates and whole-air grab samples for gases. Launch debris was identified in the particulate samples at ground level(taken immediately after launch) and in the airborne measurements (taken 40 to 50 minutes after launch approximately 40 km downwind of the pad). Operational problems were identified and included the need for higher instrumentation mobility and the need for real-time sampling instrumentation as opposed to collection-type samples such as the whole-air grab sample.

Modeling of Lunar Dust Contamination Due to Plume Impingement

NASA Technical Reports Server (NTRS)

Woronowicz, Michael

2009-01-01

During the Apollo missions it became apparent that lunar dust was a significant hazard. Problems included: surface obscuration during landing sequence; abrasion damage to gouge faces and helmet visors; mechanism clogging; development of space suit pressurization leaks; loss of radiator heat rejection capabilities to the point where vulnerable equipment exceeded maximum survival temperature ratings; temporary vision and respiratory problems within the Apollo Lunar Module (LM). NASA Constellation Program features many system-level components, including the Altair Lunar Lander. Altair to endure longer periods at lunar surface conditions: Apollo LM, about three days; Altair, over seven months. Program managers interested in plume-generated dust transport onto thermal control surface radiators of the first Altair created by its own landing operations.

Apollo 16 Command Module during recovery operations after splashdown

NASA Image and Video Library

1972-04-27

S72-36602 (27 April 1972) --- The Apollo 16 Command Module bobbles photographed in the waters of the central Pacific Ocean during recovery operations. The prime recovery ship, USS Ticonderoga, is in the background. A recovery helicopter hovers overhead. The Apollo 16 crew, astronauts John W. Young, Thomas K. Mattingly II, and Charles M. Duke Jr., were picked up by helicopter and flown to the deck of the ship. The splashdown occurred at 290:37:06 ground elapsed time, 1:45:06 p.m. (CST), Thursday, April 27, 1972, at coordinates of 00:45.2 degrees south latitude and 156:11.4 degrees west longitude, a point approximately 215 miles southeast of Christmas Island. A team of Earth Landing System swimmers assisted with the recovery operations.

KSC-99pp0875

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

NASA Administrator Dan Goldin greets Neil Armstrong at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

During an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible, former Apollo astronaut Neil A. Armstrong (left) shakes the hand of Judy Goldin (center), wife of NASA Administrator Daniel S. Goldin (right). The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Apollo2Go: a web service adapter for the Apollo genome viewer to enable distributed genome annotation

PubMed Central

Klee, Kathrin; Ernst, Rebecca; Spannagl, Manuel; Mayer, Klaus FX

2007-01-01

Background Apollo, a genome annotation viewer and editor, has become a widely used genome annotation and visualization tool for distributed genome annotation projects. When using Apollo for annotation, database updates are carried out by uploading intermediate annotation files into the respective database. This non-direct database upload is laborious and evokes problems of data synchronicity. Results To overcome these limitations we extended the Apollo data adapter with a generic, configurable web service client that is able to retrieve annotation data in a GAME-XML-formatted string and pass it on to Apollo's internal input routine. Conclusion This Apollo web service adapter, Apollo2Go, simplifies the data exchange in distributed projects and aims to render the annotation process more comfortable. The Apollo2Go software is freely available from . PMID:17760972

Apollo 13 emblem

NASA Technical Reports Server (NTRS)

1969-01-01

This is the insignia of the Apollo 13 lunar landing mission. Represented in the Apollo 13 emblem is Apollo, the sun god of Greek mythology, symbolizing how the Apollo flights have extended the light of knowledge to all mankind. The Latin phrase Ex Luna, Scientia means 'From the Moon, Knowledge'.

Apollo 17: On the Shoulders of Giants

NASA Technical Reports Server (NTRS)

1973-01-01

A documentary view of the Apollo 17 journey to Taurus-Littrow, the final lunar landing mission in the Apollo program is discussed. The film depicts the highlights of the mission and relates the Apollo program to Skylab, the Apollo-Soyuz linkup and the Space Shuttle.

KSC-2014-3232

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At the Kennedy Space Center in Florida, NASA officials and Apollo astronauts tour the refurbished Operations and Checkout Building, newly named for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Viewing the Orion crew module stacked on top of the service module from left, are Kennedy Center Director Bob Cabana, Apollo 11 astronaut Michael Collins, Apollo astronaut Jim Lovell, Apollo 11 astronaut Buzz Aldrin, and NASA Administrator Charlie Bolden. The building's high bay is being used to support the agency's new Orion spacecraft, which will lift off atop the Space Launch System. Orion is designed to take humans farther than they've ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the moon landing. As the world watched, Neil Armstrong and Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56699 (22 Oct. 1969) --- Astronauts Charles Conrad Jr. (left), Apollo 12 commander; and Alan L. Bean, lunar module pilot, are shown in the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

Pack Density Limitations of Hybrid Parachutes

NASA Technical Reports Server (NTRS)

Zwicker, Matthew L.; Sinclair, Robert J.

2013-01-01

The development and testing of the Orion crew capsule parachute system has provided a unique opportunity to study dense parachute packing techniques and limits, in order to establish a new baseline for future programs. The density of parachute packs has a significant influence on vibration loads, retention system stresses, and parachute mortar performance. Material compositions and pack densities of existing designs for space capsule recovery were compared, using the pack density of the Apollo main parachutes as the current baseline. The composition of parachutes has changed since Apollo, incorporating new materials such as Kevlar , Vectran , Teflon and Spectra . These materials have different specific densities than Nylon, so the densities of hybrid parachute packs cannot be directly compared to Nylon parachutes for determination of feasibility or volume allocation. Six parachute packs were evaluated in terms of weighted average solid density in order to achieve a non-dimensional comparison of packing density. Means of mitigating damage due to packing pressure and mortar firing were examined in light of the Capsule Parachute Assembly System (CPAS) and Apollo experience. Parachute design improvements including incorporation of modern materials and manufacturing processes serves to make CPAS the new knowledge base on which future spacecraft parachute systems will be built.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-08-11

Eugene Cernan (Apollo 10, Apollo 17) , right, speaks, as Thomas Stafford (Apollo 10) looks on during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington Photo Credit: (NASA/Paul E. Alers)

MSFC Skylab Apollo Telescope Mount summary mission report

NASA Technical Reports Server (NTRS)

Morse, A. R.

1974-01-01

A summary of the Apollo Telescope Mount (ATM) performance during the 8.5-month Skylab mission is presented. A brief description of each ATM system, system performance summaries, discussion of all significant ATM anomalies which occurred during the Skylab mission, and, in an appendix, a summary of the Skylab ATM Calibration Rocket Project (CALROC) are provided. The text is supplemented and amplified by photographs, drawings, curves, and tables. The report shows that the ATM not only met, but exceeded premission performance criteria, and that participation of man in space for this scientific investigation greatly enhanced the quality and quantity of the data attained.

Aerial Video Imaging

NASA Technical Reports Server (NTRS)

1991-01-01

When Michael Henry wanted to start an aerial video service, he turned to Johnson Space Center for assistance. Two NASA engineers - one had designed and developed TV systems in Apollo, Skylab, Apollo- Soyuz and Space Shuttle programs - designed a wing-mounted fiberglass camera pod. Camera head and angles are adjustable, and the pod is shaped to reduce vibration. The controls are located so a solo pilot can operate the system. A microprocessor displays latitude, longitude, and bearing, and a GPS receiver provides position data for possible legal references. The service has been successfully utilized by railroads, oil companies, real estate companies, etc.

Apollo experience report: Voice communications techniques and performance

NASA Technical Reports Server (NTRS)

Dabbs, J. H.; Schmidt, O. L.

1972-01-01

The primary performance requirement of the spaceborne Apollo voice communications system is percent word intelligibility, which is related to other link/channel parameters. The effect of percent word intelligibility on voice channel design and a description of the verification procedures are included. Development and testing performance problems and the techniques used to solve the problems are also discussed. Voice communications performance requirements should be comprehensive and verified easily; the total system must be considered in component design, and the necessity of voice processing and the associated effect on noise, distortion, and cross talk should be examined carefully.

Apollo experience report: Crew provisions and equipment subsystem

NASA Technical Reports Server (NTRS)

Mcallister, F.

1972-01-01

A description of the construction and use of crew provisions and equipment subsystem items for the Apollo Program is presented. The subsystem is composed principally of survival equipment, bioinstrumentation devices, medical components and accessories, water- and waste-management equipment, personal-hygiene articles, docking aids, flight garments (excluding the pressure garment assembly), and various other crew-related accessories. Particular attention is given to items and assemblies that presented design, development, or performance problems: the crew optical alinement sight system, the metering water dispenser, and the waste-management system. Changes made in design and materials to improve the fire safety of the hardware are discussed.

Restoration and Future Analysis of the Apollo Lunar Dust Detector Data

NASA Astrophysics Data System (ADS)

McBride, M.; Williams, D. R.; Hills, H. K.

2012-12-01

The Dust, Thermal and Radiation Engineering Measurement (DTREM) packages mounted on the central stations of the Apollo 11, 12, 14, and 15 ALSEPs (Apollo Lunar Surface Experiments Packages) measured the outputs of exposed solar cells and thermistors over time. The goal of the experiment, also commonly known as the dust detector, was to study the long-term effects of dust, radiation, and temperature at the lunar surface on solar cells. The original data were never archived with NASA, with the exception of 38 reels of microfilm archived at the National Space Science Data Center. These reels contained images of computer printouts of times and raw and calibrated DTREM data for Apollo 14 and 15. The high volume of data is not readily accessible in this form. The raw telemetry for the DTREM also exists as part of the ALSEP housekeeping (Word 33) telemetry. As part of the lunar data restoration effort we are converting the telemetry to digital tables containing the fully calibrated dust detector data. These restored data sets will be archived through the Lunar Data Node of the Planetary Data System (PDS) for general use by the lunar community. In this form, these data will finally be amenable to study by modern techniques not available during the Apollo era. Over the past year, analysis of the correlation between the NSSDC microfilm record and the raw telemetry was used to determine the translations and calibrations necessary to convert the digital telemetry into a fully calibrated data set giving temperatures and solar cell outputs over time. The final data set consists of a reading every 54 seconds over periods of 5 years for Apollo 14 and 15. The sheer quantity of data shows why a fully digital form is necessary for proper analysis. The Apollo 11 DTREM was designed for a short lifetime and returned less than two lunations of data. We do not currently have the translation and calibration information necessary to convert the raw telemetry to a calibrated data set for Apollo 11, but we have found some preliminary information which we believe will lead to full restoration of this data set. The dust detector on Apollo 12 was configured differently from the other DTREMs. While the Apollo 11, 14, and 15 instruments had three upward-facing solar cells, one glass-covered, one uncovered, and one pre-irradiated and glass-covered, the Apollo 12 dust detector had three identical cells with only one facing upwards. The other two faced to the east and west, respectively. For Apollo 12 we have the raw telemetry but not the necessary calibration information to fully restore these data sets. As with Apollo 11, we are attempting to obtain the required information to translate the raw telemetry counts into voltages and temperatures and apply the correct calibrations. We are also currently analyzing the restored and raw data and will present results of our analysis, including revisiting the earlier published Apollo results. The scientific community has shown great interest in the outcome of these restorations. The microfilm data have been scanned and converted to PDS data sets which have undergone review and will be archived. The digital data sets will soon be available to the full lunar community after restoration has been completed and they have undergone PDS review and validation.

Inflight dynamics testing of the Apollo spacecraft

NASA Technical Reports Server (NTRS)

Peters, W. H.; Marchantel, B.

1972-01-01

Response of the Apollo command module, service and lunar module airframe while in a docked configuration in the flight environment was measured in a frequency band encompassing the first two bending modes. Transfer characteristics from thrust-application point to control-system sensor were examined. The frequency and the stability margins of the first two predominant structural resonances were verified by the test. This report describes the flight test that was performed and the postflight data analysis.

Saturn Apollo Program

NASA Image and Video Library

1970-06-01

This image depicts the Apollo 16 mission astronauts John Young (right) and Charles Duke (left) in pressure suits during a final crew training on the Lunar Roving Vehicle (LRV) at the Marshall Space Flight Center (MSFC), building 4619. Developed by the MSFC, the LRV was the lightweight electric car designed to increase the range of mobility and productivity of astronauts on the lunar surface. It was used on the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17.

Project management in the Apollo program: An interdisciplinary study

NASA Technical Reports Server (NTRS)

Drucker, E. E.; Pooler, W. S.; Wilemon, D. L.; Wood, B. D.

1972-01-01

Findings concerning project management in the NASA Apollo program are presented. The Apollo program in the context of the total NASA organization is examined along with the nature of project management and the manner in which project managers functioned in the Apollo program. The utilization of the in-house technical competence in the support of the Apollo program, and the formal and informal relationships between Apollo managers and the contractors are discussed.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, at left, the Apollo, Challenger, Columbia Lessons Learned Program manager, presents a certificate to Charlie Duke, former Apollo 16 astronaut and member of the Apollo 1 Emergency Egress Investigation Team, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The program's theme was "To There and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-99pp0874

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

Cernan, Stafford, and Young talk at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Some of the former Apollo program astronauts tour the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. The astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. Discussing old times are (from left) Apollo 10 Lunar Module Pilot and Apollo 17 Commander Eugene A. Cernan; Apollo 10 Commander Thomas P. Stafford and Apollo 16 Commander John W. Young. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/ Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Apollo 13 MCC - MSC

NASA Image and Video Library

1970-04-14

S70-34986 (14 April 1970) --- A group of six astronauts and two flight controllers monitor the console activity in the Mission Operations Control Room (MOCR) of the Mission Control Center (MCC) during the problem-plagued Apollo 13 lunar landing mission. Seated, left to right, are MOCR Guidance Officer Raymond F. Teague; astronaut Edgar D. Mitchell, Apollo 14 prime crew lunar module pilot; and astronaut Alan B. Shepard Jr., Apollo 14 prime crew commander. Standing, left to right, are scientist-astronaut Anthony W. England; astronaut Joe H. Engle, Apollo 14 backup crew lunar module pilot; astronaut Eugene A. Cernan, Apollo 14 backup crew commander; astronaut Ronald E. Evans, Apollo 14 backup crew command module pilot; and M.P. Frank, a flight controller. When this picture was made, the Apollo 13 moon landing had already been canceled, and the Apollo 13 crew men were in trans-Earth trajectory attempting to bring their damaged spacecraft back home.

Update on Apollo Data Restoration by the NSSDC and the PDS Lunar Data Node

NASA Technical Reports Server (NTRS)

Williams, David R.; Hills, K. Kent; Taylor, Patrick T.; McBride, Marie J.; Guinness, Edward A.

2012-01-01

The Lunar Data Node (LDN) , under the auspices of the Geosciences Node of the Planetary Data System (PDS) and the National Space Science Data Center (NSSDC), is continuing its efforts to recover and restore Apollo science data. The data being restored are in large part archived with NSSDC on older media, but unarchived data are also being recovered from other sources. They are typically on 7- or 9-track magnetic tapes, often in obsolete formats, or held on microfilm, microfiche, or paper documents. The goal of the LDN is to restore these data from their current form, which is difficult for most researchers to access, into common digital formats with all necessary supporting data (metadata) and archive the data sets with PDS. Restoration involves reading the data from the original media, deciphering the data formats to produce readable digital data and converting the data into usable tabular formats. Each set of values in the table must then be understood in terms of the quantity measured and the units used. Information on instrument properties, operational history, and calibrations is gathered and added to the data set, along with pertinent references, contacts, and other ancillary documentation. The data set then undergoes a peer review and the final validated product is archived with PDS. Although much of this effort has concentrated on data archived at NSSDC in the 1970's, we have also recovered data and information that were never sent to NSSDC. These data, retrieved from various outside sources, include raw and reduced Gamma-Ray Spectrometer data from Apollos 15 and 16, information on the Apollo 17 Lunar Ejecta And Meteorites experiment, Dust Detector data from Apollos 11, 12, 14, and I5, raw telemetry tapes from the Apollo ALSEPs, and Weekly Status Reports for all the Apollo missions. These data are currently being read or organized, and supporting data is being gathered. We are still looking for the calibrated heat flow data from Apollos 15 and 17 for the period 1975-1977, any assistance or information on these data would be welcome. NSSDC has recently been tasked to release its hard-copy archive, comprising photography, microfilm, and microfiche. The details are still being discussed, but we are concentrating on recovering the valuable lunar data from these materials while they are still readily accessible. We have identified the most critical of these data and written a LASER proposal to fund their restoration. Included in this effort are data from the Apollo 15 and 16 Mass Spectrometers and the Apollo 17 Par-UV Spectrometer and ancillary information on the Apollo 17 Surface Electrical Properties Experiment.

Antibody engineering--a valuable asset in preventing closed environment epidemics.

PubMed

Fjallman, Ted; Hall, J Christopher

2005-01-01

Investigations of Mir, Space Shuttle, Skylab and Apollo missions report extensive colonisation of the spacecraft by bacteria and fungi, which can lead to degradative effects on spacecraft equipment and devastating effects on space-grown crops. More than 80% of terrestrial greenhouse epidemics are due to the fungal genera Phytophthora, Pythium and Fusarium, which have been found in life support system test-beds. The advent of recombinant antibody technologies, including ribosome display and phage display, has made it possible to develop antibodies against virtually any toxin or organism and allows for maturation of antibodies by in vitro molecular evolution. These antibodies may play an important role in an integrated pest management regime for life support systems. Efficacy of existing fungal countermeasures could be increased by chemical linkage to antibodies, which target the site of action of the biocide or trap the pathogen in a biofilter. Novel recombinant antibody-biocide fusions can be expressed in situ by plants or symbiotic microbes to create direct disease resistance. c2005 Elsevier Ltd. All rights reserved.

Long-lasting Science Returns from the Apollo Heat Flow Experiments

NASA Astrophysics Data System (ADS)

Nagihara, S.; Taylor, P. T.; Williams, D. R.; Zacny, K.; Hedlund, M.; Nakamura, Y.

2012-12-01

The Apollo astronauts deployed geothermal heat flow instruments at landing sites 15 and 17 as part of the Apollo Lunar Surface Experiments Packages (ALSEP) in July 1971 and December 1972, respectively. These instruments continuously transmitted data to the Earth until September 1977. Four decades later, the data from the two Apollo sites remain the only set of in-situ heat flow measurements obtained on an extra-terrestrial body. Researchers continue to extract additional knowledge from this dataset by utilizing new analytical techniques and by synthesizing it with data from more recent lunar orbital missions such as the Lunar Reconnaissance Orbiter. In addition, lessons learned from the Apollo experiments help contemporary researchers in designing heat flow instruments for future missions to the Moon and other planetary bodies. For example, the data from both Apollo sites showed gradual warming trends in the subsurface from 1971 to 1977. The cause of this warming has been debated in recent years. It may have resulted from fluctuation in insolation associated with the 18.6-year-cycle precession of the Moon, or sudden changes in surface thermal environment/properties resulting from the installation of the instruments and the astronauts' activities. These types of re-analyses of the Apollo data have lead a panel of scientists to recommend that a heat flow probe carried on a future lunar mission reach 3 m into the subsurface, ~0.6 m deeper than the depths reached by the Apollo 17 experiment. This presentation describes the authors' current efforts for (1) restoring a part of the Apollo heat flow data that were left unprocessed by the original investigators and (2) designing a compact heat flow instrument for future robotic missions to the Moon. First, at the conclusion of the ALSEP program in 1977, heat flow data obtained at the two Apollo sites after December 1974 were left unprocessed and not properly archived through NASA. In the following decades, heat flow data from January 1975 through February 1976, as well as the metadata necessary for processing the data (the data reduction algorithm, instrument calibration data, etc.), were somehow lost. In 2010, we located 450 original master archival tapes of unprocessed data from all the ALSEP instruments for a period of April through June 1975 at the Washington National Records Center. We are currently extracting the heat flow data packets from these tapes and processing them. Second, on future lunar missions, heat flow probes will likely be deployed by a network of small robotic landers, as recommended by the latest Decadal Survey of the National Academy of Science. In such a scenario, the heat flow probe must be a compact system, and that precludes use of heavy excavation equipment such as a rotary drill for reaching the 3-m target depth. The new heat flow system under development uses a pneumatically driven penetrator. It utilizes a stem that winds out of a reel and pushes its conical tip into the regolith. Simultaneously, gas jets, emitted from the cone tip, loosen and blow away the soil. Lab experiments have demonstrated its effectiveness in lunar vacuum.

Long-Lasting Science Returns from the Apollo Heat Flow Experiments

NASA Technical Reports Server (NTRS)

Nagihara, S.; Taylor, P. T.; Williams, D. R.; Zacny, K.; Hedlund, M.; Nakamura, Y.

2012-01-01

The Apollo astronauts deployed geothermal heat flow instruments at landing sites 15 and 17 as part of the Apollo Lunar Surface Experiments Packages (ALSEP) in July 1971 and December 1972, respectively. These instruments continuously transmitted data to the Earth until September 1977. Four decades later, the data from the two Apollo sites remain the only set of in-situ heat flow measurements obtained on an extra-terrestrial body. Researchers continue to extract additional knowledge from this dataset by utilizing new analytical techniques and by synthesizing it with data from more recent lunar orbital missions such as the Lunar Reconnaissance Orbiter. In addition, lessons learned from the Apollo experiments help contemporary researchers in designing heat flow instruments for future missions to the Moon and other planetary bodies. For example, the data from both Apollo sites showed gradual warming trends in the subsurface from 1971 to 1977. The cause of this warming has been debated in recent years. It may have resulted from fluctuation in insolation associated with the 18.6-year-cycle precession of the Moon, or sudden changes in surface thermal environment/properties resulting from the installation of the instruments and the astronauts' activities. These types of reanalyses of the Apollo data have lead a panel of scientists to recommend that a heat flow probe carried on a future lunar mission reach 3 m into the subsurface, approx 0.6 m deeper than the depths reached by the Apollo 17 experiment. This presentation describes the authors current efforts for (1) restoring a part of the Apollo heat flow data that were left unprocessed by the original investigators and (2) designing a compact heat flow instrument for future robotic missions to the Moon. First, at the conclusion of the ALSEP program in 1977, heat flow data obtained at the two Apollo sites after December 1974 were left unprocessed and not properly archived through NASA. In the following decades, heat flow data from January 1975 through February 1976, as well as the metadata necessary for processing the data (the data reduction algorithm, instrument calibration data, etc.), were somehow lost. In 2010, we located 450 original master archival tapes of unprocessed data from all the ALSEP instruments for a period of April through June 1975 at the Washington National Records Center. We are currently extracting the heat flow data packets from these tapes and processing them. Second, on future lunar missions, heat flow probes will likely be deployed by a network of small robotic landers, as recommended by the latest Decadal Survey of the National Academy of Science. In such a scenario, the heat flow probe must be a compact system, and that precludes use of heavy excavation equipment such as a rotary drill for reaching the 3-m target depth. The new heat flow system under development uses a pneumatically driven penetrator. It utilizes a stem that winds out of a reel and pushes its conical tip into the regolith. Simultaneously, gas jets, emitted from the cone tip, loosen and blow away the soil. Lab experiments have demonstrated its effectiveness in lunar vacuum.

The Lunar Atmosphere: History, Status, Current Problems, and Context

NASA Technical Reports Server (NTRS)

Stern, S. Alan .

1997-01-01

After decades of speculation and fruitless searches, the lunar atmosphere was first observed by Apollo surface and orbital instruments between 1970 and 1972. With the demise of Apollo in 1972, and the termination of funding for Apollo lunar ground station studies in 1977, the field withered for many years, but has recently enjoyed a renaissance. This reflowering has been driven by the discovery and exploration of sodium and potassium in the lunar exosphere by groundbased observers, the detection of metal ions derived from the Moon in interplanetary space, the possible discoveries of H2O ice at the poles of the Moon and Mercury, and the detections of tenuous atmospheres around more remote sites in the solar system, including Mercury and the Galilean satellites. In this review we summarize the present state of knowledge about the lunar atmosphere, describe the important physical processes taking place within it, and then discuss related topics including a comparison of the lunar atmosphere to other surface boundary exospheres in the solar system.

Comparison of Nonlinear Filtering Techniques for Lunar Surface Roving Navigation

NASA Technical Reports Server (NTRS)

Kimber, Lemon; Welch, Bryan W.

2008-01-01

Leading up to the Apollo missions the Extended Kalman Filter, a modified version of the Kalman Filter, was developed to estimate the state of a nonlinear system. Throughout the Apollo missions, Potter's Square Root Filter was used for lunar navigation. Now that NASA is returning to the Moon, the filters used during the Apollo missions must be compared to the filters that have been developed since that time, the Bierman-Thornton Filter (UD) and the Unscented Kalman Filter (UKF). The UD Filter involves factoring the covariance matrix into UDUT and has similar accuracy to the Square Root Filter; however it requires less computation time. Conversely, the UKF, which uses sigma points, is much more computationally intensive than any of the filters; however it produces the most accurate results. The Extended Kalman Filter, Potter's Square Root Filter, the Bierman-Thornton UD Filter, and the Unscented Kalman Filter each prove to be the most accurate filter depending on the specific conditions of the navigation system.

Development of the J-2X Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle: Building on the Apollo Program for Lunar Return Missions

NASA Technical Reports Server (NTRS)

Snoddy, Jim

2006-01-01

The United States (U.S.) Vision for Space Exploration directs NASA to develop two new launch vehicles for sending humans to the Moon, Mars, and beyond. In January 2006, NASA streamlined its hardware development approach for replacing the Space Shuttle after it is retired in 2010. Benefits of this approach include reduced programmatic and technical risks and the potential to return to the Moon by 2020, by developing the Ares I Crew Launch Vehicle (CLV) propulsion elements now, with full extensibility to future Ares V Cargo Launch Vehicle (CaLV) lunar systems. This decision was reached after the Exploration Launch Projects Office performed a variety of risk analyses, commonality assessments, and trade studies. The Constellation Program selected the Pratt & Whitney Rocketdyne J-2X engine to power the Ares I Upper Stage Element and the Ares V Earth Departure Stage. This paper narrates the evolution of that decision; describes the performance capabilities expected of the J-2X design, including potential commonality challenges and opportunities between the Ares I and Ares V launch vehicles; and provides a current status of J-2X design, development, and hardware testing activities. This paper also explains how the J-2X engine effort mitigates risk by building on the Apollo Program and other lessons lived to deliver a human-rated engine that is on an aggressive development schedule, with its first demonstration flight in 2012.

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56700 (22 Oct. 1969) --- A fish-eye lens view of astronauts Charles Conrad Jr. (on left), Apollo 12 commander, and Alan L. Bean, lunar module pilot, inside the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

Saturn Apollo Program

NASA Image and Video Library

1972-01-01

This photograph was taken during the testing of the Lunar Roving Vehicle (LRV) at the Johnson Space Center. Developed by the MSFC, the LRV was the lightweight electric car designed to increase the range of mobility and productivity of astronauts on the lunar surface. It was used on the last three Apollo missions; Apollo 15, Apollo 16, and Apollo 17.

Mission requirements CSM-111/DM-2 Apollo/Soyuz test project

NASA Technical Reports Server (NTRS)

Blackmer, S. M.

1974-01-01

Test systems are developed for rendezvous and docking of manned spacecraft and stations that are suitable for use as a standard international system. This includes the rendezvous and docking of Apollo and Soyuz spacecraft, and crew transfer. The conduct of the mission will include: (1) testing of compatible rendezvous systems in orbit; (2) testing of universal docking assemblies; (3) verifying the techniques for transfer of cosmonauts and astronauts; (4) performing certain activities by U.S.A. and U.S.S.R. crews in joint flight; and (5) gaining of experience in conducting joint flights by U.S.A. and U.S.S.R. spacecraft, including, in case of necessity, rendering aid in emergency situations.

KSC-99pp0876

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- During an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible, former Apollo astronaut Neil A. Armstrong (left) shakes the hand of Judy Goldin (center), wife of NASA Administrator Daniel S. Goldin (right). The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

Apollo 14 - Press Kit

NASA Technical Reports Server (NTRS)

1971-01-01

Apollo 14, the sixth United States manned flight to the Moon and fourth Apollo mission with an objective of landing men on the Moon, is scheduled for launch Jan. 31 at 3:23 p.m. EST from Kennedy Space Center, Fla. The Apollo 14 lunar module is to land in the hilly upland region north of the Fra Mauro crater for a stay of about 33 hours, during which the landing crew will leave the spacecraft twice to set up scientific experiments on the lunar surface and to continue geological explorations. The two earlier Apollo lunar landings were Apollo 11 at Tranquility Base and Apollo 12 at Surveyor 3 crater in the Ocean of Storms.

Astrionics system designers handbook, volume 1

NASA Technical Reports Server (NTRS)

1973-01-01

Hardware elements in new and advanced astrionics system designs are discussed. This cost effective approach has as its goal the reduction of R&D and testing costs through the application of proven and tested astrionics components. The ready availability to the designer of data facts for applicable system components is highly desirable. The astrionics System Designers Handbook has as its objective this documenting of data facts to serve the anticipated requirements of the astrionics system designer. Eleven NASA programs were selected as the reference base for the document. These programs are: ATS-F, ERTS-B, HEAO-A, OSO-I, Viking Orbiter, OAO-C, Skylab AM/MDA, Skylab ATM, Apollo 17 CSM, Apollo 17 LM and Mariner Mars 71. Four subsystems were chosen for documentation: communications, data management, electrical power and guidance, navigation and control.

Apollo experience report: Mission planning for Apollo entry

NASA Technical Reports Server (NTRS)

Graves, C. A.; Harpold, J. C.

1972-01-01

The problems encountered and the experience gained in the entry mission plans, flight software, trajectory-monitoring procedures, and backup trajectory-control techniques of the Apollo Program should provide a foundation upon which future spacecraft programs can be developed. Descriptions of these entry activities are presented. Also, to provide additional background information needed for discussion of the Apollo entry experience, descriptions of the entry targeting for the Apollo 11 mission and the postflight analysis of the Apollo 10 mission are presented.

Neil Armstrong chats with attendees at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong talks with a former Apollo team member during an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon.

Apollo-Lunar Orbital Rendezvous Technique

NASA Technical Reports Server (NTRS)

1963-01-01

The film shows artists rendition of the spacecrafts, boosters, and flight of the Apollo lunar missions. The Apollo spacecraft will consist of three modules: the manned Command Module; the Service Module, which contains propulsion systems; and the Lunar Excursion Module (LEM) to carry astronauts to the moon and back to the Command and Service Modules. The spacecraft will be launched via a three-stage Saturn booster. The first stage will provide 7.5 million pounds of thrust from five F-1 engines for liftoff and initial powered flight. The second stage will develop 1 million pounds of thrust from five J-2 engines to boost the spacecraft almost into Earth orbit. Immediately after ignition of the second stage, the Launch Escape System will be jettisoned. A single J-2 engine in the S4B stage will provide 200,000 pounds of thrust to place the spacecraft in an earth parking orbit. It also will be used to propel the spacecraft into a translunar trajectory, then it will separate from the Apollo Modules. Onboard propulsion systems will be used to insert the spacecraft into lunar orbit. Two astronauts will enter the LEM, which will separate from the command and service modules. The LEM will go into elliptical orbit and prepare for landing. The LEM will lift off of the Moon's surface to return to the Command and Service Modules, and most likely be left in lunar orbit. After leaving the Moon's orbit, and shortly before entering Earth's orbit, the Service Module will be ejected. The Command Module will be oriented for reentry into the Earth's atmosphere. A drogue parachute will deploy at approximately 50,000 feet, followed by the main parachute system for touchdown.

Preliminary examination of lunar samples from apollo 14.

PubMed

1971-08-20

The major findings of the preliminary examination of the lunar samples are as follows: 1) The samples from Fra Mauro base may be contrasted with those from Tranquillity base and the Ocean of Storms in that about half the Apollo 11 samples consist of basaltic rocks, and all but three Apollo 12 rocks are basaltic, whereas in the Apollo 14 samples only two rocks of the 33 rocks over 50 grams have basaltic textures. The samples from Fra Mauro base consist largely of fragmental rocks containing clasts of diverse lithologies and histories. Generally the rocks differ modally from earlier lunar samples in that they contain more plagioclase and contain orthopyroxene. 2) The Apollo 14 samples differ chemically from earlier lunar rocks and from their closest meteorite and terrestrial analogs. The lunar material closest in composition is the KREEP component (potassium, rare earth elements, phosphorus), "norite," "mottled gray fragments" (9) from the soil samples (in particular, sample 12033) from the Apollo 12 site, and the dark portion of rock 12013 (10). The Apollo 14 material is richer in titanium, iron, magnesium, and silicon than the Surveyor 7 material, the only lunar highlands material directly analyzed (11). The rocks also differ from the mare basalts, having much lower contents of iron, titanium, manganese, chromium, and scandium and higher contents of silicon, aluminum, zirconium, potassium, uranium, thorium, barium, rubidium, sodium, niobium, lithium, and lanthanum. The ratios of potassium to uranium are lower than those of terrestrial rocks and similar to those of earlier lunar samples. 3) The chemical composition of the soil closely resembles that of the fragmental rocks and the large basaltic rock (sample 14310) except that some elements (potassium, lanthanum, ytterbium, and barium) may be somewhat depleted in the soil with respect to the average rock composition. 4) Rocks display characteristic surface features of lunar material (impact microcraters, rounding) and shock effects similar to those observed in rocks and soil from the Apollo 11 and Apollo 12 missions. The rocks show no evidence of exposure to water, and their content of metallic iron suggests that they, like the Apollo 11 and Apollo 12 material, were formed and have remained in an environment with low oxygen activity. 5) The concentration of solar windimplanted material in the soil is large, as was the case for Apollo 11 and Apollo 12 soil. However, unlike previous fragmental rocks, Apollo 14 fragmental rocks possess solar wind contents ranging from approximately that of the soil to essentially zero, with most rocks investigated falling toward one extreme of this range. A positive correlation appears to exist between the solar wind components, carbon, and (20)Ne, of fragmental rocks and their friability (Fig. 12). 6) Carbon contents lie within the range of carbon contents for Apollo 11 and Apollo 12 samples. 7) Four fragmental rocks show surface exposure times (10 x 10(6) to 20 x 10(6) years) about an order of magnitude less than typical exposure times of Apollo 11 and Apollo 12 rocks. 8) A much broader range of soil mechanics properties was encountered at the Apollo 14 site than has been observed at the Apollo 11, Apollo 12, and Surveyor landing sites. At different points along the traverses of the Apollo 14 mission, lesser cohesion, coarser grain size, and greater resistance to penetration was found than at the Apollo 11 and Apollo 12 sites. These variations are indicative of a very complex, heterogeneous deposit. The soils are more poorly sorted, but the range of grain size is similar to those of the Apollo 11 and Apollo 12 soils. 9) No evidence of biological material has been found in the samples to date.

Apollo 40th Anniversary Morning Television

NASA Image and Video Library

2009-07-19

Apollo astronaut Alan Bean, center, laughs at a comment made by Apollo astronaut Charles Duke, right, as Apollo astronaut Buzz Aldrin, left, looks on during a live television interview on Monday, July 20, 2009, at NASA Headquarters in Washington. Monday marked the 40th Anniversary of the historic landing of Apollo 11 on the Moon. Photo Credit: (NASA/Paul E. Alers)

Astronaut Alan Bean deploys ALSEP during first Apollo 12 EVA on moon

NASA Technical Reports Server (NTRS)

1969-01-01

Astronaut Alan L. Bean, Apollo 12 lunar module pilot, deploys components of the Apollo Lunar Surface Experiments Package (ALSEP) during the first Apollo 12 extravehicular activity (EVA) on the moon. The photo was made by Astronaut Charles Conrad Jr., Apollo 12 commander, using a 70mm handheld Haselblad camera modified for lunar surface usage.

The formation of Hadley Rille and implications for the geology of the Apollo 15 region

NASA Technical Reports Server (NTRS)

Spudis, Paul D.; Swann, Gordon A.; Greeley, Ronald

1988-01-01

The results of studies of terrestrial lava tube systems and the regional and detailed site geology of the Apollo 15 area have been combined to develop a model for the formation of Hadley Rille. The regional geology of the Apennine bench formation and its relation to Mozart and Hadley Rilles is discussed. It is shown that the total thickness of mare basalt at the Apollo landing site is on the order of a few tens of meters, mostly less than 50 m. It is suggested that the role of thermal erosion in the development of sinuous rilles on the moon may be less important than previously assumed and that the assimilation of refractory highland rock types into mare basaltic magma is a minor lunar process.

Apollo oxygen tank stratification analysis, volume 2

NASA Technical Reports Server (NTRS)

Barton, J. E.; Patterson, H. W.

1972-01-01

An analysis of flight performance of the Apollo 15 cryogenic oxygen tanks was conducted with the variable grid stratification math model developed earlier in the program. Flight conditions investigated were the CMP-EVA and one passive thermal control period which exhibited heater temperature characteristics not previously observed. Heater temperatures for these periods were simulated with the math model using flight acceleration data. Simulation results (heater temperature and tank pressure) compared favorably with the Apollo 15 flight data, and it was concluded that tank performance was nominal. Math model modifications were also made to improve the simulation accuracy. The modifications included the addition of the effects of the tank wall thermal mass and an improved system flow distribution model. The modifications improved the accuracy of simulated pressure response based on comparisons with flight data.

Crew Exploration Vehicle Ascent Abort Trajectory Analysis and Optimization

NASA Technical Reports Server (NTRS)

Falck, Robert D.; Gefert, Leon P.

2007-01-01

The Orion Crew Exploration Vehicle is the first crewed capsule design to be developed by NASA since Project Apollo. Unlike Apollo, however, the CEV is being designed for service in both Lunar and International Space Station missions. Ascent aborts pose some issues that were not present for Apollo, due to its launch azimuth, nor Space Shuttle, due to its cross range capability. The requirement that a North Atlantic splashdown following an abort be avoidable, in conjunction with the requirement for overlapping abort modes to maximize crew survivability, drives the thrust level of the service module main engine. This paper summarizes 3DOF analysis conducted by NASA to aid in the determination of the appropriate propulsion system for the service module, and the appropriate propellant loading for ISS missions such that crew survivability is maximized.

MSFC Skylab Apollo Telescope Mount experiment systems mission evaluation

NASA Technical Reports Server (NTRS)

White, A. F., Jr.

1974-01-01

A detailed evaluation is presented of the Skylab Apollo Telescope Mount experiments performance throughout the eight and one-half month Skylab Mission. Descriptions and the objectives of each instrument are included. The anomalies experienced, the causes, and corrective actions taken are discussed. Conclusions, based on evaluation of the performance of each instrument, are presented. Examples of the scientific data obtained, as well as a discussion of the quality and quantity of the data, are presented.

APOLLO: A computer program for the calculation of chemical equilibrium and reaction kinetics of chemical systems

DOE Office of Scientific and Technical Information (OSTI.GOV)

Nguyen, H.D.

1991-11-01

Several of the technologies being evaluated for the treatment of waste material involve chemical reactions. Our example is the in situ vitrification (ISV) process where electrical energy is used to melt soil and waste into a ``glass like`` material that immobilizes and encapsulates any residual waste. During the ISV process, various chemical reactions may occur that produce significant amounts of products which must be contained and treated. The APOLLO program was developed to assist in predicting the composition of the gases that are formed. Although the development of this program was directed toward ISV applications, it should be applicable tomore » other technologies where chemical reactions are of interest. This document presents the mathematical methodology of the APOLLO computer code. APOLLO is a computer code that calculates the products of both equilibrium and kinetic chemical reactions. The current version, written in FORTRAN, is readily adaptable to existing transport programs designed for the analysis of chemically reacting flow systems. Separate subroutines EQREACT and KIREACT for equilibrium ad kinetic chemistry respectively have been developed. A full detailed description of the numerical techniques used, which include both Lagrange multiplies and a third-order integrating scheme is presented. Sample test problems are presented and the results are in excellent agreement with those reported in the literature.« less

APOLLO: A computer program for the calculation of chemical equilibrium and reaction kinetics of chemical systems

DOE Office of Scientific and Technical Information (OSTI.GOV)

Nguyen, H.D.

1991-11-01

Several of the technologies being evaluated for the treatment of waste material involve chemical reactions. Our example is the in situ vitrification (ISV) process where electrical energy is used to melt soil and waste into a glass like'' material that immobilizes and encapsulates any residual waste. During the ISV process, various chemical reactions may occur that produce significant amounts of products which must be contained and treated. The APOLLO program was developed to assist in predicting the composition of the gases that are formed. Although the development of this program was directed toward ISV applications, it should be applicable tomore » other technologies where chemical reactions are of interest. This document presents the mathematical methodology of the APOLLO computer code. APOLLO is a computer code that calculates the products of both equilibrium and kinetic chemical reactions. The current version, written in FORTRAN, is readily adaptable to existing transport programs designed for the analysis of chemically reacting flow systems. Separate subroutines EQREACT and KIREACT for equilibrium ad kinetic chemistry respectively have been developed. A full detailed description of the numerical techniques used, which include both Lagrange multiplies and a third-order integrating scheme is presented. Sample test problems are presented and the results are in excellent agreement with those reported in the literature.« less

Study of the detail content of Apollo orbital photography

NASA Technical Reports Server (NTRS)

Kinzly, R. E.

1972-01-01

The results achieved during a study of the Detail Content of Apollo Orbital Photography are reported. The effect of residual motion smear or image reproduction processes upon the detail content of lunar surface imagery obtained from the orbiting command module are assessed. Data and conclusions obtained from the Apollo 8, 12, 14 and 15 missions are included. For the Apollo 8, 12 and 14 missions, the bracket-mounted Hasselblad camera had no mechanism internal to the camera for motion compensation. If the motion of the command module were left totally uncompensated, these photographs would exhibit a ground smear varying from 12 to 27 meters depending upon the focal length of the lens and the exposure time. During the photographic sequences motion compensation was attempted by firing the attitude control system of the spacecraft at a rate to compensate for the motion relative to the lunar surface. The residual smear occurring in selected frames of imagery was assessed using edge analyses methods to obtain and achieved modulation transfer function (MTF) which was compared to a baseline MTF.

Artist's Concept of the Apollo-Soyuz Test Project

NASA Technical Reports Server (NTRS)

1974-01-01

This artist's concept depicts the Apollo-Soyuz Test Project (ASTP), the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. The objective of the ASTP mission was to provide the basis for a standardized international system for docking of marned spacecraft. The Soyuz spacecraft, with Cosmonauts Alexei Leonov and Valeri Kubasov aboard, was launched from the Baikonur Cosmodrome near Tyuratam in the Kazakh, Soviet Socialist Republic, at 8:20 a.m. (EDT) on July 15, 1975. The Apollo spacecraft, with Astronauts Thomas Stafford, Vance Brand, and Donald Slayton aboard, was launched from Launch Complex 39B, Kennedy Space Center, Florida, at 3:50 p.m. (EDT) on July 15, 1975. The Primary objectives of the ASTP were achieved. They performed spacecraft rendezvous, docking and undocking, conducted intervehicular crew transfer, and demonstrated the interaction of U.S. and U.S.S.R. control centers and spacecraft crews. The mission marked the last use of a Saturn launch vehicle. The Marshall Space Flight Center was responsible for development and sustaining engineering of the Saturn IB launch vehicle during the mission.

Apollo-Soyuz Test Project (ASTP)

NASA Technical Reports Server (NTRS)

1974-01-01

This artist's concept depicts the Apollo-Soyuz Test Project (ASTP) with insets of photographs of three U.S. astronauts (Thomas Stafford, Vance Brand, and Donald Slayton) and two U.S.S.R. cosmonauts (Alexei Leonov and Valeri Kubasov). The objective of the ASTP mission was to accomplish the first docking of a standardized international system, the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft, in space. The Soyuz spacecraft was launched from the Baikonur Cosmodrome near Tyuratam in the Kazakh, Soviet Socialist Republic, at 8:20 a.m. (EDT) on July 15, 1975. The Apollo spacecraft was launched from Launch Complex 39B, Kennedy Space Center, Florida, at 3:50 p.m. (EDT) on July 15, 1975. The Primary objectives of the ASTP were achieved. They performed spacecraft rendezvous, docking and undocking, conducted intervehicular crew transfer, and demonstrated the interaction of U.S. and U.S.S.R. control centers and spacecraft crews. The mission marked the last use of a Saturn launch vehicle. The Marshall Space Flight Center was responsible for development and sustaining engineering of the Saturn IB launch vehicle during the mission.

Pesticide Manufacturers, Formulators, Producers, and Registrants

Science.gov Websites

International Apollo Industries, Inc. (see Apollo Technologies, Inc.) Apollo Technologies, Inc. Applied Products, Inc.) SPECKoZ, Inc. Spectrum Brands (aka Spectrum Group) Speer Products, Inc. (see Apollo

OFFICIAL EMBLEM - APOLLO-SOYUZ TEST PROJECT (ASTP)

NASA Image and Video Library

1974-03-01

S74-17843 (March 1974) --- This is the official emblem of the Apollo-Soyuz Test Project chosen by NASA and the Soviet Academy of Sciences. The joint U.S.-USSR space mission is scheduled to be flown in July 1975. Of circular design, the emblem has the words Apollo in English and Soyuz in Russian around a center disc which depicts the two spacecraft docked together in Earth orbit. The Apollo-Soyuz Test Project will be carried out by a Soviet Soyuz spacecraft and a U.S. Apollo spacecraft which will rendezvous and dock in orbit. Soyuz and Apollo will remain docked for as long as two days in which period, the three Apollo astronauts will enter Soyuz and the two Soyuz cosmonauts will visit Apollo via a docking module. The Russian word "soyuz" means "union" in English.

Identifying Sociological Factors for the Success of Space Exploration

NASA Astrophysics Data System (ADS)

Lundquist, C. A.; Tarter, D.; Coleman, A.

Astrosociology factors relevant to success of future space exploration may best be identified through studies of sociological circumstances of past successful explorations, such as the Apollo-Lunar Missions. These studies benefit from access to primary records of the past programs. The Archives and Special Collections Division of the Salmon Library at the University of Alabama Huntsville (UAH) houses large collections of material from the early periods of the space age. The Huntsville campus of the University of Alabama System had its birth in the mid-1950s at the time when the von Braun rocket team was relocated from Texas to Huntsville. The University, the City of Huntsville and the US Government rocket organizations developed in parallel over subsequent years. As a result, the University has a significant space heritage and focus. This is true not only for the engineering and science disciplines, but also for the social sciences. The life of the University spans the period when Huntsville government and industrial organizations were responsible for producing the rocket vehicles to first take mankind to the Moon. That endeavor was surely as significant sociologically as technologically. In the 1980s, Donald E. Tarter, conducted a series of video interviews with some leading members of the original von Braun team. Although the interviews ranged over many engineering subjects, they also recorded personal features of people involved in the Apollo lunar exploration program and the interactions between these people. Such knowledge was of course an objective. These interviews are now in the collections of the UAH Library Archives, along with extensive documentation from the same period. Under sponsorship of the Archives and the NASA-Marshall Retiree Association, the interview series was restarted in 2006 to obtain comparable oral-history interviews with more than fifty US born members of the rocket team from the 1960s. Again these video interviews are rich with insights into the people involved in the Apollo lunar exploration program. A common thought in the original and recent interviews is that the 1960s rocket team was a unique assembly of people with leadership and modes of operation that has not been reproduced since. If mankind is again going to the Moon, Mars, an asteroid or elsewhere in the solar system, a similar assembly of people and sociological conditions may well be required.

Rock and Roll at the Apollo 17 Site

NASA Astrophysics Data System (ADS)

Martel, L. M. V.

2016-06-01

Astronauts Eugene A. Cernan and Harrison H. (Jack) Schmitt collected 243 pounds (110 kg) of rock and regolith samples during 22 hours working on the lunar surface during the Apollo 17 mission in December 1972, while Astronaut Ronald Evans orbited in the command module. The field observations, audio descriptions, and photographs coupled with orbital data and detailed, laboratory analyses of Apollo samples provided unprecedented information about the Moon and its geologic history. The Apollo samples continue to inspire new questions and answers about the Moon. Debra Hurwitz and David Kring (Lunar and Planetary Institute and NASA Solar System Exploration Research Virtual Institute; Hurwitz now at NASA Goddard Space Flight Center) were particularly interested in solving the mystery of where the boulders came from at the base of the North Massif (station 6) and at the base of the South Massif (station 2) from which Apollo 17 astronauts collected samples of impact melt breccias. The breccias were unequivocally formed by impact processes, but forty years of analyses had not yet determined unambiguously which impact event was responsible. Was it the basin-forming event of the landing site's neighbor Serenitatis (possibly Nectarian age); the larger, nearby Imbrium basin (Imbrian age and one of the last large basins to form); a combination of these impacts or an impact event older or younger than all of the above. Tracking down the origin of the boulders would ideally unravel details of the formation age of the breccias and, ultimately, help with the historical record of basin formation on the Moon. Hurwitz and Kring verified the boulders rolled down from massif walls - Apollo 17 impact melt breccias originated in massif material, not from the Sculptured Hills, an overlying geologic unit. But the relative geologic context is easier to explain than the absolute age, at least until some discrepancies are resolved in existing Ar-Ar and U-Pb radiometric ages of the Apollo 17 impact melt breccias.

Last chance at Taurus-Littrow

NASA Technical Reports Server (NTRS)

Wilhelms, D. E.

1992-01-01

By the fall of 1971, it was known that only two more Apollos would land on the Moon. Most geoscientists agreed that both should concentrate on the previously neglected terrae (highlands). In June 1991, the Apollo Site Selection Board (ASSB) had chosen Descartes as the site of the Apollo 16 terra landing, scheduled for April 1972. Therefore, we had to assess how many pre-Apollo objectives the first four landings had met, how many Apollo 16 was likely to meet, and how to meet the remaining ones with Apollo 17. Geologists convened at Caltech in November 1971 and formulated a list of major lunar problems. An edited version of the list is presented, and how the remaining problems influenced the Apollo 16 and 17 landing site selection process is discussed with particular emphasis on the selection of Taurus-Littrow as the landing site for Apollo 17. Apollo 17 returned a fine collection from the massifs, bright mantle, Sculptured Hills, subfloor basalt, and dark mantle of Taurus-Littrow. They answered many of 1971's questions, showed others to have been wrongly asked, and left others for us to ponder still today. A brief discussion of the problems solved and the questions raised by the Apollo Program are presented.

The structures of the SNM1A and SNM1B/Apollo nuclease domains reveal a potential basis for their distinct DNA processing activities

PubMed Central

Allerston, Charles K.; Lee, Sook Y.; Newman, Joseph A.; Schofield, Christopher J.; McHugh, Peter J.; Gileadi, Opher

2015-01-01

The human SNM1A and SNM1B/Apollo proteins are members of an extended family of eukaryotic nuclease containing a motif related to the prokaryotic metallo-β-lactamase (MBL) fold. SNM1A is a key exonuclease during replication-dependent and transcription-coupled interstrand crosslink repair, while SNM1B/Apollo is required for maintaining telomeric overhangs. Here, we report the crystal structures of SNM1A and SNM1B at 2.16 Å. While both proteins contain a typical MBL-β-CASP domain, a region of positive charge surrounds the active site of SNM1A, which is absent in SNM1B and explains the greater apparent processivity of SNM1A. The structures of both proteins also reveal a putative, wide DNA-binding groove. Extensive mutagenesis of this groove, coupled with detailed biochemical analysis, identified residues that did not impact on SNM1A catalytic activity, but drastically reduced its processivity. Moreover, we identified a key role for this groove for efficient digestion past DNA interstrand crosslinks, facilitating the key DNA repair reaction catalysed by SNM1A. Together, the architecture and dimensions of this groove, coupled to the surrounding region of high positive charge, explain the remarkable ability of SNM1A to accommodate and efficiently digest highly distorted DNA substrates, such as those containing DNA lesions. PMID:26582912

Working on the moon: The Apollo experience

DOE Office of Scientific and Technical Information (OSTI.GOV)

Jones, E.M.

1989-01-01

The successful completion of any scientific or engineering project on the Moon will depend, in part, on human ability to do useful work under lunar conditions. In making informed decisions about such things as the use of humans rather than robots for specific tasks, the scheduling of valuable human time, and the design and selection of equipment and tools, good use can be made of the existing experience base. During the six completed landing missions, Apollo lunar surface crews conducted 160 astronaut-hours of extra-vehicular activities (EVAs) and also spent a similar sum of waking hours working in the cramped confinesmore » of the Lunar Module. The first three missions were primarily proof-tests of flight hardware and procedures. The ability to land equipment and consumables was very modest but, despite stay times of no more than 32 hours, the crews of Apollos 11, 12, and 14 were able to test their mobility and their capability of doing useful work outside the spacecraft. For the last three missions, thanks to LM modifications which enabled landings with significant amounts of cargo, stay times more than doubled to three days. The crews were able to use Lunar Rovers to conduct extensive local exploration and to travel up to 10 kilometers away from their immediate landing sites. During these final missions, the astronauts spent enough time doing work of sufficient complexity that their experience should be of use in the formulation early-stage lunar base operating plans. 2 refs.« less

Apollo 14 mission report. Supplement 5: Descent propulsion system final flight evaluation

NASA Technical Reports Server (NTRS)

Avvenire, A. T.; Wood, S. C.

1972-01-01

The performance of the LM-8 descent propulsion system during the Apollo 14 mission was evaluated and found to be satisfactory. The average engine effective specific impulse was 0.1 second higher than predicted, but well within the predicted l sigma uncertainty. The engine performance corrected to standard inlet conditions for the FTP portion of the burn at 43 seconds after ignition was as follows: thrust, 9802, lbf; specific impulse, 304.1 sec; and propellant mixture ratio, 1603. These values are + or - 0.8, -0.06, and + or - 0.3 percent different respectively, from the values reported from engine acceptance tests and were within specification limits.

Apollo experience report: Potable water system

NASA Technical Reports Server (NTRS)

Sauer, R. L.; Calley, D. J.

1973-01-01

A description of the design and function of the Apollo potable water system is presented. The command module potable water is supplied as a byproduct of the fuel cells. The cells, located in the service module, function primarily to supply electrical energy to the spacecraft. The source of the lunar module potable water is three tanks, which are filled before lift-off. The technique of supplying the water in each of these cases and the problems associated with materials compatibility are described. The chemical and microbiological quality of the water is reviewed, as are efforts to maintain the water in a microbially safe condition for drinking and food mixing.

Agent Interaction with Human Systems in Complex Environments: Requirements for Automating the Function of CapCom in Apollo 17

NASA Technical Reports Server (NTRS)

Clancey, William J.

2003-01-01

A human-centered approach to computer systems design involves reframing analysis in terms of people interacting with each other, not only human-machine interaction. The primary concern is not how people can interact with computers, but how shall we design computers to help people work together? An analysis of astronaut interactions with CapCom on Earth during one traverse of Apollo 17 shows what kind of information was conveyed and what might be automated today. A variety of agent and robotic technologies are proposed that deal with recurrent problems in communication and coordination during the analyzed traverse.

Apollo experience report: Systems and flight procedures development

NASA Technical Reports Server (NTRS)

Kramer, P. C.

1973-01-01

This report describes the process of crew procedures development used in the Apollo Program. The two major categories, Systems Procedures and Flight Procedures, are defined, as are the forms of documentation required. A description is provided of the operation of the procedures change control process, which includes the roles of man-in-the-loop simulations and the Crew Procedures Change Board. Brief discussions of significant aspects of the attitude control, computer, electrical power, environmental control, and propulsion subsystems procedures development are presented. Flight procedures are subdivided by mission phase: launch and translunar injection, rendezvous, lunar descent and ascent, and entry. Procedures used for each mission phase are summarized.

[327] Biomedical Research Deferred in the Aftermath of the Apollo Fire: Impact to Progress in Human Spaceflight

NASA Technical Reports Server (NTRS)

Charles, John B.

2017-01-01

Before Apollo fire, early Apollo missions were expected to continue pattern established in Gemini program of accommodating significant scientific and biological experimentation, including human biomedical studies, during flights. Apollo1 and Apollo2, both 2-week engineering test flights, were to carry almost as many biomedical studies as Gemini 7, a 2-week medical test mission.

Launch of the Apollo 17 lunar landing mission

NASA Image and Video Library

1972-12-07

S72-55482 (7 Dec. 1972) --- The huge, 363-feet tall Apollo 17 (Spacecraft 114/Lunar Module 12/Saturn 512) space vehicle is launched from Pad A., Launch Complex 39, Kennedy Space Center (KSC), Florida, at 12:33 a.m. (EST), Dec. 7, 1972. Apollo 17, the final lunar landing mission in NASA's Apollo program, was the first nighttime liftoff of the Saturn V launch vehicle. Aboard the Apollo 17 spacecraft were astronaut Eugene A. Cernan, commander; astronaut Ronald E. Evans, command module pilot; and scientist-astronaut Harrison H. Schmitt, lunar module pilot. Flame from the five F-1 engines of the Apollo/Saturn first (S-1C) stage illuminates the nighttime scene. A two-hour and 40-minute hold delayed the Apollo 17 launching.

Launch of the Apollo 17 lunar landing mission

NASA Image and Video Library

1972-09-07

S72-55070 (7 Dec. 1972) --- The huge, 363-feet tall Apollo 17 (Spacecraft 114/Lunar Module 12/Saturn 512) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), Florida, at 12:33 a.m. (EST), Dec. 7, 1972. Apollo 17, the final lunar landing mission in NASA's Apollo program, was the first nighttime liftoff of the Saturn V launch vehicle. Aboard the Apollo 17 spacecraft were astronaut Eugene A. Cernan, commander; astronaut Ronald E. Evans, command module pilot; and scientist-astronaut Harrison H. Schmitt, lunar module pilot. Flame from the five F-1 engines of the Apollo/Saturn first (S-1C) stage illuminates the nighttime scene. A two-hour and 40-minute hold delayed the Apollo 17 launching.

Apollo 40th Anniversary Press Conference

NASA Image and Video Library

2009-07-19

Astronaut James Lovell (Apollo 8 Apollo 13) gestures during the 40th anniversary of the Apollo 11 mission and the walk on the moon press conference, Monday, July 20, 2009, at NASA Headquarters in Washington. Photo Credit: (NASA/Paul E. Alers)

Vestibular response to pseudorandom angular velocity input: progress report.

PubMed

Lessard, C S; Wong, W C

1987-09-01

Space motion sickness was not reported during the first Apollo missions; however, since Apollo 8 through the current Shuttle and Skylab missions, approximately 50% of the crewmembers have experienced instances of space motion sickness. One of NASA's efforts to resolve the space adaptation syndrome is to model the vestibular response for both basic knowledge and as a possible predictor of an individual's susceptibility to the disorder. This report describes a method to analyze the vestibular system when subjected to a pseudorandom angular velocity input.

Saturn Apollo Program

NASA Image and Video Library

1968-01-01

This view depicts engineers conducting a system test on the Saturn V instrument unit (IU) at International Business Machines (IBM) in Huntsville, Alabama. IBM is a prime contractor for development and fabrication of the IU. The IU is vital to the proper flight of the vehicle. It contains navigation, guidance, control, and sequencing equipment for the launch vehicle. Three-feet tall, twenty-one feet in diameter, and weighing about 4,000 pounds, the IU is mounted atop the S-IVB (third) stage, between the S-IVB stage and the Apollo spacecraft.

KSC-2014-3193

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, NASA officials and Apollo astronauts visiting Launch Pad 39B with their families and friends preserve the moment with a group portrait. The group was at Kennedy for a ceremony renaming the Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. From left are NASA Administrator Charles Bolden, Neil's granddaughter Lily Armstrong, Neil's grandson Bryce Armstrong, Neil's son Mark Armstrong, Neil's former wife Janet Armstrong, Neil's son Rick Armstrong, Apollo 11 moonwalker Buzz Aldrin, Buzz's friend Judy Rice, Apollo astronaut Jim Lovell, Mike Collins' daughter Ann Starr, Apollo 11 command module pilot Mike Collins, Buzz's grandson Jeffrey Schuss, Jeffrey's wife April Schuss, Buzz's son-in-law Bruce Hanifan, Buzz's daughter Jan Aldrin, Buzz's son Andy Aldrin, and Center Director Bob Cabana. The pad is being modified to support the agency's new Orion spacecraft which will lift off atop the Space Launch System rocket. Orion is designed to take humans farther than they’ve ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Neil Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Michael Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kim Shiflett

Crew Training - Apollo X (Apollo Mission Simulator [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32788 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

CREW TRAINING - APOLLO X (APOLLO MISSION SIMULATOR [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32789 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

Apollo A-7L Spacesuit Tests and Certification, and Apollo 7 Through 14 Missions Experience

NASA Technical Reports Server (NTRS)

McBarron, James W., II

2015-01-01

As a result of his 50 years of experience and research, Jim McBarron shared his significant knowledge about Apollo A-7L spacesuit certification testing and Apollo 7 through 14 missions' spacesuit details.

KSC-2011-1308

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Lunar module pilot of Apollo 10 and commander of Apollo 17 Gene Cernan talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Cernan was the backup commander for the Apollo 14 mission. Photo credit: NASA/Kim Shiflett

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Mike Ciannilli, the Apollo, Challenger, Columbia Lessons Learned program manager, at left, presents a certificate to Ernie Reyes, retired, former Apollo 1 senior operations manager, during the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

Saturn Apollo Program

NASA Image and Video Library

1968-10-01

AS-205, the fifth Saturn IB launch vehicle developed by the Marshall Space Flight Center (MSFC), lifts off from Cape Canaveral, Florida on the first marned Apollo-Saturn mission, Apollo 7. Primary mission objectives included demonstration of the Apollo crew (Walter Schirra, Don Eisele, and Walter Cunningham) capabilities and the Command/Service Module rendezvous capability. In all, nine Saturn IB flights were made, ending with the Apollo-Soyuz Test Project in July 1975.

Apollo Spacesuit Modifications for the Apollo-Soyuz Test Project (ASTP) Spacesuit

NASA Technical Reports Server (NTRS)

McBarron, James W., II

2015-01-01

With over 50 years of experience with NASA spacesuit development and operations, as well as for early U.S. Air Force pressure suits, Jim McBarron shared his significant knowledge about modifications to the Apollo spacesuit for use in the Apollo-Soyuz Test Project (ASTP). This included requirements and design changes implemented to establish the ASTP spacesuit design baseline. Additionally, he identified Apollo spacesuit contact details including quantity of spacesuits delivered to support the Apollo and Skylab Programs, and the ASTP. He concluded by identifying a summary of noteworthy lessons learned with recommendations for future spacesuit development.

KSC-2012-1845

NASA Image and Video Library

2012-02-17

Apollo Capsule/Lunar Lander: The goal of Project Apollo was to land man on the moon and return them safely to the Earth. The Apollo spacecraft consisted of a command module serving as the crew’s quarters and flight control section and the lunar module, carrying two crewmembers to the surface of the moon. The first Apollo spacecraft to land on the moon was Apollo 11 on July 20, 1969. The program concluded with Apollo 17 in December 1972 after putting 27 men into lunar orbit and 12 of them on the surface of the moon. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

Artist's concept of oxygen tanks of the Apollo 14 spacecraft

NASA Image and Video Library

1971-01-12

S71-16745 (January 1971) --- An artist's concept illustrating a cutaway view of one of the three oxygen tanks of the Apollo 14 spacecraft. This is the new Apollo oxygen tank design, developed since the Apollo 13 oxygen tank explosion. Apollo 14 has three oxygen tanks redesigned to eliminate ignition sources, minimize the use of combustible materials, and simplify the fabrication process. The third tank has been added to the Apollo 14 Service Module, located in the SM's sector one, apart from the pair of oxygen tanks in sector four. Arrows point out various features of the oxygen tank.

Auto-metasomatism of the western lunar highlands: Result of closed system fractionation and mobilization of a KREEPy trapped liquid

NASA Technical Reports Server (NTRS)

Shervais, John W.; Vetter, Scott K.

1993-01-01

The discovery of REE-rich phosphates (dominantly whitlockite) in pristine, non-mare rocks of the western lunar nearside (Apollo 14, Apollo 12, and most recently, Apollo 17) has created a paradox for lunar petrologists. These phases are found in feldspar-rich cumulates of both the Mg-suite and the Alkali suite, which differ significantly in their mineral chemistries and major element compositions. Despite the differences in host rock compositions, whitlockites in both suites have similar compositions, with LREE concentrations around 21,000 to 37,000 x chondrite. Simple modeling of possible parent magma compositions using the experimental whitlockite/liquid partition coefficients of Dickinson and Hess show that these REE concentrations are too high to form from normal lunar magmas, even those characterized as 'urKREEP.'

View of damaged Apollo 13 Service Module from the Lunar/Command Modules

NASA Image and Video Library

1970-04-17

This view of the damaged Apollo 13 Service Module (SM) was photographed from the Lunar Module/Command Module following SM jettisoning. As seen here, an entire panel on the SM was blown away by the apparent explosion of oxygen tank number two located in Sector 4 of the SM. Two of the three fuel cells are visible just forward (above) the heavily damaged area. Three fuel cells, two oxygen tanks, and two hydrogen tanks are locate in Sector 4. The damaged area is located above the S-band high gain antenna. Nearest the camera is the Service Propulsion System (SPS) engine and nozzle. The damage to the SM caused the Apollo 13 crewmen to use the Lunar Module (LM) as a "lifeboat". The LM was jettisoned just prior to Earth reentry by the Command Module.

Magnesium and Silicon Isotopes in HASP Glasses from Apollo 16 Lunar Soil 61241

NASA Technical Reports Server (NTRS)

Herzog, G. F.; Delaney, J. S.; Lindsay, F.; Alexander, C. M. O'D; Chakrabarti, R.; Jacobsen, S. B.; Whattam, S.; Korotev, R.; Zeigler, R. A.

2012-01-01

The high-Al (>28 wt %), silica-poor (<45 wt %) (HASP) feldspathic glasses of Apollo 16 are widely regarded as the evaporative residues of impacts in the lunar regolith [1-3]. By virtue of their small size, apparent homogeneity, and high inferred formation temperatures, the HASP glasses appear to be good samples in which to study fractionation processes that may accompany open system evaporation. Calculations suggest that HASP glasses with present-day Al2O3 concentrations of up to 40 wt% may have lost 19 wt% of their original masses, calculated as the oxides of iron and silicon, via evaporation [4]. We report Mg and Si isotope abundances in 10 HASP glasses and 2 impact-glass spherules from a 64-105 m grain-size fraction taken from Apollo 16 soil sample 61241.

In-Situ XRF Measurements in Lunar Surface Exploration Using Apollo Samples as a Standard

NASA Technical Reports Server (NTRS)

Young, Kelsey E.; Evans, C.; Allen, C.; Mosie, A.; Hodges, K. V.

2011-01-01

Samples collected during the Apollo lunar surface missions were sampled and returned to Earth by astronauts with varying degrees of geological experience. The technology used in these EVAs, or extravehicular activities, included nothing more advanced than traditional terrestrial field instruments: rock hammer, scoop, claw tool, and sample bags. 40 years after Apollo, technology is being developed that will allow for a high-resolution geochemical map to be created in the field real-time. Handheld x-ray fluorescence (XRF) technology is one such technology. We use handheld XRF to enable a broad in-situ characterization of a geologic site of interest based on fairly rapid techniques that can be implemented by either an astronaut or a robotic explorer. The handheld XRF instrument we used for this study was the Innov-X Systems Delta XRF spectrometer.

Artist's drawing of internal arrangement of orbiting Apollo and Soyuz crafts

NASA Technical Reports Server (NTRS)

1974-01-01

Artist's drawing illustrating the internal arrangement of orbiting the Apollo and Soyuz spacecraft in Earth orbit in a docked configuration. The three American Apollo crewmen and the two Soviet Soyuz crewmen will transfer to each other's spacecraft during the July Apollo Soyuz Test Project (ASTP) mission. The four ASTP visible components are, left to right, the Apollo Command Module, the Docking Module, the Soyuz Orbital Module and the Soyuz Descent Vehicle.

Food technology problems related to space feeding.

PubMed

Hollender, H A; Klicka, M V; Smith, M C

1970-01-01

The development of foods suitable for extraterrestrial consumption posed unique problems. Limitations on weight, volume and stability of space food together with the lack of refrigeration favored the use of dehydrated foods on Gemini and Apollo menus. Environmental constraints, cabin pressures of 1/3 atmosphere with exposure of the food assembly to the vacuum of space in conjunction with extravehicular activities and zero gravity required special packaging and adaptation of foods considered suitable for space flight use. Requirements for acceptable, familiar, crumb free, low residue, non-gas producing, stable foods added to the complexity of the developmental effort. Four basic approaches: semisolid foods in metal tubes, dehydrated bite-size foods to be eaten dry, dehydrated foods to be reconstituted before eating and flexibly packaged thermostabilized wet meat products have been utilized in the feeding systems developed for Projects Mercury, Gemini and Apollo. The development of each type posed many interesting technologic problems. Data from current Apollo flights have pointed to certain deficiencies which still remain to be corrected. Work is progressing to eliminate current problems and to provide feeding systems suitable for both short-term and long-term space flights.

Operational Assessment of Apollo Lunar Surface Extravehicular Activity

NASA Technical Reports Server (NTRS)

Miller, Matthew James; Claybrook, Austin; Greenlund, Suraj; Marquez, Jessica J.; Feigh, Karen M.

2017-01-01

Quantifying the operational variability of extravehicular activity (EVA) execution is critical to help design and build future support systems to enable astronauts to monitor and manage operations in deep-space, where ground support operators will no longer be able to react instantly and manage execution deviations due to the significant communication latency. This study quantifies the operational variability exhibited during Apollo 14-17 lunar surface EVA operations to better understand the challenges and natural tendencies of timeline execution and life support system performance involved in surface operations. Each EVA (11 in total) is individually summarized as well as aggregated to provide descriptive trends exhibited throughout the Apollo missions. This work extends previous EVA task analyses by calculating deviations between planned and as-performed timelines as well as examining metabolic rate and consumables usage throughout the execution of each EVA. The intent of this work is to convey the natural variability of EVA operations and to provide operational context for coping with the variability inherent to EVA execution as a means to support future concepts of operations.

APOLLO X - CREW TRAINING

NASA Image and Video Library

1969-06-03

S69-35503 (June 1969) --- Astronaut Eugene A. Cernan (left), lunar module pilot of the Apollo 10 lunar orbit mission, confers with astronaut Edwin E. Aldrin Jr. during an Apollo 10 postflight de-briefing session. Aldrin is the lunar module pilot of the Apollo 11 lunar landing mission.

Apollo 17 KREEPy basalts - Evidence for nonuniformity of KREEP

NASA Technical Reports Server (NTRS)

Salpas, Peter A.; Taylor, Lawrence A.; Lindstrom, Marilyn M.

1987-01-01

Breccia 72275 contains pristine KREEPy basalt clasts that are not found among other samples collected at Apollo 17. These basalts occur as discrete clasts and as clasts enclosed within basaltic microbreccias. Mineral and whole-rock chemical analyses reveal that the microbreccias are compositionally indistinguishable from the basalt clasts. Samples of the 72275 matrix also have the same compositions as the basalts and the basaltic microbreccias. 72275 was assembled in situ from a single flow or series of closely related flows of Apollo 17 KREEPy basalt before it was transported to the Apollo 17 site. As a rock type, Apollo 17 KREEPy basalts are distinct from Apollo 15 KREEP basalts. The Apollo 17 samples have lower REE concentrations, steeper negative slopes of the HREE, and are less magnesian than the Apollo 15 samples. The two basalt types cannot be related by fractional crystallization, partial melting, or assimilation. This is evidence for the compositional nonuniformity of KREEP as a function of geography.

Cyclic Peptidic Mimetics of Apollo Peptides Targeting Telomeric Repeat Binding Factor 2 (TRF2) and Apollo Interaction.

PubMed

Chen, Xia; Liu, Liu; Chen, Yong; Yang, Yuting; Yang, Chao-Yie; Guo, Tianyue; Lei, Ming; Sun, Haiying; Wang, Shaomeng

2018-05-10

Telomeric repeat binding factor 2 (TRF2) is a telomere-associated protein that plays an important role in the formation of the 3' single strand DNA overhang and the "T loop", two structures critical for the stability of the telomeres. Apollo is a 5'-exonuclease recruited by TRF2 to the telomere and contributes to the formation of the 3' single strand DNA overhang. Knocking down of Apollo can induce DNA damage response similar to that caused by the knocking down of TRF2. In this Letter, we report the design and synthesis of a class of cyclic peptidic mimetics of the TRFH binding motif of Apollo (Apollo TBM ). We found conformational control of the C terminal residues of Apollo TBM can effectively improve the binding affinity. We have obtained a crystal structure of a cyclic peptidic Apollo peptide mimetic ( 34 ) complexed with TRF2, which provides valuable guidance to the future design of TRF2 inhibitors.

Apollo contributes to G overhang maintenance and protects leading-end telomeres.

PubMed

Wu, Peng; van Overbeek, Megan; Rooney, Sean; de Lange, Titia

2010-08-27

Mammalian telomeres contain a single-stranded 3' overhang that is thought to mediate telomere protection. Here we identify the TRF2-interacting factor Apollo as a nuclease that contributes to the generation/maintenance of this overhang. The function of mouse Apollo was determined using Cre-mediated gene deletion, complementation with Apollo mutants, and the TRF2-F120A mutant that cannot bind Apollo. Cells lacking Apollo activated the ATM kinase at their telomeres in S phase and showed leading-end telomere fusions. These telomere dysfunction phenotypes were accompanied by a reduction in the telomeric overhang signal. The telomeric functions of Apollo required its TRF2-interaction and nuclease motifs. Thus, TRF2 recruits the Apollo nuclease to process telomere ends synthesized by leading-strand DNA synthesis, thereby creating a terminal structure that avoids ATM activation and resists end-joining. These data establish that the telomeric overhang is required for the protection of telomeres from the DNA damage response. Copyright (c) 2010 Elsevier Inc. All rights reserved.

Comparative Planetary Mineralogy: Basaltic Plagioclase from Earth, Moon, Mars and 4 Vesta

NASA Technical Reports Server (NTRS)

Karner, J. M.; Papike, J. J.; Shearer, C. K.

2003-01-01

Major, minor and trace element analysis of silicates has allowed for the study of planetary basalts in a comparative planetary mineralogy context. We continue this initiative by exploring the chemistry of plagioclase feldspar in basalts from the Earth, Moon, Mars and 4 Vesta. This paper presents new data on plagioclase from six terrestrial basalt suites including Keweenawan, Island Arc, Hawaiian, Columbia Plateau, Taos Plateau, and Ocean Floor; six lunar basalt suites including Apollo 11 Low K, Apollo 12 Ilmenite, Apollo 12 Olivine, Apollo 12 Pigeonite, Apollo 15 Olivine, and Apollo 15 Pigeonite; two basaltic martian meteorites, Shergotty and QUE 94201; and one unequilibrated eucrite, Pasamonte.

Schweickart and guest at ASVC prior to grand opening

NASA Technical Reports Server (NTRS)

1997-01-01

Apollo 9 Lunar Module Pilot Russell L. Schweikart poses in front of an Apollo Command and Service Module in the the new Apollo/Saturn V Center (ASVC) at KSC prior to the gala grand opening ceremony for the facility that was held Jan. 8, 1997. Several Apollo astronauts were invited to participate in the event, which also featured NASA Administrator Dan Goldin and KSC Director Jay Honeycutt. The ASVC also features several other Apollo program spacecraft components, multimedia presentations and a simulated Apollo/Saturn V liftoff. The facility will be a part of the KSC bus tour that embarks from the KSC Visitor Center.

Apollo 13 - Press Kit

NASA Technical Reports Server (NTRS)

1970-01-01

Apollo 13, the third U.S. manned lunar landing mission, will be launched April 11 from Kennedy Space Center, Fla., to explore a hilly upland region of the Moon and bring back rocks perhaps five billion years old. The Apollo 13 lunar module will stay on the Moon more than 33 hours and the landing crew will leave the spacecraft twice to emplace scientific experiments on the lunar surface and to continue geological investigations. The Apollo 13 landing site is in the Fra Mauro uplands; the two National Aeronautics and Space Administration previous landings were in mare or 'sea' areas, Apollo 11 in the Sea of Tranquility and Apollo 12 in the Ocean of Storms.

KSC-99pp0844

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- In the Apollo/Saturn V Center, Lisa Malone (left), chief of KSC's Media Services branch, laughs at a humorous comment along with former Apollo astronauts Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch to the moon; Gene Cernan, who flew on Apollo 10 and 17; and Walt Cunningham, who flew on Apollo 7. The four met with the media before an anniversary banquet celebrating the accomplishments of the Apollo program team. This is the 30th anniversary of the launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Integration of Apollo Lunar Sample Data into Google Moon

NASA Technical Reports Server (NTRS)

Dawson, Melissa D.; Todd, Nancy S.; Lofgren, Gary

2010-01-01

The Google Moon Apollo Lunar Sample Data Integration project is a continuation of the Apollo 15 Google Moon Add-On project, which provides a scientific and educational tool for the study of the Moon and its geologic features. The main goal of this project is to provide a user-friendly interface for an interactive and educational outreach and learning tool for the Apollo missions. Specifically, this project?s focus is the dissemination of information about the lunar samples collected during the Apollo missions by providing any additional information needed to enhance the Apollo mission data on Google Moon. Apollo missions 15 and 16 were chosen to be completed first due to the availability of digitized lunar sample photographs and the amount of media associated with these missions. The user will be able to learn about the lunar samples collected in these Apollo missions, as well as see videos, pictures, and 360 degree panoramas of the lunar surface depicting the lunar samples in their natural state, following collection and during processing at NASA. Once completed, these interactive data layers will be submitted for inclusion into the Apollo 15 and 16 missions on Google Moon.

Apollo 7 Mission,Apollo Commander Walter Schirra Jr. inside Co

NASA Image and Video Library

1968-10-20

AS07-04-1596 (20 Oct. 1968) --- A heavy beard covers the face of astronaut Walter M. Schirra Jr., Apollo 7 commander, as he looks out the rendezvous window in front of the commander's station on the ninth day of the Apollo 7 mission.

76 FR 7853 - Patient Safety Organizations: Voluntary Delisting From Apollo Publishing, Inc.

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-11

... Organizations: Voluntary Delisting From Apollo Publishing, Inc. AGENCY: Agency for Healthcare Research and Quality (AHRQ), HHS. ACTION: Notice of Delisting. SUMMARY: Apollo Publishing, Inc.: AHRQ has accepted a notification of voluntary relinquishment from Apollo Publishing, Inc., of its status as a Patient Safety...

Health protection and food preservation by gamma irradiation

NASA Technical Reports Server (NTRS)

1976-01-01

Results of several major studies on food systems for space missions beginning with Apollo 12 through Apollo-Soyuz and investigations of the application of irradiation to food for manned space flight are reported. The study of flight food systems involved the application of radurization (pasteurizing levels) doses of gamma irradiation to flour and bread supplied by Pepperidge Farms in advance of the missions. All flights from Apollo 12 through 17 carried irradiated fresh bread. On Apollo 17, cooperation with Natick Laboratories permitted the introduction of a ham sandwich using irradiated bread and irradiated sterile ham. Investigations centered on irradiated bread were conducted during the course of these missions. Studies were applied to the concept of improving fresh bread from the point of view of mold inhibition. The studies considered how irradiation could best be applied at what levels and on a variety of bread types. Throughout the studies of the application of gamma irradiation the emphasis was placed upon using low levels of irradiation in the pasteurizing or radurizing doses--under a Megarad. The primary goal was to determine if a public health benefit could be demonstrated using radurization along with food preservation and food quality improvements. The public health benefit would be parallel to that of pasteurization of milk as a concept. Publications are included providing the details of these observations, one dealing with the flour characteristics and the other dealing with the influence on fresh bread types. These demonstrate the major findings noted during the period of the studies examining bread.

Nutrition and Foods as Related to Space Flight

NASA Technical Reports Server (NTRS)

Lane, Helen W.; Smith, Scott M.; Bourland, Charles T.; Paloski, W. H. (Technical Monitor)

1999-01-01

U.S. space food development began with highly engineered foods that met rigid requirements imposed by the spacecraft design and short mission durations of the Mercury and Gemini programs. The lack of adequate bathroom facilities and limited food storage capacity promoted the development of low fiber diets to reduce fecal output. As missions lengthened, space food systems evolved, with the most basic design consideration always being the method of water supply. On the Apollo spacecraft, where water was abundant as a byproduct of fuel cell electricity generation, dehydrated food was used extensively. Such food has little advantage when water has to be transported to space to rehydrate it; therefore, more complex food systems were planned for Skylab, which used solar panels rather than fuel cells for electricity generation. The Skylab food system, the most advanced used in space to date, included freezers and refrigerators, increasing the palatability, variety, and nutritional value of the diet. On the Space Shuttle, power and weight constraints precluded the use of freezers, refrigerators, and microwave ovens. The availability of fuel cell by-product water was conducive to a shelf-stable food system with approximately half of the food dehydrated and the remainder made up of thermostabilized, irradiated, and intermediate-moisture foods.

Apollo program flight summary report: Apollo missions AS-201 through Apollo 16, revision 11

NASA Technical Reports Server (NTRS)

Holcomb, J. K.

1972-01-01

A summary of the Apollo flights from AS-201 through Apollo 16 is presented. The following subjects are discussed for each flight: (1) mission primary objectives, (2) principle objectives of the launch vehicle and spacecraft, (3) secondary objectives of the launch vehicle and spacecraft, (4) unusual features of the mission, (5) general information on the spacecraft and launch vehicle, (6) space vehicle and pre-launch data, and (7) recovery data.

Apollo 40th Anniversary Morning Television

NASA Image and Video Library

2009-07-19

Apollo 11 astronaut Buzz Aldrin, the second man to walk on the Moon, seated left, responds to a question during a live television interview on Monday, July 20, 2009, at NASA Headquarters in Washington as Apollo 12 astronaut Alan Bean and Apollo 16 astronaut Charles Duke, right look on. The three sat in for interviews with morning talks shows covering the 40th Anniversary of the Apollo 11 landing on the Moon. Photo Credit: (NASA/Paul E. Alers)

Damping Effects of Drogue Parachutes on Orion Crew Module Dynamics

NASA Technical Reports Server (NTRS)

Aubuchon, Vanessa V.

2013-01-01

Currently, simulation predictions of the Orion Crew Module (CM) dynamics with drogue parachutes deployed are under-predicting the amount of damping as seen in free-flight tests. The Apollo Legacy Chute Damping model has been resurrected and applied to the Orion system. The legacy model has been applied to predict CM damping under drogue parachutes for both Vertical Spin Tunnel free flights and the Pad Abort-1 flight test. Comparisons between the legacy Apollo prediction method and test data are favorable. A key hypothesis in the Apollo legacy drogue damping analysis is that the drogue parachutes' net load vector aligns with the CM drogue attachment point velocity vector. This assumption seems reasonable and produces good results, but has never been quantitatively proven. The wake of the CM influences the drogue parachutes, which makes performance predictions of the parachutes difficult. Many of these effects are not currently modeled in the simulations. A forced oscillation test of the CM with parachutes was conducted in the NASA LaRC 20-Ft Vertical Spin Tunnel (VST) to gather additional data to validate and refine the Apollo legacy drogue model. A second loads balance was added to the original Orion VST model to measure the drogue parachute loads independently of the CM. The objective of the test was to identify the contribution of the drogues to CM damping and provide additional information to quantify wake effects and the interactions between the CM and parachutes. The drogue parachute force vector was shown to be highly dependent on the CM wake characteristics. Based on these wind tunnel test data, the Apollo Legacy Chute Damping model was determined to be a sufficient approximation of the parachute dynamics in relationship to the CM dynamics for preliminary entry vehicle system design. More wake effects should be included to better model the system. These results are being used to improve simulation model fidelity of CM flight with drogues deployed, which has been identified by the project as key to a successful Orion Critical Design Review.

Minimally invasive evacuation of intraventricular hemorrhage with the Apollo vibration/suction device.

PubMed

Tan, Lee A; Lopes, Demetrius K; Munoz, Lorenzo F; Shah, Yojan; Bhabad, Sudeep; Jhaveri, Miral; Moftakhar, Roham

2016-05-01

Intraventricular hemorrhages (IVH) can occur as a consequence of spontaneous intracerebral hemorrhage, aneurysm rupture, arteriovenous malformation hemorrhage, trauma, or coagulopathy. IVH is a known risk factor for poor clinical outcome with up to 80% mortality. The current standard treatment strategy for IVH consists of the placement of an external ventricular drain. We report our early experience with using the Apollo suction/vibration aspiration system (Penumbra, Alameda, CA, USA) for minimally invasive evacuation of IVH with a review of the pertinent literature. Medical records of patients with IVH who were admitted to Rush University Medical Center, USA, from July to November 2014 were queried from the electronic database. Patients with Graeb Scores (GS) >6 were selected for minimally invasive IVH evacuation with the Apollo aspiration system. Patient demographics, pre- and post-operative GS, pre- and post-operative modified Graeb Score (mGS), as well procedure related complications were analyzed and recorded. A total of eight patients (five men) were identified during the study period. The average age was 55.5years. The mean GS was 9.6 pre-operatively and decreased to 4.9 post-operatively (p=0.0002). The mean mGS was 22.9 pre-operatively and decreased to 11.4 post-operatively (p=0.0001). Most of the IVH reduction occurred in the frontal horn and atrium of the lateral ventricle, as well the third ventricle. One (1/8) procedure-related complication occurred consisted of a tract hemorrhage. The Apollo system can be used for minimally invasive IVH evacuation to achieve significant blood clot volume reduction with minimal procedure-related complication. Copyright © 2016. Published by Elsevier Ltd.

Lunokhod 2 - A retrospective Glance after 30 Years

NASA Astrophysics Data System (ADS)

Gromov, V.; Kemurdjian, A.; Bogatchev, A.; Koutcherenko, V.; Malenkov, M.; Matrossov, S.; Vladykin, S.; Petriga, V.; Khakhanov, Y.

2003-04-01

30 years have passed since the second Soviet research Lunokhod-2 rover landed on the Moon on January 16, 1973 within the framework of the Luna-21 mission. Scientific explorations of the lunar surface and space, begun with the Lunokhod-1 rover (1970-1971), were continued with Lunokhod-2. Creation of Lunokhod-1 and Lunokhod-2 marked realization of direction on study of planets using mobile self-propelled robots. Other direction connected with using planetary rovers to transport astronauts, scientific equipment and weights was realized as a result of creation of the American LRV lunar rover. Astronauts during Apollo-15 (1971), Apollo-15 (1972) and Apollo-15 (1972) missions used it. Programs of operation for Lunokhod-1,-2 on the Moon envisaged investigations of topographic and morphological peculiarities of the terrain, determination of the chemical composition and physical and mechanical properties of soil, experiments on the laser detection and ranging of the Moon and, etc. Successful fulfilment of programs was ensured, to a considerable extent, with the self-propelled chassis developed at VNIITRANSMASH to order of the Lavochkin Scientific and Production Association (NPOL). The chassis, on the one hand, ensured necessary cross-country ability for Lunokhod-1,-2, on the other hand, it was as the independent scientific instrument, which provided investigation as temperature measurement of the lunar surface, surface topography and craters distribution, physical and mechanical properties of soil with the special PROP instrument equipped with the penetrometer, chassis traction-cohesive characteristics, upper surface layer by a character its deformation by the mover, etc. A number of improvements of Lunokhod-2 improving its operating characteristics were performed on the basis of results of Lunokhod-1 operation. Lunokhod-1,-2 operation confirmed that automatic mobile robots can be used as effective means for studying planets and their satellites. At the same time, an operational experience of Lunokhod-1,-2, also American LRV rover, given extensive material, which as being used while developing and manufacturing chassis and their systems for new-generation planetary rovers, as well as special equipment to Earth-based tests. The present paper considers features of the Lunochod-2 design, some results of the Lunokhod-1,-2 operation on the Moon, examples of locomotion systems for new-generation rovers with the ski-walking, wheel-walking and hopping movers. A brief review of locomotion system demonstrators (IDD-1,-2, IARES, LRMC, JRover-1,-2, etc), developed at VNIITRANSMASH and Science &Technology Rover Co. Ltd. to order of ESA and foreign organizations taking part in space explorations. The locomotion systems description for the RoSA-2 project and ExoMaDeR model for "ExoMars-2009" project, developed by RCL in cooperation and to order of ESA, is given.

Apollo Lightcraft project

NASA Technical Reports Server (NTRS)

Myrabo, Leik N.; Blandino, John S.; Borkowski, Chris A.; Cross, David P.; Frazier, Scott R.; Hill, Stephen C.; Mitty, Todd J.; Moder, Jeffrey P.; Morales, Ciro; Nyberg, Gregory A.

1987-01-01

The detailed design of a beam-powered transatmospheric vehicle, the Apollo Lightcraft, was selected as the project for the design course. The principal goal is to reduce the LEO payload delivery cost by at least three orders of magnitude below the Space Shuttle Orbiter in the post 2020 era. The completely reusable, single-stage-to-orbit shuttlecraft will take off and land vertically, and have a reentry heat shield integrated with its lower surface. At appropriate points along the launch trajectory, the combined cycle propulsion system will transition through three or four airbreathing modes, and finally use a pure rocket mode for orbital insertion. The objective for the Spring semester propulsion source was to design and perform a detailed theoretical analysis on an advanced combined-cycle engine suitable for the Apollo Lightcraft. The preliminary theoretical analysis of this combined-cycle engine is now completed, and the acceleration performance along representative orbital trajectories was simulated. The total round trip cost is $3430 or $686 per person. This represents a payload delivery cost of $3.11/lb, which is a factor of 1000 below the STS. The Apollo Lightcraft concept is now ready for a more detailed investigation during the Fall semester Transatmosphere Vehicle Design course.

KSC-2014-3199

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- At the Kennedy Space Center in Florida, NASA officials and Apollo astronauts have a group portrait taken in front of the refurbished Operations and Checkout Building, newly named for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. From left are NASA Administrator Charles Bolden, Apollo astronauts Mike Collins, Buzz Aldrin and Jim Lovell, and Center Director Robert Cabana. The building's high bay is being used to support the agency's new Orion spacecraft, which will lift off atop the Space Launch System rocket. Orion is designed to take humans farther than they’ve ever gone before, serving as the exploration vehicle that will carry astronauts to deep space and sustain the crew during travel to destinations such as an asteroid or Mars. The visit of the former astronauts was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Aldrin landed in the moon's Sea of Tranquility aboard the lunar module Eagle on July 20, 1969. Meanwhile, crewmate Collins orbited above in the command module Columbia. For more, visit http://www.nasa.gov/press/2014/july/nasa-honors-historic-first-moon-landing-eyes-first-mars-mission. Photo credit: NASA/Kevin O'Connell

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

Apollo 11 astronaut Buzz Aldrin reads an introduction to Gustav Holst: The Planets Suite during the "Salute to Apollo" ceremony at the Kennedy Center for the Performing Arts, Saturday, July 18, 2009 in Washington. The event was part of NASA's week long celebration of the Apollo 40th Anniversary. Photo Credit: (NASA/Bill Ingalls)

Topographic mapping of the Apollo 16 landing site

NASA Technical Reports Server (NTRS)

Hill, R. O.; Bender, M. J.

1972-01-01

The techniques are described for obtaining high resolution photographs from the Apollo 14 lunar orbiter for topographic mapping of the Descartes landing site for use in planning Apollo 16. The Apollo 16 spacecraft landed approximately 250 m from the selected target point, and few topographic surprises were encountered.

ASTRONAUT LOVELL, JAMES A., JR. - APOLLO VIII (GUIDANCE & NAVIGATION [G&N])

NASA Image and Video Library

1969-05-25

S69-35099 (21-27 Dec. 1968) --- Astronaut James A. Lovell Jr., Apollo 8 command module pilot, is seen at the Apollo 8 Spacecraft Command Module's Guidance and Navigation station during the Apollo 8 lunar orbit mission. This picture was taken from 16mm motion picture film.

Saturn Apollo Program

NASA Image and Video Library

1968-06-03

Pictured left to right, in the Apollo 7 Crew Portrait, are astronauts R. Walter Cunningham, Lunar Module pilot; Walter M. Schirra, Jr., commander; and Donn F. Eisele, Command Module Pilot. The Apollo 7 mission, boosted by a Saturn IB launch vehicle on October 11, 1968, was the first manned flight of the Apollo spacecraft.

Testing Gravity via Lunar Laser Ranging: Maximizing Data Quality

NASA Astrophysics Data System (ADS)

Murphy, Thomas

We propose to continue leading-edge observations with the Apache Point Observatory Lunar Laser-ranging Operation (APOLLO), in an effort to subject gravity to the most stringent tests yet. APOLLO has delivered a dramatic improvement in the measurement of the lunar orbit: now at the millimeter level. Yet incomplete models are thus far unable to confirm the accuracy. We therefore seek to build a calibration system to ensure that APOLLO meets its millimeter measurement goal. Gravity--the most evident force of nature--is in fact the weakest of the fundamental forces, and consequently the most poorly tested. Einstein’s general relativity, which is currently our best description of gravity, is fundamentally incompatible with quantum mechanics and is likely to be replaced by a more complete theory in the future. A modified theory would predict small deviations in the solar system that could have profound consequences for our understanding of the Universe as a whole. Lunar laser ranging (LLR), in which short laser pulses launched from a telescope are bounced off of reflectors placed on the Moon by U.S. astronauts and Soviet landers, has for decades produced some of the leading tests of gravity by mapping the shape of the lunar orbit to high precision. These include tests of the strong equivalence principle, the time-rate-ofchange of Newton’s gravitational constant, gravitomagnetism, the inverse-square law, and many others. Among the attributes that contribute to APOLLO’s superior observations, routine ranging to all five lunar reflectors on timescales of minutes dramatically improves our ability to gauge lunar orientation and body distortion. This information produces insights into the interior structure and dynamics of the Moon, allowing a more precise determination of the path for the Moon’s center of mass, lending to tests of fundamental gravity. Simultaneously, higher precision range measurements, together with data from a superconducting gravimeter at the Apache Observatory and from a high-quality Global Positioning System (GPS) station 2.5 km away, will greatly improve our understanding of the instantaneous location of the Observatory with respect to the Earth’s center of mass (needed for the gravitational tests) by exposing subtle Earth dynamics that must be incorporated into the model. In addition to dramatic improvements in the classical gravitational tests listed above, APOLLO will permit exploration of new ideas in physics relating to dark energy, extra dimensions, and violations of Lorentz Invariance. This proposal will have two thrusts: to continue acquiring APOLLO data, thereby probing longer-period terms in the lunar orbit; and to design and construct an absolute calibration system that can either verify APOLLO data accuracy and stability or expose elements in need of attention. APOLLO has been effective at public outreach and education not only by direct involvement with students and underrepresented groups, but also via news articles, magazine articles, radio interviews, and appearances on popular television shows. This level of media attention should continue into the future, given the appealing combination of tests of Einstein's gravity, the legendary lunar landings, and remarkable technology.

Critical soft landing technology issues for future US space missions

NASA Technical Reports Server (NTRS)

Macha, J. M.; Johnson, D. W.; Mcbride, D. D.

1992-01-01

A programmatic need for research and development to support parachute-based landing systems has not existed since the end of the Apollo missions in the mid-1970s. Now, a number of planned space programs require advanced landing capabilities for which the experience and technology base does not currently exist. New requirements for landing on land with controllable, gliding decelerators and for more effective impact attenuation devices justify a renewal of the landing technology development effort that existed during the Mercury, Gemini, and Apollo programs. A study was performed to evaluate the current and projected national capability in landing systems and to identify critical deficiencies in the technology base required to support the Assured Crew Return Vehicle and the Two-Way Manned Transportation System. A technology development program covering eight landing system performance issues is recommended.

Fifteen-foot diameter modular space station Kennedy Space Center launch site support definition (space station program Phase B extension definition)

NASA Technical Reports Server (NTRS)

Bjorn, L. C.; Martin, M. L.; Murphy, C. W.; Niebla, J. F., V

1971-01-01

This document defines the facilities, equipment, and operational plans required to support the MSS Program at KSC. Included is an analysis of KSC operations, a definition of flow plans, facility utilization and modifications, test plans and concepts, activation, and tradeoff studies. Existing GSE and facilities that have a potential utilization are identified, and new items are defined where possible. The study concludes that the existing facilities are suitable for use in the space station program without major modification from the Saturn-Apollo configuration.

Astronaut Russell Schweickart photographed during EVA

NASA Image and Video Library

1969-03-06

AS09-19-2983 (6 March 1969) --- Astronaut Russell L. Schweickart, lunar module pilot, operates a 70mm Hasselblad camera during his extravehicular activity (EVA) on the fourth day of the Apollo 9 Earth-orbital mission. The Command and Service Modules (CSM) and Lunar Module (LM) "Spider" are docked. This view was taken from the Command Module (CM) "Gumdrop". Schweickart, wearing an Extravehicular Mobility Unit (EMU), is standing in "golden slippers" on the LM porch. On his back, partially visible, are a Portable Life Support System (PLSS) and an Oxygen Purge System (OPS). Astronaut James A. McDivitt, Apollo 9 commander, was inside the "Spider". Astronaut David R. Scott, command module pilot, remained at the controls in the CM.

Apollo 9 Mission image - Astronaut Russell L. Schweickart, lunar module pilot, during EVA

NASA Image and Video Library

1969-03-03

Astronaut Russell L. Schweickart, lunar module pilot, operates a 70mm Hasselblad camera during his extravehicular activity on the fourth day of the Apollo 9 earth-orbital mission. The Command/Service Module and the Lunar Module 3 "Spider" are docked. This view was taken form the Command Module "Gumdrop". Schweickart, wearing an Extravehicular Mobility Unit (EMU), is standing in "golden slippers" on the Lunar Module porch. On his back, partially visible, are a Portable Life Support System (PLSS) and an Oxygen Purge System (OPS). Film magazine was A,film type was SO-368 Ektachrome with 0.460 - 0.710 micrometers film / filter transmittance response and haze filter,80mm lens.

Research, development and application of noncombustible Beta fiber structures. [for Apollo

NASA Technical Reports Server (NTRS)

Dillon, J. J.; Cobb, E. S.

1975-01-01

Beta fiber was selected as the primary material for flexible fibrous structures used in spacecraft and crew systems applications in the Apollo program because it was noncombustible in a 100 percent oxygen atmosphere up to 16.5 psia. It met NASA criteria for outgassing, toxicity, odor, and crew comfort, and possessed sufficient durability to last through the mission. Topics discussed include: study of spacecraft applications; design of Beta fiber textile structures to meet the requirements; selection of surface treatments (finishes, coatings, and printing systems) to impart the required durability and special functional use to the textile structures; development of sewing and fabrication techniques; and testing and evaluation programs, and development of production sources.

Endocrine Laboratory Results Apollo Missions 14 and 15

NASA Technical Reports Server (NTRS)

Leach, C. S.

1972-01-01

Endocrine/metabolic responses to space flight have been measured on the crewmen of Apollo missions 14 and 15. There were significant biochemical changes in the crewmen of both missions immediately postflight. However, the Apollo 15 mission results differed from Apollo 14 and preflight shown by a normal to increased urine volume with slight increases in antidiuretic hormone. Although Apollo 15 was the first mission in which the exchangeable potassium measurement was made (a decrease), results from other missions were indicative of similar conclusions.

Neil Armstrong chats with attendees at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong poses for a photograph with fans who attended the anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon.

Glenn Lecture With Crew of Apollo 11

NASA Image and Video Library

2009-07-18

On the eve of the fortieth anniversary of Apollo 11's first human landing on the Moon, Apollo 11 crew member, Michael Collins speaks during a lecture in honor of Apollo 11 at the National Air and Space Museum in Washington, Sunday, July 19, 2009. Guest speakers included Former NASA Astronaut and U.S. Senator John Glenn, NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft and the crew of Apollo 11. Photo Credit: (NASA/Bill Ingalls)

Glenn Lecture With Crew of Apollo 11

NASA Image and Video Library

2009-07-18

On the eve of the fortieth anniversary of Apollo 11's first human landing on the Moon, Apollo 11 crew member, Buzz Aldrin speaks during a lecture in honor of Apollo 11 at the National Air and Space Museum in Washington, Sunday, July 19, 2009. Guest speakers included Former NASA Astronaut and U.S. Senator John Glenn, NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft and the crew of Apollo 11. Photo Credit: (NASA/Bill Ingalls)

KSC-99pp0855

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- Former Apollo 11 astronaut Neil A. Armstrong talks with a former Apollo team member during an anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Dedication Ceremony

NASA Technical Reports Server (NTRS)

1999-01-01

Alabama Governor Don Seigleman cuts the ribbon marking the dedication of the Saturn V rocket replica that was constructed at the U. S. Space and Rocket Center in honor of the 30th arniversary of the lunar landing. Accompanying the Governor are (L/R): Mike Wing, CEO US Space Rocket Center; Mike Gillespie, Madison County Commissioner, Dist. Seven; Buzz Aldrin, Apollo 11 Astronaut; Governor Seigleman; Walt Cunningham, Apollo 7 Astronaut; Dick Gordon, Apollo 12 Astronaut; Ed Mitchell, Apollo 14 Astronaut; Charlie Duke, Apollo 16 Astronaut; and Owen Garriott, Skylab 3 Astronaut.

Around Marshall

NASA Image and Video Library

1999-07-16

Alabama Governor Don Seigleman cuts the ribbon marking the dedication of the Saturn V rocket replica that was constructed at the U. S. Space and Rocket Center in honor of the 30th arniversary of the lunar landing. Accompanying the Governor are (L/R): Mike Wing, CEO US Space Rocket Center; Mike Gillespie, Madison County Commissioner, Dist. Seven; Buzz Aldrin, Apollo 11 Astronaut; Governor Seigleman; Walt Cunningham, Apollo 7 Astronaut; Dick Gordon, Apollo 12 Astronaut; Ed Mitchell, Apollo 14 Astronaut; Charlie Duke, Apollo 16 Astronaut; and Owen Garriott, Skylab 3 Astronaut.

Artist's drawing of internal arrangement of orbiting Apollo & Soyuz crafts

NASA Image and Video Library

1974-12-01

S74-05269 (December 1974) --- An artist?s drawing illustrating the internal arrangement of the Apollo and Soyuz spacecraft in Earth orbit in a docked configuration. The three American Apollo crewmen and the two Soviet Soyuz crewmen will transfer to each other?s spacecraft during the July 1975 ASTP mission. The four Apollo-Soyuz Test Project visible components are, left to right, the Apollo Command Module, the Docking Module, the Soyuz Orbital Module and the Soyuz Descent Vehicle.

Apollo 16 astronauts in Apollo Command Module Mission Simulator

NASA Technical Reports Server (NTRS)

1972-01-01

Astronaut Thomas K. Mattingly II, command module pilot of the Apollo 16 lunar landing mission, participates in extravehicular activity (EVA) training in bldg 5 at the Manned Spacecraft Center (MSC). In the right background is Astronaut Charles M. Duke Jr., lunar module pilot. They are inside the Apollo Command Module Mission Simulator (31046); Mattingly (right foreground) and Duke (right backgroung) in the Apollo Command Module Mission Simulator for EVA simulation and training. Astronaut John W. Young, commander, can be seen in the left background (31047).

INFLIGHT - APOLLO X (CREW ACTIVITIES)

NASA Image and Video Library

1969-05-18

S69-33999 (18 May 1969) --- A close-up view of the face of astronaut, Thomas P. Stafford, Apollo 10 commander, is seen in this color reproduction taken from the third television transmission made by the color television camera aboard the Apollo 10 spacecraft. When this picture was made the Apollo 10 spacecraft was on a trans-lunar course, and was already about 36,000 nautical miles from Earth. Also, aboard Apollo 10 were astronauts John W. Young, command module pilot, and Eugene A. Cernan, lunar module pilot.

Examining Volcanic Terrains Using In Situ Geochemical Technologies; Implications for Planetary Field Geology

NASA Technical Reports Server (NTRS)

Young, K. E.; Bleacher, J. E.; Evans, C. A.; Rogers, A. D.; Ito, G.; Arzoumanian, Z.; Gendreau, K.

2015-01-01

Regardless of the target destination for the next manned planetary mission, the crew will require technology with which to select samples for return to Earth. The six Apollo lunar surface missions crews had only the tools to enable them to physically pick samples up off the surface or from a boulder and store those samples for return to the Lunar Module and eventually to Earth. Sample characterization was dependent upon visual inspection and relied upon their extensive geology training. In the four decades since Apollo however, great advances have been made in traditionally laboratory-based instrument technologies that enable miniaturization to a field-portable configuration. The implications of these advancements extend past traditional terrestrial field geology and into planetary surface exploration. With tools that will allow for real-time geochemical analysis, an astronaut can better develop a series of working hypotheses that are testable during surface science operations. One such technology is x-ray fluorescence (XRF). Traditionally used in a laboratory configuration, these instruments have now been developed and marketed commercially in a field-portable mode. We examine this technology in the context of geologic sample analysis and discuss current and future plans for instrument deployment. We also discuss the development of the Chromatic Mineral Identification and Surface Texture (CMIST) instrument at the NASA Goddard Space Flight Center (GSFC). Testing is taking place in conjunction with the RIS4E (Remote, In Situ, and Synchrotron Studies for Science and Exploration) SSERVI (Solar System Exploration and Research Virtual Institute) team activities, including field testing at Kilauea Volcano, HI..

Apollo 16 astronauts in Apollo Command Module Mission Simulator

NASA Image and Video Library

1972-03-14

S72-31047 (March 1972) --- Astronaut Thomas K. Mattingly II (right foreground), command module pilot of the Apollo 16 lunar landing mission, participates in extravehicular activity (EVA) training in Building 5 at the Manned Spacecraft Center (MSC). Mattingly is scheduled to perform EVA during the Apollo 16 journey home from the moon. Astronaut John W. Young, commander, can be seen in the left background. In the right background is astronaut Charles M. Duke Jr., lunar module pilot. They are inside the Apollo Command Module Mission Simulator. While Mattingly remains with the Apollo 16 Command and Service Modules (CSM) in lunar orbit, Young and Duke will descend in the Lunar Module (LM) to the moon's Descartes landing site.

KSC-2012-6147

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Charles Duke, chairman of the board of directors for the Astronaut Scholarship Foundation welcomes guests who have gathered for the organization's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

KSC-2012-6146

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Charles Duke, chairman of the board of directors for the Astronaut Scholarship Foundation welcomes guests who have gathered for the organization's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

Radioactivities vs. depth in Apollo 16 and 17 soil

NASA Technical Reports Server (NTRS)

Fireman, E. L.; D'Amico, J.; Defelice, J.

1973-01-01

The radioactivities of Ar-37, Ar-39, and H-3 measured at a number of depths for Apollo 16 and 17 soil are reported. The Ar-37 activities vs depth in the Apollo 16 drill string increased with depth and reached a broad maximum in the neighborhood of 50 g per sq cm before decreasing. The Ar-39 activities in Apollo 17 soil were higher than in Apollo 16 soil, probably owing to the higher Fe and Ti contents. The H-3 activities in Apollo 16 and 17 soil were quite similar and indicate that the 4 August 1972 flare produced very little H-3 compared to the amount produced by solar flares during the previous 50 years.

Project M: Scale Model of Lunar Landing Site of Apollo 17: Focus on Lighting Conditions and Analysis

NASA Technical Reports Server (NTRS)

Vanik, Christopher S.; Crain, Timothy P.

2010-01-01

This document captures the research and development of a scale model representation of the Apollo 17 landing site on the moon as part of the NASA INSPIRE program. Several key elements in this model were surface slope characteristics, crater sizes and locations, prominent rocks, and lighting conditions. This model supports development of Autonomous Landing and Hazard Avoidance Technology (ALHAT) and Project M for the GN&C Autonomous Flight Systems Branch. It will help project engineers visualize the landing site, and is housed in the building 16 Navigation Systems Technology Lab. The lead mentor was Dr. Timothy P. Crain. The purpose of this project was to develop an accurate scale representation of the Apollo 17 landing site on the moon. This was done on an 8'2.5"X10'1.375" reduced friction granite table, which can be restored to its previous condition if needed. The first step in this project was to research the best way to model and recreate the Apollo 17 landing site for the mockup. The project required a thorough plan, budget, and schedule, which was presented to the EG6 Branch for build approval. The final phase was to build the model. The project also required thorough research on the Apollo 17 landing site and the topography of the moon. This research was done on the internet and in person with Dean Eppler, a space scientist, from JSC KX. This data was used to analyze and calculate the scale of the mockup and the ratio of the sizes of the craters, ridges, etc. The final goal was to effectively communicate project status and demonstrate the multiple advantages of using our model. The conclusion of this project was that the mockup was completed as accurately as possible, and it successfully enables the Project M specialists to visualize and plan their goal on an accurate three dimensional surface representation.

Results of the Apollo 15 and 16 X-ray experiment

NASA Technical Reports Server (NTRS)

Adler, I.; Trombka, J. I.; Schmadebeck, R.; Lowman, P.; Blodget, H.; Yin, L.; Eller, E.; Podwysocki, M.; Weidner, J. R.; Bickel, A. L.

1973-01-01

Except for some minor modifications the Apollo 16 X-ray fluorescence experiment was similar to that flown aboard Apollo 15. The Apollo 16 provided data for a number of features not previously covered such as Mare Cognitum, Mare Nubium, Ptolemaeus, Descartes, Mendeleev, and other areas. Many data points were obtained by the X-ray experiments, so that comparisons could be drawn between Apollo 15 and 16 flights. The agreement was generally within about 10%. Al/Si concentration ratios ranged from 0.38% in Mare Cognitum to 0.67% in the Descartes area highlands. A comparison of the Apollo 16 data Al/Si values with optical albedo values along the ground tracks showed the same positive correlation as in the Apollo 15 flight. A reexamination of the detector and collimator geometries showed that the spatial resolution was better by almost a factor of two than the initial estimates.

Interaction of gases with lunar materials. [analysis of lunar samples from Apollo 17 flight

NASA Technical Reports Server (NTRS)

Holmes, H. F.; Fuller, E. L., Jr.; Gammage, R. B.

1974-01-01

The surface chemistry of Apollo 17 lunar fines samples 74220 (the orange soil) and 74241 (the gray control soil) has been studied by measuring the adsorption of nitrogen, argon, and oxygen (all at 77 K) and also water vapor (at 20 or 22 C). In agreement with results for samples from other missions, both samples had low initial specific surface areas, consisted of nonporous particles, and were attacked by water vapor at high relative pressure to give an increased specific surface area and create a pore system which gave rise to a capillary condensation hysteresis loop in the adsorption isotherms. In contrast to previous samples, both of the Apollo 17 soils were partially hydrophobic in their initial interaction with water vapor (both samples were completely hydrophilic after the reaction with water). The results are consistent with formation at high temperatures without subsequent exposure to significant amounts of water.

Apollo 13 Service Module

NASA Image and Video Library

1970-04-17

AS13-59-8500A (17 April 1970) --- This view of the severely damaged Apollo 13 Service Module (SM) was photographed from the Lunar Module/Command Module (LM/CM) following SM jettisoning. As seen in this cropped image, enlarged to provide a close-up view of the damaged area, an entire panel on the SM was blown away by the apparent explosion of oxygen tank number two located in Sector 4 of the SM. Two of the three fuel cells are visible just forward (above) the heavily damaged area. Three fuel cells, two oxygen tanks, and two hydrogen tanks are located in Sector 4. The damaged area is located above the S-Band high gain antenna. Nearest the camera is the Service Propulsion System (SPS) engine and nozzle. The damage to the SM caused the Apollo 13 crew members to use the LM as a "lifeboat". The LM was jettisoned just prior to Earth re-entry by the CM. Photo credit: NASA

View of damaged Apollo 13 Service Module from the Lunar/Command Modules

NASA Image and Video Library

1970-04-17

AS13-59-8501 (17 April 1970) --- This view of the severely damaged Apollo 13 Service Module (SM) was photographed from the Lunar Module/Command Module (LM/CM) following SM jettisoning. As seen here, an entire panel on the SM was blown away by the apparent explosion of oxygen tank number two located in Sector 4 of the SM. Two of the three fuel cells are visible just forward (above) the heavily damaged area. Three fuel cells, two oxygen tanks, and two hydrogen tanks are located in Sector 4. The damaged area is located above the S-Band high gain antenna. Nearest the camera is the Service Propulsion System (SPS) engine and nozzle. The damage to the SM caused the Apollo 13 crew men to use the LM as a "lifeboat." The LM was jettisoned just prior to Earth re-entry by the CM.

Petrographic and petrological studies of lunar rocks. [from the Apollo 15 mission

NASA Technical Reports Server (NTRS)

Winzer, S. R.

1978-01-01

Thin sections and polished electron probe mounts of Apollo 15 glasscoated breccias 15255, 15286, 15466, and 15505 were examined optically and analyzed by sem/microprobe. Sections from breccias 15465 and 15466 were examined in detail, and chemical and mineralogical analyses of several larger lithic clasts, green glass, and partly crystallized green glass spheres are presented. Area analyses of 33 clasts from the above breccias were also done using the SEM/EDS system. Mineralogical and bulk chemical analyses of clasts from the Apollo 15 glass-coated breccias reveal a diverse set of potential rock types, including plutonic and extrusive igneous rocks and impact melts. Examination of the chemistry of the clasts suggests that many of these clasts, like those found in 61175, are impact melts. Their variability suggests formation by several small local impacts rather than by a large basin-forming event.

Evaluation of the electromechanical properties of the cardiovascular system after prolonged weightlessness

NASA Technical Reports Server (NTRS)

Bergman, S. A., Jr.; Johnson, R. L.; Hoffler, G. W.

1977-01-01

Devices and techniques for measuring and analyzing systolic time intervals and quantitative phonocardiograms were initiated during Apollo 17. The data show that the systolic time interval from Apollo 17 crewmen remained elevated longer postflight than the response criteria of heart rate, blood pressure, and percent change in leg volume all of which had returned to preflight levels by the second day postflight. Although the systolic time interval values were only slightly outside the preflight fiducial limits, this finding suggested that: the analysis of systolic time intervals may help to identify the mechanisms of postflight orthostatic intolerance by virtue of measuring ventricular function more directly and, the noninvasive technique may prove useful in determining the extent and duration of cardiovascular instability after long duration space flight. The systolic time intervals obtained on the Apollo 17 crewmen during lower body negative pressure were similar to those noted in patients with significant heart disease.

Manned Venus Flyby

NASA Technical Reports Server (NTRS)

Feldman, M. S.; Ferrara, L. A.; Havenstein, P. L.; Volonte, J. E.; Whipple, P. H.

1967-01-01

This study is one of several being conducted at Bellcomm and in Manned Space Flight whose purpose is to give guidance to the Apollo Applications Program's technical objectives by focusing on a longer range goal. The assumed mission in this case is a three-man flyby of Venus launched in November, 1973 on a single standard Saturn V. The selected flight configuration includes a Command and Service Module similar in some respects to Apollo, an Environmental Support Module which occupies the adapter area and a spent S-IVB stage which is utilized for habitable volume and structural support of a solar cell electrical power system. The total injected weight, 106,775 lbs., is within the capability of a single Saturn V of the early 1970's. The study is focused on the selection of subsystem technologies appropriate to long duration flight. The conclusions are reported in terms of the technical characteristics to be achieved as part of the Apollo Applications Program's long duration objectives.

Apollo lunar descent guidance

NASA Technical Reports Server (NTRS)

Klumpp, A. R.

1974-01-01

Apollo lunar-descent guidance transfers the Lunar Module from a near-circular orbit to touchdown, traversing a 17 deg central angle and a 15 km altitude in 11 min. A group of interactive programs in an onboard computer guide the descent, controlling altitude and the descent propulsion system throttle. A ground-based program pre-computes guidance targets. The concepts involved in this guidance are described. Explicit and implicit guidance are discussed, guidance equations are derived, and the earlier Apollo explicit equation is shown to be an inferior special case of the later implicit equation. Interactive guidance, by which the two-man crew selects a landing site in favorable terrain and directs the trajectory there, is discussed. Interactive terminal-descent guidance enables the crew to control the essentially vertical descent rate in order to land in minimum time with safe contact speed. The altitude maneuver routine uses concepts that make gimbal lock inherently impossible.

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

Apollo 11 astronaut Buzz Aldrin, left, meets with Gene Kranz, retired NASA Flight Director and manager, back stage after the "Salute to Apollo" ceremony at the Kennedy Center for the Performing Arts, Saturday, July 18, 2009 in Washington. The event was part of NASA's week long celebration of the Apollo 40th Anniversary. Photo Credit: (NASA/Bill Ingalls)

Apollo 7 prime crew during water egress training in Gulf of Mexico

NASA Technical Reports Server (NTRS)

1968-01-01

The prime crew of the first manned Apollo space mission, Apollo 7, is seen in Apollo Command Module Boilerplate 1102 during water egress training in the Gulf of Mexico. In foreground is Astronaut Walter M. Schirra Jr., in center is Astronaut Donn F. Eisele, and in background is Astronaut Walter Cunningham.

Lunar Reconnaissance Orbiter Camera

Science.gov Websites

them out » Traverse featurette Traverse the Apollo Landing Sites & More. By combining LROC imagery , data, and historical data, we've created detailed, interactive maps of the Apollo Landing Sites and taken by the original Apollo crews. ASU maintains the Apollo Digital Image Archive and the March to the

COMMAND MODULE - APOLLO - INTERIOR - SPACECRAFT (S/C) 101 - PANEL - CONTROL - NORTH AMERICAN AVIATION (NAA), CA

NASA Image and Video Library

1967-01-27

S67-23078 (27 Jan. 1967) --- Three astronauts (later to be named the Apollo 9 prime crew) in Apollo spacecraft 101 Command module during Apollo crew compartment fit and function test. Left to right are astronauts James A. McDivitt, David R. Scott, and Russell L. Schweickart.

Apollo 9 - Prime Crew - Apollo Command Module (CM)-103 - Post-Test

NASA Image and Video Library

1968-07-19

S68-42164 (19 July 1968) --- The prime crew of the third manned Apollo space mission stands in front of the Apollo Command Module 103 after egress during crew compartment fit and function test activity. Left to right are astronauts Russell L. Schweickart, David R. Scott, and James A. McDivitt.

Function of Apollo (SNM1B) at telomere highlighted by a splice variant identified in a patient with Hoyeraal–Hreidarsson syndrome

PubMed Central

Touzot, Fabien; Callebaut, Isabelle; Soulier, Jean; Gaillard, Laetitia; Azerrad, Chantal; Durandy, Anne; Fischer, Alain; de Villartay, Jean-Pierre; Revy, Patrick

2010-01-01

Telomeres, the protein–DNA complexes at the ends of linear chromosomes, are protected and regulated by the shelterin molecules, the telomerase complex, and other accessory factors, among which is Apollo, a DNA repair factor of the β-lactamase/β-CASP family. Impaired telomere protection in humans causes dyskeratosis congenita and Hoyeraal–Hreidarsson (HH) syndrome, characterized by premature aging, bone marrow failure, and immunodeficiency. We identified a unique Apollo splice variant (designated Apollo-Δ) in fibroblasts from a patient with HH syndrome. Apollo-Δ generates a dominant negative form of Apollo lacking the telomeric repeat-binding factor homology (TRFH)-binding motif (TBM) required for interaction with the shelterin TRF2 at telomeres. Apollo-Δ hampers the proper replication of telomeres, leading to major telomeric dysfunction and cellular senescence, but maintains its DNA interstrand cross-link repair function in the whole genome. These results identify Apollo as a crucial actor in telomere maintenance in vivo, independent of its function as a general DNA repair factor. PMID:20479256

Function of Apollo (SNM1B) at telomere highlighted by a splice variant identified in a patient with Hoyeraal-Hreidarsson syndrome.

PubMed

Touzot, Fabien; Callebaut, Isabelle; Soulier, Jean; Gaillard, Laetitia; Azerrad, Chantal; Durandy, Anne; Fischer, Alain; de Villartay, Jean-Pierre; Revy, Patrick

2010-06-01

Telomeres, the protein-DNA complexes at the ends of linear chromosomes, are protected and regulated by the shelterin molecules, the telomerase complex, and other accessory factors, among which is Apollo, a DNA repair factor of the beta-lactamase/beta-CASP family. Impaired telomere protection in humans causes dyskeratosis congenita and Hoyeraal-Hreidarsson (HH) syndrome, characterized by premature aging, bone marrow failure, and immunodeficiency. We identified a unique Apollo splice variant (designated Apollo-Delta) in fibroblasts from a patient with HH syndrome. Apollo-Delta generates a dominant negative form of Apollo lacking the telomeric repeat-binding factor homology (TRFH)-binding motif (TBM) required for interaction with the shelterin TRF2 at telomeres. Apollo-Delta hampers the proper replication of telomeres, leading to major telomeric dysfunction and cellular senescence, but maintains its DNA interstrand cross-link repair function in the whole genome. These results identify Apollo as a crucial actor in telomere maintenance in vivo, independent of its function as a general DNA repair factor.

Osmium isotope and highly siderophile element systematics of lunar impact melt breccias: Implications for the late accretion history of the Moon and Earth

USGS Publications Warehouse

Puchtel, I.S.; Walker, R.J.; James, O.B.; Kring, D.A.

2008-01-01

To characterize the compositions of materials accreted to the Earth-Moon system between about 4.5 and 3.8 Ga, we have determined Os isotopic compositions and some highly siderophile element (HSE: Re, Os, Ir, Ru, Pt, and Pd) abundances in 48 subsamples of six lunar breccias. These are: Apollo 17 poikilitic melt breccias 72395 and 76215; Apollo 17 aphanitic melt breccias 73215 and 73255; Apollo 14 polymict breccia 14321; and lunar meteorite NWA482, a crystallized impact melt. Plots of Ir versus other HSE define excellent linear correlations, indicating that all data sets likely represent dominantly two-component mixtures of a low-HSE target, presumably endogenous component, and a high-HSE, presumably exogenous component. Linear regressions of these trends yield intercepts that are statistically indistinguishable from zero for all HSE, except for Ru and Pd in two samples. The slopes of the linear regressions are insensitive to target rock contributions of Ru and Pd of the magnitude observed; thus, the trendline slopes approximate the elemental ratios present in the impactor components contributed to these rocks. The 187Os/188Os and regression-derived elemental ratios for the Apollo 17 aphanitic melt breccias and the lunar meteorite indicate that the impactor components in these samples have close affinities to chondritic meteorites. The HSE in the Apollo 17 aphanitic melt breccias, however, might partially or entirely reflect the HSE characteristics of HSE-rich granulitic breccia clasts that were incorporated in the impact melt at the time of its creation. In this case, the HSE characteristics of these rocks may reflect those of an impactor that predated the impact event that led to the creation of the melt breccias. The impactor components in the Apollo 17 poikilitic melt breccias and in the Apollo 14 breccia have higher 187Os/188Os, Pt/Ir, and Ru/Ir and lower Os/Ir than most chondrites. These compositions suggest that the impactors they represent were chemically distinct from known chondrite types, and possibly represent a type of primitive material not currently delivered to Earth as meteorites. ?? 2008 Elsevier Ltd.

APOLLO XI - CREW ARRIVAL - ELLINGTON AFB (EAFB), TX

NASA Image and Video Library

1969-07-27

S69-40217 (27 July 1969) --- Neil A. Armstrong, commander of the Apollo 11 flight, greets his son Mark, on telephone intercom system, while his wife Jan and another son Eric look on. Armstrong had just arrived in early morning with the Mobile Quarantine Facility (MQF) at Ellington Air Force Base. Armstrong and fellow astronauts will remain in the MQF until arrival and confinement in the Crew Reception Area (CRA) of the Lunar Receiving Laboratory (LRL) at the Manned Spacecraft Center (MSC). Quarantine period will end on Aug. 11, 1969.

Apollo 16, LM-11 ascent propulsion system final flight evaluation

NASA Technical Reports Server (NTRS)

Griffin, W. G.

1974-01-01

The duty cycle for the LM-11 APS consisted of two firings, an ascent stage liftoff from the lunar surface, and the terminal phase initiation (TPI) burn. APS performance for the first firing was evaluated and found to be satisfactory. No propulsion data were received from the second APS burn; however, all indications were that the burn was nominal. Engine ignition for the APS lunar liftoff burn occured at the Apollo elapsed time (AET) of 175:31:47.9 (hours:minutes:seconds). Burn duration was 427.7 seconds.

The Apollo 17 far ultraviolet spectrometer experiment

NASA Technical Reports Server (NTRS)

Fastie, W. G.

1972-01-01

The Apollo 17 command service module in lunar orbit will carry a far ultraviolet scanning spectrometer whose prime mission will be to measure the composition of the lunar atmosphere. Additional observations will include the spectral lunar albedo, the temporary atmosphere injected by the engines of the lunar exploration module, the solar system atmosphere, the galactic atmosphere and the spectra of astronomical sources, including the earth. A detailed description of the experimental equipment which observes the spectral range 1180 to 1680 A, the observing program and broad speculation about the possible results of the experiment, are presented.

APOLLO_NG - a probabilistic interpretation of the APOLLO legacy for AVHRR heritage channels

NASA Astrophysics Data System (ADS)

Klüser, L.; Killius, N.; Gesell, G.

2015-10-01

The cloud processing scheme APOLLO (AVHRR Processing scheme Over cLouds, Land and Ocean) has been in use for cloud detection and cloud property retrieval since the late 1980s. The physics of the APOLLO scheme still build the backbone of a range of cloud detection algorithms for AVHRR (Advanced Very High Resolution Radiometer) heritage instruments. The APOLLO_NG (APOLLO_NextGeneration) cloud processing scheme is a probabilistic interpretation of the original APOLLO method. It builds upon the physical principles that have served well in the original APOLLO scheme. Nevertheless, a couple of additional variables have been introduced in APOLLO_NG. Cloud detection is no longer performed as a binary yes/no decision based on these physical principles. It is rather expressed as cloud probability for each satellite pixel. Consequently, the outcome of the algorithm can be tuned from being sure to reliably identify clear pixels to conditions of reliably identifying definitely cloudy pixels, depending on the purpose. The probabilistic approach allows retrieving not only the cloud properties (optical depth, effective radius, cloud top temperature and cloud water path) but also their uncertainties. APOLLO_NG is designed as a standalone cloud retrieval method robust enough for operational near-realtime use and for application to large amounts of historical satellite data. The radiative transfer solution is approximated by the same two-stream approach which also had been used for the original APOLLO. This allows the algorithm to be applied to a wide range of sensors without the necessity of sensor-specific tuning. Moreover it allows for online calculation of the radiative transfer (i.e., within the retrieval algorithm) giving rise to a detailed probabilistic treatment of cloud variables. This study presents the algorithm for cloud detection and cloud property retrieval together with the physical principles from the APOLLO legacy it is based on. Furthermore a couple of example results from NOAA-18 are presented.

APOLLO_NG - a probabilistic interpretation of the APOLLO legacy for AVHRR heritage channels

NASA Astrophysics Data System (ADS)

Klüser, L.; Killius, N.; Gesell, G.

2015-04-01

The cloud processing scheme APOLLO (Avhrr Processing scheme Over cLouds, Land and Ocean) has been in use for cloud detection and cloud property retrieval since the late 1980s. The physics of the APOLLO scheme still build the backbone of a range of cloud detection algorithms for AVHRR (Advanced Very High Resolution Radiometer) heritage instruments. The APOLLO_NG (APOLLO_NextGeneration) cloud processing scheme is a probabilistic interpretation of the original APOLLO method. While building upon the physical principles having served well in the original APOLLO a couple of additional variables have been introduced in APOLLO_NG. Cloud detection is not performed as a binary yes/no decision based on these physical principals but is expressed as cloud probability for each satellite pixel. Consequently the outcome of the algorithm can be tuned from clear confident to cloud confident depending on the purpose. The probabilistic approach allows to retrieving not only the cloud properties (optical depth, effective radius, cloud top temperature and cloud water path) but also their uncertainties. APOLLO_NG is designed as a standalone cloud retrieval method robust enough for operational near-realtime use and for the application with large amounts of historical satellite data. Thus the radiative transfer solution is approximated by the same two stream approach which also had been used for the original APOLLO. This allows the algorithm to be robust enough for being applied to a wide range of sensors without the necessity of sensor-specific tuning. Moreover it allows for online calculation of the radiative transfer (i.e. within the retrieval algorithm) giving rise to a detailed probabilistic treatment of cloud variables. This study presents the algorithm for cloud detection and cloud property retrieval together with the physical principles from the APOLLO legacy it is based on. Furthermore a couple of example results from on NOAA-18 are presented.

Saturn Apollo Program

NASA Image and Video Library

1979-05-01

This montage depicts the flight crew patches for the manned Apollo 7 thru Apollo 17 missions. The Apollo 7 through 10 missions were basically manned test flights that paved the way for lunar landing missions. Primary objectives met included the demonstration of the Command Service Module (CSM) crew performance; crew/space vehicle/mission support facilities performance and testing during a manned CSM mission; CSM rendezvous capability; translunar injection demonstration; the first manned Apollo docking, the first Apollo Extra Vehicular Activity (EVA), performance of the first manned flight of the lunar module (LM); the CSM-LM docking in translunar trajectory, LM undocking in lunar orbit, LM staging in lunar orbit, and manned LM-CSM docking in lunar orbit. Apollo 11 through 17 were lunar landing missions with the exception of Apollo 13 which was forced to circle the moon without landing due to an onboard explosion. The craft was,however, able to return to Earth safely. Apollo 11 was the first manned lunar landing mission and performed the first lunar surface EVA. Landing site was the Sea of Tranquility. A message for mankind was delivered, the U.S. flag was planted, experiments were set up and 47 pounds of lunar surface material was collected for analysis back on Earth. Apollo 12, the 2nd manned lunar landing mission landed in the Ocean of Storms and retrieved parts of the unmanned Surveyor 3, which had landed on the Moon in April 1967. The Apollo Lunar Surface Experiments Package (ALSEP) was deployed, and 75 pounds of lunar material was gathered. Apollo 14, the 3rd lunar landing mission landed in Fra Mauro. ALSEP and other instruments were deployed, and 94 pounds of lunar materials were gathered, using a hand cart for first time to transport rocks. Apollo 15, the 4th lunar landing mission landed in the Hadley-Apennine region. With the first use of the Lunar Roving Vehicle (LRV), the crew was bale to gather 169 pounds of lunar material. Apollo 16, the 5th lunar landing mission, landed in the Descartes Highlands for the first study of highlands area. Selected surface experiments were deployed, the ultraviolet camera/spectrograph was used for first time on the Moon, and the LRV was used for second time for a collection of 213 pounds of lunar material. The Apollo program came to a close with Apollo 17, the 6th and final manned lunar landing mission that landed in the Taurus-Littrow highlands and valley area. This mission hosted the first scientist-astronaut, Schmitt, to land on the Moon. The 6th automated research station was set up, and 243 ponds of lunar material was gathered using the LRV.

Montage of Apollo Crew Patches

NASA Technical Reports Server (NTRS)

1979-01-01

This montage depicts the flight crew patches for the manned Apollo 7 thru Apollo 17 missions. The Apollo 7 through 10 missions were basically manned test flights that paved the way for lunar landing missions. Primary objectives met included the demonstration of the Command Service Module (CSM) crew performance; crew/space vehicle/mission support facilities performance and testing during a manned CSM mission; CSM rendezvous capability; translunar injection demonstration; the first manned Apollo docking, the first Apollo Extra Vehicular Activity (EVA), performance of the first manned flight of the lunar module (LM); the CSM-LM docking in translunar trajectory, LM undocking in lunar orbit, LM staging in lunar orbit, and manned LM-CSM docking in lunar orbit. Apollo 11 through 17 were lunar landing missions with the exception of Apollo 13 which was forced to circle the moon without landing due to an onboard explosion. The craft was,however, able to return to Earth safely. Apollo 11 was the first manned lunar landing mission and performed the first lunar surface EVA. Landing site was the Sea of Tranquility. A message for mankind was delivered, the U.S. flag was planted, experiments were set up and 47 pounds of lunar surface material was collected for analysis back on Earth. Apollo 12, the 2nd manned lunar landing mission landed in the Ocean of Storms and retrieved parts of the unmanned Surveyor 3, which had landed on the Moon in April 1967. The Apollo Lunar Surface Experiments Package (ALSEP) was deployed, and 75 pounds of lunar material was gathered. Apollo 14, the 3rd lunar landing mission landed in Fra Mauro. ALSEP and other instruments were deployed, and 94 pounds of lunar materials were gathered, using a hand cart for first time to transport rocks. Apollo 15, the 4th lunar landing mission landed in the Hadley-Apennine region. With the first use of the Lunar Roving Vehicle (LRV), the crew was bale to gather 169 pounds of lunar material. Apollo 16, the 5th lunar landing mission, landed in the Descartes Highlands for the first study of highlands area. Selected surface experiments were deployed, the ultraviolet camera/spectrograph was used for first time on the Moon, and the LRV was used for second time for a collection of 213 pounds of lunar material. The Apollo program came to a close with Apollo 17, the 6th and final manned lunar landing mission that landed in the Taurus-Littrow highlands and valley area. This mission hosted the first scientist-astronaut, Schmitt, to land on the Moon. The 6th automated research station was set up, and 243 ponds of lunar material was gathered using the LRV.

Study of Airline Computer Reservation Systems

DOT National Transportation Integrated Search

1988-05-01

The study addresses possible competitive issues concerning the five airline-owned computer reservation systems (SABRE, APOLLO, SYSTEMONE, PARS and DATAS II). The relationship of the fees charged by the vendor airlines to participating airlines and tr...

The structures of the SNM1A and SNM1B/Apollo nuclease domains reveal a potential basis for their distinct DNA processing activities.

PubMed

Allerston, Charles K; Lee, Sook Y; Newman, Joseph A; Schofield, Christopher J; McHugh, Peter J; Gileadi, Opher

2015-12-15

The human SNM1A and SNM1B/Apollo proteins are members of an extended family of eukaryotic nuclease containing a motif related to the prokaryotic metallo-β-lactamase (MBL) fold. SNM1A is a key exonuclease during replication-dependent and transcription-coupled interstrand crosslink repair, while SNM1B/Apollo is required for maintaining telomeric overhangs. Here, we report the crystal structures of SNM1A and SNM1B at 2.16 Å. While both proteins contain a typical MBL-β-CASP domain, a region of positive charge surrounds the active site of SNM1A, which is absent in SNM1B and explains the greater apparent processivity of SNM1A. The structures of both proteins also reveal a putative, wide DNA-binding groove. Extensive mutagenesis of this groove, coupled with detailed biochemical analysis, identified residues that did not impact on SNM1A catalytic activity, but drastically reduced its processivity. Moreover, we identified a key role for this groove for efficient digestion past DNA interstrand crosslinks, facilitating the key DNA repair reaction catalysed by SNM1A. Together, the architecture and dimensions of this groove, coupled to the surrounding region of high positive charge, explain the remarkable ability of SNM1A to accommodate and efficiently digest highly distorted DNA substrates, such as those containing DNA lesions. © The Author(s) 2015. Published by Oxford University Press on behalf of Nucleic Acids Research.

Vertical view Apollo 16 Descartes landing sites as photographed by Apollo 14

NASA Technical Reports Server (NTRS)

1972-01-01

An almost vertical view of the Apollo 16 Descartes landing sites as photographed from the Apollo 14 spacecraft. Overlays are provided to point out extravehicular activity (EVA), Lunar Roving Vehicle (LRV) travers routes and the nicknames of features. The Roman numerals indicate the EVA numbers and the Arabic numbers point out stations or traverse stops.

Apollo Project

NASA Image and Video Library

2012-09-07

Image L61-8036 is available as an electronic file from the photo lab. See URL. -- Photographed on 12/05/1961. -- Multiple exposure of an impact test of the Apollo command module. In this test the Apollo capsule was tested making a sand landing. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 361-366.

Apollo 11: A good ending to a bad decade

NASA Technical Reports Server (NTRS)

1979-01-01

The Gemini program and the Apollo program which culminated in landing a man on the moon and safely returning him to earth are highlighted. The space program in the aftermath of Apollo 11 is briefly summarized, including: Skylab, Apollo Soyuz, Mars and Venus probes, improved world communications, remote sensing of world resources, and finally, space shuttle.

Apollo 1 Lessons Learned Show

NASA Image and Video Library

2017-01-27

Ernie Reyes, retired, former Apollo 1 senior operations manager, signs a book for a worker after the Apollo 1 Lessons Learned presentation in the Training Auditorium at NASA's Kennedy Space Center in Florida. The theme of the program was "To there and Back Again." The event helped pay tribute to the Apollo 1 crew, Gus Grissom, Ed White II, and Roger Chaffee.

KSC-99pp0859

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- Former Apollo astronaut Gene Cernan makes a point during a presentation at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Cernan appeared with other former astronauts Neil Armstrong, the first man to walk on the moon; Edwin "Buzz" Aldrin; Walt Cunningham; and others

APOLLO XII - LAUNCH DAY ACTIVITIES - LAUNCH COMPLEX 39A - KSC

NASA Image and Video Library

1969-11-14

S69-58880 (14 Nov. 1969) --- Astronaut Alan L. Bean, Apollo 12 lunar module pilot, suits up in the Kennedy Space Center's (KSC) Manned Spacecraft Operations Building during the Apollo 12 prelaunch countdown. Minutes later astronauts Bean; Charles Conrad Jr., commander; and Richard F. Gordon Jr., command module pilot, rode a special transport van over to Pad A, Launch Complex 39, where their spacecraft awaited. The Apollo 12 liftoff occurred at 11:22 a.m. (EST), Nov. 14, 1969. Apollo 12 is the United States' second lunar landing mission.

Lightning around the Apollo 15 stack prior to launch

NASA Image and Video Library

1971-07-25

S89-41564 (25 July 1971) --- Lightning streaks through the sky around the Apollo 15 stack of hardware prior to the Apollo 15 launch. The huge 363-feet tall Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle is scheduled to launch from Pad A, Launch Complex 39, at 9:34:00:79 p.m. (EDT) on July 26, 1971. The prime crewmembers for the Apollo 15 mission are astronauts David R. Scott, commander; James B. Irwin, lunar module pilot; and Alfred M. Worden, command module pilot.

INFLIGHT - APOLLO 10 (CREW ACTIVITIES)

NASA Image and Video Library

1969-05-20

S69-34313 (20 May 1969) --- Astronaut Eugene A. Cernan is shown spinning a water bag to demonstrate the collection of hydrogen bubbles in this color reproduction taken from the fifth telecast made by the color television camera aboard the Apollo 10 spacecraft. When this picture was made the Apollo 10 spacecraft was approximately 175,300 nautical miles from Earth, and only 43,650 nautical miles from the moon. Cernan is the Apollo 10 lunar module pilot. Also, aboard Apollo 10 were astronauts Thomas P. Stafford, commander; and John W. Young, command module pilot.

KSC-2012-6140

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – The Astronaut Scholarship Foundation hosts a dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. An auction of space-related memorabilia was held with proceeds supporting college scholarships for students who exhibit imagination and exceptional performance in science, technology, engineering and math. The gala commemorating the anniversary of Apollo 17 included mission commander Eugene Cernan and other astronauts who flew Apollo missions. Launched Dec. 7, 1972, Cernan and lunar module pilot Harrison Schmitt landed in the moon's Taurus-Littrow highlands while command module pilot Ronald Evans remained in lunar orbit operating a scientific instrument module. For more information, visit http://www-pao.ksc.nasa.gov/history/apollo/apollo-17/apollo-17.htm Photo credit: NASA/Kim Shiflett

Phase Equilibrium Experiments on Potential Lunar Core Compositions: Extension of Current Knowledge to Multi-Component (Fe-Ni-Si-S-C) Systems

NASA Technical Reports Server (NTRS)

Righter, K.; Pando, K.; Danielson, L.

2014-01-01

Numerous geophysical and geochemical studies have suggested the existence of a small metallic lunar core, but the composition of that core is not known. Knowledge of the composition can have a large impact on the thermal evolution of the core, its possible early dynamo creation, and its overall size and fraction of solid and liquid. Thermal models predict that the current temperature at the core-mantle boundary of the Moon is near 1650 K. Re-evaluation of Apollo seismic data has highlighted the need for new data in a broader range of bulk core compositions in the PT range of the lunar core. Geochemical measurements have suggested a more volatile-rich Moon than previously thought. And GRAIL mission data may allow much better constraints on the physical nature of the lunar core. All of these factors have led us to determine new phase equilibria experimental studies in the Fe-Ni-S-C-Si system in the relevant PT range of the lunar core that will help constrain the composition of Moon's core.

Ares I Crew Launch Vehicle Upper Stage/Upper Stage Engine Element Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

The Ares I upper stage is an integral part of the Constellation Program transportation system. The upper stage provides guidance, navigation and control (GN and C) for the second stage of ascent flight for the Ares I vehicle. The Saturn-derived J-2X upper stage engine will provide thrust and propulsive impulse for the second stage of ascent flight for the Ares I launch vehicle. Additionally, the upper stage is responsible for the avionics system of the the entire Ares I. This brief presentation highlights the requirements, design, progress and production of the upper stage. Additionally, test facilities to support J-2X development are discussed and an overview of the operational and manufacturing flows are provided. Building on the heritage of the Apollo and Space Shuttle Programs, the Ares I Us and USE teams are utilizing extensive lessons learned to place NASA and the US into another era of space exploration. The NASA, Boeing and PWR teams are integrated and working together to make progress designing and building the Ares I upper stage to minimize cost, technical and schedule risks.

Systems concepts: Lectures on contemporary approaches to systems.

NASA Technical Reports Server (NTRS)

Miles, R. F., Jr.

1973-01-01

Collection of papers dealing with the application of systems concepts to a wide range of disciplines. The topics include systems definitions and designs, models for systems engineering, the evolution of the JPL, systems concepts in lunar and planetary projects, civil systems projects, and Apollo program evaluation. Individual items are announced in this issue.

Apollo Mission Techniques Lunar Orbit Activities - Part 1a

NASA Technical Reports Server (NTRS)

Interbartolo, Michael A.

2009-01-01

This slide presentation reviews the planned sequence of events and the rationale for all lunar missions, and the flight experiences and lessons learned for the lunar orbit activities from a trajectory perspective. Shown are trajectories which include the moon's position at the various stages in the complete trip from launch, to the return and reentry. Included in the presentation are objectives and the sequence of events,for the Apollo 8, and Apollo 10. This is followed by a discussion of Apollo 11, including: the primary mission objective, the sequence of events, and the flight experience. The next mission discussed was Apollo 12. It reviews the objectives, the ground tracking, procedure changes, and the sequence of events. The aborted Apollo 13 mission is reviewed, including the objectives, and the sequence of events. Brief summaries of the flight experiences for Apollo 14-16 are reviewed. The flight sequence of events of Apollo 17 are discussed. In summary each mission consistently performing precision landings required that Apollo lunar orbit activities devote considerable attention to: (1) Improving fidelity of lunar gravity models, (2) Maximizing availability of ground tracking, (3) Minimizing perturbations on the trajectory, (4) Maximizing LM propellant reserves for hover time. Also the use of radial separation maneuvers (1) allows passive re-rendezvous after each rev, but ... (2) sensitive to small dispersions in initial sep direction

Acquisition of an Integrated System for Laser-Assisted Non-Intrusive Experimentation and Data-Driven Reduced-Order Modeling

DTIC Science & Technology

2015-05-13

Tailored Metal Hydride and Innovative Reactor System for High Temperature Thermal Energy Storage” (DOE, APOLLO , FOA# DE-FOA-0001186, pending). Technology Transfer PERCENT_SUPPORTEDNAME FTE Equivalent: Total Number:

The Apollo Expericence Lessons Learned for Constellation Lunar Dust Management

NASA Astrophysics Data System (ADS)

Wagner, Sandra

2006-09-01

Lunar dust will present significant challenges to NASA's Lunar Exploration Missions. The challenges can be overcome by using best practices in system engineering design. For successful lunar surface missions, all systems that come into contact with lunar dust must consider the effects throughout the entire design process. Interfaces between all these systems with other systems also must be considered. Incorporating dust management into Concept of Operations and Requirements development are the best place to begin to mitigate the risks presented by lunar dust. However, that is only the beginning. To be successful, every person who works on NASA's Constellation lunar missions must be mindful of this problem. Success will also require fiscal responsibility. NASA must learn from Apollo the root cause of problems caused by dust, and then find the most cost-effective solutions to address each challenge. This will require a combination of common sense existing technologies and promising, innovative technical solutions

Artist concept illustrating key events on day by day basis during Apollo 9

NASA Technical Reports Server (NTRS)

1969-01-01

Artist concept illustrating key events on day by day basis during Apollo 9 mission. First photograph illustrates activities on the first day of the mission, including flight crew preparation, orbital insertion, 103 north mile orbit, separations, docking and docked Service Propulsion System Burn (19792); Second day events include landmark tracking, pitch maneuver, yaw-roll maneuver, and high apogee orbits (19793); Third day events include crew transfer and Lunar Module system evaluation (19794); Fourth day events include use of camera, day-night extravehicular activity, use of golden slippers, and television over Texas and Louisiana (19795); Fifth day events include vehicles undocked, Lunar Module burns for rendezvous, maximum separation, ascent propulsion system burn, formation flying and docking, and Lunar Module jettison ascent burn (19796); Sixth thru ninth day events include service propulsion system burns and landmark sightings, photograph special tests (19797); Tenth day events i

The Apollo Experience Lessons Learned for Constellation Lunar Dust Management

NASA Technical Reports Server (NTRS)

Wagner, Sandra

2006-01-01

Lunar dust will present significant challenges to NASA's Lunar Exploration Missions. The challenges can be overcome by using best practices in system engineering design. For successful lunar surface missions, all systems that come into contact with lunar dust must consider the effects throughout the entire design process. Interfaces between all these systems with other systems also must be considered. Incorporating dust management into Concept of Operations and Requirements development are the best place to begin to mitigate the risks presented by lunar dust. However, that is only the beginning. To be successful, every person who works on NASA's Constellation lunar missions must be mindful of this problem. Success will also require fiscal responsibility. NASA must learn from Apollo the root cause of problems caused by dust, and then find the most cost-effective solutions to address each challenge. This will require a combination of common sense existing technologies and promising, innovative technical solutions

Crystal growth from the vapor phase experiment MA-085

NASA Technical Reports Server (NTRS)

Wiedemeir, H.; Sadeek, H.; Klaessig, F. C.; Norek, M.

1976-01-01

Three vapor transport experiments on multicomponent systems were performed during the Apollo Soyuz mission to determine the effects of microgravity forces on crystal morphology and mass transport rates. The mixed systems used germanium selenide, tellurium, germanium tetraiodide (transport agent), germanium monosulfide, germanium tetrachloride (transport agent), and argon (inert atmosphere). The materials were enclosed in evacuated sealed ampoules of fused silica and were transported in a temperature gradient of the multipurpose electric furnace onboard the Apollo Soyuz spacecraft. Preliminary evaluation of 2 systems shows improved quality of space grown crystals in terms of growth morphology and bulk perfection. This conclusion is based on a direct comparison of space grown and ground based crystals by means of X-ray diffraction, microscopic, and chemical etching techniques. The observation of greater mass transport rates than predicted for a microgravity environment by existing vapor transport models indicates the existence of nongravity caused transport effects in a reactive solid/gas phase system.

Experiment S-213 selenocentric geodetic reference system

NASA Technical Reports Server (NTRS)

Doyle, F. J.; Elassal, A. A.; Lucas, J. R.

1976-01-01

Development and implementation of a photogrammetric system was undertaken to provide accurate selenodetic positions and topographic mapping of all areas overflown by orbital spacecraft. The system was installed in the scientific instrument module (SIM) bay of the Apollo command service module (CSM). In theory, this system provided everything a photogrammetrist could want: the position of each exposure station would be obtained from Earth-based tracking; the orientation of each photograph could be computed from the synchronized stellar exposure and the lock-angles determined by preflight calibration; and the scale of each stereomodel would be obtained directly from the altimeter data. Operationally, the data acquisition was adequate, but less than optimum. Systematic errors are believed to be the result of the primitive orbit determination procedures in use at the time of the Apollo 15 mission, inadequate models of the lunar gravity field, and spacecraft oscillations induced by uncoupled thrusting and various activities of the astronauts.

Astronaut Vance Brand seen in hatchway leading to Apollo Docking module

NASA Technical Reports Server (NTRS)

1975-01-01

Astronaut Vance D. Brand, command module pilot of the American Apollo Soyuz Test Project (ASTP) crew, is seen in the hatchway leading from the Apollo Command Module (CM) into the Apollo Docking Module (DM) during joint U.S.-USSR ASTP docking in Earth orbit mission. The 35mm camera is looking from the DM into the CM.

Air and Space Museum Apollo 40th Celebration

NASA Image and Video Library

2009-07-19

Guest, front row from right, U.S. Senator Bill Nelson (D-FL), Apollo 11 Command Module Pilot Michael Collins, U.S. Congresswoman Gabrielle Giffords (D-AZ), and Apollo 11 Lunar Module Pilot Buzz Aldrin, listen during the Apollo 40th anniversary celebration held at the National Air and Space Museum, Monday, July 20, 2009 in Washington. Photo Credit: (NASA/Bill Ingalls)

APOLLO XIII CREW - MISSION OPERATIONS CONTROL ROOM (MOCR) - APOLLO XII - LUNAR EXTRAVEHICULAR ACTIVITY (EVA) - MSC

NASA Image and Video Library

1969-11-21

S69-59525 (19 Nov. 1969) --- Overall view of activity in the Mission Operations Control Room (MOCR) in the Mission Control Center (MCC), Building 30, during the Apollo 12 lunar landing mission. When this picture was made the first Apollo 12 extravehicular activity (EVA) was being televised from the surface of the moon. Photo credit: NASA

Exploring the Moon: A Teacher's Guide with Activities for Earth and Space Sciences.

ERIC Educational Resources Information Center

National Aeronautics and Space Administration, Washington, DC.

This educational guide concerns exploring the moon. Activities are divided into three units: Pre-Apollo, Learning from Apollo, and The Future. These correspond, at least roughly, to exercises that can be done before the Lunar Sample Disk (available from NASA) arrives to the school (Pre-Apollo), while it is there (Learning from Apollo), and after…

President Obama Meets with Crew of Apollo 11

NASA Image and Video Library

2014-07-22

President Barack Obama meets with Apollo 11 astronauts Michael Collins, seated left, Buzz Aldrin, center, Carol Armstrong, widow of Apollo 11 commander, Neil Armstrong, and NASA Administrator Charles Bolden, Tuesday, July 22, 2014, in the Oval Office of the White House in Washington, during the 45th anniversary week of the Apollo 11 lunar landing. Photo Credit: (NASA/Bill Ingalls)

KSC-2011-1310

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Command module pilot of Apollo 9 and commander of Apollo 15 David Scott talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Photo credit: NASA/Kim Shiflett

KSC-2011-1314

NASA Image and Video Library

2011-01-29

CAPE CANAVERAL, Fla. -- Command module pilot of Apollo 9 and commander of Apollo 15 David Scott talks to attendees of the Apollo 14 Anniversary Soirée at the Kennedy Space Center Visitor Complex's Saturn V Center. The celebration was hosted by the Astronaut Scholarship Foundation. Apollo 14 landed on the lunar surface 40 years ago on Feb. 5, 1971. Photo credit: NASA/Kim Shiflett