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Image L66-9788 is available as an electronic file from the photo lab. See URL. -- Photographed on 11/30/66. -- A Lunar Orbiter II oblique view of Copernicus and the Carpathian Mountains.

Researcher checks model of Project Fire Reentry package to be tested in Unitary Plan Wind Tunnel. Project FIRE (Flight Investigation Reentry Environment) studied the effects of reentry heating on spacecraft materials. It involved both wind tunnel and flight tests, although the majority were tests with Atlas rockets and recoverable reentry packages. These flight tests took place at Cape Canaveral in Florida. Wind tunnel tests were made in several Langley tunnels including the Unitary Plan Wind Tunnel, the 8-foot High-Temperature Tunnel and the 9x6-Foot Thermal Structures Tunnel.

The Apollo Soyuz Test Project was conducted in 1975 between the United States and the Soviet Union. It was the first incident of cooperation between the two countries in space and had a resounding impact on political tensions between the countries in the middle of the Cold War. It also marked the end of the Space Race between the US and the USSR and offered a new outlook on the future of space travel and research. Now, for the first time ever, you can 3D print both the Apollo 18 Command Module and the Soyuz 19 spacecraft and dock them together yourself. Designed to scale with slight manipulation on each craft so that they can be joined together when printed.

Project Apollo - NASSP dumped using WikiTeam tools.

Results are presented of the frequency response test performed on the dynamic docking test system (DDTS) active table. Sinusoidal displacement commands were applied to the table and the dynamic response determined from measured actuator responses and accelerometers mounted to the table and one actuator.

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.

Stability analysis of Apollo attitude control during service propulsion thrusting

Evaluating land landing problem from prelaunch measured wind effects on launch escape vehicle aborts from Saturn 1B launch vehicle

Teasel Muir-Harmony, curator of the Apollo collection at the Smithsonian National Air and Space Museum, examined the history of Project Apollo (1961-75) and how the NASA program impacted American society and politics. This event took place at the Virginia Museum of History & Culture in Richmond, Virginia. Sponsor: Virginia Museum of History and Culture

Image L63-1164 is available as an electronic file from the photo lab. See URL. -- Photographed on 02/06/1963. -- Construction of the track which runs in front of Model 3: Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) Ellis J. White wrote in his paper "Discussion of Three Typical Langley Research Center Simulation Programs," "The model system is designed so that a television camera is mounted on a camera boom on each transport cart and each cart system is shared by two models. The cart's travel along the tracks represents longitudinal motion along the plane of a nominal orbit, vertical travel of the camera boom represents latitude on out-of-plane travel, and horizontal travel of the camera boom represents altitude changes." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, NASA SP-4308, p. 379; Ellis J. White, "Discussion of Three Typical Langley Research Center Simulation Programs," Paper presented at the Eastern Simulation Council (EAI's Princeton Computation Center), Princeton, NJ, October 20, 1966.

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.

Lunar Orbiter was essentially a flying camera. The payload structure was built around a pressurized shell holding Eastman Kodak's dual-imaging photographic system, which used a camera with wide-angle and telephoto lenses that could simultaneously take two kinds of pictures on the same film.

No Abstract Available

No Abstract Available

Apollo Soyuz Test Project ASTP, Soyuz-19, Docking End, Range = 23 Meters. Image taken on Revolution 57. Greenwich Mean Time GMT of Photo 200:12:31, Ground Elapsed Time GET 88:41. Altitude 222 km. Original Film Magazine: CX-11, Laboratory Roll 9; Camera Data: Hasselblad Reflex,70-mm, Module 500EL, NASA Modified; Film Data: 70-mm Ektachrome EF,Type QX-807, ASA=64 Laboratory Adjusted, 50mm Lens

Reduced Gravity Walking Simulator located in the hanger at Langley Research Center. The initial version of this simulator was located inside the hanger. Later a larger version would be located at the Lunar Landing Facility. The purpose of this simulator was to study the subject while walking, jumping or running. Researchers conducted studies of various factors such as fatigue limit, energy expenditure, and speed of locomotion. A.W. Vigil wrote in his paper "Discussion of Existing and Planned Simulators for Space Research," "When the astronauts land on the moon they will be in an unfamiliar environment involving, particularly, a gravitational field only one-sixth as strong as on earth. A novel method of simulating lunar gravity has been developed and is supported by a puppet-type suspension system at the end of a long pendulum. A floor is provided at the proper angle so that one-sixth of the subject's weight is supported by the floor with the remainder being supported by the suspension system. This simulator allows almost complete freedom in vertical translation and pitch and is considered to be a very realistic simulation of the lunar walking problem. For this problem this simulator suffers only slightly from the restrictions in lateral movement it puts on the test subject. This is not considered a strong disadvantage for ordinary walking problems since most of the motions do, in fact, occur in the vertical plane. However, this simulation technique would be severely restrictive if applied to the study of the extra-vehicular locomotion problem, for example, because in this situation complete six degrees of freedom are rather necessary. This technique, in effect, automatically introduces a two-axis attitude stabilization system into the problem. The technique could, however, be used in preliminary studies of extra-vehicular locomotion where, for example, it might be assumed that one axis of the attitude control system on the astronaut maneuvering unit may have failed." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, NASA SP-4308, p. 377; A.W. Vigil, "Discussion of Existing and Planned Simulators for Space Research," Paper presented at Conference on the Role of Simulation in Space Technology," Blacksburg, VA, August 17-21, 1964.

Lunar Landing Research Facility (LLRF) in operation.

Lunar landing test of the Lunar Excursion Module (LEM) at the Lunar Landing Research Facility (LLRF).

Donald Hewes at Lunar Landing Research Facility (LLRF).

The Lunar Orbiter spacecraft

Image L65-8009 is available as an electronic file from the photo lab. See URL. -- Photographed on 10/29/1965. -- 1/4 scale model of Apollo Heat Shield being prepared for testing. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 356.

Teasel Muir-Harmony, curator of the Apollo collection at the Smithsonian National Air and Space Museum, examined the history of Project Apollo (1961-75) and how the NASA program impacted American society and politics. This event took place at the Virginia Museum of History & Culture in Richmond, Virginia. Sponsor: Virginia Museum of History and Culture

This silent film footage shows a mobility test conducted as part of the Apollo program. It's unclear when it is from or where it was shot, but it likely dates to the early 1960s and the era of Lunar Module / Lunar Excursion Module design.The mock-up shown in the film might be the TM-1 mockup of the lunar module, built in 1964 out of wood by Grumman. What's also interesting is that it appears to be shown inside a mock-up of the Lunar Module Adapter. The film was simply marked "Seeman spacesuit." It's likely that the reference is to Jerome Seeman, a researcher who worked either at NASA or the USAF Aerospace Medical Research Laboratory at Wright Patterson AFB. It's possible the film documents a test performed under his guidance. The spacesuit shown in the film doesn't appear to be a spacesuit at all, but something more akin to a mock-up pressure suit with a helmet similar to those used by rocket fuel handlers and a dummy life support backpack. The film roughly shows how an astronaut might enter and exit a spacecraft. He is shown entering the simulated lunar lander (its thrusters are visible at 1:59). He climbs a ladder at 3:45 and enters a hatch at 5:40. At 9:15 he leaves the mock-up on a set of stairs. Motion picture films don't last forever; many have already been lost or destroyed. For almost two decades, we've worked to collect, scan and preserve the world as it was captured on 35mm, 16mm and 8mm movies -- including home movies, industrial films, and other non-fiction. If you have endangered films you'd like to have scanned, or wish to donate celluloid to Periscope Film so that we can share them with the world, we'd love to hear from you. Contact us via the weblink below. This film is part of the Periscope Film LLC archive, one of the largest historic military, transportation, and aviation stock footage collections in the USA. Entirely film backed, this material is available for licensing in 24p HD, 2k and 4k. For more information visit http://www.PeriscopeFilm.com

An early version of an Augmented Reality proposal for the "Apollo Beyond" project that centered around space science. Concept by Stephen Barker of Digital Frontiers Media and Song Speckels of Illustration4Hire, 2005.

An early version of an Augmented Reality proposal for the "Apollo Beyond" project that centered around space science. Concept by Stephen Barker of Digital Frontiers Media and Song Speckels of Illustration4Hire, 2005.

No Abstract Available

One of a series of films released by Hearst as part of the Screen News Digest series of educational movies, "The Apollo Project" provides an overview of the Apollo moon missions. Since the film predates the Apollo 11 landing on the Moon, the film features animated segments and speaks speculatively about certain aspects of the mission. The animation also contains some outmoded design elements, including the look of the Lunar Excursion Module. Opening titles: The Screen News Digest (:08) presented by the Philadelphia Evening Bulletin newspaper. Title: The Apollo Project (:40). Mighty Saturn V rocket at Cape Kennedy (:57). Mission Control (1:15). Lifelike animation illustrates the entire lunar journey and explains the rendezvous between the Lunar Module and Command Module (1:22). The mission of the Lunar Excursion Module or "bug" (2:11). Spacecraft on its course (2:31). Two of three astronauts will go into a smaller module to land on the moon while the third stays on the mothership (3:10). Landing on the moon (4:00). Walking on the moon (4:18). Leaving the moon's surface (4:29). Docking in space (4:41). Command Module heads back for Earth (5:05). The real Saturn V rocket shown on its massive transport vehicle (5:09). Saturn V on launchpad with liquid hydrogen tank nearby (5:50). Close on the Saturn V (6:20). Dr. Wernher Von Braun watches the launch through a periscope (6:37). Footage of the real Saturn V test - rocket has liftoff (6:48). Saturn V heads for space (7:11). Liquid hydrogen moves within the first stage of the huge rocket (7:38). First stage reaches 6000 mph (8:11). Rocket continues onward (8:37). Second stage (8:54). Animation of the rocket orbiting (9:18). Heat shield on the capsule (9:48). Parachutes help the capsule have a smooth descent once back in earth's atmosphere (10:06). Helicopter goes to retrieve the capsule that floats (10:36). Capsule brought onboard a ship (11:31). Capsule recovered (11:57). President of the USA, John F. Kennedy speaks about the ambitious project, "this nation should commit itself to the goal of landing a man on the Moon and returning him to Earth...". (12:03). Saturn V rocket lifts off (12:23). Rocket in the sky (12:52). End credits (13:02). We encourage viewers to add comments and, especially, to provide additional information about our videos by adding a comment! See something interesting? Tell people what it is and what they can see by writing something for example: "01:00:12:00 -- President Roosevelt is seen meeting with Winston Churchill at the Quebec Conference." This film is part of the Periscope Film LLC archive, one of the largest historic military, transportation, and aviation stock footage collections in the USA. Entirely film backed, this material is available for licensing in 24p HD, 2k and 4k. For more information visit http://www.PeriscopeFilm.com

Made prior to the mission and featuring cosmonauts Alexey Leonov and Valerie Kubasov and astronaut Deke Slaton, this film presents an overview of the Apollo–Soyuz Test Project.  This mission was conducted in July 1975 and was the first joint U.S.–Soviet space flight, and the last flight of an Apollo spacecraft. Its primary purpose was as a symbol of the policy of détente that the two superpowers were pursuing at the time, and marked the end of the Space Race between them that began in 1957. The mission included both joint and separate scientific experiments (including an engineered eclipse of the Sun by Apollo to allow Soyuz to take photographs of the solar corona), and provided useful engineering experience for future joint US–Russian space flights, such as the Shuttle–Mir Program and the International Space Station. ASTP was the last manned US space mission until the first Space Shuttle flight in April 1981. It was also U.S. astronaut Donald "Deke" Slayton's only space flight. He was chosen as one of the original Mercury Seven astronauts in April 1959, but had been grounded until 1972 for medical reasons. This film is part of the Periscope Film LLC archive, one of the largest historic military, transportation, and aviation stock footage collections in the USA. Entirely film backed, this material is available for licensing in 24p HD and 2k. For more information visit http://www.PeriscopeFilm.com

Made prior to the mission and featuring cosmonauts Alexey Leonov and Valerie Kubasov and astronaut Deke Slaton, this film presents an overview of the Apollo–Soyuz Test Project.  This mission was conducted in July 1975 and was the first joint U.S.–Soviet space flight, and the last flight of an Apollo spacecraft. Its primary purpose was as a symbol of the policy of détente that the two superpowers were pursuing at the time, and marked the end of the Space Race between them that began in 1957. The mission included both joint and separate scientific experiments (including an engineered eclipse of the Sun by Apollo to allow Soyuz to take photographs of the solar corona), and provided useful engineering experience for future joint US–Russian space flights, such as the Shuttle–Mir Program and the International Space Station. ASTP was the last manned US space mission until the first Space Shuttle flight in April 1981. It was also U.S. astronaut Donald "Deke" Slayton's only space flight. He was chosen as one of the original Mercury Seven astronauts in April 1959, but had been grounded until 1972 for medical reasons. This film is part of the Periscope Film LLC archive, one of the largest historic military, transportation, and aviation stock footage collections in the USA. Entirely film backed, this material is available for licensing in 24p HD and 2k. For more information visit http://www.PeriscopeFilm.com

This video shows footage of the ground support team tracking Apollo 11's progress on its way to the Moon.

Cable system which supports the test subject on the Reduced Gravity Walking Simulator. The purpose of this simulator was to study the subject while walking, jumping or running. Researchers conducted studies of various factors such as fatigue limit, energy expenditure, and speed of locomotion. A.W. Vigil described the purpose of the simulator as follows: "When the astronauts land on the moon they will be in an unfamiliar environment involving, particularly, a gravitational field only one-sixth as strong as on earth. A novel method of simulating lunar gravity has been developed and is supported by a puppet-type suspension system at the end of a long pendulum. A floor is provided at the proper angle so that one-sixth of the subject's weight is supported by the floor with the remainder being supported by the suspension system. This simulator allows almost complete freedom in vertical translation and pitch and is considered to be a very realistic simulation of the lunar walking problem. For this problem this simulator suffers only slightly from the restrictions in lateral movement it puts on the test subject. This is not considered a strong disadvantage for ordinary walking problems since most of the motions do, in fact, occur in the vertical plane. However, this simulation technique would be severely restrictive if applied to the study of the extra-vehicular locomotion problem, for example, because in this situation complete six degrees of freedom are rather necessary. This technique, in effect, automatically introduces a two-axis attitude stabilization system into the problem. The technique could, however, be used in preliminary studies of extra-vehicular locomotion where, for example, it might be assumed that one axis of the attitude control system on the astronaut maneuvering unit may have failed." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995); A.W. Vigil, "Discussion of Existing and Planned Simulators for Space Research," Paper presented at Conference on the Role of Simulation in Space Technology," Blacksburg, VA, August 17-21, 1964.

This video shows footage of ground control when the Apollo 11 spacecraft is recovered from its water landing.

Image L64-11454 is available as an electronic file from the photo lab. See URL. -- Photographed on 12/14/1964. -- The lunar module design underwent gradual evolution from the first configuration proposed by Grumman in 1962. This model is the 1964 version. Langley had the task of building a simulator for the astronauts to practice lunar landings. The configuration of the initial vehicle used with the Lunar Landing Research Facility (LLRF) was changed in 1967 to more accurately reflect the standing position of the astronauts, cockpit arrangement, instrumentation, controls and field of view.

Originally the Rendezvous was used by the astronauts preparing for Gemini missions. The Rendezvous Docking Simulator was then modified and used to develop docking techniques for the Apollo program. By 1966, it was noted by A.W. Vogeley (in the paper cited below) that: "since emphasis on space docking is decreasing, the facility is being modified to serve as a closed-circuit TV carriage. It will view an HO-scale model of a Kennedy Airport runway in the study of Category II (break-out at 100 feet) landing problems. This simulation technique is considered adequate in this case because of the large model-scale and because visibility under Category II conditions is often rather poor. Peripheral vision will also be supplied in these studies (which is not generally the case) - an important requirement, particularly where rapid decisions (upon break-out) must be made." This last simulation application is shown as it was displayed for a public open house at Langley Research Center. From A.W. Vogeley, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966. "The Rendezvous Docking Simulator and also the Lunar Landing Research Facility are both rather large moving-base simulators. It should be noted, however, that neither was built primarily because of its motion characteristics. The main reason they were built was to provide a realistic visual scene. A secondary reason was that they would provide correct angular motion cues (important in control of vehicle short-period motions) even though the linear acceleration cues would be incorrect.

Special "space" suit for the Reduced Gravity Walking Simulator located at the Lunar Landing Facility. The purpose of this simulator was to study the subject while walking, jumping or running. Researchers conducted studies of various factors such as fatigue limit, energy expenditure, and speed of locomotion. A.W. Vigil described the purpose of the simulator in his paper "Discussion of Existing and Planned Simulators for Space Research," "When the astronauts land on the moon they will be in an unfamiliar environment involving, particularly, a gravitational field only one-sixth as strong as on earth. A novel method of simulating lunar gravity has been developed and is supported by a puppet-type suspension system at the end of a long pendulum. A floor is provided at the proper angle so that one-sixth of the subject's weight is supported by the floor with the remainder being supported by the suspension system. This simulator allows almost complete freedom in vertical translation and pitch and is considered to be a very realistic simulation of the lunar walking problem. For this problem this simulator suffers only slightly from the restrictions in lateral movement it puts on the test subject. This is not considered a strong disadvantage for ordinary walking problems since most of the motions do, in fact, occur in the vertical plane. However, this simulation technique would be severely restrictive if applied to the study of the extra-vehicular locomotion problem, for example, because in this situation complete six degrees of freedom are rather necessary. This technique, in effect, automatically introduces a two-axis attitude stabilization system into the problem. The technique could, however, be used in preliminary studies of extra-vehicular locomotion where, for example, it might be assumed that one axis of the attitude control system on the astronaut maneuvering unit may have failed." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 377; A.W. Vigil, "Discussion of Existing and Planned Simulators for Space Research," Paper presented at Conference on the Role of Simulation in Space Technology," Blacksburg, VA, August 17-21, 1964.

Test subject wearing the pressurized "space" suit for the Reduced Gravity Walking Simulator located at the Lunar Landing Facility. The purpose of this simulator was to study the subject while walking, jumping or running. Researchers conducted studies of various factors such as fatigue limit, energy expenditure, and speed of locomotion. A.W. Vigil described the purpose of the simulator in his paper "Discussion of Existing and Planned Simulators for Space Research," "When the astronauts land on the moon they will be in an unfamiliar environment involving, particularly, a gravitational field only one-sixth as strong as on earth. A novel method of simulating lunar gravity has been developed and is supported by a puppet-type suspension system at the end of a long pendulum. A floor is provided at the proper angle so that one-sixth of the subject's weight is supported by the floor with the remainder being supported by the suspension system. This simulator allows almost complete freedom in vertical translation and pitch and is considered to be a very realistic simulation of the lunar walking problem. For this problem this simulator suffers only slightly from the restrictions in lateral movement it puts on the test subject. This is not considered a strong disadvantage for ordinary walking problems since most of the motions do, in fact, occur in the vertical plane. However, this simulation technique would be severely restrictive if applied to the study of the extra-vehicular locomotion problem, for example, because in this situation complete six degrees of freedom are rather necessary. This technique, in effect, automatically introduces a two-axis attitude stabilization system into the problem. The technique could, however, be used in preliminary studies of extra-vehicular locomotion where, for example, it might be assumed that one axis of the attitude control system on the astronaut maneuvering unit may have failed." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 377; A.W. Vigil, "Discussion of Existing and Planned Simulators for Space Research," Paper presented at Conference on the Role of Simulation in Space Technology," Blacksburg, VA, August 17-21, 1964.

Images L63-2988 and L63-2989 are available as an electronic files from the photo lab. See URL. -- Photographed on 04/08/1963. -- Construction of the Lunar Landing Research Facility. James Hansen noted that "it was conceived in 1962 by engineer Donald Hewes and built under the careful direction of his quiet but ingenious division chief, W. Hewitt Phillips, this gigantic facility designed to develop techniques for landing the rocket-powered LEM on the moon's surface." (p. 373) A.W. Vigil wrote in his paper "Piloted Space-Flight Simulation at Langley Research Center," "Ground-based simulators are not very satisfactory for studying the problems associated with the final phases of landing. This is due primarily to the fact that the visual scene cannot be simulated with sufficient realism. For this reason it is preferable to go to some sort of flight-test simulator which can provide real-life visual cues. One research facility designed to study the final phases of lunar landing is in operation at Langley. ... The facility is an overhead crane structure about 250 feet tall and 400 feet long. The crane system supports five-sixths of the vehicle's weight through servo-driven vertical cables. The remaining one-sixth of the vehicle weight pulls the vehicle downward simulating the lunar gravitational force. During actual flights the overhead crane system is slaved to keep the cable near vertical at all times. A gimbal system on the vehicle permits angular freedom for pitch, roll, and yaw. The facility is capable of testing vehicles up to 20,000 pounds. A research vehicle, weighing 10,500 pounds fully loaded, is being used and is shown [in this picture]. This vehicle is provided with a large degree of flexibility in cockpit positions, instrumentation, and control parameters. It has main engines of 6,000 pounds thrust, throttle able down to 600 pounds, and attitude jets. This facility is studying the problems of the final 200 feet of lunar landing and the problems of maneuvering about in close proximity to the lunar surface." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 373-378; A.W. Vigil, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

Lunar orbit insertion abort procedures for hybrid lunar missions

The Apollo 11, 12, and 14 through 17 missions orbited and landed on the Moon, carrying scientific instruments that returned data from all phases of the missions, included long-lived Apollo Lunar Surface Experiments Packages (ALSEPs) deployed by the astronauts on the lunar surface. Much of these data were never archived, and some of the archived data were on media and in formats that are outmoded, or were deposited with little or no useful documentation to aid outside users. This is particularly true of the ALSEP data returned autonomously for many years after the Apollo missions ended. The purpose of the Lunar Data Project and the Planetary Data System (PDS) Lunar Data Node is to take data collections already archived at the NASA Space Science Data Coordinated Archive (NSSDCA) and prepare them for archiving through PDS, and to locate lunar data that were never archived, bring them into NSSDCA, and then archive them through PDS. Preparing these data for archiving involves reading the data from the original media, be it magnetic tape, microfilm, microfiche, or hard-copy document, converting the outmoded, often binary, formats when necessary, putting them into a standard digital form accepted by PDS, collecting the necessary ancillary data and documentation (metadata) to ensure that the data are usable and well-described, summarizing the metadata in documentation to be included in the data set, adding other information such as references, mission and instrument descriptions, contact information, and related documentation, and packaging the results in a PDS-compliant data set. The data set is then validated and reviewed by a group of external scientists as part of the PDS final archive process. We present a status report on some of the data sets that we are processing.

It has been just over 40 years since the fulfillment of President John F. Kennedys goal of landing a man on the moon and returning him safely to the earth. As we reflect on this technological triumph, we find numerous examples of acquisition best practices and lessons learned, many of which are manifest in our current DoD acquisition management system.From its earliest stages, the U.S. space program pioneered and implemented many innovative ideas and best practicesoften out of necessityand many of those ideas have evolved and are now common tenets of todays defense acquisition practices.

No Description

A prelaunch press conference shows the crewmembers of Apollo 11, Commander Neil A. Armstrong, Lunar Module Pilot Edwin E. Aldrin, Jr., and Command Module Pilot Michael Collins, answering questions about their upcoming mission this section has sound, the rest of the video is without sound. Footage is seen of the crew during training for the extravehicular activity portion of the mission and using the flight simulator.

100th Research flight at Lunar Landing Research Facility (LLRF).

Originally the Rendezvous was used by the astronauts preparing for Gemini missions. The Rendezvous Docking Simulator was then modified and used to develop docking techniques for the Apollo program. This picture shows a later configuration of the Apollo docking with the LEM target. A.W. Vogeley described the simulator as follows: "The Rendezvous Docking Simulator and also the Lunar Landing Research Facility are both rather large moving-base simulators. It should be noted, however, that neither was built primarily because of its motion characteristics. The main reason they were built was to provide a realistic visual scene. A secondary reason was that they would provide correct angular motion cues (important in control of vehicle short-period motions) even though the linear acceleration cues would be incorrect." Published in A.W. Vogeley, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

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.

The electrophoresis of six columns was accomplished on the Apollo-Soyuz test Project. After separation, these columns were frozen in orbit and were returned for ground-based analyses. One major goal of the MA-011 experiment was the assessment of the separation achieved in orbit by slicing these frozen columns. The slicing of the frozen columns required a new device. The development of that device is described.

Requirements for antennas, radio and terminal equipment aboard Apollo communication and tracking ships to communicate with land stations by satellite relay

No abstract available

Evaluation of ablation heat shield material incorporating electrical connectors

Project Apollo - NASSP dumped with wikiteam3 tools.