Guidance Concept for a Mars Ascent Vehicle First Stage

NASA Technical Reports Server (NTRS)

Queen, Eric M.

2000-01-01

This paper presents a guidance concept for use on the first stage of a Mars Ascent Vehicle (MAV). The guidance is based on a calculus of variations approach similar to that used for the final phase of the Apollo Earth return guidance. A three degree-of-freedom (3DOF) Monte Carlo simulation is used to evaluate performance and robustness of the algorithm.

Unified powered flight guidance

NASA Technical Reports Server (NTRS)

Brand, T. J.; Brown, D. W.; Higgins, J. P.

1973-01-01

A complete revision of the orbiter powered flight guidance scheme is presented. A unified approach to powered flight guidance was taken to accommodate all phases of exo-atmospheric orbiter powered flight, from ascent through deorbit. The guidance scheme was changed from the previous modified version of the Lambert Aim Point Maneuver Mode used in Apollo to one that employs linear tangent guidance concepts. This document replaces the previous ascent phase equation document.

Entry Guidance for the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; Craig, Lynn E.

2011-01-01

The 2011 Mars Science Laboratory will be the first Mars mission to attempt a guided entry to safely deliver the rover to a touchdown ellipse of 25 km x 20 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented.

Post-Flight EDL Entry Guidance Performance of the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2013-01-01

The 2011 Mars Science Laboratory was the first Mars guided entry which safely delivered the rover to a landing within a touchdown ellipse of 19.1 km x 6.9 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. The guided entry performed as designed without any significant exceptions. The Curiosity rover was delivered about 2.2 km from the expected touchdown. This miss distance is attributed to little time to correct the downrange drift from the final bank reversal and a suspected tailwind during heading alignment. The successful guided entry for the Mars Science Laboratory lays the foundation for future Mars missions to improve upon.

Apollo

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

Beckingsal, David; Gamblin, Todd

Modern performance portability frameworks provide application developers with a flexible way to determine how to run application kernels, however, they provide no guidance as to the best configuration for a given kernel. Apollo provides a model-generation framework that, when integrated with the RAJA library, uses lightweight decision tree models to select the fastest execution configuration on a per-kernel basis

Development of an analytical guidance algorithm for lunar descent

NASA Astrophysics Data System (ADS)

Chomel, Christina Tvrdik

In recent years, NASA has indicated a desire to return humans to the moon. With NASA planning manned missions within the next couple of decades, the concept development for these lunar vehicles has begun. The guidance, navigation, and control (GN&C) computer programs that will perform the function of safely landing a spacecraft on the moon are part of that development. The lunar descent guidance algorithm takes the horizontally oriented spacecraft from orbital speeds hundreds of kilometers from the desired landing point to the landing point at an almost vertical orientation and very low speed. Existing lunar descent GN&C algorithms date back to the Apollo era with little work available for implementation since then. Though these algorithms met the criteria of the 1960's, they are cumbersome today. At the basis of the lunar descent phase are two elements: the targeting, which generates a reference trajectory, and the real-time guidance, which forces the spacecraft to fly that trajectory. The Apollo algorithm utilizes a complex, iterative, numerical optimization scheme for developing the reference trajectory. The real-time guidance utilizes this reference trajectory in the form of a quartic rather than a more general format to force the real-time trajectory errors to converge to zero; however, there exist no guarantees under any conditions for this convergence. The proposed algorithm implements a purely analytical targeting algorithm used to generate two-dimensional trajectories "on-the-fly"' or to retarget the spacecraft to another landing site altogether. It is based on the analytical solutions to the equations for speed, downrange, and altitude as a function of flight path angle and assumes two constant thrust acceleration curves. The proposed real-time guidance algorithm has at its basis the three-dimensional non-linear equations of motion and a control law that is proven to converge under certain conditions through Lyapunov analysis to a reference trajectory formatted as a function of downrange, altitude, speed, and flight path angle. The two elements of the guidance algorithm are joined in Monte Carlo analysis to prove their robustness to initial state dispersions and mass and thrust errors. The robustness of the retargeting algorithm is also demonstrated.

Astronomical activities of the Apollo orbital science photographic team

NASA Technical Reports Server (NTRS)

Mercer, R. D.

1974-01-01

A partial accounting of Apollo Orbital Science Photographic Team (APST) work is presented as reported by one of its members who provided scientific recommendations for, guidance in, and reviews of photography in astronomy. Background on the formation of the team and its functions and management are discussed. It is concluded that the APST clearly performed the overall objective for which it was established - to improve the scientific value of the Apollo lunar missions. Specific reasons for this success are given.

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.

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.

Saturn Apollo Program

NASA Image and Video Library

2004-04-15

This undated chart provides a description of the Saturn IB and Saturn V's Instrument Unit (IU) and its major components. Designed by NASA at the Marshall Space Flight Center (MSFC), the Instrument Unit, sandwiched between the S-IVB stage and the Apollo spacecraft, served as the Saturn's "nerve center" providing guidance and control, command and sequence of vehicle functions, telemetry, and environmental control.

MSL EDL Entry Guidance using the Entry Terminal Point Controller

NASA Technical Reports Server (NTRS)

2006-01-01

The Mars Science Laboratory will be the first Mars mission to attempt a guided entry with the objective of safely delivering the entry vehicle to a survivable parachute deploy state within 10 km of the pre-designated landing site. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control range based on deviations in range, altitude rate, and drag acceleration from a reference trajectory. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last four years. Performance tradeoffs between ellipse size and deploy altitude will be presented, along with imposed constraints of entry acceleration and heating. Performance sensitivities to the bank reversal deadbands, heading alignment, attitude initialization error, and atmospheric delivery errors are presented. Guidance settings for contingency operations, such as those appropriate for severe dust storm scenarios, are evaluated.

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)

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 experience report guidance and control systems: Lunar module abort guidance system

NASA Technical Reports Server (NTRS)

Kurten, P. M.

1975-01-01

The history of a unique development program that produced an operational fixed guidance system of inertial quality is presented. Each phase of development, beginning with requirement definition and concluding with qualification and testing, is addressed, and developmental problems are emphasized. Software generation and mission operations are described, and specifications for the inertial reference unit are included, as are flight performance results. Significant program observations are noted.

Apollo 14 visibility tests: Visibility of lunar surface features and lunar landing

NASA Technical Reports Server (NTRS)

Ziedman, K.

1972-01-01

An in-flight visibility test conducted on the Apollo 14 mission is discussed. The need for obtaining experimental data on lunar feature visibility arose from visibility problems associated with various aspects of the Apollo missions; and especially from anticipated difficulties of recognizing lunar surface features at the time of descent and landing under certain illumination conditions. Although visibility problems have influenced many other aspects of the Apollo mission, they have been particularly important for descent operations, due to the criticality of this mission phase and the crew's guidance and control role for landing site recognition and touchdown point selection. A series of analytical and photographic studies were conducted during the Apollo program (prior to as well as after the initial manned lunar operations) to delineate constraints imposed on landing operations by visibility limitations. The purpose of the visibility test conducted on Apollo 14 was to obtain data to reduce uncertainties and to extend the analytical models of visibility in the lunar environment.

Apollo Guidance, Navigation, and Control (GNC) Hardware Overview

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

This viewgraph presentation reviews basic guidance, navigation and control (GNC) concepts, examines the Command and Service Module (CSM) and Lunar Module (LM) GNC organization and discusses the primary GNC and the CSM Stabilization and Control System (SCS), as well as other CSM-specific hardware. The LM Abort Guidance System (AGS), Control Electronics System (CES) and other LM-specific hardware are also addressed. Three subsystems exist on each vehicle: the computer subsystem (CSS), the inertial subsystem (ISS) and the optical subsystem (OSS). The CSS and ISS are almost identical between CSM and LM and each is designed to operate independently. CSM SCS hardware are highlighted, including translation control, rotation controls, gyro assemblies, a gyro display coupler and flight director attitude indicators. The LM AGS hardware are also highlighted and include the abort electronics assembly and the abort sensor assembly; while the LM CES hardware includes the attitude controller assembly, thrust/translation controller assemblies and the ascent engine arming assemble. Other common hardware including the Orbital Rate Display - Earth and Lunar (ORDEAL) and the Crewman Optical Alignment Sight (COAS), a docking aid, are also highlighted.

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 Onboard Navigation Techniques

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

This viewgraph presentation reviews basic navigation concepts, describes coordinate systems and identifies attitude determination techniques including Primary Guidance, Navigation and Control System (PGNCS) IMU management and Command and Service Module Stabilization and Control System/Lunar Module (LM) Abort Guidance System (AGS) attitude management. The presentation also identifies state vector determination techniques, including PGNCS coasting flight navigation, PGNCS powered flight navigation and LM AGS navigation.

Apollo 15 mission report: Apollo 15 guidance, navigation, and control system performance analysis report (supplement 1)

NASA Technical Reports Server (NTRS)

1972-01-01

This report contains the results of additional studies which were conducted to confirm the conclusions of the MSC Mission Report and contains analyses which were not completed in time to meet the mission report deadline. The LM IMU data were examined during the lunar descent and ascent phases. Most of the PGNCS descent absolute velocity error was caused by platform misalignments. PGNCS radial velocity divergence from AGS during the early part of descent was partially caused by PGNCS gravity computation differences from AGS. The remainder of the differences between PGNCS and AGS velocity were easily attributable to attitude reference alignment differences and tolerable instrument errors. For ascent the PGNCS radial velocity error at insertion was examined. The total error of 10.8 ft/sec was well within mission constraints but larger than expected. Of the total error, 2.30 ft/sec was PIPA bias error, which was suspected to exist pre-lunar liftoff. The remaining 8.5 ft/sec is most probably satisified with a large pre-liftoff planform misalignment.

Job-mix modeling and system analysis of an aerospace multiprocessor.

NASA Technical Reports Server (NTRS)

Mallach, E. G.

1972-01-01

An aerospace guidance computer organization, consisting of multiple processors and memory units attached to a central time-multiplexed data bus, is described. A job mix for this type of computer is obtained by analysis of Apollo mission programs. Multiprocessor performance is then analyzed using: 1) queuing theory, under certain 'limiting case' assumptions; 2) Markov process methods; and 3) system simulation. Results of the analyses indicate: 1) Markov process analysis is a useful and efficient predictor of simulation results; 2) efficient job execution is not seriously impaired even when the system is so overloaded that new jobs are inordinately delayed in starting; 3) job scheduling is significant in determining system performance; and 4) a system having many slow processors may or may not perform better than a system of equal power having few fast processors, but will not perform significantly worse.

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.

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.

A Triangular Teaching Process: Using Mass Communication as a Media to Integrate Vocational and Academic Curricula through Cooperative Efforts of a Public High School, a Vocational School, and a Four Year College. Final Report.

ERIC Educational Resources Information Center

List, Frank A.

In order to offer students guidance about the rapidly increasing field of communications, Apollo High School developed a cooperative radio and television communication program to be added to the English curriculum. The objectives of the project were (1) to utilize the expertise of the staff and the resources of Apollo High School, the Daviess…

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.

Apollo guidance, navigation and control: Guidance system operations plan for manned CM earth orbital and lunar missions using Program COLOSSUS 3. Section 3: Digital autopilots (revision 14)

NASA Technical Reports Server (NTRS)

1972-01-01

Digital autopilots for the manned command module earth orbital and lunar missions using program COLOSSUS 3 are discussed. Subjects presented are: (1) reaction control system digital autopilot, (2) thrust vector control autopilot, (3) entry autopilot and mission control programs, (4) takeover of Saturn steering, and (5) coasting flight attitude maneuver routine.

PredGuid+A: Orion Entry Guidance Modified for Aerocapture

NASA Technical Reports Server (NTRS)

Lafleur, Jarret

2013-01-01

PredGuid+A software was developed to enable a unique numerical predictor-corrector aerocapture guidance capability that builds on heritage Orion entry guidance algorithms. The software can be used for both planetary entry and aerocapture applications. Furthermore, PredGuid+A implements a new Delta-V minimization guidance option that can take the place of traditional targeting guidance and can result in substantial propellant savings. PredGuid+A allows the user to set a mode flag and input a target orbit's apoapsis and periapsis. Using bank angle control, the guidance will then guide the vehicle to the appropriate post-aerocapture orbit using one of two algorithms: Apoapsis Targeting or Delta-V Minimization (as chosen by the user). Recently, the PredGuid guidance algorithm was adapted for use in skip-entry scenarios for NASA's Orion multi-purpose crew vehicle (MPCV). To leverage flight heritage, most of Orion's entry guidance routines are adapted from the Apollo program.

Saturn Apollo Program

NASA Image and Video Library

1967-10-01

This is a view of the Saturn V instrument unit (IU) being manufactured in the east high bay 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.

Programmable Logic Application Notes

NASA Technical Reports Server (NTRS)

Katz, Richard

2000-01-01

This column will be provided each quarter as a source for reliability, radiation results, NASA capabilities, and other information on programmable logic devices and related applications. This quarter will continue a series of notes concentrating on analysis techniques with this issue's section discussing: Digital Timing Analysis Tools and Techniques. Articles in this issue include: SX and SX-A Series Devices Power Sequencing; JTAG and SXISX-AISX-S Series Devices; Analysis Techniques (i.e., notes on digital timing analysis tools and techniques); Status of the Radiation Hard reconfigurable Field Programmable Gate Array Program, Input Transition Times; Apollo Guidance Computer Logic Study; RT54SX32S Prototype Data Sets; A54SX32A - 0.22 micron/UMC Test Results; Ramtron FM1608 FRAM; and Analysis of VHDL Code and Synthesizer Output.

Faster Finances

NASA Technical Reports Server (NTRS)

1976-01-01

TRW has applied the Apollo checkout procedures to retail-store and bank-transaction systems, as well as to control systems for electric power transmission grids -- reducing the chance of power blackouts. Automatic checkout equipment for Apollo Spacecraft is one of the most complex computer systems in the world. Used to integrate extensive Apollo checkout procedures from manufacture to launch, it has spawned major advances in computer systems technology. Store and bank credit system has caused significant improvement in speed and accuracy of transactions, credit authorization, and inventory control. A similar computer service called "Validata" is used nationwide by airlines, airline ticket offices, car rental agencies, and hotels.

Improved Lunar Lander Handling Qualities Through Control Response Type and Display Enhancements

NASA Technical Reports Server (NTRS)

Mueller, Eric Richard; Bilimoria, Karl D.; Frost, Chad Ritchie

2010-01-01

A piloted simulation that studied the handling qualities for a precision lunar landing task from final approach to touchdown is presented. A vehicle model based on NASA's Altair Lunar Lander was used to explore the design space around the nominal vehicle configuration to determine which combination of factors provides satisfactory pilot-vehicle performance and workload; details of the control and propulsion systems not available for that vehicle were derived from Apollo Lunar Module data. The experiment was conducted on a large motion base simulator. Eight Space Shuttle and Apollo pilot astronauts and three NASA test pilots served as evaluation pilots, providing Cooper-Harper ratings, Task Load Index ratings and qualitative comments. Each pilot flew seven combinations of control response types and three sets of displays, including two varieties of guidance and a nonguided approach. The response types included Rate Command with Attitude Hold, which was used in the original Apollo Moon landings, a Velocity Increment Command response type designed for up-and-away flight, three response types designed specifically for the vertical descent portion of the trajectory, and combinations of these. It was found that Velocity Increment Command significantly improved handling qualities when compared with the baseline Apollo design, receiving predominantly Level 1 ratings. This response type could be flown with or without explicit guidance cues, something that was very difficult with the baseline design, and resulted in approximately equivalent touchdown accuracies and propellant burn as the baseline response type. The response types designed to be used exclusively in the vertical descent portion of the trajectory did not improve handling qualities.

Gravity measured at the apollo 14 lading site.

PubMed

Nance, R L

1971-12-03

The gravity at the Apollo 14 landing site has been determined from the accelerometer data that were telemetered from the lunar module. The values for the lunar gravity measured at the Apollo 11, 12, and 14 sites were reduced to a common elevation and were then compared between sites. A theoretical gravity, based on the assumption of a spherical moon, was computed for each landing site and compared with the observed value. The observed gravity was also used to compute the lunar radius at each landing site.

Experimental and simulation study results of an Adaptive Video Guidance System /AVGS/

NASA Technical Reports Server (NTRS)

Schappell, R. T.; Knickerbocker, R. L.

1975-01-01

Studies relating to stellar-body exploration programs have pointed out the need for an adaptive guidance scheme capable of providing automatic real-time guidance and site selection capability. For the case of a planetary lander, without such guidance, targeting is limited to what are believed to be generally benign areas in order to ensure a reasonable landing-success probability. Typically, the Mars Viking Lander will be jeopardized by obstacles exceeding 22 centimers in diameter. The benefits of on-board navigation and real-time selection of a landing site and obstacle avoidance have been demonstrated by the Apollo lunar landings, in which man performed the surface sensing and steering functions. Therefore, an Adaptive Video Guidance System (AVGS) has been developed, bread-boarded, and flown on a six-degree-of-freedom simulator.

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.

Post-Flight EDL Entry Guidance Performance of the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2012-01-01

The 2011 Mars Science Laboratory was the first successful Mars mission to attempt a guided entry which safely delivered the rover to a final position approximately 2 km from its target within a touchdown ellipse of 19.1 km x 6.9 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented. Just prior to the entry and landing of MSL in August 2012, the EDL team examined minute tuning of the reference trajectory for the selected landing site, analyzed whether adjustment of bank reversal deadbands were necessary, the heading alignment velocity trigger was in union with other parameters to balance the EDL risks, and the vertical L/D command limits. This paper details a preliminary postflight assessment of the telemetry and trajectory reconstruction that is being performed, and updates the information presented in the former paper Entry Guidance for the 2011 Mars Science Laboratory Mission (AIAA Atmospheric Flight Mechanics Conference; 8-11 Aug. 2011; Portland, OR; United States)

Apollo 13 Guidance, Navigation, and Control Challenges

NASA Technical Reports Server (NTRS)

Goodman, John L.

2009-01-01

Combustion and rupture of a liquid oxygen tank during the Apollo 13 mission provides lessons and insights for future spacecraft designers and operations personnel who may never, during their careers, have participated in saving a vehicle and crew during a spacecraft emergency. Guidance, Navigation, and Control (GNC) challenges were the reestablishment of attitude control after the oxygen tank incident, re-establishment of a free return trajectory, resolution of a ground tracking conflict between the LM and the Saturn V S-IVB stage, Inertial Measurement Unit (IMU) alignments, maneuvering to burn attitudes, attitude control during burns, and performing manual GNC tasks with most vehicle systems powered down. Debris illuminated by the Sun and gaseous venting from the Service Module (SM) complicated crew attempts to identify stars and prevented execution of nominal IMU alignment procedures. Sightings on the Sun, Moon, and Earth were used instead. Near continuous communications with Mission Control enabled the crew to quickly perform time critical procedures. Overcoming these challenges required the modification of existing contingency procedures.

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.

Sleep apps: what role do they play in clinical medicine?

PubMed

Lorenz, Christopher P; Williams, Adrian J

2017-11-01

Today's smartphones boast more computing power than the Apollo Guidance Computer. Given the ubiquity and popularity of smartphones, are we already carrying around miniaturized sleep labs in our pockets? There is still a lack of validation studies for consumer sleep technologies in general and apps for monitoring sleep in particular. To overcome this gap, multidisciplinary teams are needed that focus on feasibility work at the intersection of software engineering, data science and clinical sleep medicine. To date, no smartphone app for monitoring sleep through movement sensors has been successfully validated against polysomnography, despite the role and validity of actigraphy in sleep medicine having been well established. Missing separation of concerns, not methodology, poses the key limiting factor: The two essential steps in the monitoring process, data collection and scoring, are chained together inside a black box due to the closed nature of consumer devices. This leaves researchers with little room for influence nor can they access raw data. Multidisciplinary teams that wield complete power over the sleep monitoring process are sorely needed.

Orion Powered Flight Guidance Burn Options for Near Term Exploration

NASA Technical Reports Server (NTRS)

Fill, Tom; Goodman, John; Robinson, Shane

2018-01-01

NASA's Orion exploration spacecraft will fly more demanding mission profiles than previous NASA human flight spacecraft. Missions currently under development are destined for cislunar space. The EM-1 mission will fly unmanned to a Distant Retrograde Orbit (DRO) around the Moon. EM-2 will fly astronauts on a mission to the lunar vicinity. To fly these missions, Orion requires powered flight guidance that is more sophisticated than the orbital guidance flown on Apollo and the Space Shuttle. Orion's powered flight guidance software contains five burn guidance options. These five options are integrated into an architecture based on a proven shuttle heritage design, with a simple closed-loop guidance strategy. The architecture provides modularity, simplicity, versatility, and adaptability to future, yet-to-be-defined, exploration mission profiles. This paper provides a summary of the executive guidance architecture and details the five burn options to support both the nominal and abort profiles for the EM-1 and EM-2 missions.

Orion's Powered Flight Guidance Burn Options for Near Term Exploration Missions

NASA Technical Reports Server (NTRS)

Fill, Thomas; Goodman, John; Robinson, Shane

2018-01-01

NASA's Orion exploration spacecraft will fly more demanding mission profiles than previous NASA human flight spacecraft. Missions currently under development are destined for cislunar space. The EM-1 mission will fly unmanned to a Distant Retrograde Orbit (DRO) around the Moon. EM-2 will fly astronauts on a mission to the lunar vicinity. To fly these missions, Orion requires powered flight guidance that is more sophisticated than the orbital guidance flown on Apollo and the Space Shuttle. Orion's powered flight guidance software contains five burn guidance options. These five options are integrated into an architecture based on a proven shuttle heritage design, with a simple closed-loop guidance strategy. The architecture provides modularity, simplicity, versatility, and adaptability to future, yet-to-be-defined, exploration mission profiles. This paper provides a summary of the executive guidance architecture and details the five burn options to support both the nominal and abort profiles for the EM-1 and EM-2 missions.

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.

Effect of Counterflow Jet on a Supersonic Reentry Capsule

NASA Technical Reports Server (NTRS)

Chang, Chau-Lyan; Venkatachari, Balaji Shankar; Cheng, Gary C.

2006-01-01

Recent NASA initiatives for space exploration have reinvigorated research on Apollo-like capsule vehicles. Aerothermodynamic characteristics of these capsule configurations during reentry play a crucial role in the performance and safety of the planetary entry probes and the crew exploration vehicles. At issue are the forebody thermal shield protection and afterbody aeroheating predictions. Due to the lack of flight or wind tunnel measurements at hypersonic speed, design decisions on such vehicles would rely heavily on computational results. Validation of current computational tools against experimental measurement thus becomes one of the most important tasks for general hypersonic research. This paper is focused on time-accurate numerical computations of hypersonic flows over a set of capsule configurations, which employ a counterflow jet to offset the detached bow shock. The accompanying increased shock stand-off distance and modified heat transfer characteristics associated with the counterflow jet may provide guidance for future design of hypersonic reentry capsules. The newly emerged space-time conservation element solution element (CESE) method is used to perform time-accurate, unstructured mesh Navier-Stokes computations for all cases investigated. The results show good agreement between experimental and numerical Schlieren pictures. Surface heat flux and aerodynamic force predictions of the capsule configurations are discussed in detail.

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 Multiplexer operations manual

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

Miller, M.M.

1985-04-01

This report describes the operation of the the Apollo Multiplexer, a microprocessor based communications device designed to process data between an Apollo computer and up to four Gandalf PACXIV data switches. Details are given on overall operation, hardware, and troubleshooting. The reader should gain sufficient knowledge from this report to understand the operation of the multiplexer and effectively analyze and correct any problems that might occur.

Assessment of CFD Estimation of Aerodynamic Characteristics of Basic Reusable Rocket Configurations

NASA Astrophysics Data System (ADS)

Fujimoto, Keiichiro; Fujii, Kozo

Flow-fields around the basic SSTO-rocket configurations are numerically simulated by the Reynolds-averaged Navier-Stokes (RANS) computations. Simulations of the Apollo-like configuration is first carried out, where the results are compared with NASA experiments and the prediction ability of the RANS simulation is discussed. The angle of attack of the freestream ranges from 0° to 180° and the freestream Mach number ranges from 0.7 to 2.0. Computed aerodynamic coefficients for the Apollo-like configuration agree well with the experiments under a wide range of flow conditions. The flow simulations around the slender Apollo-type configuration are carried out next and the results are compared with the experiments. Computed aerodynamic coefficients also agree well with the experiments. Flow-fields are dominated by the three-dimensional massively separated flow, which should be captured for accurate aerodynamic prediction. Grid refinement effects on the computed aerodynamic coefficients are investigated comprehensively.

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

Guidance and Control Algorithms for the Mars Entry, Descent and Landing Systems Analysis

NASA Technical Reports Server (NTRS)

Davis, Jody L.; CwyerCianciolo, Alicia M.; Powell, Richard W.; Shidner, Jeremy D.; Garcia-Llama, Eduardo

2010-01-01

The purpose of the Mars Entry, Descent and Landing Systems Analysis (EDL-SA) study was to identify feasible technologies that will enable human exploration of Mars, specifically to deliver large payloads to the Martian surface. This paper focuses on the methods used to guide and control two of the contending technologies, a mid- lift-to-drag (L/D) rigid aeroshell and a hypersonic inflatable aerodynamic decelerator (HIAD), through the entry portion of the trajectory. The Program to Optimize Simulated Trajectories II (POST2) is used to simulate and analyze the trajectories of the contending technologies and guidance and control algorithms. Three guidance algorithms are discussed in this paper: EDL theoretical guidance, Numerical Predictor-Corrector (NPC) guidance and Analytical Predictor-Corrector (APC) guidance. EDL-SA also considered two forms of control: bank angle control, similar to that used by Apollo and the Space Shuttle, and a center-of-gravity (CG) offset control. This paper presents the performance comparison of these guidance algorithms and summarizes the results as they impact the technology recommendations for future study.

Encke-Beta Predictor for Orion Burn Targeting and Guidance

NASA Technical Reports Server (NTRS)

Robinson, Shane; Scarritt, Sara; Goodman, John L.

2016-01-01

The state vector prediction algorithm selected for Orion on-board targeting and guidance is known as the Encke-Beta method. Encke-Beta uses a universal anomaly (beta) as the independent variable, valid for circular, elliptical, parabolic, and hyperbolic orbits. The variable, related to the change in eccentric anomaly, results in integration steps that cover smaller arcs of the trajectory at or near perigee, when velocity is higher. Some burns in the EM-1 and EM-2 mission plans are much longer than burns executed with the Apollo and Space Shuttle vehicles. Burn length, as well as hyperbolic trajectories, has driven the use of the Encke-Beta numerical predictor by the predictor/corrector guidance algorithm in place of legacy analytic thrust and gravity integrals.

High-performing simulations of the space radiation environment for the International Space Station and Apollo Missions

NASA Astrophysics Data System (ADS)

Lund, Matthew Lawrence

The space radiation environment is a significant challenge to future manned and unmanned space travels. Future missions will rely more on accurate simulations of radiation transport in space through spacecraft to predict astronaut dose and energy deposition within spacecraft electronics. The International Space Station provides long-term measurements of the radiation environment in Low Earth Orbit (LEO); however, only the Apollo missions provided dosimetry data beyond LEO. Thus dosimetry analysis for deep space missions is poorly supported with currently available data, and there is a need to develop dosimetry-predicting models for extended deep space missions. GEANT4, a Monte Carlo Method, provides a powerful toolkit in C++ for simulation of radiation transport in arbitrary media, thus including the spacecraft and space travels. The newest version of GEANT4 supports multithreading and MPI, resulting in faster distributive processing of simulations in high-performance computing clusters. This thesis introduces a new application based on GEANT4 that greatly reduces computational time using Kingspeak and Ember computational clusters at the Center for High Performance Computing (CHPC) to simulate radiation transport through full spacecraft geometry, reducing simulation time to hours instead of weeks without post simulation processing. Additionally, this thesis introduces a new set of detectors besides the historically used International Commission of Radiation Units (ICRU) spheres for calculating dose distribution, including a Thermoluminescent Detector (TLD), Tissue Equivalent Proportional Counter (TEPC), and human phantom combined with a series of new primitive scorers in GEANT4 to calculate dose equivalence based on the International Commission of Radiation Protection (ICRP) standards. The developed models in this thesis predict dose depositions in the International Space Station and during the Apollo missions showing good agreement with experimental measurements. From these models the greatest contributor to radiation dose for the Apollo missions was from Galactic Cosmic Rays due to the short time within the radiation belts. The Apollo 14 dose measurements were an order of magnitude higher compared to other Apollo missions. The GEANT4 model of the Apollo Command Module shows consistent doses due to Galactic Cosmic Rays and Radiation Belts for all missions, with a small variation in dose distribution across the capsule. The model also predicts well the dose depositions and equivalent dose values in various human organs for the International Space Station or Apollo Command Module.

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

NASA Technical Reports Server (NTRS)

Littleton, O. P.

1974-01-01

The concepts, design, development, testing, and flight results of the command and service module stabilization and control system are discussed. The period of time covered was from November 1961 to December 1972. Also included are a functional description of the system, a discussion of the major problems, and recommendations for future programs.

Lightning effects on the NASA F-8 digital-fly-by-wire airplane

NASA Technical Reports Server (NTRS)

Plumer, J. A.; Fisher, F. A.; Walko, L. C.

1975-01-01

The effects of lightning on a Digital Fly-By-Wire (DFBW)aircraft control system were investigated. The aircraft was a NASA operated F-8 fitted with a modified Apollo guidance computer. Current pulses similar in waveshape to natural lightning, but lower in amplitude, were injected into the aircraft. Measurements were made of the voltages induced on the DFBW circuits, the total current induced on the bundles of wires, the magnetic field intensity inside the aircraft, and the current density on the skin of the aircraft. Voltage measurements were made in both the line-to-ground and line-to-line modes. Voltages measured at the non-destructive test level were then scaled upward to determine how much would be produced by actual lightning. A 200,000 ampere severe lightning flash would produce between 40 and 2000 volts in DFBW circuits. Some system components are expected to be vulnerable to these voltages.

Predictive Lateral Logic for Numerical Entry Guidance Algorithms

NASA Technical Reports Server (NTRS)

Smith, Kelly M.

2016-01-01

Recent entry guidance algorithm development123 has tended to focus on numerical integration of trajectories onboard in order to evaluate candidate bank profiles. Such methods enjoy benefits such as flexibility to varying mission profiles and improved robustness to large dispersions. A common element across many of these modern entry guidance algorithms is a reliance upon the concept of Apollo heritage lateral error (or azimuth error) deadbands in which the number of bank reversals to be performed is non-deterministic. This paper presents a closed-loop bank reversal method that operates with a fixed number of bank reversals defined prior to flight. However, this number of bank reversals can be modified at any point, including in flight, based on contingencies such as fuel leaks where propellant usage must be minimized.

The Apollo Capsule Optimization for Improved Stability and Computational/Experimental Data Comparisons

NASA Technical Reports Server (NTRS)

Cliff, Susan E.; Thomas, Scott D.

2005-01-01

Numerical optimization was employed on the Apollo Command Module to modify its external shape. The Apollo Command Module (CM) that was used on all NASA human space flights during the Apollo Space Program is stable and trimmed in an apex forward (alpha of approximately 40 to 80 degrees) position. This poses a safety risk if the CM separates from the launch tower during abort. Optimization was employed on the Apollo CM to remedy the undesirable stability characteristics of the configuration. Geometric shape changes were limited to axisymmetric modifications that altered the radius of the apex (R(sub A)), base radius (R(sub O)), corner radius (R(sub C)), and the cone half angle (theta), while the maximum diameter of the CM was held constant. The results of multipoint optimization on the CM indicated that the cross-range performance can be improved while maintaining robust apex-aft stability with a single trim point. Navier-Stokes computations were performed on the baseline and optimized configurations and confirmed the Euler-based optimization results. Euler Analysis of ten alternative CM vehicles with different values of the above four parameters are compared with the published experimental results of numerous wind tunnel tests during the late 1960's. These comparisons cover a wide Mach number range and a full 180-degree pitch range and show that the Euler methods are capable of fairly accurate force and moment computations and can separate the vehicle characteristics of these ten alternative configurations.

Apollo guidance, navigation, and control: Candidate configuration trade study, Stellar-Inertial Measurement System (SIMS) for an Earth Observation Satellite (EOS)

NASA Technical Reports Server (NTRS)

Ogletree, G.; Coccoli, J.; Mckern, R.; Smith, M.; White, R.

1972-01-01

The ten candidate SIMS configurations were reduced to three in preparation for the final trade comparison. The report emphasizes subsystem design trades, star availability studies, data processing (smoothing) methods, and the analytical and simulation studies at subsystem and system levels from which candidate accuracy estimates will be presented.

Apollo Ring Optical Switch

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

Maestas, J.H.

1987-03-01

An optical switch was designed, built, and installed at Sandia National Laboratories in Albuquerque, New Mexico, to facilitate the integration of two Apollo computer networks into a single network. This report presents an overview of the optical switch as well as its layout, switch testing procedure and test data, and installation.

Apollo: a sequence annotation editor

PubMed Central

Lewis, SE; Searle, SMJ; Harris, N; Gibson, M; Iyer, V; Richter, J; Wiel, C; Bayraktaroglu, L; Birney, E; Crosby, MA; Kaminker, JS; Matthews, BB; Prochnik, SE; Smith, CD; Tupy, JL; Rubin, GM; Misra, S; Mungall, CJ; Clamp, ME

2002-01-01

The well-established inaccuracy of purely computational methods for annotating genome sequences necessitates an interactive tool to allow biological experts to refine these approximations by viewing and independently evaluating the data supporting each annotation. Apollo was developed to meet this need, enabling curators to inspect genome annotations closely and edit them. FlyBase biologists successfully used Apollo to annotate the Drosophila melanogaster genome and it is increasingly being used as a starting point for the development of customized annotation editing tools for other genome projects. PMID:12537571

Activity Book. Celebrate Apollo 11.

ERIC Educational Resources Information Center

Barchert, Linda; And Others

1994-01-01

An activity book helps students learn about the 1969 Apollo 11 mission to the moon as they get a sense of the mission's impact on their lives. The activities enhance understanding of science, math, social studies, and language arts. A teacher's page offers information on books, magazines, computer materials, and special resources. (SM)

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.

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.

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.

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.

Environmental health program activities

NASA Technical Reports Server (NTRS)

Bergtholdt, C. P.

1969-01-01

Activities reported include studies on toxic air contaminants, excessive noise, poor lighting, food sanitation, water pollution, and exposure to nonionizing radiation as health hazards. Formulations for a radiological health manual provide guidance to personnel in the procurement and safe handling of radiation producing equipment and Apollo mission planning. A literature search and development of a water analysis laboratory are outlined to obtain information regarding microbiological problems involving potable water, waste management, and personal hygiene.

Engineering support activities for the Apollo 17 Surface Electrical Properties Experiment.

NASA Technical Reports Server (NTRS)

Cubley, H. D.

1972-01-01

Description of the engineering support activities which were required to ensure fulfillment of objectives specified for the Apollo 17 SEP (Surface Electrical Properties) Experiment. Attention is given to procedural steps involving verification of hardware acceptability to the astronauts, computer simulation of the experiment hardware, field trials, receiver antenna pattern measurements, and the qualification test program.

Apollo Photograph Evaluation (APE) programming manual

NASA Technical Reports Server (NTRS)

Kim, I. J.

1974-01-01

This document describes the programming techniques used to implement the equations of the Apollo Photograph Evaluation (APE) program on the UNIVAC 1108 computer and contains detailed descriptions of the program structure, a User's Guide section to provide the necessary information for proper operation of the program, and information for the assessment of the program's adaptability to future problems.

Doppler measurements of the ionosphere on the occasion of the Apollo-Soyuz test project. Part 1: Computer simulation of ionospheric-induced Doppler shifts

NASA Technical Reports Server (NTRS)

Grossi, M. D.; Gay, R. H.

1975-01-01

A computer simulation of the ionospheric experiment of the Apollo-Soyuz Test Project (ASTP) was performed. ASTP is the first example of USA/USSR cooperation in space and is scheduled for summer 1975. The experiment consists of performing dual-frequency Doppler measurements (at 162 and 324 MHz) between the Apollo Command Service Module (CSM) and the ASTP Docking Module (DM), both orbiting at 221-km height and at a relative distance of 300 km. The computer simulation showed that, with the Doppler measurement resolution of approximately 3 mHz provided by the instrumentation (in 10-sec integration time), ionospheric-induced Doppler shifts will be measurable accurately at all times, with some rare exceptions occurring when the radio path crosses regions of minimum ionospheric density. The computer simulation evaluated the ability of the experiment to measure changes of columnar electron content between CSM and DM (from which horizontal gradients of electron density at 221-km height can be obtained) and to measure variations in DM-to-ground columnar content (from which an averaged columnar content and the electron density at the DM can be deduced, under some simplifying assumptions).

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

Saturn Apollo Program

NASA Image and Video Library

1967-01-01

This cutaway illustration shows the Saturn V S-II (second) stage with callouts of major components. When the Saturn V first stage burns out and drops away, power for the Saturn was provided by the S-II (second) stage with five J-2 engines which produced a total of 1,150,000 pounds of thrust. Four outer engines are placed in a square pattern with gimbaling capability for control and guidance, with the fifth engine fixed rigidly in the center.

Evaluation of Drogue Parachute Damping Effects Utilizing the Apollo Legacy Parachute Model

NASA Technical Reports Server (NTRS)

Currin, Kelly M.; Gamble, Joe D.; Matz, Daniel A.; Bretz, David R.

2011-01-01

Drogue parachute damping is required to dampen the Orion Multi Purpose Crew Vehicle (MPCV) crew module (CM) oscillations prior to deployment of the main parachutes. During the Apollo program, drogue parachute damping was modeled on the premise that the drogue parachute force vector aligns with the resultant velocity of the parachute attach point on the CM. Equivalent Cm(sub q) and Cm(sub alpha) equations for drogue parachute damping resulting from the Apollo legacy parachute damping model premise have recently been developed. The MPCV computer simulations ANTARES and Osiris have implemented high fidelity two-body parachute damping models. However, high-fidelity model-based damping motion predictions do not match the damping observed during wind tunnel and full-scale free-flight oscillatory motion. This paper will present the methodology for comparing and contrasting the Apollo legacy parachute damping model with full-scale free-flight oscillatory motion. The analysis shows an agreement between the Apollo legacy parachute damping model and full-scale free-flight oscillatory motion.

The application of automatic recognition techniques in the Apollo 9 SO-65 experiment

NASA Technical Reports Server (NTRS)

Macdonald, R. B.

1970-01-01

A synoptic feature analysis is reported on Apollo 9 remote earth surface photographs that uses the methods of statistical pattern recognition to classify density points and clusterings in digital conversion of optical data. A computer derived geological map of a geological test site indicates that geological features of the range are separable, but that specific rock types are not identifiable.

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

Computers in Spaceflight: the NASA Experience

NASA Technical Reports Server (NTRS)

Tomayko, James E.

1988-01-01

This book examines the computer systems used in actual spaceflight or in close support of it. Each chapter deals with either a specific program, such as Gemini or Apollo onboard computers, or a closely related set of systems, such as launch processing or mission control. A glossary of computer terms is included.

Specification of Computer Systems by Objectives.

ERIC Educational Resources Information Center

Eltoft, Douglas

1989-01-01

Discusses the evolution of mainframe and personal computers, and presents a case study of a network developed at the University of Iowa called the Iowa Computer-Aided Engineering Network (ICAEN) that combines Macintosh personal computers with Apollo workstations. Functional objectives are stressed as the best measure of system performance. (LRW)

Radioactivity observed in the sodium iodide gamma-ray spectrometer returned on the Apollo 17 mission

NASA Technical Reports Server (NTRS)

Dyer, C. S.; Trombka, J. I.; Schmadebeck, R. L.; Eller, E.; Bielefeld, M. J.; Okelley, G. D.; Eldridge, J. S.; Northcutt, K. J.; Metzger, A. E.; Reedy, R. C.

1975-01-01

In order to obtain information on radioactive background induced in the Apollo 15 and 16 gamma-ray spectrometers (7 cm x 7 cm NaI) by particle irradiation during spaceflight, and identical detector was flown and returned to earth on the Apollo 17 mission. The induced radioactivity was monitored both internally and externally from one and a half hours after splashdown. When used in conjunction with a computation scheme for estimating induced activation from calculated trapped proton and cosmic-ray fluences, these results show an important contribution resulting from both thermal and energetic neutrons produced in the heavy spacecraft by cosmic-ray interactions.

Noise Abatement

NASA Technical Reports Server (NTRS)

1983-01-01

SMART, Sound Modification and Regulated Temperature compound, is a liquid plastic mixture with exceptional energy and sound absorbing qualities. It is derived from a very elastic plastic which was an effective noise abatement material in the Apollo Guidance System. Discovered by a NASA employee, it is marketed by Environmental Health Systems, Inc. (EHS). The product has been successfully employed by a diaper company with noisy dryers and a sugar company with noisy blowers. The company also manufactures an audiometric test booth and acoustical office partitions.

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...

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.

Saturn Apollo Program

NASA Image and Video Library

1964-09-01

This image depicts a high angle view of technicians working on the instrument unit (IU) component assembly for the SA-8 mission in Marshall Space Flight Center's building 4705. A thin, circular structure, only 1-meter high and 7.6 meters in diameter, the IU was sandwiched between the S-IV and Apollo spacecraft. Packed inside were the computers, gyroscopes, and assorted black boxes necessary to keep the launch vehicle properly functioning and on its course.

Structure from Motion Photogrammetry and Micro X-Ray Computed Tomography 3-D Reconstruction Data Fusion for Non-Destructive Conservation Documentation of Lunar Samples

NASA Technical Reports Server (NTRS)

Beaulieu, K. R.; Blumenfeld, E. H.; Liddle, D. A.; Oshel, E. R.; Evans, C. A.; Zeigler, R. A.; Righter, K.; Hanna, R. D.; Ketcham, R. A.

2017-01-01

Our team is developing a modern, cross-disciplinary approach to documentation and preservation of astromaterials, specifically lunar and meteorite samples stored at the Johnson Space Center (JSC) Lunar Sample Laboratory Facility. Apollo Lunar Sample 60639, collected as part of rake sample 60610 during the 3rd Extra-Vehicular Activity of the Apollo 16 mission in 1972, served as the first NASA-preserved lunar sample to be examined by our team in the development of a novel approach to internal and external sample visualization. Apollo Sample 60639 is classified as a breccia with a glass-coated side and pristine mare basalt and anorthosite clasts. The aim was to accurately register a 3-dimensional Micro X-Ray Computed Tomography (XCT)-derived internal composition data set and a Structure-From-Motion (SFM) Photogrammetry-derived high-fidelity, textured external polygonal model of Apollo Sample 60639. The developed process provided the means for accurate, comprehensive, non-destructive visualization of NASA's heritage lunar samples. The data products, to be ultimately served via an end-user web interface, will allow researchers and the public to interact with the unique heritage samples, providing a platform to "slice through" a photo-realistic rendering of a sample to analyze both its external visual and internal composition simultaneously.

Fast non-overlapping Schwarz domain decomposition methods for solving the neutron diffusion equation

NASA Astrophysics Data System (ADS)

Jamelot, Erell; Ciarlet, Patrick

2013-05-01

Studying numerically the steady state of a nuclear core reactor is expensive, in terms of memory storage and computational time. In order to address both requirements, one can use a domain decomposition method, implemented on a parallel computer. We present here such a method for the mixed neutron diffusion equations, discretized with Raviart-Thomas-Nédélec finite elements. This method is based on the Schwarz iterative algorithm with Robin interface conditions to handle communications. We analyse this method from the continuous point of view to the discrete point of view, and we give some numerical results in a realistic highly heterogeneous 3D configuration. Computations are carried out with the MINOS solver of the APOLLO3® neutronics code. APOLLO3 is a registered trademark in France.

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.

Noise Protection

NASA Technical Reports Server (NTRS)

1980-01-01

Environmental Health Systems puts forth an increasing effort in the U.S. to develop ways of controlling noise, particularly in industrial environments due to Federal and State laws, labor union insistence and new findings relative to noise pollution impact on human health. NASA's Apollo guidance control system aided in the development of a noise protection product, SMART. The basis of all SMART products is SMART compound a liquid plastic mixture with exceptional energy/sound absorbing qualities. The basic compound was later refined for noise protection use.

Automated, real-time fresh gas flow recommendations alter isoflurane consumption during the maintenance phase of anesthesia in a simulator-based study.

PubMed

Luria, Isaac; Lampotang, Samsun; Schwab, Wilhelm; Cooper, Lou Ann; Lizdas, David; Gravenstein, Nikolaus

2013-11-01

The Low Flow Wizard (LFW) provides real-time guidance for user optimization of fresh gas flow (FGF) settings during general inhaled anesthesia. The LFW can continuously inform users whether it determines their FGF to be too little, efficient, or too much, and its color-coded recommendations respond in real time to changes in FGF performed by users. Our study objective was to determine whether the LFW feature, as implemented in the Dräger Apollo workstation, alters FGF selection and thereby volatile anesthetic consumption without affecting patient care. To reduce potentially confounding variables, we used a human patient simulator that consumes and exhales volatile anesthetics. Standard monitoring was provided for the patient initially with invasive arterial blood pressure added after anesthetic induction. In this within-group study, each of 17 participants acted as his or her own control. Each participant was asked to anesthetize an identical simulated patient twice using a Dräger Apollo workstation, first with the LFW feature disabled and subsequently enabled. The volatile anesthetic was isoflurane. Both simulation runs were set up to have similar time durations for the different phases of anesthesia: induction, incision, and maintenance. Emergence was not simulated. The isoflurane vaporizer was weighed before and after each simulation run on a digital scale to verify total computed volatile liquid anesthetic consumption. In addition, the product of FGF (reported by the Apollo) times the isoflurane volumetric concentration (sampled by a multigas analyzer at the equivalent of the FGF hose for the Apollo) was integrated over time to obtain isoflurane consumption rate (on-the-fly anesthetic consumption rate measurement). The maintenance isoflurane consumption rate and FGF were significantly lower with the LFW display enabled than without (P = 0.005). The mean reduction in FGF was 53.6% (95% confidence interval, 39.2%-67.9%). There was no significant difference in alveolar isoflurane concentration (P = 0.13 for differences <0.1%). The isoflurane consumption measurement closely matched the consumption measured via the digital scale. Our data in a simulated anesthetic suggest that enabling the display of FGF efficiency data by the LFW results in a median percent reduction in volatile liquid anesthetic consumption rate of 53.2%. Since the lower limit of the 95% confidence interval for the median is 39.4%, this finding is likely to translate into cost savings and less waste anesthetic gas generated in the clinical setting and released into the atmosphere.

77 FR 39498 - Guidances for Industry and Food and Drug Administration Staff: Computer-Assisted Detection...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-07-03

...] Guidances for Industry and Food and Drug Administration Staff: Computer-Assisted Detection Devices Applied... Clinical Performance Assessment: Considerations for Computer-Assisted Detection Devices Applied to... guidance, entitled ``Computer-Assisted Detection Devices Applied to Radiology Images and Radiology Device...

Autonomous docking ground demonstration (category 3)

NASA Technical Reports Server (NTRS)

Lamkin, Steve L.; Eick, Richard E.; Baxter, James M.; Boyd, M. G.; Clark, Fred D.; Lee, Thomas Q.; Othon, L. T.; Prather, Joseph L.; Spehar, Peter T.; Teders, Rebecca J.

1991-01-01

The NASA Johnson Space Center (JSC) is involved in the development of an autonomous docking ground demonstration. The demonstration combines the technologies, expertise and facilities of the JSC Tracking and Communications Division (EE), Structures and Mechanics Division (ES), and the Navigation, Guidance and Control Division (EG) and their supporting contractors. The autonomous docking ground demonstration is an evaluation of the capabilities of the laser sensor system to support the docking phase (12ft to contact) when operated in conjunction with the Guidance, Navigation and Control Software. The docking mechanism being used was developed for the Apollo Soyuz Test Program. This demonstration will be conducted using the Six-Degrees of Freedom (6-DOF) Dynamic Test System (DTS). The DTS environment simulates the Space Station Freedom as the stationary or target vehicle and the Orbiter as the active or chase vehicle. For this demonstration the laser sensor will be mounted on the target vehicle and the retroreflectors on the chase vehicle. This arrangement was used to prevent potential damage to the laser. The sensor system. GN&C and 6-DOF DTS will be operated closed-loop. Initial condition to simulate vehicle misalignments, translational and rotational, will be introduced within the constraints of the systems involved. Detailed description of each of the demonstration components (e.g., Sensor System, GN&C, 6-DOF DTS and supporting computer configuration) including their capabilities and limitations will be discussed. A demonstration architecture drawing and photographs of the test configuration will be presented.

Autonomous docking ground demonstration (category 3)

NASA Astrophysics Data System (ADS)

Lamkin, Steve L.; Eick, Richard E.; Baxter, James M.; Boyd, M. G.; Clark, Fred D.; Lee, Thomas Q.; Othon, L. T.; Prather, Joseph L.; Spehar, Peter T.; Teders, Rebecca J.

The NASA Johnson Space Center (JSC) is involved in the development of an autonomous docking ground demonstration. The demonstration combines the technologies, expertise and facilities of the JSC Tracking and Communications Division (EE), Structures and Mechanics Division (ES), and the Navigation, Guidance and Control Division (EG) and their supporting contractors. The autonomous docking ground demonstration is an evaluation of the capabilities of the laser sensor system to support the docking phase (12ft to contact) when operated in conjunction with the Guidance, Navigation and Control Software. The docking mechanism being used was developed for the Apollo Soyuz Test Program. This demonstration will be conducted using the Six-Degrees of Freedom (6-DOF) Dynamic Test System (DTS). The DTS environment simulates the Space Station Freedom as the stationary or target vehicle and the Orbiter as the active or chase vehicle. For this demonstration the laser sensor will be mounted on the target vehicle and the retroreflectors on the chase vehicle. This arrangement was used to prevent potential damage to the laser. The sensor system. GN&C and 6-DOF DTS will be operated closed-loop. Initial condition to simulate vehicle misalignments, translational and rotational, will be introduced within the constraints of the systems involved. Detailed description of each of the demonstration components (e.g., Sensor System, GN&C, 6-DOF DTS and supporting computer configuration) including their capabilities and limitations will be discussed. A demonstration architecture drawing and photographs of the test configuration will be presented.

78 FR 18353 - Guidance for Industry: Blood Establishment Computer System Validation in the User's Facility...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-26

...; (Formerly FDA-2007D-0393)] Guidance for Industry: Blood Establishment Computer System Validation in the User... Industry: Blood Establishment Computer System Validation in the User's Facility'' dated April 2013. The... document entitled ``Guidance for Industry: Blood Establishment Computer System Validation in the User's...

Information Security: Governmentwide Guidance Needed to Assist Agencies in Implementing Cloud Computing

DTIC Science & Technology

2010-07-01

Cloud computing , an emerging form of computing in which users have access to scalable, on-demand capabilities that are provided through Internet... cloud computing , (2) the information security implications of using cloud computing services in the Federal Government, and (3) federal guidance and...efforts to address information security when using cloud computing . The complete report is titled Information Security: Federal Guidance Needed to

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.

Automating CapCom: Pragmatic Operations and Technology Research for Human Exploration of Mars

NASA Technical Reports Server (NTRS)

Clancey, William J.

2003-01-01

During the Apollo program, NASA and the scientific community used terrestrial analog sites for understanding planetary features and for training astronauts to be scientists. More recently, computer scientists and human factors specialists have followed geologists and biologists into the field, learning how science is actually done on expeditions in extreme environments. Research stations have been constructed by the Mars Society in the Arctic and American southwest, providing facilities for hundreds of researchers to investigate how small crews might live and work on Mars. Combining these interests-science, operations, and technology-in Mars analog field expeditions provides tremendous synergy and authenticity to speculations about Mars missions. By relating historical analyses of Apollo and field science, engineers are creating experimental prototypes that provide significant new capabilities, such as a computer system that automates some of the functions of Apollo s CapCom. Thus, analog studies have created a community of practice-a new collaboration between scientists and engineers-so that technology begins with real human needs and works incrementally towards the challenges of the human exploration of Mars.

Comparison of the Effects of Velocity and Range Triggers on Trajectory Dispersions for the Mars 2020 Mission

NASA Technical Reports Server (NTRS)

Dutta, Soumyo; Way, David W.

2017-01-01

Mars 2020, the next planned U.S. rover mission to land on Mars, is based on the design of the successful 2012 Mars Science Laboratory (MSL) mission. Mars 2020 retains most of the entry, descent, and landing (EDL) sequences of MSL, including the closed-loop entry guidance scheme based on the Apollo guidance algorithm. However, unlike MSL, Mars 2020 will trigger the parachute deployment and descent sequence on range trigger rather than the previously used velocity trigger. This difference will greatly reduce the landing ellipse sizes. Additionally, the relative contribution of each models to the total ellipse sizes have changed greatly due to the switch to range trigger. This paper considers the effect on trajectory dispersions due to changing the trigger schemes and the contributions of these various models to trajectory and EDL performance.

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.

Programmer's guide for the GNAT computer program (numerical analysis of stratification in supercritical oxygen)

NASA Technical Reports Server (NTRS)

Heinmiller, J. P.

1971-01-01

This document is the programmer's guide for the GNAT computer program developed under MSC/TRW Task 705-2, Apollo cryogenic storage system analysis, subtask 2, is reported. Detailed logic flow charts and compiled program listings are provided for all program elements.

Ways of achieving continuous service from computers

NASA Technical Reports Server (NTRS)

Quinn, M. J., Jr.

1974-01-01

This paper outlines the methods used in the real-time computer complex to keep computers operating. Methods include selectover, high-speed restart, and low-speed restart. The hardware and software needed to implement these methods is discussed as well as the system recovery facility, alternate device support, and timeout. In general, methods developed while supporting the Gemini, Apollo, and Skylab space missions are presented.

Entry, Descent, and Landing Guidance and Control Approaches to Satisfy Mars Human Mission Landing Criteria

NASA Technical Reports Server (NTRS)

Dwyer Cianciolo, Alicia; Powell, Richard W.

2017-01-01

Precision landing on Mars is a challenge. All Mars lander missions prior to the 2012 Mars Science Laboratory (MSL) had landing location uncertainty ellipses on the order of hundreds of kilometers. Sending humans to the surface of Mars will likely require multiple landers delivered in close proximity, which will in turn require orders of magnitude improvement in landing accuracy. MSL was the first Mars mission to use an Apollo-derived bank angle guidance to reduce the size of the landing ellipse. It utilized commanded bank angle magnitude to control total range and bank angle reversals to control cross range. A shortcoming of this bank angle guidance is that the open loop phase of flight created by use of bank reversals increases targeting errors. This paper presents a comparison of entry, descent and landing performance for a vehicle with a low lift-to-drag ratio using both bank angle control and an alternative guidance called Direct Force Control (DFC). DFC eliminates the open loop flight errors by directly controlling two forces independently, lift and side force. This permits independent control of down range and cross range. Performance results, evaluated using the Program to Optimize Simulated Trajectories (POST2), including propellant use and landing accuracy, are presented.

Spacecraft guidance, navigation, and control requirements for an intelligent plug-n-play avionics (PAPA) architecture

NASA Technical Reports Server (NTRS)

Kulkarni, Nilesh; Krishnakumar, Kalmaje

2005-01-01

The objective of this research is to design an intelligent plug-n-play avionics system that provides a reconfigurable platform for supporting the guidance, navigation and control (GN&C) requirements for different elements of the space exploration mission. The focus of this study is to look at the specific requirements for a spacecraft that needs to go from earth to moon and back. In this regard we will identify the different GN&C problems in various phases of flight that need to be addressed for designing such a plug-n-play avionics system. The Apollo and the Space Shuttle programs provide rich literature in terms of understanding some of the general GN&C requirements for a space vehicle. The relevant literature is reviewed which helps in narrowing down the different GN&C algorithms that need to be supported along with their individual requirements.

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/

Uneven drive rates of the scanning telescope: Apollo 16 mission

NASA Technical Reports Server (NTRS)

1972-01-01

An investigation was made into the cause or causes of uneven drive rates during operation of the Apollo 16 scanning telescope. It was suggested that such erratic behavior was caused by either changes in the characteristics noise level of the optics counter on the panels or the repositioning process by the computer or zero optics mode. Test results show the anomaly was not caused by either of the above suggestions, instead they were caused by a broken socket spring in the telescope harness. New harnesses will be manufactured for future flights.

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.

F-8 DFBW on-board electronics

NASA Image and Video Library

1971-07-18

The Apollo hardware jammed into the F-8C. The computer is partially visible in the avionics bay at the top of the fuselage behind the cockpit. Note the display and keyboard unit in the gun bay. To carry the computers and other equipment, the F-8 DFBW team removed the aircraft's guns and ammunition boxes.

Study of the National Science Foundation's South Pole Station as an analogous data base for the logistical support of a Moon laboratory

NASA Technical Reports Server (NTRS)

Hickam, H. H., Jr.

1993-01-01

The day will come when the United States will want to return to the Earth's Moon. When that occurs, NASA may look to the Apollo program for technical and inspirational guidance. The Apollo program, however, was designed to be an end to itself--the landing of a man on the Moon and his return safely within the decade of the 1960's. When that was accomplished, the program folded because it was not self-sustaining. The next time we return to the Moon, we should base our planning on a program that is designed to be a sustained effort for an indefinite period. It is the thrust of this report that the South Pole Station of the National Science Foundation can be used to develop analogs for the construction, funding, and logistical support of a lunar base. Other analogs include transportation and national efforts versus international cooperation. A recommended lunar base using the South Pole Station as inspiration is provided, as well as details concerning economical construction of the base over a 22-year period.

A Simplified Guidance for Target Missiles Used in Ballistic Missile Defence Evaluation

NASA Astrophysics Data System (ADS)

Prabhakar, N.; Kumar, I. D.; Tata, S. K.; Vaithiyanathan, V.

2013-01-01

A simplified guidance scheme for the target missiles used in Ballistic Missile Defence is presented in this paper. The proposed method has two major components, a Ground Guidance Computation (GGC) and an In-Flight Guidance Computation. The GGC which runs on the ground uses a missile model to generate attitude history in pitch plane and computes launch azimuth of the missile to compensate for the effect of earth rotation. The vehicle follows the pre launch computed attitude (theta) history in pitch plane and also applies the course correction in azimuth plane based on its deviation from the pre launch computed azimuth plane. This scheme requires less computations and counters In-flight disturbances such as wind, gust etc. quite efficiently. The simulation results show that the proposed method provides the satisfactory performance and robustness.

Designing Programs for Multiple Configurations: "You Mean Everyone Doesn't Have a Pentium or Better!"

ERIC Educational Resources Information Center

Conkright, Thomas D.; Joliat, Judy

1996-01-01

Discusses the challenges, solutions, and compromises involved in creating computer-delivered training courseware for Apollo Travel Services, a company whose 50,000 agents must access a mainframe from many different computing configurations. Initial difficulties came in trying to manage random access memory and quicken response time, but the future…

Man-rated flight software for the F-8 DFBW program

NASA Technical Reports Server (NTRS)

Bairnsfather, R. R.

1976-01-01

The design, implementation, and verification of the flight control software used in the F-8 DFBW program are discussed. Since the DFBW utilizes an Apollo computer and hardware, the procedures, controls, and basic management techniques employed are based on those developed for the Apollo software system. Program assembly control, simulator configuration control, erasable-memory load generation, change procedures and anomaly reporting are discussed. The primary verification tools are described, as well as the program test plans and their implementation on the various simulators. Failure effects analysis and the creation of special failure generating software for testing purposes are described.

A Computationally Inexpensive Optimal Guidance via Radial-Basis-Function Neural Network for Autonomous Soft Landing on Asteroids

PubMed Central

Zhang, Peng; Liu, Keping; Zhao, Bo; Li, Yuanchun

2015-01-01

Optimal guidance is essential for the soft landing task. However, due to its high computational complexities, it is hardly applied to the autonomous guidance. In this paper, a computationally inexpensive optimal guidance algorithm based on the radial basis function neural network (RBFNN) is proposed. The optimization problem of the trajectory for soft landing on asteroids is formulated and transformed into a two-point boundary value problem (TPBVP). Combining the database of initial states with the relative initial co-states, an RBFNN is trained offline. The optimal trajectory of the soft landing is determined rapidly by applying the trained network in the online guidance. The Monte Carlo simulations of soft landing on the Eros433 are performed to demonstrate the effectiveness of the proposed guidance algorithm. PMID:26367382

Space shuttle guidance, navigation and control design equations. Volume 4: Deorbit and atmospheric operations

NASA Technical Reports Server (NTRS)

Cox, K. J.

1971-01-01

A baseline set of equations which fulfill the computation requirements for guidance, navigation, and control of the space shuttle orbiter vehicle is presented. All shuttle mission phases are covered from prelaunch through landing/rollout. The spacecraft flight mode and the aircraft flight mode are addressed. The baseline equations may be implemented in a single guidance, navigation, and control computer or may be distributed among several subsystem computers.

X-Ray Micro-Computed Tomography of Apollo Samples as a Curation Technique Enabling Better Research

NASA Technical Reports Server (NTRS)

Ziegler, R. A.; Almeida, N. V.; Sykes, D.; Smith, C. L.

2014-01-01

X-ray micro-computed tomography (micro-CT) is a technique that has been used to research meteorites for some time and many others], and recently it is becoming a more common tool for the curation of meteorites and Apollo samples. Micro-CT is ideally suited to the characterization of astromaterials in the curation process as it can provide textural and compositional information at a small spatial resolution rapidly, nondestructively, and without compromising the cleanliness of the samples (e.g., samples can be scanned sealed in Teflon bags). This data can then inform scientists and curators when making and processing future sample requests for meteorites and Apollo samples. Here we present some preliminary results on micro-CT scans of four Apollo regolith breccias. Methods: Portions of four Apollo samples were used in this study: 14321, 15205, 15405, and 60639. All samples were 8-10 cm in their longest dimension and approximately equant. These samples were micro-CT scanned on the Nikon HMXST 225 System at the Natural History Museum in London. Scans were made at 205-220 kV, 135-160 microamps beam current, with an effective voxel size of 21-44 microns. Results: Initial examination of the data identify a variety of mineral clasts (including sub-voxel FeNi metal grains) and lithic clasts within the regolith breccias. Textural information within some of the lithic clasts was also discernable. Of particular interest was a large basalt clast (approx.1.3 cc) found within sample 60639, which appears to have a sub-ophitic texture. Additionally, internal void space, e.g., fractures and voids, is readily identifiable. Discussion: It is clear from the preliminary data that micro-CT analyses are able to identify important "new" clasts within the Apollo breccias, and better characterize previously described clasts or igneous samples. For example, the 60639 basalt clast was previously believed to be quite small based on its approx.0.5 sq cm exposure on the surface of the main mass. These scans show the clast to be approx.4.5 g, however (assuming a density of approx.3.5 g/cc). This is large enough for detailed studies including multiple geo-chronometers. This basalt clast is of particular interest as it is the largest Apollo 16 basalt, and it is the only mid-TiO2 basalt in the Apollo sample suite. By identifying the location of interesting clasts or grains within a sample, we will be able to make more informed decisions about where to cut a sample in order to best expose clasts of interest for future study. Moreover, knowing the location of internal defects (e.g., fractures) will allow more precise chipping and extraction of clasts or grains. By combining micro-CT scans with compositional techniques like micro x-ray fluorescence (particularly on sawn slabs), we will be able to provide even more comprehensive information to scientists trying to best select samples that fit their scientific needs.

SIGI: A Computer-Based System of Interactive Guidance and Information.

ERIC Educational Resources Information Center

Educational Testing Service, Princeton, NJ.

This pamphlet describes SIGI, a computer-based System of Interactive Guidance and Information designed to help students in community and junior colleges make career decisions. SIGI is based on a humanistic philosophy, a theory of guidance that emphasizes individual values, a vast store of occupational data, and a strategy for processing…

Computed intraoperative navigation guidance--a preliminary report on a new technique.

PubMed

Enislidis, G; Wagner, A; Ploder, O; Ewers, R

1997-08-01

To assess the value of a computer-assisted three-dimensional guidance system (Virtual Patient System) in maxillofacial operations. Laboratory and open clinical study. Teaching Hospital, Austria. 6 patients undergoing various procedures including removal of foreign body (n=3) and biopsy, maxillary advancement, and insertion of implants (n=1 each). Storage of computed tomographic (CT) pictures on an optical disc, and imposition of intraoperative video images on to these. The resulting display is shown to the surgeon on a micromonitor in his head-up display for guidance during the operations. To improve orientation during complex or minimally invasive maxillofacial procedures and to make such operations easier and less traumatic. Successful transferral of computed navigation technology into an operation room environment and positive evaluation of the method by the surgeons involved. Computer-assisted three-dimensional guidance systems have the potential for making complex or minimally invasive procedures easier to do, thereby reducing postoperative morbidity.

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.

The Impact on Future Guidance Programs of Current Developments in Computer Science, Telecommunications, and Biotechnology.

ERIC Educational Resources Information Center

Mitchell, Lynda K.; Hardy, Philippe L.

The purpose of this chapter is to envision how the era of technological revolution will affect the guidance, counseling, and student support programs of the future. Advances in computer science, telecommunications, and biotechnology are discussed. These advances have the potential to affect dramatically the services of guidance programs of the…

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)

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.

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.

The Delta launch vehicle Model 2914 series

NASA Technical Reports Server (NTRS)

Gunn, C. R.

1973-01-01

Description of a new, medium-class Delta launch-vehicle configuration, the three-stage Model 2914. The first stage of this vehicle is composed of a liquid-propellant core which is thrust-augmented with up to nine strap-on solid-propellant motors. The second stage, recently uprated with a strap-down inertial guidance system, is now being modified to adapt the liquid-propellant descent engine from the Apollo Lunar Excursion Module. The third stage is a spin-stabilized solid-propellant motor. The Model 2914 is capable of injecting 2040 kg into low earth orbit, 705 kg into geosynchronous transfer orbit, or 455 kg into an escape trajectory.

Potential for Integrating Entry Guidance into the Multi-Disciplinary Entry Vehicle Optimization Environment

NASA Technical Reports Server (NTRS)

D'souza, Sarah N.; Kinney, David J.; Garcia, Joseph A.; Sarigul-Klijn, Nesrin

2014-01-01

The state-of-the-art in vehicle design decouples flight feasible trajectory generation from the optimization process of an entry spacecraft shape. The disadvantage to this decoupled process is seen when a particular aeroshell does not meet in-flight requirements when integrated into Guidance, Navigation, and Control simulations. It is postulated that the integration of a guidance algorithm into the design process will provide a real-time, rapid trajectory generation technique to enhance the robustness of vehicle design solutions. The potential benefit of this integration is a reduction in design cycles (possible cost savings) and increased accuracy in the aerothermal environment (possible mass savings). This work examines two aspects: 1) the performance of a reference tracking guidance algorithm for five different geometries with the same reference trajectory and 2) the potential of mass savings from improved aerothermal predictions. An Apollo Derived Guidance (ADG) algorithm is used in this study. The baseline geometry and five test case geometries were flown using the same baseline trajectory. The guided trajectory results are compared to separate trajectories determined in a vehicle optimization study conducted for NASA's Mars Entry, Descent, and Landing System Analysis. This study revealed several aspects regarding the potential gains and required developments for integrating a guidance algorithm into the vehicle optimization environment. First, the generation of flight feasible trajectories is only as good as the robustness of the guidance algorithm. The set of dispersed geometries modelled aerodynamic dispersions that ranged from +/-1% to +/-17% and a single extreme case was modelled where the aerodynamics were approximately 80% less than the baseline geometry. The ADG, as expected, was able to guide the vehicle into the aeroshell separation box at the target location for dispersions up to 17%, but failed for the 80% dispersion cases. Finally, the results revealed that including flight feasible trajectories for a set of dispersed geometries has the potential to save mass up to 430 kg.

Computer-based Written Emotional Disclosure: The Effects of Advance or Real-time Guidance and Moderation by Big 5 Personality Traits

PubMed Central

Beyer, Jonathan A.; Lumley, Mark A.; Latsch, Deborah A.; Oberleitner, Lindsay M.S.; Carty, Jennifer N.; Radcliffe, Alison M.

2014-01-01

Standard written emotional disclosure (WED) about stress, which is private and unguided, yields small health benefits. The effect of providing individualized guidance to writers may enhance WED, but has not been tested. This trial of computer-based WED compared two novel therapist-guided forms of WED—advance guidance (before sessions) or real-time guidance (during sessions, through instant messaging)—to both standard WED and control writing; it also tested Big 5 personality traits as moderators of guided WED. Young adult participants (n = 163) with unresolved stressful experiences were randomized to conditions, had three, 30-min computer-based writing sessions, and were reassessed 6 weeks later. Contrary to hypotheses, real-time guidance WED had poorer outcomes than the other conditions on several measures, and advance guidance WED also showed some poorer outcomes. Moderator analyses revealed that participants with low baseline agreeableness, low extraversion, or high conscientiousness had relatively poor responses to guidance. We conclude that providing guidance for WED, especially in real-time, may interfere with emotional processing of unresolved stress, particularly for people whose personalities have poor fit with this interactive form of WED. PMID:24266598

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.

Methods for design and evaluation of integrated hardware-software systems for concurrent computation

NASA Technical Reports Server (NTRS)

Pratt, T. W.

1985-01-01

Research activities and publications are briefly summarized. The major tasks reviewed are: (1) VAX implementation of the PISCES parallel programming environment; (2) Apollo workstation network implementation of the PISCES environment; (3) FLEX implementation of the PISCES environment; (4) sparse matrix iterative solver in PSICES Fortran; (5) image processing application of PISCES; and (6) a formal model of concurrent computation being developed.

Computer Viruses and Related Threats: A Management Guide.

ERIC Educational Resources Information Center

Wack, John P.; Carnahan, Lisa J.

This document contains guidance for managing the threats of computer viruses, Trojan horses, network worms, etc. and related software along with unauthorized use. It is geared towards managers of end-user groups, managers dealing with multi-user systems, personal computers, and networks. The guidance is general and addresses the vulnerabilities…

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.

RESEARCH VISIBILITY. VOCATIONAL EDUCATION IS SERVICE--VOCATIONAL GUIDANCE.

ERIC Educational Resources Information Center

LAW, GORDON F.

NINETEEN REVIEWS IN THIS ISSUE PERTAIN TO VOCATIONAL GUIDANCE AND ARE ORGANIZED BY TOPICS--(1) "SYSTEMS TECHNOLOGY IN GUIDANCE" REVIEWS AN EXPLORATORY STUDY OF INFORMATION PROCESSING PROCEDURES AND COMPUTER APPLICATIONS IN GUIDANCE, AND A CONFERENCE ON SYSTEMS DEVELOPMENT FOR VOCATIONAL GUIDANCE, (2) "CAREER DEVELOPMENT THEORY AND PRACTICE" TREATS…

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.

Apollo 16 far-ultraviolet imagery and spectra of the Large Magellanic Cloud

NASA Technical Reports Server (NTRS)

Page, T.; Carruthers, G. R.

1976-01-01

The Large Magellanic Cloud was observed by the far ultraviolet camera spectrograph from the lunar surface during the Apollo 16 mission 22 April 1972. Images were obtained with about 3 arc min resolution, in the 1,050 to 1,600 and 1,250 to 1,600 A wavelength ranges, of nearly the entire LMC. Spectra were also obtained in the 1,050 to 1,600 and 900 to 1,600 A ranges along a strip 1/4 deg wide (determined by the instrument's grid collimator) passing across the LMC. The images and spectra have been scanned with a PDS microdensitometer, and isodensity contour plots have been prepared using the Univac 1108 computer.

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.

Methods for design and evaluation of parallel computating systems (The PISCES project)

NASA Technical Reports Server (NTRS)

Pratt, Terrence W.; Wise, Robert; Haught, Mary JO

1989-01-01

The PISCES project started in 1984 under the sponsorship of the NASA Computational Structural Mechanics (CSM) program. A PISCES 1 programming environment and parallel FORTRAN were implemented in 1984 for the DEC VAX (using UNIX processes to simulate parallel processes). This system was used for experimentation with parallel programs for scientific applications and AI (dynamic scene analysis) applications. PISCES 1 was ported to a network of Apollo workstations by N. Fitzgerald.

Computerized Vocational Guidance (CVG) Systems: Evaluation for Use in Military Recruiting.

DTIC Science & Technology

1984-02-01

how to relate the two, and how to explore, project, and choose. Whether Rogerian or more directive in nature, the essential counseling ingredient is to...Conference, Princeton, NJ: Educational Testing Service, 1974, 43-69. Katz, M. R., & Shatkin, L. Computer-assisted guidance: Concepts and practices (Res. Rep...Canadian Forces Personnel Applied Research Unit, 1980. Katz, M. R., & Shatkin, L. Computer-assisted guidance: Concepts and practices (Res. Rep. RR-80-1

Further Analysis on the Mystery of the Surveyor III Dust Deposits

NASA Technical Reports Server (NTRS)

Metzger, Philip; Hintze, Paul; Trigwell, Steven; Lane, John

2011-01-01

The Apollo 12 lunar module (LM) landing near the Surveyor 1lI spacecraft at the end of 1969 has remained the primary experimental verification of the predicted physics of plume ejecta effects from a rocket engine interacting with the surface of the moon. This was made possible by the return of the Surveyor 1lI camera housing by the Apollo 12 astronauts, allowing detailed analysis of the composition of dust deposited by the Apollo 12 LM plume. It was soon realized after the initial analysis of the camera housing that the LM plume tended to remove more dust than it had deposited. In the present study, coupons from the camera housing were reexamined by a KSC research team using SEM/EDS and XPS analysis. In addition, plume effects recorded in landing videos from each Apollo mission have been studied for possible clues. Several likely scenarios are proposed to explain the Surveyor III dust observations. These include electrostatic attraction of the dust to the surface of the Surveyor as a result of electrostatic charging of the jet gas exiting the engine nozzle during descent; dust blown by the Apollo 12 LM fly-by while on its descent trajectory; dust ejected from the lunar surface due to gas forced into the soil by the Surveyor 1lI rocket nozzle, based on Darcy's law; and mechanical movement of dust during the Surveyor landing. Even though an absolute answer is not possible based on available data and theory, various computational models are employed to estimate the feasibility of each of these proposed mechanisms. Scenarios are then discussed which combine multiple mechanisms to produce results consistent with observations.

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.

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)

Concept development of automatic guidance for rotorcraft obstacle avoidance

NASA Technical Reports Server (NTRS)

Cheng, Victor H. L.

1990-01-01

The automatic guidance of rotorcraft for obstacle avoidance in nap-of-the-earth flight is studied. A hierarchical breakdown of the guidance components is used to identify the functional requirements. These requirements and anticipated sensor capabilities lead to a preliminary guidance concept, which has been evaluated via computer simulations.

The high energy multicharged particle exposure of the microbial ecology evaluation device on board the Apollo 16 spacecraft

NASA Technical Reports Server (NTRS)

Benton, E. V.; Henke, R. P.

1973-01-01

The high energy multicharged cosmic-ray-particle exposure of the Microbial Ecology Evaluation Device package on board the Apollo 16 spacecraft was monitored using cellulose nitrate, Lexan polycarbonate, nuclear emulsion, and silver chloride crystal nuclear-track detectors. The results of the analysis of these detectors include the measured particle fluences, the linear energy transfer spectra, and the integral atomic number spectrum of stopping particle density. The linear energy transfer spectrum is used to compute the fractional cell loss in human kidney (T1) cells caused by heavy particles. Because the Microbial Ecology Evaluation Device was better shielded, the high-energy multicharged particle exposure was less than that measured on the crew passive dosimeters.

Multiple burn fuel-optimal orbit transfers: Numerical trajectory computation and neighboring optimal feedback guidance

NASA Technical Reports Server (NTRS)

Chuang, C.-H.; Goodson, Troy D.; Ledsinger, Laura A.

1995-01-01

This report describes current work in the numerical computation of multiple burn, fuel-optimal orbit transfers and presents an analysis of the second variation for extremal multiple burn orbital transfers as well as a discussion of a guidance scheme which may be implemented for such transfers. The discussion of numerical computation focuses on the use of multivariate interpolation to aid the computation in the numerical optimization. The second variation analysis includes the development of the conditions for the examination of both fixed and free final time transfers. Evaluations for fixed final time are presented for extremal one, two, and three burn solutions of the first variation. The free final time problem is considered for an extremal two burn solution. In addition, corresponding changes of the second variation formulation over thrust arcs and coast arcs are included. The guidance scheme discussed is an implicit scheme which implements a neighboring optimal feedback guidance strategy to calculate both thrust direction and thrust on-off times.

Strap-Down Inertial Systems

DTIC Science & Technology

1978-05-01

navigation computer (SNC), sepa- rate alterable memory units for the computer, a control /display unit (CDU), a computer control unit (CCU), and a non ...AND SYSTEM Advisory Group for Aerospace Research and Development, Paris (France). Presented at the 15th Meeting of the Guidance and Control Panel of... Group , Redondo Beach, Calif.) American Institute of Aeronautics and Astronautics, Guidance and Control Conference, Key Biscayne, Fla., August 20-22

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.

Small-group, computer-mediated argumentation in middle-school classrooms: the effects of gender and different types of online teacher guidance.

PubMed

Asterhan, Christa S C; Schwarz, Baruch B; Gil, Julia

2012-09-01

Research has shown the importance of careful teacher support during collaborative group work to promote productive discourse between students (Webb, 2009). However, this research has traditionally focused on face-to-face communication. The role of online teacher guidance of small-group computer-mediated discussions has received little attention, especially in secondary school classroom settings. Researchers of computer-supported collaborative learning (CSCL), on the other hand, have traditionally focused on software-embedded features, such as scripts, to support a-synchronous peer dialogue, and less so on human guidance of synchronous group discussions. The main aim of the present in vivo, experimental study is to examine whether online teacher guidance can improve the quality of small-group synchronous discussions, and whether different types of guidance (epistemic or interaction guidance) affect these discussions differently, when compared to an unguided condition. The second goal of this study is to explore potential differences between all-female and all-male discussion groups. Eighty-two 9th graders (three classrooms) and six teachers from a rural high school in Israel. Whereas epistemic guidance only improved aspects of the argumentative quality of the discussion, interaction guidance only improved aspects of collaboration. Discussions of all-girls groups scored higher on aspects of collaboration and argumentative quality, compared to all-boys groups. The findings show that teacher guidance of synchronous, online discussions in classrooms is realizable and reasonably reaches its intended goals. Training should be focused on acquiring various guidance strategies to augment their beneficial effects. Furthermore, future research should pay more attention to potential gender differences in peer-to-peer argumentation. ©2011 The British Psychological Society.

Recovery and Restoration of Apollo Data - An Update

NASA Astrophysics Data System (ADS)

Williams, D. R.; Taylor, P. T.; Hills, H. K.; Nagihara, S.; Nakamura, Y.; Kiefer, W. S.; Guinness, E. A.

2017-12-01

The effort to restore Apollo lunar data, much of which was stored in obsolete formats and on unwieldy media, typically without sufficient documentation, continues to provide new insights into the workings of the Moon. The endeavor, under the auspices of the NASA Space Science Data Coordinated Archive (NSSDCA) Lunar Data Project and Planetary Data System (PDS) Lunar Data Node, and also funded by LASER and PDART proposals, is designed to take the data from the Apollo orbital instruments, astronaut experiments, and long-lived surface stations and convert them into well-documented, digital formats for archive in the NSSDCA and PDS. The data from the ALSEP (Apollo Lunar Surface Experiment Package) surface stations in particular had not been thoroughly examined. Now in standard digital formats with the aid of modern computers and algorithms, they are yielding long-term information on the lunar environment. We will review the data restoration effort in general, concentrating on data sets we have completed and those we are currently working on, which have resulted in advances in our understanding of the Moon. For example, we have restored the archived ALSEP heat flow data from Apollo 15 and 17 that covered the period from deployment to 1 January 1975 and archived them with PDS. In addition, raw data for a three month period from April to June, 1975 have been discovered and restored, and data from March 1976 through September 1977 have been read from the Apollo Work Tapes. These data confirm the subsurface temperatures at the heat flow site have been warming over many years, even at depth, and have implications for the interpretation of the heat flow coming from the Moon. Examination of the restored Lunar Ejecta And Meteorite (LEAM) data and comparison with the restored ALSEP Housekeeping data indicates that the anomalous signals recorded by LEAM are not due to electrical interference and may be due to charged dust particles. Re-examination of restored Lunar Atmospheric Composition Experiment (LACE) data is allowing measurement of diffusion rates of gaseous species in the lunar regolith, with implications for the composition of the tenuous lunar atmosphere as well as for the character of the lunar dust grains. We will discuss these results in more detail, along with other scientific advances that have emerged from the Apollo data restorations.

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.

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.

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.

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.

DISCOVER: A Computer-Based Career Guidance and Counselor-Administrative Support System. Final Report. July 1974-August 1975.

ERIC Educational Resources Information Center

Harris-Bowlsbey, JoAnn

Based on the Computerized Vocational Information System (CVIS), Project DISCOVER was conceptualized in three parts: Guidance subsystem for direct use by individuals at three age levels (grades 4-6, grades 7-12, and adult) seeking career guidance; the counselor-support subsystem; and the administrator support subsystem. Guidance development and…

Use of Apollo 17 Epoch Neutron Spectrum as a Benchmark in Testing LEND Collimated Sensor

NASA Technical Reports Server (NTRS)

Chin, Gordon; Sagdeev, R.; Milikh, G.

2011-01-01

The Apollo 17 neutron experiment LPNE provided a unique set of data on production of neutrons in the Lunar soil bombarded by Galactic Cosmic Rays (GCR). It serves as valuable "ground-truth" in the age of orbital remote sensing. We used the neutron data attributed to Apollo 17 epoch as a benchmark for testing the LEND's collimated sensor, as introduced by the geometry of collimator and efficiency of He3 counters. The latter is defined by the size of gas counter and pressure inside it. The intensity and energy spectrum of neutrons escaping the lunar surface are dependent on incident flux of Galactic Cosmic Rays (GCR) whose variability is associated with Solar Cycle and its peculiarities. We obtain first the share of neutrons entering through the field of view of collimator as a fraction of the total neutron flux by using the angular distribution of neutron exiting the Moon described by our Monte Carlo code. We computed next the count rate of the 3He sensor by using the neutron energy spectrum from McKinney et al. [JGR, 2006] and by consider geometry and gas pressure of the LEND sensor. Finally the neutron count rate obtained for the Apollo 17 epoch characterized by intermediate solar activity was adjusted to the LRO epoch characterized by low solar activity. It has been done by taking into account solar modulation potential, which affects the GCR flux, and in turn changes the neutron albedo flux.

Entry Vehicle Control System Design for the Mars Smart Lander

NASA Technical Reports Server (NTRS)

Calhoun, Philip C.; Queen, Eric M.

2002-01-01

The NASA Langley Research Center, in cooperation with the Jet Propulsion Laboratory, participated in a preliminary design study of the Entry, Descent and Landing phase for the Mars Smart Lander Project. This concept utilizes advances in Guidance, Navigation and Control technology to significantly reduce uncertainty in the vehicle landed location on the Mars surface. A candidate entry vehicle controller based on the Reaction Control System controller for the Apollo Lunar Excursion Module digital autopilot is proposed for use in the entry vehicle attitude control. A slight modification to the phase plane controller is used to reduce jet-firing chattering while maintaining good control response for the Martian entry probe application. The controller performance is demonstrated in a six-degree-of-freedom simulation with representative aerodynamics.

Development of a unified guidance system for geocentric transfer. [for solar electric propulsion spacecraft

NASA Technical Reports Server (NTRS)

Cake, J. E.; Regetz, J. D., Jr.

1975-01-01

A method is presented for open loop guidance of a solar electric propulsion spacecraft to geosynchronous orbit. The method consists of determining the thrust vector profiles on the ground with an optimization computer program, and performing updates based on the difference between the actual trajectory and that predicted with a precision simulation computer program. The motivation for performing the guidance analysis during the mission planning phase is discussed, and a spacecraft design option that employs attitude orientation constraints is presented. The improvements required in both the optimization program and simulation program are set forth, together with the efforts to integrate the programs into the ground support software for the guidance system.

Development of a unified guidance system for geocentric transfer. [solar electric propulsion spacecraft

NASA Technical Reports Server (NTRS)

Cake, J. E.; Regetz, J. D., Jr.

1975-01-01

A method is presented for open loop guidance of a solar electric propulsion spacecraft to geosynchronsus orbit. The method consists of determining the thrust vector profiles on the ground with an optimization computer program, and performing updates based on the difference between the actual trajectory and that predicted with a precision simulation computer program. The motivation for performing the guidance analysis during the mission planning phase is discussed, and a spacecraft design option that employs attitude orientation constraints is presented. The improvements required in both the optimization program and simulation program are set forth, together with the efforts to integrate the programs into the ground support software for the guidance system.

Implementation of an optimum profile guidance system on STOLAND

NASA Technical Reports Server (NTRS)

Flanagan, P. F.

1978-01-01

The implementation on the STOLAND airborne digital computer of an optimum profile guidance system for the augmentor wing jet STOL research aircraft is described. Major tasks were to implement the guidance and control logic to airborne computer software and to integrate the module with the existing STOLAND navigation, display, and autopilot routines. The optimum profile guidance system comprises an algorithm for synthesizing mimimum fuel trajectories for a wide range of starting positions in the terminal area and a control law for flying the aircraft automatically along the trajectory. The avionics software developed is described along with a FORTRAN program that was constructed to reflect the modular nature and algorthms implemented in the avionics software.

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.

Benefit from NASA

NASA Image and Video Library

2001-08-01

Apollo-era technology spurred the development of cordless products that we take for granted everyday. In the 1960s, NASA asked Black Decker to develop a special drill that would be powerful enough to cut through hard layers of the lunar surface and be lightweight, compact, and operate under its own power source, allowing Apollo astronauts to collect lunar samples further away from the Lunar Experiment Module. In response, Black Decker developed a computer program that analyzed and optimized drill motor operations. From their analysis, engineers were able to design a motor that was powerful yet required minimal battery power to operate. Since those first days of cordless products, Black Decker has continued to refine this technology and they now sell their rechargeable products worldwide (i.e. the Dustbuster, cordless tools for home and industrial use, and medical tools.)

Cordless Products

NASA Technical Reports Server (NTRS)

2001-01-01

Apollo-era technology spurred the development of cordless products that we take for granted everyday. In the 1960s, NASA asked Black Decker to develop a special drill that would be powerful enough to cut through hard layers of the lunar surface and be lightweight, compact, and operate under its own power source, allowing Apollo astronauts to collect lunar samples further away from the Lunar Experiment Module. In response, Black Decker developed a computer program that analyzed and optimized drill motor operations. From their analysis, engineers were able to design a motor that was powerful yet required minimal battery power to operate. Since those first days of cordless products, Black Decker has continued to refine this technology and they now sell their rechargeable products worldwide (i.e. the Dustbuster, cordless tools for home and industrial use, and medical tools.)

Toward a Script Theory of Guidance in Computer-Supported Collaborative Learning

ERIC Educational Resources Information Center

Fischer, Frank; Kollar, Ingo; Stegmann, Karsten; Wecker, Christof

2013-01-01

This article presents an outline of a script theory of guidance for computer-supported collaborative learning (CSCL). With its 4 types of components of internal and external scripts (play, scene, role, and scriptlet) and 7 principles, this theory addresses the question of how CSCL practices are shaped by dynamically reconfigured internal…

The Role of Guidance in Computer-Based Problem Solving for the Development of Concepts of Logic.

ERIC Educational Resources Information Center

Eysink, Tessa H. S.; Dijkstra, Sanne; Kuper, Jan

2002-01-01

Describes a study at the University of Twente (Netherlands) that investigated the effect of two instructional variables, manipulation of objects and guidance, in learning to use the logical connective, conditional with a computer-based learning environment, Tarski's World, designed to teach first-order logic. Discusses results of…

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.

PLOT3D/AMES, APOLLO UNIX VERSION USING GMR3D (WITHOUT TURB3D)

NASA Technical Reports Server (NTRS)

Buning, P.

1994-01-01

PLOT3D is an interactive graphics program designed to help scientists visualize computational fluid dynamics (CFD) grids and solutions. Today, supercomputers and CFD algorithms can provide scientists with simulations of such highly complex phenomena that obtaining an understanding of the simulations has become a major problem. Tools which help the scientist visualize the simulations can be of tremendous aid. PLOT3D/AMES offers more functions and features, and has been adapted for more types of computers than any other CFD graphics program. Version 3.6b+ is supported for five computers and graphic libraries. Using PLOT3D, CFD physicists can view their computational models from any angle, observing the physics of problems and the quality of solutions. As an aid in designing aircraft, for example, PLOT3D's interactive computer graphics can show vortices, temperature, reverse flow, pressure, and dozens of other characteristics of air flow during flight. As critical areas become obvious, they can easily be studied more closely using a finer grid. PLOT3D is part of a computational fluid dynamics software cycle. First, a program such as 3DGRAPE (ARC-12620) helps the scientist generate computational grids to model an object and its surrounding space. Once the grids have been designed and parameters such as the angle of attack, Mach number, and Reynolds number have been specified, a "flow-solver" program such as INS3D (ARC-11794 or COS-10019) solves the system of equations governing fluid flow, usually on a supercomputer. Grids sometimes have as many as two million points, and the "flow-solver" produces a solution file which contains density, x- y- and z-momentum, and stagnation energy for each grid point. With such a solution file and a grid file containing up to 50 grids as input, PLOT3D can calculate and graphically display any one of 74 functions, including shock waves, surface pressure, velocity vectors, and particle traces. PLOT3D's 74 functions are organized into five groups: 1) Grid Functions for grids, grid-checking, etc.; 2) Scalar Functions for contour or carpet plots of density, pressure, temperature, Mach number, vorticity magnitude, helicity, etc.; 3) Vector Functions for vector plots of velocity, vorticity, momentum, and density gradient, etc.; 4) Particle Trace Functions for rake-like plots of particle flow or vortex lines; and 5) Shock locations based on pressure gradient. TURB3D is a modification of PLOT3D which is used for viewing CFD simulations of incompressible turbulent flow. Input flow data consists of pressure, velocity and vorticity. Typical quantities to plot include local fluctuations in flow quantities and turbulent production terms, plotted in physical or wall units. PLOT3D/TURB3D includes both TURB3D and PLOT3D because the operation of TURB3D is identical to PLOT3D, and there is no additional sample data or printed documentation for TURB3D. Graphical capabilities of PLOT3D version 3.6b+ vary among the implementations available through COSMIC. Customers are encouraged to purchase and carefully review the PLOT3D manual before ordering the program for a specific computer and graphics library. There is only one manual for use with all implementations of PLOT3D, and although this manual generally assumes that the Silicon Graphics Iris implementation is being used, informative comments concerning other implementations appear throughout the text. With all implementations, the visual representation of the object and flow field created by PLOT3D consists of points, lines, and polygons. Points can be represented with dots or symbols, color can be used to denote data values, and perspective is used to show depth. Differences among implementations impact the program's ability to use graphical features that are based on 3D polygons, the user's ability to manipulate the graphical displays, and the user's ability to obtain alternate forms of output. The Apollo implementation of PLOT3D uses some of the capabilities of Apollo's 3-dimensional graphics hardware, but does not take advantage of the shading and hidden line/surface removal capabilities of the Apollo DN10000. Although this implementation does not offer a capability for putting text on plots, it does support the use of a mouse to translate, rotate, or zoom in on views. The version 3.6b+ Apollo implementations of PLOT3D (ARC-12789) and PLOT3D/TURB3D (ARC-12785) were developed for use on Apollo computers running UNIX System V with BSD 4.3 extensions and the graphics library GMR3D Version 2.0. The standard distribution media for each of these programs is a 9-track, 6250 bpi magnetic tape in TAR format. Customers purchasing one implementation version of PLOT3D or PLOT3D/TURB3D will be given a $200 discount on each additional implementation version ordered at the same time. Version 3.6b+ of PLOT3D and PLOT3D/TURB3D are also supported for the following computers and graphics libraries: 1) generic UNIX Supercomputer and IRIS, suitable for CRAY 2/UNICOS, CONVEX, and Alliant with remote IRIS 2xxx/3xxx or IRIS 4D (ARC-12779, ARC-12784); 2) VAX computers running VMS Version 5.0 and DISSPLA Version 11.0 (ARC-12777, ARC-12781); 3) generic UNIX and DISSPLA Version 11.0 (ARC-12788, ARC-12778); and (4) Silicon Graphics IRIS 2xxx/3xxx or IRIS 4D workstations (ARC-12783, ARC-12782). Silicon Graphics Iris, IRIS 4D, and IRIS 2xxx/3xxx are trademarks of Silicon Graphics Incorporated. VAX and VMS are trademarks of Digital Electronics Corporation. DISSPLA is a trademark of Computer Associates. CRAY 2 and UNICOS are trademarks of CRAY Research, Incorporated. CONVEX is a trademark of Convex Computer Corporation. Alliant is a trademark of Alliant. Apollo and GMR3D are trademarks of Hewlett-Packard, Incorporated. UNIX is a registered trademark of AT&T.

PLOT3D/AMES, APOLLO UNIX VERSION USING GMR3D (WITH TURB3D)

NASA Technical Reports Server (NTRS)

Buning, P.

1994-01-01

PLOT3D is an interactive graphics program designed to help scientists visualize computational fluid dynamics (CFD) grids and solutions. Today, supercomputers and CFD algorithms can provide scientists with simulations of such highly complex phenomena that obtaining an understanding of the simulations has become a major problem. Tools which help the scientist visualize the simulations can be of tremendous aid. PLOT3D/AMES offers more functions and features, and has been adapted for more types of computers than any other CFD graphics program. Version 3.6b+ is supported for five computers and graphic libraries. Using PLOT3D, CFD physicists can view their computational models from any angle, observing the physics of problems and the quality of solutions. As an aid in designing aircraft, for example, PLOT3D's interactive computer graphics can show vortices, temperature, reverse flow, pressure, and dozens of other characteristics of air flow during flight. As critical areas become obvious, they can easily be studied more closely using a finer grid. PLOT3D is part of a computational fluid dynamics software cycle. First, a program such as 3DGRAPE (ARC-12620) helps the scientist generate computational grids to model an object and its surrounding space. Once the grids have been designed and parameters such as the angle of attack, Mach number, and Reynolds number have been specified, a "flow-solver" program such as INS3D (ARC-11794 or COS-10019) solves the system of equations governing fluid flow, usually on a supercomputer. Grids sometimes have as many as two million points, and the "flow-solver" produces a solution file which contains density, x- y- and z-momentum, and stagnation energy for each grid point. With such a solution file and a grid file containing up to 50 grids as input, PLOT3D can calculate and graphically display any one of 74 functions, including shock waves, surface pressure, velocity vectors, and particle traces. PLOT3D's 74 functions are organized into five groups: 1) Grid Functions for grids, grid-checking, etc.; 2) Scalar Functions for contour or carpet plots of density, pressure, temperature, Mach number, vorticity magnitude, helicity, etc.; 3) Vector Functions for vector plots of velocity, vorticity, momentum, and density gradient, etc.; 4) Particle Trace Functions for rake-like plots of particle flow or vortex lines; and 5) Shock locations based on pressure gradient. TURB3D is a modification of PLOT3D which is used for viewing CFD simulations of incompressible turbulent flow. Input flow data consists of pressure, velocity and vorticity. Typical quantities to plot include local fluctuations in flow quantities and turbulent production terms, plotted in physical or wall units. PLOT3D/TURB3D includes both TURB3D and PLOT3D because the operation of TURB3D is identical to PLOT3D, and there is no additional sample data or printed documentation for TURB3D. Graphical capabilities of PLOT3D version 3.6b+ vary among the implementations available through COSMIC. Customers are encouraged to purchase and carefully review the PLOT3D manual before ordering the program for a specific computer and graphics library. There is only one manual for use with all implementations of PLOT3D, and although this manual generally assumes that the Silicon Graphics Iris implementation is being used, informative comments concerning other implementations appear throughout the text. With all implementations, the visual representation of the object and flow field created by PLOT3D consists of points, lines, and polygons. Points can be represented with dots or symbols, color can be used to denote data values, and perspective is used to show depth. Differences among implementations impact the program's ability to use graphical features that are based on 3D polygons, the user's ability to manipulate the graphical displays, and the user's ability to obtain alternate forms of output. The Apollo implementation of PLOT3D uses some of the capabilities of Apollo's 3-dimensional graphics hardware, but does not take advantage of the shading and hidden line/surface removal capabilities of the Apollo DN10000. Although this implementation does not offer a capability for putting text on plots, it does support the use of a mouse to translate, rotate, or zoom in on views. The version 3.6b+ Apollo implementations of PLOT3D (ARC-12789) and PLOT3D/TURB3D (ARC-12785) were developed for use on Apollo computers running UNIX System V with BSD 4.3 extensions and the graphics library GMR3D Version 2.0. The standard distribution media for each of these programs is a 9-track, 6250 bpi magnetic tape in TAR format. Customers purchasing one implementation version of PLOT3D or PLOT3D/TURB3D will be given a $200 discount on each additional implementation version ordered at the same time. Version 3.6b+ of PLOT3D and PLOT3D/TURB3D are also supported for the following computers and graphics libraries: 1) generic UNIX Supercomputer and IRIS, suitable for CRAY 2/UNICOS, CONVEX, and Alliant with remote IRIS 2xxx/3xxx or IRIS 4D (ARC-12779, ARC-12784); 2) VAX computers running VMS Version 5.0 and DISSPLA Version 11.0 (ARC-12777, ARC-12781); 3) generic UNIX and DISSPLA Version 11.0 (ARC-12788, ARC-12778); and (4) Silicon Graphics IRIS 2xxx/3xxx or IRIS 4D workstations (ARC-12783, ARC-12782). Silicon Graphics Iris, IRIS 4D, and IRIS 2xxx/3xxx are trademarks of Silicon Graphics Incorporated. VAX and VMS are trademarks of Digital Electronics Corporation. DISSPLA is a trademark of Computer Associates. CRAY 2 and UNICOS are trademarks of CRAY Research, Incorporated. CONVEX is a trademark of Convex Computer Corporation. Alliant is a trademark of Alliant. Apollo and GMR3D are trademarks of Hewlett-Packard, Incorporated. UNIX is a registered trademark of AT&T.

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.

G-Guidance Interface Design for Small Body Mission Simulation

NASA Technical Reports Server (NTRS)

Acikmese, Behcet; Carson, John; Phan, Linh

2008-01-01

The G-Guidance software implements a guidance and control (G and C) algorithm for small-body, autonomous proximity operations, developed under the Small Body GN and C task at JPL. The software is written in Matlab and interfaces with G-OPT, a JPL-developed optimization package written in C that provides G-Guidance with guaranteed convergence to a solution in a finite computation time with a prescribed accuracy. The resulting program is computationally efficient and is a prototype of an onboard, real-time algorithm for autonomous guidance and control. Two thruster firing schemes are available in G-Guidance, allowing tailoring of the software for specific mission maneuvers. For example, descent, landing, or rendezvous benefit from a thruster firing at the maneuver termination to mitigate velocity errors. Conversely, ascent or separation maneuvers benefit from an immediate firing to avoid potential drift toward a second body. The guidance portion of this software explicitly enforces user-defined control constraints and thruster silence times while minimizing total fuel usage. This program is currently specialized to small-body proximity operations, but the underlying method can be generalized to other applications.

Development of STOLAND, a versatile navigation, guidance and control system

NASA Technical Reports Server (NTRS)

Young, L. S.; Hansen, Q. M.; Rouse, W. E.; Osder, S. S.

1972-01-01

STOLAND has been developed to perform navigation, guidance, control, and flight management experiments in advanced V/STOL aircraft. The experiments have broad requirements and have dictated that STOLAND be capable of providing performance that would be realistic and equivalent to a wide range of current and future avionics systems. An integrated digital concept using modern avionics components was selected as the simplest approach to maximizing versatility and growth potential. Unique flexibility has been obtained by use of a single, general-purpose digital computer for all navigation, guidance, control, and displays computation.

V/STOL AND digital avionics system for UH-1H

NASA Technical Reports Server (NTRS)

Liden, S.

1978-01-01

A hardware and software system for the Bell UH-1H helicopter was developed that provides sophisticated navigation, guidance, control, display, and data acquisition capabilities for performing terminal area navigation, guidance and control research. Two Sperry 1819B general purpose digital computers were used. One contains the development software that performs all the specified system flight computations. The second computer is available to NASA for experimental programs that run simultaneously with the other computer programs and which may, at the push of a button, replace selected computer computations. Other features that provide research flexibility include keyboard selectable gains and parameters and software generated alphanumeric and CRT displays.

Interpretation of lunar and planetary electromagnetic scattering using the full wave solutions

NASA Technical Reports Server (NTRS)

Bahar, E.; Haugland, M.

1993-01-01

Bistatic radar experiments carried out during the Apollo 14, 15, and 16 missions provide a very useful data set with which to compare theoretical models and experimental data. Vesecky, et al. report that their model for near grazing angles compares favorably with experimental data. However, for angles of incidence around 80 degrees, all the analytical models considered by Vesecky, et al. predict values for the quasi-specular cross sections that are about half the corresponding values taken from the Apollo 16 data. In this work, questions raised by this discrepancy between the reported analytical and experimental results are addressed. The unified full wave solutions are shown to be in good agreement with the bistatic radar taken during Apollo 14 and 16 missions. Using the full wave approach, the quasi-specular contributions to the scattered field from the large scale surface roughness as well as the diffuse Bragg-like scattering from the small scale surface roughness are accounted for in a unified self-consistent manner. Since the full wave computer codes for the scattering cross sections contain ground truth data only, it is shown how it can be reliably used to predict the rough surface parameters of planets based on the measured data.

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).

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.

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.

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

Safety Criticality Standards Using the French CRISTAL Code Package: Application to the AREVA NP UO{sub 2} Fuel Fabrication Plant

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

Doucet, M.; Durant Terrasson, L.; Mouton, J.

2006-07-01

Criticality safety evaluations implement requirements to proof of sufficient sub critical margins outside of the reactor environment for example in fuel fabrication plants. Basic criticality data (i.e., criticality standards) are used in the determination of sub critical margins for all processes involving plutonium or enriched uranium. There are several criticality international standards, e.g., ARH-600, which is one the US nuclear industry relies on. The French Nuclear Safety Authority (DGSNR and its advising body IRSN) has requested AREVA NP to review the criticality standards used for the evaluation of its Low Enriched Uranium fuel fabrication plants with CRISTAL V0, the recentlymore » updated French criticality evaluation package. Criticality safety is a concern for every phase of the fabrication process including UF{sub 6} cylinder storage, UF{sub 6}-UO{sub 2} conversion, powder storage, pelletizing, rod loading, assembly fabrication, and assembly transportation. Until 2003, the accepted criticality standards were based on the French CEA work performed in the late seventies with the APOLLO1 cell/assembly computer code. APOLLO1 is a spectral code, used for evaluating the basic characteristics of fuel assemblies for reactor physics applications, which has been enhanced to perform criticality safety calculations. Throughout the years, CRISTAL, starting with APOLLO1 and MORET 3 (a 3D Monte Carlo code), has been improved to account for the growth of its qualification database and for increasing user requirements. Today, CRISTAL V0 is an up-to-date computational tool incorporating a modern basic microscopic cross section set based on JEF2.2 and the comprehensive APOLLO2 and MORET 4 codes. APOLLO2 is well suited for criticality standards calculations as it includes a sophisticated self shielding approach, a P{sub ij} flux determination, and a 1D transport (S{sub n}) process. CRISTAL V0 is the result of more than five years of development work focusing on theoretical approaches and the implementation of user-friendly graphical interfaces. Due to its comprehensive physical simulation and thanks to its broad qualification database with more than a thousand benchmark/calculation comparisons, CRISTAL V0 provides outstanding and reliable accuracy for criticality evaluations for configurations covering the entire fuel cycle (i.e. from enrichment, pellet/assembly fabrication, transportation, to fuel reprocessing). After a brief description of the calculation scheme and the physics algorithms used in this code package, results for the various fissile media encountered in a UO{sub 2} fuel fabrication plant will be detailed and discussed. (authors)« less

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.

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.

An analysis of approach navigation accuracy and guidance requirements for the grand tour mission to the outer planets

NASA Technical Reports Server (NTRS)

Jones, D. W.

1971-01-01

The navigation and guidance process for the Jupiter, Saturn and Uranus planetary encounter phases of the 1977 Grand Tour interior mission was simulated. Reference approach navigation accuracies were defined and the relative information content of the various observation types were evaluated. Reference encounter guidance requirements were defined, sensitivities to assumed simulation model parameters were determined and the adequacy of the linear estimation theory was assessed. A linear sequential estimator was used to provide an estimate of the augmented state vector, consisting of the six state variables of position and velocity plus the three components of a planet position bias. The guidance process was simulated using a nonspherical model of the execution errors. Computation algorithms which simulate the navigation and guidance process were derived from theory and implemented into two research-oriented computer programs, written in FORTRAN.

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)

LUNSORT list of lunar orbiter data by LAC area

NASA Technical Reports Server (NTRS)

Hixon, S.

1976-01-01

Lunar orbiter (missions 1-5) photographic data are listed sequentially according to the number (1 to 147) LAC (Lunar Aeronautical Chart) areas by use of a computer program called LUNSORT. This listing, as well as a similar one from Apollo would simplify the task of identifying images of a given Lunar area. Instructions and sample case are included.

Houston Operations Predictor/Estimator (HOPE) programming manual, volume 1. [Apollo orbit determination

NASA Technical Reports Server (NTRS)

Daly, J. K.

1974-01-01

The programming techniques used to implement the equations and mathematical techniques of the Houston Operations Predictor/Estimator (HOPE) orbit determination program on the UNIVAC 1108 computer are described. Detailed descriptions are given of the program structure, the internal program structure, the internal program tables and program COMMON, modification and maintainence techniques, and individual subroutine documentation.

Automation of checkout for the shuttle operations era

NASA Technical Reports Server (NTRS)

Anderson, J. A.; Hendrickson, K. O.

1985-01-01

The Space Shuttle checkout is different from its Apollo predecessor. The complexity of the hardware, the shortened turnaround time, and the software that performs ground checkout are outlined. Generating new techniques and standards for software development and the management structure to control it are implemented. The utilization of computer systems for vehicle testing is high lighted.

Skylab program CSM verification analysis report

NASA Technical Reports Server (NTRS)

Schaefer, J. L.; Vanderpol, G. A.

1970-01-01

The application of the SINDA computer program for the transient thermodynamic simulation of the Apollo fuel cell/radiator system for the limit condition of the proposed Skylab mission is described. Results are included for the thermal constraints imposed upon the Pratt and Whitney fuel cell power capability by the Block 2 EPS radiator system operating under the Skylab fixed attitude orbits.

Parallel Simulation of Subsonic Fluid Dynamics on a Cluster of Workstations.

DTIC Science & Technology

1994-11-01

inside wind musical instruments. Typical simulations achieve $80\\%$ parallel efficiency (speedup/processors) using 20 HP-Apollo workstations. Detailed...TERMS AI, MIT, Artificial Intelligence, Distributed Computing, Workstation Cluster, Network, Fluid Dynamics, Musical Instruments 17. SECURITY...for example, the flow of air inside wind musical instruments. Typical simulations achieve 80% parallel efficiency (speedup/processors) using 20 HP

America's Space Program: Exploring a New Frontier. Teaching with Historic Places.

ERIC Educational Resources Information Center

Koman, Rita G.

Several hundred thousand people converged on the Kennedy Space Center (Florida) on July 16, 1969, to view the launch of the "Saturn V" rocket that would propel "Apollo 11" to the moon. The engineers and technicians watching their computer screens may secretly have kept their fingers crossed, but at two minutes before launch, a…

An Automated Method to Compute Orbital Re-entry Trajectories with Heating Constraints

NASA Technical Reports Server (NTRS)

Zimmerman, Curtis; Dukeman, Greg; Hanson, John; Fogle, Frank R. (Technical Monitor)

2002-01-01

Determining how to properly manipulate the controls of a re-entering re-usable launch vehicle (RLV) so that it is able to safely return to Earth and land involves the solution of a two-point boundary value problem (TPBVP). This problem, which can be quite difficult, is traditionally solved on the ground prior to flight. If necessary, a nearly unlimited amount of time is available to find the 'best' solution using a variety of trajectory design and optimization tools. The role of entry guidance during flight is to follow the pre- determined reference solution while correcting for any errors encountered along the way. This guidance method is both highly reliable and very efficient in terms of onboard computer resources. There is a growing interest in a style of entry guidance that places the responsibility of solving the TPBVP in the actual entry guidance flight software. Here there is very limited computer time. The powerful, but finicky, mathematical tools used by trajectory designers on the ground cannot in general be converted to do the job. Non-convergence or slow convergence can result in disaster. The challenges of designing such an algorithm are numerous and difficult. Yet the payoff (in the form of decreased operational costs and increased safety) can be substantiaL This paper presents an algorithm that incorporates features of both types of guidance strategies. It takes an initial RLV orbital re-entry state and finds a trajectory that will safely transport the vehicle to Earth. During actual flight, the computed trajectory is used as the reference to be flown by a more traditional guidance method.

Boundary Layer Transition and Trip Effectiveness on an Apollo Capsule in the JAXA High Enthalpy Shock Tunnel (HIEST) Facility

NASA Technical Reports Server (NTRS)

Kirk, Lindsay C.; Lillard, Randolph P.; Olejniczak, Joseph; Tanno, Hideyuki

2015-01-01

Computational assessments were performed to size boundary layer trips for a scaled Apollo capsule model in the High Enthalpy Shock Tunnel (HIEST) facility at the JAXA Kakuda Space Center in Japan. For stagnation conditions between 2 MJ/kg and 20 MJ/kg and between 10 MPa and 60 MPa, the appropriate trips were determined to be between 0.2 mm and 1.3 mm high, which provided kappa/delta values on the heatshield from 0.15 to 2.25. The tripped configuration consisted of an insert with a series of diamond shaped trips along the heatshield downstream of the stagnation point. Surface heat flux measurements were obtained on a capsule with a 250 mm diameter, 6.4% scale model, and pressure measurements were taken at axial stations along the nozzle walls. At low enthalpy conditions, the computational predictions agree favorably to the test data along the heatshield centerline. However, agreement becomes less favorable as the enthalpy increases conditions. The measured surface heat flux on the heatshield from the HIEST facility was under-predicted by the computations in these cases. Both smooth and tripped configurations were tested for comparison, and a post-test computational analysis showed that kappa/delta values based on the as-measured stagnation conditions ranged between 0.5 and 1.2. Tripped configurations for both 0.6 mm and 0.8 mm trip heights were able to effectively trip the flow to fully turbulent for a range of freestream conditions.

Program For Generating Interactive Displays

NASA Technical Reports Server (NTRS)

Costenbader, Jay; Moleski, Walt; Szczur, Martha; Howell, David; Engelberg, Norm; Li, Tin P.; Misra, Dharitri; Miller, Philip; Neve, Leif; Wolf, Karl;

Another Program For Generating Interactive Graphics

NASA Technical Reports Server (NTRS)

Costenbader, Jay; Moleski, Walt; Szczur, Martha; Howell, David; Engelberg, Norm; Li, Tin P.; Misra, Dharitri; Miller, Philip; Neve, Leif; Wolf, Karl;

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.

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.

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.

A Functional Description of a Digital Flight Test System for Navigation and Guidance Research in the Terminal Area

NASA Technical Reports Server (NTRS)

Hegarty, D. M.

1974-01-01

A guidance, navigation, and control system, the Simulated Shuttle Flight Test System (SS-FTS), when interfaced with existing aircraft systems, provides a research facility for studying concepts for landing the space shuttle orbiter and conventional jet aircraft. The SS-FTS, which includes a general-purpose computer, performs all computations for precisely following a prescribed approach trajectory while properly managing the vehicle energy to allow safe arrival at the runway and landing within prescribed dispersions. The system contains hardware and software provisions for navigation with several combinations of possible navigation aids that have been suggested for the shuttle. The SS-FTS can be reconfigured to study different guidance and navigation concepts by changing only the computer software, and adapted to receive different radio navigation information through minimum hardware changes. All control laws, logic, and mode interlocks reside solely in the computer software.

Design and Flight Evaluation of an Integrated Navigation and Near-Terrain Helicopter Guidance System for Nighttime and Adverse Weather Operations

DOT National Transportation Integrated Search

1994-08-01

NASA and the U.S. Army have designed, developed, and flight evaluated a : Computer Aiding for Low-Altitude Helicopter Flight (CALAHF) guidance system. : This system provides guidance to the pilot for near-terrain covert helicopter : operations. It au...

NASP guidance design for vehicle autonomy

NASA Astrophysics Data System (ADS)

Wagner, E. A.; Li, I.; Nguyen, D. D.; Nguyen, P. L.

1990-10-01

Vehicle guidance for General Dynamics' NASP vehicle is planned to be self-contained onboard the vehicle, and independent of any ground support during the mission. It will include real-time onboard abort and ascent trajectory optimization capability. Although these features should be considered a natural outgrowth of research in guidance and trajectory optimization and advances in computation, facilitating full vehicle autonomy for NASP represents a significant advance relative to any flight-demonstrated guidance. Algorithms and processing requirements for autonomous NASP vehicle guidance are considered.

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.

The Role of Breccia Lenses in Regolith Generation From the Formation of Small, Simple Craters: Application to the Apollo 15 Landing Site

NASA Astrophysics Data System (ADS)

Hirabayashi, M.; Howl, B. A.; Fassett, C. I.; Soderblom, J. M.; Minton, D. A.; Melosh, H. J.

2018-02-01

Impact cratering is likely a primary agent of regolith generation on airless bodies. Regolith production via impact cratering has long been a key topic of study since the Apollo era. The evolution of regolith due to impact cratering, however, is not well understood. A better formulation is needed to help quantify the formation mechanism and timescale of regolith evolution. Here we propose an analytically derived stochastic model that describes the evolution of regolith generated by small, simple craters. We account for ejecta blanketing as well as regolith infilling of the transient crater cavity. Our results show that the regolith infilling plays a key role in producing regolith. Our model demonstrates that because of the stochastic nature of impact cratering, the regolith thickness varies laterally, which is consistent with earlier work. We apply this analytical model to the regolith evolution at the Apollo 15 site. The regolith thickness is computed considering the observed crater size-frequency distribution of small, simple lunar craters (< 381 m in radius for ejecta blanketing and <100 m in radius for the regolith infilling). Allowing for some amount of regolith coming from the outside of the area, our result is consistent with an empirical result from the Apollo 15 seismic experiment. Finally, we find that the timescale of regolith growth is longer than that of crater equilibrium, implying that even if crater equilibrium is observed on a cratered surface, it is likely that the regolith thickness is still evolving due to additional impact craters.

The Prediction of the Motion of Atens, Apollos and Amors over Long Intervals of Time

NASA Astrophysics Data System (ADS)

Wlodarczyk, I.

2002-01-01

Equations of motion of 930 Atens, Apollos and Amors (AAA) were integrated 300,000 years forward using RA15 Everhart method (Everhart, 1974). The Osterwinter model of Solar System was used (Osterwinter and Cohen, 1972). The differences in mean anomaly between unchanged and changed orbits were calculated. The changed orbits were constructed by adding or subtracting to the starting orbital elements one after the other errors of determination of orbital elements. When the differences in mean anomaly were greater than 360 deg. then computations were stopped. In almost all cases after about 1000 years in forwards or backwards integrations differences in mean anomaly between neighbors orbits growth rapidly. It denotes that it is impossible to predict behavior of asteroids outside this time. This time I have called time of stability.

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

Learning Density in Vanuatu High School with Computer Simulation: Influence of Different Levels of Guidance

ERIC Educational Resources Information Center

Moli, Lemuel; Delserieys, Alice Pedregosa; Impedovo, Maria Antonietta; Castera, Jeremy

2017-01-01

This paper presents a study on discovery learning of scientific concepts with the support of computer simulation. In particular, the paper will focus on the effect of the levels of guidance on students with a low degree of experience in informatics and educational technology. The first stage of this study was to identify the common misconceptions…

Case Studies in Practical Career Guidance, Number 5: Computerized Vocational Information System Willowbrook High School, Villa Park, Illinois.

ERIC Educational Resources Information Center

Arutunian, Carol Ann

The Computerized Vocational Information System (CVIS) at Willowbrook High School in Villa Park, Illinois, uses the computer as a tool to help each student explore a wide range of occupations and educational opportunities with some feedback from his own record of ability, achievement, and interest. Computer-based guidance systems are considered a…

Small-Group, Computer-Mediated Argumentation in Middle-School Classrooms: The Effects of Gender and Different Types of Online Teacher Guidance

ERIC Educational Resources Information Center

Asterhan, Christa S. C.; Schwarz, Baruch B.; Gil, Julia

2012-01-01

CoBackground: Research has shown the importance of careful teacher support during collaborative group work to promote productive discourse between students (Webb, 2009). However, this research has traditionally focused on face-to-face communication. The role of online teacher guidance of small-group computer-mediated discussions has received…

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.

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.

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.

Error Free Software

NASA Technical Reports Server (NTRS)

1985-01-01

A mathematical theory for development of "higher order" software to catch computer mistakes resulted from a Johnson Space Center contract for Apollo spacecraft navigation. Two women who were involved in the project formed Higher Order Software, Inc. to develop and market the system of error analysis and correction. They designed software which is logically error-free, which, in one instance, was found to increase productivity by 600%. USE.IT defines its objectives using AXES -- a user can write in English and the system converts to computer languages. It is employed by several large corporations.

AutoCNet: A Python library for sparse multi-image correspondence identification for planetary data

NASA Astrophysics Data System (ADS)

Laura, Jason; Rodriguez, Kelvin; Paquette, Adam C.; Dunn, Evin

2018-01-01

In this work we describe the AutoCNet library, written in Python, to support the application of computer vision techniques for n-image correspondence identification in remotely sensed planetary images and subsequent bundle adjustment. The library is designed to support exploratory data analysis, algorithm and processing pipeline development, and application at scale in High Performance Computing (HPC) environments for processing large data sets and generating foundational data products. We also present a brief case study illustrating high level usage for the Apollo 15 Metric camera.

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.

An Automated Method to Compute Orbital Re-Entry Trajectories with Heating Constraints

NASA Technical Reports Server (NTRS)

Zimmerman, Curtis; Dukeman, Greg; Hanson, John; Fogle, Frank R. (Technical Monitor)

2002-01-01

Determining how to properly manipulate the controls of a re-entering re-usable launch vehicle (RLV) so that it is able to safely return to Earth and land involves the solution of a two-point boundary value problem (TPBVP). This problem, which can be quite difficult, is traditionally solved on the ground prior to flight. If necessary, a nearly unlimited amount of time is available to find the "best" solution using a variety of trajectory design and optimization tools. The role of entry guidance during flight is to follow the pre-determined reference solution while correcting for any errors encountered along the way. This guidance method is both highly reliable and very efficient in terms of onboard computer resources. There is a growing interest in a style of entry guidance that places the responsibility of solving the TPBVP in the actual entry guidance flight software. Here there is very limited computer time. The powerful, but finicky, mathematical tools used by trajectory designers on the ground cannot in general be made to do the job. Nonconvergence or slow convergence can result in disaster. The challenges of designing such an algorithm are numerous and difficult. Yet the payoff (in the form of decreased operational costs and increased safety) can be substantial. This paper presents an algorithm that incorporates features of both types of guidance strategies. It takes an initial RLV orbital re-entry state and finds a trajectory that will safely transport the vehicle to a Terminal Area Energy Management (TAEM) region. During actual flight, the computed trajectory is used as the reference to be flown by a more traditional guidance method.

Hidden Figures and Katherine Johnson

NASA Image and Video Library

2016-12-23

Katherine Johnson and other "Human Computers" played an integral role in the early days of America's space program. With a slide rule and a pencil, Katherine was responsible for calculating orbital trajectories of numerous space flights, including Alan Shepard, the first American in space and the Apollo 11 flight to the Moon. Her brilliance and perseverance still resonate with employees at NASA's Ames Research Center today!

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.

Function library programming to support B89 evaluation of Sheffield Apollo RS50 DCC (Direct Computer Control) CMM (Coordinate Measuring Machine)

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

Frank, R.N.

1990-02-28

The Inspection Shop at Lawrence Livermore Lab recently purchased a Sheffield Apollo RS50 Direct Computer Control Coordinate Measuring Machine. The performance of the machine was specified to conform to B89 standard which relies heavily upon using the measuring machine in its intended manner to verify its accuracy (rather than parametric tests). Although it would be possible to use the interactive measurement system to perform these tasks, a more thorough and efficient job can be done by creating Function Library programs for certain tasks which integrate Hewlett-Packard Basic 5.0 language and calls to proprietary analysis and machine control routines. This combinationmore » provides efficient use of the measuring machine with a minimum of keyboard input plus an analysis of the data with respect to the B89 Standard rather than a CMM analysis which would require subsequent interpretation. This paper discusses some characteristics of the Sheffield machine control and analysis software and my use of H-P Basic language to create automated measurement programs to support the B89 performance evaluation of the CMM. 1 ref.« less

Computer-Assisted Guidance in New York City High Schools: A Demonstration of Feasibility and Impact on Students.

ERIC Educational Resources Information Center

Heller, Barbara R.; Chitayat, Linda

This report covers three time periods during which students in five New York City high schools had use of a Computer Assisted Guidance (CAG) system. The basic objectives of the CAG project were to demonstrate the feasibility of using an automated system to provide high school students with factual and current information on colleges and careers,…

A Differential Feature-Cost Analysis of Fifteen Computer-Assisted Career Guidance Systems: Technical Report Number 10. (Fourth Edition).

ERIC Educational Resources Information Center

Sampson, James P., Jr.; And Others

This study examined similarities and differences among 15 computer-assisted career guidance (CACG) systems: (1) the Career Information System; (2) Choices; (3) Choices CT; (4) Choices Jr; (5) MODULAR C-LECT; (6) COIN; (7) COIN Jr; (8) DISCOVER for Colleges and Adults; (9) DISCOVER for High Schools; (10) DISCOVER for Junior High and Middle Schools;…

The development of regulatory expectations for computer-based safety systems for the UK nuclear programme

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

Hughes, P. J.; Westwood, R.N; Mark, R. T.

2006-07-01

The Nuclear Installations Inspectorate (NII) of the UK's Health and Safety Executive (HSE) has completed a review of their Safety Assessment Principles (SAPs) for Nuclear Installations recently. During the period of the SAPs review in 2004-2005 the designers of future UK naval reactor plant were optioneering the control and protection systems that might be implemented. Because there was insufficient regulatory guidance available in the naval sector to support this activity the Defence Nuclear Safety Regulator (DNSR) invited the NII to collaborate with the production of a guidance document that provides clarity of regulatory expectations for the production of safety casesmore » for computer based safety systems. A key part of producing regulatory expectations was identifying the relevant extant standards and sector guidance that reflect good practice. The three principal sources of such good practice were: IAEA Safety Guide NS-G-1.1 (Software for Computer Based Systems Important to Safety in Nuclear Power Plants), European Commission consensus document (Common Position of European Nuclear Regulators for the Licensing of Safety Critical Software for Nuclear Reactors) and IEC nuclear sector standards such as IEC60880. A common understanding has been achieved between the NII and DNSR and regulatory guidance developed which will be used by both NII and DNSR in the assessment of computer-based safety systems and in the further development of more detailed joint technical assessment guidance for both regulatory organisations. (authors)« less

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.

[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.

Lessons learned in creating spacecraft computer systems: Implications for using Ada (R) for the space station

NASA Technical Reports Server (NTRS)

Tomayko, James E.

1986-01-01

Twenty-five years of spacecraft onboard computer development have resulted in a better understanding of the requirements for effective, efficient, and fault tolerant flight computer systems. Lessons from eight flight programs (Gemini, Apollo, Skylab, Shuttle, Mariner, Voyager, and Galileo) and three reserach programs (digital fly-by-wire, STAR, and the Unified Data System) are useful in projecting the computer hardware configuration of the Space Station and the ways in which the Ada programming language will enhance the development of the necessary software. The evolution of hardware technology, fault protection methods, and software architectures used in space flight in order to provide insight into the pending development of such items for the Space Station are reviewed.

Nuclear emulsion measurements of the astronauts' radiation exposure on the Apollo-Soyuz mission

NASA Technical Reports Server (NTRS)

Schaefer, H. J.; Sullivan, J. J.

1976-01-01

On the Apollo-Soyuz mission each astronaut carried one passive dosimeter containing nuclear photographic emulsions, plastic foils, TLD chips, and neutron-activation foils for recording radiation exposure. This report is limited to the presentation of data retrieved from nuclear emulsions. Protons, most of them trapped particles encountered in numerous passes through the South Atlantic Anomaly, contributed by far the largest share to the mission dose. Their linear energy transfer (LET) spectrum was established from track and grain counts in a G.5 emulsion which is used for medium and high energies, and from ender counts in a K.2 emulsion which is used for low energies. The total mission fluence of protons was found to be equivalent to a unidirectional beam of 448,500 square centimeters. The broad spectrum was broken down into small LET intervals, which allowed for the computation of absorbed doses and dose equivalents. The totals are 51 millirad and 74 millirem. Counts of disintegration stars in K.2 emulsion are incomplete at present. While a total of 467 stars were identified, counting their prong numbers is still in progress. It was concluded that the Apollo-Soyuz astronauts' radiation exposure as such did not contain anything out of the ordinary that would seem to require special attention.

Doppler measurements of the ionosphere on the occasion of the Apollo-Soyuz test project. Part 2: Inversion of differential and rotating Doppler shifts

NASA Technical Reports Server (NTRS)

Gay, R. H.; Grossi, M. D.

1975-01-01

The preparation of the analytical approach and of the related software used in the inversion of the differential and rotating Doppler data obtained from the ionospheric experiment of the Apollo-Soyuz Test Project (ASTP) is discussed. These data were collected in space-to-space paths (between the ASTP Docking Module (DM) and the Apollo Command Service Module and in space-to-ground paths (between the DM and ground). The Doppler links operated at 162 and 324 MHz and have an accuracy better than 3 MHz over 10-sec integration time. The inversion approach was tested with dummy data obtained with a computer simulation. It was found that a measurement accuracy of 1 to 10% in the value of the horizontal electron density gradient at 221-km altitude can be achieved, in space-to-space paths. For space-to-ground paths near the orbital plane, possible effects of the horizontal gradients on the received differential Doppler shifts were identified. It was possible to reduce the gradient-associated errors in the inversion that leads to the columnar electron content by approximately one-half. Accuracies of 5 to 10% in columnar electron content are achievable, with this gradient-compensation technique.

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)

Using Automated Scores of Student Essays to Support Teacher Guidance in Classroom Inquiry

ERIC Educational Resources Information Center

Gerard, Libby F.; Linn, Marcia C.

2016-01-01

Computer scoring of student written essays about an inquiry topic can be used to diagnose student progress both to alert teachers to struggling students and to generate automated guidance. We identify promising ways for teachers to add value to automated guidance to improve student learning. Three teachers from two schools and their 386 students…

Year 2000 (Y2K) computer compliance guide; guidance for FDA personnel. Food and Drug Administration. Notice.

PubMed

1999-05-14

The Food and Drug Administration (FDA) is announcing the availability of a new compliance policy guide (CPG) entitled "Year 2000 (Y2K) Computer Compliance" (section 160-800). This guidance document represents the agency's current thinking on the manufacturing and distribution of domestic and imported products regulated by FDA using computer systems that may not perform properly before, or during, the transition to the year 2000 (Y2K). The text of the CPG is included in this notice. This compliance guidance document is an update to the Compliance Policy Guides Manual (August 1996 edition). It is a new CPG, and it will be included in the next printing of the Compliance Policy Guides Manual. This CPG is intended for FDA personnel, and it is available electronically to the public.

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.

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.

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.

A lateral guidance algorithm to reduce the post-aerobraking burn requirements for a lift-modulated orbital transfer vehicle. M.S. Thesis

NASA Technical Reports Server (NTRS)

Herman, G. C.

1986-01-01

A lateral guidance algorithm which controls the location of the line of intersection between the actual and desired orbital planes (the hinge line) is developed for the aerobraking phase of a lift-modulated orbital transfer vehicle. The on-board targeting algorithm associated with this lateral guidance algorithm is simple and concise which is very desirable since computation time and space are limited on an on-board flight computer. A variational equation which describes the movement of the hinge line is derived. Simple relationships between the plane error, the desired hinge line position, the position out-of-plane error, and the velocity out-of-plane error are found. A computer simulation is developed to test the lateral guidance algorithm for a variety of operating conditions. The algorithm does reduce the total burn magnitude needed to achieve the desired orbit by allowing the plane correction and perigee-raising burn to be combined in a single maneuver. The algorithm performs well under vacuum perigee dispersions, pot-hole density disturbance, and thick atmospheres. The results for many different operating conditions are presented.

Accuracy of percutaneous soft-tissue interventions using a multi-axis, C-arm CT system and 3D laser guidance.

PubMed

Kostrzewa, Michael; Rathmann, Nils; Kara, Kerim; Schoenberg, Stefan O; Diehl, Steffen J

2015-10-01

Purpose of this phantom study was to compare the accuracy of needle placement using a multi-axis, C-arm-based, flat-panel, cone-beam computed tomography system (CBCT guidance) with that under multi-detector computed tomography guidance (MDCT guidance). In an abdominal phantom, eight lesions (six lesions in the liver and two in the renal pelvises, respectively) were each punctured in-plane and off-plane with a 20G needle under CBCT and MDCT guidance. Access paths were initially defined and reproduced identically on the two systems. In total, 32 interventions were conducted. CBCT and MDCT guidance was compared prospectively with respect to technical success, accuracy, and overall procedural time. All 32 interventions were technically successful in that it was possible to hit the respective lesion in each procedure. When comparing the accuracy of MDCT to CBCT guidance there was no significant difference in absolute, angular, and longitudinal deviation for either in- or off-plane interventions. Overall procedural duration was significantly longer under CBCT guidance for in-plane interventions (888 vs 527s, p=0.00005), whereas, for off-plane procedures there was no significant difference between CBCT and MDCT guidance (920 vs 701s, p=0.08). Off-plane interventions took significantly longer than in-plane interventions under MDCT guidance (701 vs 527s, p=0.03), whereas under CBCT guidance no significant difference could be found between off- and in-plane procedures (920 vs. 888s, p=0.2). In this phantom study, we could show that percutaneous soft-tissue interventions under CBCT guidance can be conducted with an accuracy comparable to that under MDCT guidance. Although overall procedural duration is in general shorter using MDCT guidance, CBCT-guided interventions offer the advantage of more degrees of freedom, which is of particular importance for off-plane procedures. Copyright © 2015 Elsevier Ireland Ltd. All rights reserved.

The shallow elastic structure of the lunar crust: New insights from seismic wavefield gradient analysis

NASA Astrophysics Data System (ADS)

Sollberger, David; Schmelzbach, Cedric; Robertsson, Johan O. A.; Greenhalgh, Stewart A.; Nakamura, Yosio; Khan, Amir

2016-10-01

Enigmatic lunar seismograms recorded during the Apollo 17 mission in 1972 have so far precluded the identification of shear-wave arrivals and hence the construction of a comprehensive elastic model of the shallow lunar subsurface. Here, for the first time, we extract shear-wave information from the Apollo active seismic data using a novel waveform analysis technique based on spatial seismic wavefield gradients. The star-like recording geometry of the active seismic experiment lends itself surprisingly well to compute spatial wavefield gradients and rotational ground motion as a function of time. These observables, which are new to seismic exploration in general, allowed us to identify shear waves in the complex lunar seismograms, and to derive a new model of seismic compressional and shear-wave velocities in the shallow lunar crust, critical to understand its lithology and constitution, and its impact on other geophysical investigations of the Moon's deep interior.

Man-rated flight software for the F-8 DFBW program

NASA Technical Reports Server (NTRS)

Bairnsfather, R. R.

1975-01-01

The design, implementation, and verification of the flight control software used in the F-8 DFBW program are discussed. Since the DFBW utilizes an Apollo computer and hardware, the procedures, controls, and basic management techniques employed are based on those developed for the Apollo software system. Program Assembly Control, simulator configuration control, erasable-memory load generation, change procedures and anomaly reporting are discussed. The primary verification tools--the all-digital simulator, the hybrid simulator, and the Iron Bird simulator--are described, as well as the program test plans and their implementation on the various simulators. Failure-effects analysis and the creation of special failure-generating software for testing purposes are described. The quality of the end product is evidenced by the F-8 DFBW flight test program in which 42 flights, totaling 58 hours of flight time, were successfully made without any DFCS inflight software, or hardware, failures.

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.

The Use of Laser Guidance Reduces Fluoroscopy Time for C-Arm Cone-Beam Computed Tomography-Guided Biopsies

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

Kroes, Maarten W., E-mail: Maarten.Kroes@radboudumc.nl; Strijen, Marco J. L. van, E-mail: m.van.strijen@antoniusziekenhuis.nl; Braak, Sicco J., E-mail: sjbraak@gmail.com

2016-09-15

PurposeWhen using laser guidance for cone-beam computed tomography (CBCT)-guided needle interventions, planned needle paths are visualized to the operator without the need to switch between entry- and progress-view during needle placement. The current study assesses the effect of laser guidance during CBCT-guided biopsies on fluoroscopy and procedure times.Materials and MethodsProspective data from 15 CBCT-guided biopsies of 8–65 mm thoracic and abdominal lesions assisted by a ceiling-mounted laser guidance technique were compared to retrospective data of 36 performed CBCT-guided biopsies of lesions >20 mm using the freehand technique. Fluoroscopy time, procedure time, and number of CBCT-scans were recorded. All data are presented asmore » median (ranges).ResultsFor biopsies using the freehand technique, more fluoroscopy time was necessary to guide the needle onto the target, 165 s (83–333 s) compared to 87 s (44–190 s) for laser guidance (p < 0.001). Procedure times were shorter for freehand-guided biopsies, 24 min versus 30 min for laser guidance (p < 0.001).ConclusionThe use of laser guidance during CBCT-guided biopsies significantly reduces fluoroscopy time.« less

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.

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.

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

COLD-SAT dynamic model

NASA Technical Reports Server (NTRS)

Adams, Neil S.; Bollenbacher, Gary

1992-01-01

This report discusses the development and underlying mathematics of a rigid-body computer model of a proposed cryogenic on-orbit liquid depot storage, acquisition, and transfer spacecraft (COLD-SAT). This model, referred to in this report as the COLD-SAT dynamic model, consists of both a trajectory model and an attitudinal model. All disturbance forces and torques expected to be significant for the actual COLD-SAT spacecraft are modeled to the required degree of accuracy. Control and experimental thrusters are modeled, as well as fluid slosh. The model also computes microgravity disturbance accelerations at any specified point in the spacecraft. The model was developed by using the Boeing EASY5 dynamic analysis package and will run on Apollo, Cray, and other computing platforms.

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...

In-App Reflection Guidance: Lessons Learned Across Four Field Trials at the Workplace

ERIC Educational Resources Information Center

Fessl, Angela; Wesiak, Gudrun; Rivera-Pelayo, Verónica; Feyertag, Sandra; Pammer, Viktoria

2017-01-01

This paper presents a concept for in-app reflection guidance and its evaluation in four work-related field trials. By synthesizing across four field trials, we can show that computer-based reflection guidance can function in the workplace, in the sense of being accepted as technology, being perceived as useful and leading to reflective learning.…

Improved guidance hardware study for the scout launch vehicle

NASA Technical Reports Server (NTRS)

Schappell, R. T.; Salis, M. L.; Mueller, R.; Best, L. E.; Bradt, A. J.; Harrison, R.; Burrell, J. H.

1972-01-01

A market survey and evaluation of inertial guidance systems (inertial measurement units and digital computers) were made. Comparisons were made to determine the candidate systems for use in the Scout launch vehicle. Error analyses were made using typical Scout trajectories. A reaction control system was sized for the fourth stage. The guidance hardware to Scout vehicle interface was listed.

Advances in Orion's On-Orbit Guidance and Targeting System Architecture

NASA Technical Reports Server (NTRS)

Scarritt, Sara K.; Fill, Thomas; Robinson, Shane

2015-01-01

NASA's manned spaceflight programs have a rich history of advancing onboard guidance and targeting technology. In order to support future missions, the guidance and targeting architecture for the Orion Multi-Purpose Crew Vehicle must be able to operate in complete autonomy, without any support from the ground. Orion's guidance and targeting system must be sufficiently flexible to easily adapt to a wide array of undecided future missions, yet also not cause an undue computational burden on the flight computer. This presents a unique design challenge from the perspective of both algorithm development and system architecture construction. The present work shows how Orion's guidance and targeting system addresses these challenges. On the algorithm side, the system advances the state-of-the-art by: (1) steering burns with a simple closed-loop guidance strategy based on Shuttle heritage, and (2) planning maneuvers with a cutting-edge two-level targeting routine. These algorithms are then placed into an architecture designed to leverage the advantages of each and ensure that they function in concert with one another. The resulting system is characterized by modularity and simplicity. As such, it is adaptable to the on-orbit phases of any future mission that Orion may attempt.

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)

Feasibility Study of Needle Placement in Percutaneous Vertebroplasty: Cone-Beam Computed Tomography Guidance Versus Conventional Fluoroscopy

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

Braak, Sicco J., E-mail: sjbraak@gmail.com; Zuurmond, Kirsten, E-mail: kirsten.zuurmond@philips.com; Aerts, Hans C. J., E-mail: hans.cj.aerts@philips.com

2013-08-01

ObjectiveTo investigate the accuracy, procedure time, fluoroscopy time, and dose area product (DAP) of needle placement during percutaneous vertebroplasty (PVP) using cone-beam computed tomography (CBCT) guidance versus fluoroscopy.Materials and MethodsOn 4 spine phantoms with 11 vertebrae (Th7-L5), 4 interventional radiologists (2 experienced with CBCT guidance and two inexperienced) punctured all vertebrae in a bipedicular fashion. Each side was randomization to either CBCT guidance or fluoroscopy. CBCT guidance is a sophisticated needle guidance technique using CBCT, navigation software, and real-time fluoroscopy. The placement of the needle had to be to a specific target point. After the procedure, CBCT was performed tomore » determine the accuracy, procedure time, fluoroscopy time, and DAP. Analysis of the difference between methods and experience level was performed.ResultsMean accuracy using CBCT guidance (2.61 mm) was significantly better compared with fluoroscopy (5.86 mm) (p < 0.0001). Procedure time was in favor of fluoroscopy (7.39 vs. 10.13 min; p = 0.001). Fluoroscopy time during CBCT guidance was lower, but this difference is not significant (71.3 vs. 95.8 s; p = 0.056). DAP values for CBCT guidance and fluoroscopy were 514 and 174 mGy cm{sup 2}, respectively (p < 0.0001). There was a significant difference in favor of experienced CBCT guidance users regarding accuracy for both methods, procedure time of CBCT guidance, and added DAP values for fluoroscopy.ConclusionCBCT guidance allows users to perform PVP more accurately at the cost of higher patient dose and longer procedure time. Because procedural complications (e.g., cement leakage) are related to the accuracy of the needle placement, improvements in accuracy are clinically relevant. Training in CBCT guidance is essential to achieve greater accuracy and decrease procedure time/dose values.« less

BENCHMARK DOSE TECHNICAL GUIDANCE DOCUMENT ...

EPA Pesticide Factsheets

The purpose of this document is to provide guidance for the Agency on the application of the benchmark dose approach in determining the point of departure (POD) for health effects data, whether a linear or nonlinear low dose extrapolation is used. The guidance includes discussion on computation of benchmark doses and benchmark concentrations (BMDs and BMCs) and their lower confidence limits, data requirements, dose-response analysis, and reporting requirements. This guidance is based on today's knowledge and understanding, and on experience gained in using this approach.

SSTAC/ARTS review of the draft Integrated Technology Plan (ITP). Volume 6: Controls and guidance

NASA Technical Reports Server (NTRS)

1991-01-01

Viewgraphs of briefings from the Space Systems and Technology Advisory Committee (SSTAC)/ARTS review of the draft Integrated Technology Plan (ITP) on controls and guidance are included. Topics covered include: strategic avionics technology planning and bridging programs; avionics technology plan; vehicle health management; spacecraft guidance research; autonomous rendezvous and docking; autonomous landing; computational control; fiberoptic rotation sensors; precision instrument and telescope pointing; microsensors and microinstruments; micro guidance and control initiative; and earth-orbiting platforms controls-structures interaction.

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.

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.

V/STOLAND digital avionics system for XV-15 tilt rotor

NASA Technical Reports Server (NTRS)

Liden, S.

1980-01-01

A digital flight control system for the tilt rotor research aircraft provides sophisticated navigation, guidance, control, display and data acquisition capabilities for performing terminal area navigation, guidance and control research. All functions of the XV-15 V/STOLAND system were demonstrated on the NASA-ARC S-19 simulation facility under a comprehensive dynamic acceptance test. The most noteworthy accomplishments of the system are: (1) automatic configuration control of a tilt-rotor aircraft over the total operating range; (2) total hands-off landing to touchdown on various selectable straight-in glide slopes and on a flight path that includes a two-revolution helix; (3) automatic guidance along a programmed three-dimensional reference flight path; (4) navigation data for the automatic guidance computed on board, based on VOR/DME, TACAN, or MLS navid data; and (5) integration of a large set of functions in a single computer, utilizing 16k words of storage for programs and data.

Home Insulation

NASA Technical Reports Server (NTRS)

1994-01-01

Under the Guaranteed Watt Savers (GWS) system, plans for a new home are computer analyzed for anticipated heat loss and gain. Specifications are specifically designed for each structure and a Smart- House Radiant Barrier is installed. Designed to reflect away 95% of the Sun's radiant energy, the radiant barrier is an adaptation of an aluminum shield used on Apollo spacecraft. On completion of a home, technicians using a machine, check for air tightness, by creating a vacuum in the house and computer calculations that measure the amount of air exchanged. A guarantee that only the specified number kilowatt hours will be used is then provided.

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)

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.

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.

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.

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.

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.

Survey of computed tomography scanners in Taiwan: Dose descriptors, dose guidance levels, and effective doses

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

Tsai, H. Y.; Tung, C. J.; Yu, C. C.

2007-04-15

The IAEA and the ICRP recommended dose guidance levels for the most frequent computed tomography (CT) examinations to promote strategies for the optimization of radiation dose to CT patients. A national survey, including on-site measurements and questionnaires, was conducted in Taiwan in order to establish dose guidance levels and evaluate effective doses for CT. The beam quality and output and the phantom doses were measured for nine representative CT scanners. Questionnaire forms were completed by respondents from facilities of 146 CT scanners out of 285 total scanners. Information on patient, procedure, scanner, and technique for the head and body examinationsmore » was provided. The weighted computed tomography dose index (CTDI{sub w}), the dose length product (DLP), organ doses and effective dose were calculated using measured data, questionnaire information and Monte Carlo simulation results. A cost-effective analysis was applied to derive the dose guidance levels on CTDI{sub w} and DLP for several CT examinations. The mean effective dose{+-}standard deviation distributes from 1.6{+-}0.9 mSv for the routine head examination to 13{+-}11 mSv for the examination of liver, spleen, and pancreas. The surveyed results and the dose guidance levels were provided to the national authorities to develop quality control standards and protocols for CT examinations.« less

AVGS, AR and D for Satellites, ISS, the Moon, Mars and Beyond

NASA Technical Reports Server (NTRS)

Hintze, Geoffrey C.; Cornett, Keith G.; Rahmatipour, Michael H.; Heaton, Andrew F.; Newman, Larry E.; Fleischmann, Kevin D.; Hamby, Byron J.

2007-01-01

With the continuous need to rotate crew and re-supply the International Space Station (ISS) and the desire to return humans to the Moon and for the first time, place humans on Mars, NASA must develop a more robust and highly reliable capability to perform Autonomous Rendezvous and Capture (AR&C) because, unlike the Apollo missions, NASA plans to send the entire crew to the Lunar or Martian surface and must be able to dock with the Orion spacecraft upon return. In 1997, NASA developed the Video Guidance Sensor (VGS) which was flown and tested on STS-87 and STS-95. In 2001, NASA designed and built a more enhanced version of the VGS, called the Advanced Video Guidance Sensor (AVGS). The AVGS offered significant technology improvements to the precursor VGS design. This paper will describe the AVGS as it was in the DART mission of 2005 and the Orbital Express mission of 2007. The paper will describe the capabilities and design concepts of the AVGS as it was flown on the DART 2005 Mission and the DARPA Orbital Express Mission slated to fly in 2007. The paper will cover the Flight Software, problems encountered, testing for Orbital Express and where NASA is going in the future.

Numerical Skip-Entry Guidance

NASA Technical Reports Server (NTRS)

Tigges, Michael; Crull, Timothy; Rea, Jeremy; Johnson, Wyatt

2006-01-01

This paper assesses a preliminary guidance and targeting strategy for accomplishing Skip-Entry (SE) flight during a lunar return-capsule entry flight. One of the primary benefits of flying a SE trajectory is to provide the crew with continuous Continental United States (CONUS) landing site access throughout the lunar month. Without a SE capability, the capsule must land either in water or at one of several distributed land sites in the Southern Hemisphere for a significant portion of a lunar month using a landing and recovery scenario similar to that employed during the Apollo program. With a SE trajectory, the capsule can land either in water at a site in proximity to CONUS or at one of several distributed landing sites within CONUS, thereby simplifying the operational requirements for crew retrieval and vehicle recovery, and possibly enabling a high degree of vehicle reusability. Note that a SE capability does not require that the vehicle land on land. A SE capability enables a longer-range flight than a direct-entry flight, which permits the vehicle to land at a much greater distance from the Entry Interface (EI) point. This does not exclude using this approach to push the landing point to a water location in proximity of CONUS and utilizing water or airborne recovery forces.

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.

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.

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.

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

26 CFR 1.861-8 - Computation of taxable income from sources within the United States and from other sources and...

Code of Federal Regulations, 2010 CFR

2010-04-01

... income. [Reserved]. For guidance, see § 1.861-8T(c)(1). (2) Apportionment based on assets. [Reserved.... [Reserved]. For guidance, see § 1.861-8T(d)(2). (e) Allocation and apportionment of certain deductions—(1... section. (2) Interest. [Reserved]. For guidance, see § 1.861-8T(e)(2). (3) Research and experimental...

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.

Near-Optimal Guidance Method for Maximizing the Reachable Domain of Gliding Aircraft

NASA Astrophysics Data System (ADS)

Tsuchiya, Takeshi

This paper proposes a guidance method for gliding aircraft by using onboard computers to calculate a near-optimal trajectory in real-time, and thereby expanding the reachable domain. The results are applicable to advanced aircraft and future space transportation systems that require high safety. The calculation load of the optimal control problem that is used to maximize the reachable domain is too large for current computers to calculate in real-time. Thus the optimal control problem is divided into two problems: a gliding distance maximization problem in which the aircraft motion is limited to a vertical plane, and an optimal turning flight problem in a horizontal direction. First, the former problem is solved using a shooting method. It can be solved easily because its scale is smaller than that of the original problem, and because some of the features of the optimal solution are obtained in the first part of this paper. Next, in the latter problem, the optimal bank angle is computed from the solution of the former; this is an analytical computation, rather than an iterative computation. Finally, the reachable domain obtained from the proposed near-optimal guidance method is compared with that obtained from the original optimal control problem.

A Comparison of Two Skip Entry Guidance Algorithms

NASA Technical Reports Server (NTRS)

Rea, Jeremy R.; Putnam, Zachary R.

2007-01-01

The Orion capsule vehicle will have a Lift-to-Drag ratio (L/D) of 0.3-0.35. For an Apollo-like direct entry into the Earth's atmosphere from a lunar return trajectory, this L/D will give the vehicle a maximum range of about 2500 nm and a maximum crossrange of 216 nm. In order to y longer ranges, the vehicle lift must be used to loft the trajectory such that the aerodynamic forces are decreased. A Skip-Trajectory results if the vehicle leaves the sensible atmosphere and a second entry occurs downrange of the atmospheric exit point. The Orion capsule is required to have landing site access (either on land or in water) inside the Continental United States (CONUS) for lunar returns anytime during the lunar month. This requirement means the vehicle must be capable of flying ranges of at least 5500 nm. For the L/D of the vehicle, this is only possible with the use of a guided Skip-Trajectory. A skip entry guidance algorithm is necessary to achieve this requirement. Two skip entry guidance algorithms have been developed: the Numerical Skip Entry Guidance (NSEG) algorithm was developed at NASA/JSC and PredGuid was developed at Draper Laboratory. A comparison of these two algorithms will be presented in this paper. Each algorithm has been implemented in a high-fidelity, 6 degree-of-freedom simulation called the Advanced NASA Technology Architecture for Exploration Studies (ANTARES). NASA and Draper engineers have completed several monte carlo analyses in order to compare the performance of each algorithm in various stress states. Each algorithm has been tested for entry-to-target ranges to include direct entries and skip entries of varying length. Dispersions have been included on the initial entry interface state, vehicle mass properties, vehicle aerodynamics, atmosphere, and Reaction Control System (RCS). Performance criteria include miss distance to the target, RCS fuel usage, maximum g-loads and heat rates for the first and second entry, total heat load, and control system saturation. The comparison of the performance criteria has led to a down select and guidance merger that will take the best ideas from each algorithm to create one skip entry guidance algorithm for the Orion vehicle.

Advanced transport operating system software upgrade: Flight management/flight controls software description

NASA Technical Reports Server (NTRS)

Clinedinst, Winston C.; Debure, Kelly R.; Dickson, Richard W.; Heaphy, William J.; Parks, Mark A.; Slominski, Christopher J.; Wolverton, David A.

1988-01-01

The Flight Management/Flight Controls (FM/FC) software for the Norden 2 (PDP-11/70M) computer installed on the NASA 737 aircraft is described. The software computes the navigation position estimates, guidance commands, those commands to be issued to the control surfaces to direct the aircraft in flight based on the modes selected on the Advanced Guidance Control System (AGSC) mode panel, and the flight path selected via the Navigation Control/Display Unit (NCDU).

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.

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

Guidance system operations plan for manned CSM earth orbital and lunar missions using program COLOSSUS 3. Section 7: Erasable memory programs

NASA Technical Reports Server (NTRS)

Hamilton, M. H.

1972-01-01

Erasable-memory programs designed for guidance computers used in command and lunar modules are presented. The purpose, functional description, assumptions, restrictions, and imitations are given for each program.

Using Automated Scores of Student Essays to Support Teacher Guidance in Classroom Inquiry

NASA Astrophysics Data System (ADS)

Gerard, Libby F.; Linn, Marcia C.

2016-02-01

Computer scoring of student written essays about an inquiry topic can be used to diagnose student progress both to alert teachers to struggling students and to generate automated guidance. We identify promising ways for teachers to add value to automated guidance to improve student learning. Three teachers from two schools and their 386 students participated. We draw on evidence from student progress, observations of how teachers interact with students, and reactions of teachers. The findings suggest that alerts for teachers prompted rich teacher-student conversations about energy in photosynthesis. In one school, the combination of the automated guidance plus teacher guidance was more effective for student science learning than two rounds of personalized, automated guidance. In the other school, both approaches resulted in equal learning gains. These findings suggest optimal combinations of automated guidance and teacher guidance to support students to revise explanations during inquiry and build integrated understanding of science.

Connect Computer Education to Policies.

ERIC Educational Resources Information Center

Kimmelman, Paul

1985-01-01

The computer phenomenon has made rapid inroads into school curricula, often without proper board guidance or approval. Accordingly, this pamphlet discusses why and how computer education should be provided in schools and sets forth guidelines for school board policy regarding computers. An umbrella policy is proposed, defining "computer literacy"…

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

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.

Concepts and algorithms for terminal-area traffic management

NASA Technical Reports Server (NTRS)

Erzberger, H.; Chapel, J. D.

1984-01-01

The nation's air-traffic-control system is the subject of an extensive modernization program, including the planned introduction of advanced automation techniques. This paper gives an overview of a concept for automating terminal-area traffic management. Four-dimensional (4D) guidance techniques, which play an essential role in the automated system, are reviewed. One technique, intended for on-board computer implementation, is based on application of optimal control theory. The second technique is a simplified approach to 4D guidance intended for ground computer implementation. It generates advisory messages to help the controller maintain scheduled landing times of aircraft not equipped with on-board 4D guidance systems. An operational system for the second technique, recently evaluated in a simulation, is also described.

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

Astronaut Eugene Cernan sleeping aboard Apollo 17 spacecraft

NASA Image and Video Library

1972-12-17

AS17-162-24049 (7-19 Dec. 1972) --- A fellow crewman took this picture of astronaut Eugene A. Cernan dozing aboard the Apollo 17 spacecraft during the final lunar landing mission in NASA's Apollo program. Also, aboard Apollo 17 were astronaut Ronald E. Evans, command module pilot, and scientist-astronaut Harrison H. "Jack" Schmitt, lunar module pilot. Cernan was the mission commander.

President Nixon on deck of U.S.S. Hornet awaiting Apollo 11 crew arrival

NASA Image and Video Library

1969-07-24

S69-21736 (24 July 1969) --- President Richard M. Nixon photographed on the deck of the USS Hornet, prime recovery ship for the Apollo 11 lunar landing mission, awaiting the Apollo 11 crew arrival. Apollo 11 splashed down at 11:40 a.m. (EDT), July 24, 1969, about 812 nautical miles southwest of Hawaii.

Apollo 17 Mission Report

NASA Technical Reports Server (NTRS)

1973-01-01

Operational and engineering aspects of the Apollo 17 mission are outlined. The vehicle configuration was similar to those of Apollo 15 and 16. There were significant differences in the science payload for Apollo 17 and spacecraft hardware differences and experiment equipment are described. The mission achieved a landing in the Taurus-Littrow region of the moon and returned samples of the pre-Imbrium highlands and young craters.

Apollo experience report: Battery subsystem

NASA Technical Reports Server (NTRS)

Trout, J. B.

1972-01-01

Experience with the Apollo command service module and lunar module batteries is discussed. Significant hardware development concepts and hardware test results are summarized, and the operational performance of batteries on the Apollo 7 to 13 missions is discussed in terms of performance data, mission constraints, and basic hardware design and capability. Also, the flight performance of the Apollo battery charger is discussed. Inflight data are presented.

SNMIB/Apollo protects leading-strand telomeres against NHEJ-mediated repair.

PubMed

Lam, Yung C; Akhter, Shamima; Gu, Peili; Ye, Jing; Poulet, Anaïs; Giraud-Panis, Marie-Josèphe; Bailey, Susan M; Gilson, Eric; Legerski, Randy J; Chang, Sandy

2010-07-07

Progressive telomere attrition or deficiency of the protective shelterin complex elicits a DNA damage response as a result of a cell's inability to distinguish dysfunctional telomeric ends from DNA double-strand breaks. SNMIB/Apollo is a shelterin-associated protein and a member of the SMN1/PSO2 nuclease family that localizes to telomeres through its interaction with TRF2. Here, we generated SNMIB/Apollo knockout mouse embryo fibroblasts (MEFs) to probe the function of SNMIB/Apollo at mammalian telomeres. SNMIB/Apollo null MEFs exhibit an increased incidence of G2 chromatid-type fusions involving telomeres created by leading-strand DNA synthesis, reflective of a failure to protect these telomeres after DNA replication. Mutations within SNMIB/Apollo's conserved nuclease domain failed to suppress this phenotype, suggesting that its nuclease activity is required to protect leading-strand telomeres. SNMIB/Apollo(-/-)ATM(-/-) MEFs display robust telomere fusions when Trf2 is depleted, indicating that ATM is dispensable for repair of uncapped telomeres in this setting. Our data implicate the 5'-3' exonuclease function of SNM1B/Apollo in the generation of 3' single-stranded overhangs at newly replicated leading-strand telomeres to protect them from engaging the non-homologous end-joining pathway.

KSC-2014-3249

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- Apollo astronauts and their families receive a briefing in one of the remodeled firing rooms in the Launch Control Center at NASA's Kennedy Space Center in Florida. The facility's firing rooms were used to conduct the Saturn V countdowns during the Apollo Program. The tour followed a ceremony renaming the refurbished Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Second from left is Apollo 11 moonwalker Buzz Aldrin and former astronaut Jim Lovell, a member of the Apollo 8 and Apollo 13 crews, standing next to him, at center. The ceremony was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Buzz Aldrin landed in the moon's Sea of Tranquility on July 20, 1969, aboard the lunar module Eagle. 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

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.

Teaching Chemistry Using From the Earth to the Moon

NASA Astrophysics Data System (ADS)

Goll, James G.; Mundinger, Stacie L.

2003-03-01

The space program and media based on it have provided fascinating examples that can be used to expore chemical principles. The HBO series From the Earth to the Moon and a documentary Moonshot provide examples for teaching chemical principles from the Apollo missions. A docking problem between two spacecrafts occurred during the Apollo 14 mission. This situation can be used to discuss the conditions necessary for a chemical reaction. A catastrophic fire on Apollo 1 can be used to illustrate the influence of different conditions on the rate of a reaction. Lightning striking Apollo 12 during liftoff showed the consequence of adding ions to solution. The landing of Apollo 12, which touched down only 535 feet from Surveyor 3, can be used to teach accuracy and absolute and relative error. The astronauts of Apollo 15 discovered a sample of the primordial lunar crust, and during Apollo 17, astronauts discovered orange dust on the moon. These discoveries can be used to demonstrate the importance of trained observation skills and analytical thinking.

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.

Surprise

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

Curran, L.

1988-03-03

Interest has been building in recent months over the imminent arrival of a new class of supercomputer, called the ''supercomputer on a desk'' or the single-user model. Most observers expected the first such product to come from either of two startups, Ardent Computer Corp. or Stellar Computer Inc. But a surprise entry has shown up. Apollo Computer Inc. is launching a new work station this week that racks up an impressive list of industry first as it puts supercomputer power at the disposal of a single user. The new series 10000 from the Chelmsford, Mass., a company is built aroundmore » a reduced-instruction-set architecture that the company calls Prism, for parallel reduced-instruction-set multiprocessor. This article describes the 10000 and Prism.« less

KSC-2012-6142

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – A guest checks out an item available for auction at the Astronaut Scholarship Foundation's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The 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

Winners of student essay contest receive awards

NASA Technical Reports Server (NTRS)

1999-01-01

At the Apollo/Saturn V Center, George Meguiar (center left) and George English (center right) present scholarships to two students who entered an essay contest in conjunction with the 30th Anniversary of Apollo 11. The winners shown are Kyla Davis Horn, of Cocoa Beach, and Kyle Rukaczewski, of Satellite Beach. A third winner, Jason Gagnon, of Viera, was unable to attend. Meguiar and English head the Apollo 11 Commemoration Association which sponsored the contest in conjunction with Florida Today newspaper. The presentation was made at the Apollo/Saturn V Center during an anniversary banquet that honored all the people who made the Apollo Program possible. Special guests included former Apollo astronauts Neil Armstrong, Edwin 'Buzz' Aldrin, Gene Cernan and Walt Cunningham, who shared their experiences with the audience.

View of Mission Control Center during Apollo 13 splashdown

NASA Technical Reports Server (NTRS)

1970-01-01

Overall view of Mission Operations Control Room in Mission Control Center at the Manned Spacecraft Center (MSC) during the ceremonies aboard the U.S.S. Iwo Jima, prime recovery ship for the Apollo 13 mission. Dr. Donald K. Slayton (in black shirt, left of center), Director of Flight Crew Operations at MSC, and Chester M. Lee of the Apollo Program Directorate, Office of Manned Space Flight, NASA Headquarters, shake hands, while Dr. Rocco A. Petrone, Apollo Program Director, Office of Manned Space Flight, NASA Headquarters (standing, near Lee), watches the large screen showing Astronaut James A. Lovell Jr., Apollo 13 commander, during the on-board ceremonies. In the foreground, Glynn S. Lunney (extreme left) and Eugene F. Kranz (smoking a cigar), two Apollo 13 Flight Directors, view the activity from their consoles.

Saturn V Vehicle for the Apollo 4 Mission in the Vehicle Assembly Building

NASA Technical Reports Server (NTRS)

1967-01-01

This photograph depicts the Saturn V vehicle (SA-501) for the Apollo 4 mission in the Vehicle Assembly Building (VAB) at the Kennedy Space Center (KSC). After the completion of the assembly operation, the work platform was retracted and the vehicle was readied to rollout from the VAB to the launch pad. The Apollo 4 mission was the first launch of the Saturn V launch vehicle. Objectives of the unmanned Apollo 4 test flight were to obtain flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, and subsystems operation including testing of restart of the S-IVB stage, and to evaluate the Apollo command module heat shield. The Apollo 4 was launched on November 9, 1967 from KSC.

Apollo 1 Prime and Backup Crews

NASA Image and Video Library

1966-04-01

S66-30238 (1 April 1966) --- The National Aeronautics and Space Administration (NASA) has named these astronauts as the prime crew of the first manned Apollo Space Flight. Left to right, are Edward H. White II, command module pilot; Virgil I. Grissom, mission commander; and Roger B. Chaffee, lunar module pilot. On the second row are the Apollo 1 backup crew members, astronauts David R. Scott, James A. McDivitt and Russell L. Schweickart. EDITOR'S NOTE: Astronauts Grissom, White and Chaffee lost their lives in a Jan. 27, 1967 fire in the Apollo CM during testing at Cape Canaveral. McDivitt, Scott and Schweickart later served as crewmembers for the Apollo 9 Earth-orbital mission, which was one of the important stair-step missions leading up to the Apollo 11 manned lunar landing mission of July 1969.

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 is the center of attention at 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. He appeared at the banquet with other former astronauts Edwin 'Buzz' Aldrin, Gene Cernan, Walt Cunningham and others.

KSC-99pp0843

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, identifies a reporter to pose a question to one of the former Apollo astronauts seated next to her. From left, they are 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. 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

Neil Armstrong gets round of applaus at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

Former Apollo 11 astronaut Neil A. Armstrong stands to a round of applause after being introduced at 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. He appeared at the banquet with other former astronauts Edwin 'Buzz' Aldrin, Gene Cernan, Walt Cunningham and others.

Official Emblem - Apollo 7 - First (1st) Manned Apollo Space Mission

NASA Image and Video Library

1968-06-01

S68-26668 (June 1968) --- The official emblem of Apollo 7, the first manned Apollo space mission. The crew will consist of astronauts Walter M. Schirra Jr., Donn F. Eisele, and Walter Cunningham. The NASA insignia design for Apollo flights is reserved for use by the astronauts and for the 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 4 launch

NASA Image and Video Library

1967-09-11

S67-50903 (9 Nov. 1967) --- The Apollo 4 (Spacecraft 017/Saturn 501) space mission was launched from Pad A, Launch Complex 39, Kennedy Space Center, Florida. The liftoff of the huge 363-feet tall Apollo/Saturn V space vehicle was at 7:00:01 a.m. (EST), Nov. 9, 1967. The successful objectives of the Apollo 4 Earth-orbital unmanned space mission obtained included (1) flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, subsystem operation, emergency detection subsystem, and (2) evaluation of the Apollo Command Module heat shield under conditions encountered on return from a moon mission.

Steering a Tractor by Means of an EMG-Based Human-Machine Interface

PubMed Central

Gomez-Gil, Jaime; San-Jose-Gonzalez, Israel; Nicolas-Alonso, Luis Fernando; Alonso-Garcia, Sergio

2011-01-01

An electromiographic (EMG)-based human-machine interface (HMI) is a communication pathway between a human and a machine that operates by means of the acquisition and processing of EMG signals. This article explores the use of EMG-based HMIs in the steering of farm tractors. An EPOC, a low-cost human-computer interface (HCI) from the Emotiv Company, was employed. This device, by means of 14 saline sensors, measures and processes EMG and electroencephalographic (EEG) signals from the scalp of the driver. In our tests, the HMI took into account only the detection of four trained muscular events on the driver’s scalp: eyes looking to the right and jaw opened, eyes looking to the right and jaw closed, eyes looking to the left and jaw opened, and eyes looking to the left and jaw closed. The EMG-based HMI guidance was compared with manual guidance and with autonomous GPS guidance. A driver tested these three guidance systems along three different trajectories: a straight line, a step, and a circumference. The accuracy of the EMG-based HMI guidance was lower than the accuracy obtained by manual guidance, which was lower in turn than the accuracy obtained by the autonomous GPS guidance; the computed standard deviations of error to the desired trajectory in the straight line were 16 cm, 9 cm, and 4 cm, respectively. Since the standard deviation between the manual guidance and the EMG-based HMI guidance differed only 7 cm, and this difference is not relevant in agricultural steering, it can be concluded that it is possible to steer a tractor by an EMG-based HMI with almost the same accuracy as with manual steering. PMID:22164006

Steering a tractor by means of an EMG-based human-machine interface.

PubMed

Gomez-Gil, Jaime; San-Jose-Gonzalez, Israel; Nicolas-Alonso, Luis Fernando; Alonso-Garcia, Sergio

2011-01-01

An electromiographic (EMG)-based human-machine interface (HMI) is a communication pathway between a human and a machine that operates by means of the acquisition and processing of EMG signals. This article explores the use of EMG-based HMIs in the steering of farm tractors. An EPOC, a low-cost human-computer interface (HCI) from the Emotiv Company, was employed. This device, by means of 14 saline sensors, measures and processes EMG and electroencephalographic (EEG) signals from the scalp of the driver. In our tests, the HMI took into account only the detection of four trained muscular events on the driver's scalp: eyes looking to the right and jaw opened, eyes looking to the right and jaw closed, eyes looking to the left and jaw opened, and eyes looking to the left and jaw closed. The EMG-based HMI guidance was compared with manual guidance and with autonomous GPS guidance. A driver tested these three guidance systems along three different trajectories: a straight line, a step, and a circumference. The accuracy of the EMG-based HMI guidance was lower than the accuracy obtained by manual guidance, which was lower in turn than the accuracy obtained by the autonomous GPS guidance; the computed standard deviations of error to the desired trajectory in the straight line were 16 cm, 9 cm, and 4 cm, respectively. Since the standard deviation between the manual guidance and the EMG-based HMI guidance differed only 7 cm, and this difference is not relevant in agricultural steering, it can be concluded that it is possible to steer a tractor by an EMG-based HMI with almost the same accuracy as with manual steering.

An annotated bibliography of the Apollo program

NASA Technical Reports Server (NTRS)

Launius, Roger D.; Hunley, J. D.

1994-01-01

The topics presented include the following: general works, the space race, decisions, Apollo technology, operations, popular culture and promotion, science, astronauts, the management of the Apollo Program, and juvenile literature.

The Apollo Structured Vocabulary: an OWL2 ontology of phenomena in infectious disease epidemiology and population biology for use in epidemic simulation.

PubMed

Hogan, William R; Wagner, Michael M; Brochhausen, Mathias; Levander, John; Brown, Shawn T; Millett, Nicholas; DePasse, Jay; Hanna, Josh

2016-08-18

We developed the Apollo Structured Vocabulary (Apollo-SV)-an OWL2 ontology of phenomena in infectious disease epidemiology and population biology-as part of a project whose goal is to increase the use of epidemic simulators in public health practice. Apollo-SV defines a terminology for use in simulator configuration. Apollo-SV is the product of an ontological analysis of the domain of infectious disease epidemiology, with particular attention to the inputs and outputs of nine simulators. Apollo-SV contains 802 classes for representing the inputs and outputs of simulators, of which approximately half are new and half are imported from existing ontologies. The most important Apollo-SV class for users of simulators is infectious disease scenario, which is a representation of an ecosystem at simulator time zero that has at least one infection process (a class) affecting at least one population (also a class). Other important classes represent ecosystem elements (e.g., households), ecosystem processes (e.g., infection acquisition and infectious disease), censuses of ecosystem elements (e.g., censuses of populations), and infectious disease control measures. In the larger project, which created an end-user application that can send the same infectious disease scenario to multiple simulators, Apollo-SV serves as the controlled terminology and strongly influences the design of the message syntax used to represent an infectious disease scenario. As we added simulators for different pathogens (e.g., malaria and dengue), the core classes of Apollo-SV have remained stable, suggesting that our conceptualization of the information required by simulators is sound. Despite adhering to the OBO Foundry principle of orthogonality, we could not reuse Infectious Disease Ontology classes as the basis for infectious disease scenarios. We thus defined new classes in Apollo-SV for host, pathogen, infection, infectious disease, colonization, and infection acquisition. Unlike IDO, our ontological analysis extended to existing mathematical models of key biological phenomena studied by infectious disease epidemiology and population biology. Our ontological analysis as expressed in Apollo-SV was instrumental in developing a simulator-independent representation of infectious disease scenarios that can be run on multiple epidemic simulators. Our experience suggests the importance of extending ontological analysis of a domain to include existing mathematical models of the phenomena studied by the domain. Apollo-SV is freely available at: http://purl.obolibrary.org/obo/apollo_sv.owl .

A potpourrie of regolith breccias: ``New'' samples from the Apollo 14, 16, and 17 landing sites

NASA Astrophysics Data System (ADS)

Jerde, Eric A.; Warren, Paul H.; Morris, Richard V.; Heiken, Grant H.; Vaniman, David T.

1987-09-01

Forty suspected regolith breccias from the Apollo 14, 16, and 17 landing sites were studied as part of a search for regolith samples exotic to the small traverse areas associated with these missions, as well as a general effort to constrain the nature and origins of regolith breccias. Of these 40 samples, 31 are indeed regolith breccias. Regolith breccias from Apollo 14 exhibit much greater compositional diversity than their soil (sensu stricto) counterparts: 14004,55 displays incompatible element concentrations about 1.4× those found in typical Apollo 14 regolith, while 14315 is radically different in many respects (higher Al, lower Mg and Fe, lower incompatible elements) from all other Apollo 14 regolith materials, and hence probably exotic to the Apollo 14 traverse area. Application of ``mixing'' models to Apollo 14 regolith materials suggests that whereas ``normal'' Apollo 14 regolith contains only slightly more ferroan anorthosite (FA) than alkali anorthosite (AA) and far more KREEP than FA and AA combined, 14315 contains more FA than KREEP and roughly 10 times more FA than AA. Three ``new'' regolith breccias from Apollo 16 bring to 20 the total number of regolith breccias that have been analyzed for Mg and Fe from the site. The molar Mg/)Mg+Fe) (or mg*) ratios of lunar regolith breccias are of great interest, because lunar meteorite ALH81005 has a much higher mg* than two other lunar meteoritic regolith breccias (Y791197 and Y82192/3), even though these three samples are remarkably similar in all other compositional respects. A bimodality in mg* among Apollo 16 regolith breccias may result from: (1) statistical scattering among the small number of samples, (2) a tendency for older regolith breccias from this site to be compositionally distinct form their younger counterparts, or (3) differences between the Cayley and Descartes Formations. Among 10 samples from Apollo 17, all but one proved to be typical Apollo 17 regolith breccias. However, 72504,10 is >99% pure pyroclastic glass, compositionally identical to the Apollo 1 orange galss (74220), even though 72504,10 was obtained at a location over 4 km from Shorty Crater where 74220 was obtained. The nearly pure concentration of 74220-identical glass spherules in 72504-10 attests to the widespread distribution of these distinctive deposits.

KSC-2009-4186

NASA Image and Video Library

2009-07-16

CAPE CANAVERAL, Fla. – CNN Correspondent John Zarella (left), moderates NASA's 40th Anniversary of Apollo Celebration of the moon launch and landing in July 1969, which was held in the Apollo/Saturn V Center at NASA's Kennedy Space Center in Florida. At right are Apollo astronauts Buzz Aldrin, Walt Cunningham and Edgar Mitchell. Eight Apollo astronauts shared their experiences with a crowd of guests. Photo credit: NASA/Kim Shiflett

Apollo 9 prime crew inside Apollo command module boilerplate during training

NASA Image and Video Library

1968-11-05

S68-54850 (5 Nov. 1968) --- The prime crew of the Apollo 9 (Spacecraft 104/Lunar Module 3/Saturn 504) space mission are seen inside an Apollo command module boilerplate during water egress training activity in the Gulf of Mexico. From foreground, are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot.

Alan Bean Art Exhibit

NASA Image and Video Library

2009-07-19

NASA Apollo 7 Astronaut Walt Cunningham, left, and NASA STS-125 Mission Specialist Michael Massimino talk with another guest during the opening of "Alan Bean: Painting Apollo, First Artist on Another World" by NASA Apollo 12 Astronaut and Artist Alan Bean at the National Air and Space Museum, Monday, July 20, 2009 in Washington. The show opening coincided with the 40th anniversary celebration of Apollo. Photo Credit: (NASA/Bill Ingalls)

Artist's concept of Apollo/Soyuz spacecraft docking approach

NASA Image and Video Library

1973-08-01

S73-02395 (August 1973) --- An artist?s concept illustrating an Apollo-type spacecraft (on left) about to dock with a Soviet Soyuz-type spacecraft. A recent agreement between the United States and the Union of Soviet Socialist Republics provides for the docking in space of the Soyuz and Apollo-type spacecraft in Earth orbit in 1975. The joint venture is called the Apollo-Soyuz Test Project.

President Nixon on deck of U.S.S. Hornet awaiting Apollo 11 crew arrival

NASA Technical Reports Server (NTRS)

1969-01-01

President Richard M. Nixon photographed on the deck of the U.S.S. Hornet, prime recovery ship for the Apollo 11 lunar landing mission, awaiting the Apollo 11 crew arrival. swimmer. All four men are wearing biological isolation garments. Apollo 11 splashed down at 11:40 a.m., July 24, 1969, about 812 nautical miles southwest of Hawaii.

Notes on lunar ilmenite

NASA Technical Reports Server (NTRS)

Hutson, M. L.

1989-01-01

Opaques (mostly ilmenite) make up 0 to 5 percent of highland rocks, 1 to 11 percent of low-Ti mare basalts, and 10 to 34 percent of high-Ti mare basalts (Carter 1988). Apollos 11 and 17 sampled high-Ti basalts. Apollos 12 and 14 sampled low-Ti basalts. Apollo 15 sampled a complex mixture of mare and highland material. Apollo 16 sampled mainly highland material (Taylor 1975).

APOLLO 9 - PRELAUNCH (CDDT) - KSC

NASA Image and Video Library

1969-02-20

S69-27089 (11 March 1969) --- Overall view of Pad B, Launch Complex 39, Kennedy Space Center, showing the Apollo 10 (Spacecraft 106/Lunar Module-4/Saturn 505) space vehicle during a Countdown Demonstration Test. The Apollo 10 flight is scheduled as a lunar orbit mission. The Apollo 10 crew will be astronauts Thomas P. Stafford, commander; John W. Young, command module pilot; and Eugene A. Cernan, lunar module pilot.

Cone-Beam Computed Tomography (CBCT) Versus CT in Lung Ablation Procedure: Which is Faster?

PubMed

Cazzato, Roberto Luigi; Battistuzzi, Jean-Benoit; Catena, Vittorio; Grasso, Rosario Francesco; Zobel, Bruno Beomonte; Schena, Emiliano; Buy, Xavier; Palussiere, Jean

2015-10-01

To compare cone-beam CT (CBCT) versus computed tomography (CT) guidance in terms of time needed to target and place the radiofrequency ablation (RFA) electrode on lung tumours. Patients at our institution who received CBCT- or CT-guided RFA for primary or metastatic lung tumours were retrospectively included. Time required to target and place the RFA electrode within the lesion was registered and compared across the two groups. Lesions were stratified into three groups according to their size (<10, 10-20, >20 mm). Occurrences of electrode repositioning, repositioning time, RFA complications, and local recurrence after RFA were also reported. Forty tumours (22 under CT, 18 under CBCT guidance) were treated in 27 patients (19 male, 8 female, median age 67.25 ± 9.13 years). Thirty RFA sessions (16 under CBCT and 14 under CT guidance) were performed. Multivariable linear regression analysis showed that CBCT was faster than CT to target and place the electrode within the tumour independently from its size (β = -9.45, t = -3.09, p = 0.004). Electrode repositioning was required in 10/22 (45.4 %) tumours under CT guidance and 5/18 (27.8 %) tumours under CBCT guidance. Pneumothoraces occurred in 6/14 (42.8 %) sessions under CT guidance and in 6/16 (37.5 %) sessions under CBCT guidance. Two recurrences were noted for tumours receiving CBCT-guided RFA (2/17, 11.7 %) and three after CT-guided RFA (3/19, 15.8 %). CBCT with live 3D needle guidance is a useful technique for percutaneous lung ablation. Despite lesion size, CBCT allows faster lung RFA than CT.

SUPPORTING THE INDUSTRY BY DEVELOPING A DESIGN GUIDANCE FOR COMPUTER-BASED PROCEDURES FOR FIELD WORKERS

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

Oxstrand, Johanna; LeBlanc, Katya

The paper-based procedures currently used for nearly all activities in the commercial nuclear power industry have a long history of ensuring safe operation of the plants. However, there is potential to greatly increase efficiency and safety by improving how the human interacts with the procedures, which can be achieved through the use of computer-based procedures (CBPs). A CBP system offers a vast variety of improvements, such as context driven job aids, integrated human performance tools and dynamic step presentation. As a step toward the goal of improving procedure use performance, the U.S. Department of Energy Light Water Reactor Sustainability Programmore » researchers, together with the nuclear industry, have been investigating the possibility and feasibility of replacing current paper-based procedures with CBPs. The main purpose of the CBP research conducted at the Idaho National Laboratory was to provide design guidance to the nuclear industry to be used by both utilities and vendors. After studying existing design guidance for CBP systems, the researchers concluded that the majority of the existing guidance is intended for control room CBP systems, and does not necessarily address the challenges of designing CBP systems for instructions carried out in the field. Further, the guidance is often presented on a high level, which leaves the designer to interpret what is meant by the guidance and how to specifically implement it. The authors developed a design guidance to provide guidance specifically tailored to instructions that are carried out in the field based.« less

Success Factors in Human Space Programs - Why Did Apollo Succeed Better Than Later Programs?

NASA Technical Reports Server (NTRS)

Jones, Harry W.

2015-01-01

The Apollo Program reached the moon, but the Constellation Program (CxP) that planned to return to the moon and go on to Mars was cancelled. Apollo is NASA's greatest achievement but its success is poorly understood. The usual explanation is that President Kennedy announced we were going to the moon, the scientific community and the public strongly supported it, and Congress provided the necessary funding. This is partially incorrect and does not actually explain Apollo's success. The scientific community and the public did not support Apollo. Like Apollo, Constellation was announced by a president and funded by Congress, with elements that continued on even after it was cancelled. Two other factors account for Apollo's success. Initially, the surprise event of Uri Gagarin's first human space flight created political distress and a strong desire for the government to dramatically demonstrate American space capability. Options were considered and Apollo was found to be most effective and technically feasible. Political necessity overrode both the lack of popular and scientific support and the extremely high cost and risk. Other NASA human space programs were either canceled, such as the Space Exploration Initiative (SEI), repeatedly threatened with cancellation, such as International Space Station (ISS), or terminated while still operational, such as the space shuttle and even Apollo itself. Large crash programs such as Apollo are initiated and continued if and only if urgent political necessity produces the necessary political will. They succeed if and only if they are technically feasible within the provided resources. Future human space missions will probably require gradual step-by-step development in a more normal environment.

Mission Control Center (MCC) View - Apollo 13 Splashdown - MSC

NASA Image and Video Library

1970-04-17

S70-35145 (17 April 1970) --- Overall view of Mission Operations Control Room in Mission Control Center at the Manned Spacecraft Center (MSC) during the ceremonies aboard the USS Iwo Jima, prime recovery ship for the Apollo 13 mission. Dr. Donald K. Slayton (in black shirt, left of center), director of Flight Crew Operations at MSC, and Chester M. Lee of the Apollo Program Directorate, Office of Manned Space Flight, NASA Headquarters, shake hands, while Dr. Rocco A. Petrone, Apollo program director, Office of Manned Space Flight, NASA Headquarters (standing, near Lee), watches the large screen showing astronaut James A. Lovell Jr., Apollo 13 commander, during the onboard ceremonies. In the foreground, Glynn S. Lunney (extreme left) and Eugene F. Kranz (smoking a cigar), two Apollo 13 flight directors, view the activity from their consoles.

KSC-2012-6141

NASA Image and Video Library

2012-11-03

CAPE CANAVERAL, Fla. – Kennedy Space Center Director Bob Cabana checks out an item available for auction at the Astronaut Scholarship Foundation's dinner at the Radisson Resort at the Port in Cape Canaveral celebrating the 40th anniversary of Apollo 17. The 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

Lunar Shape via the Apollo Laser Altimeter.

PubMed

Sjogren, W L; Wollenhaupt, W R

1973-01-19

Data from the Apollo 15 and Apollo 16 laser altimeters reveal the first accurate elevation differences between distant features on both sides of the moon. The large far-side depression observed in the Apollo 15 data is not present in the Apollo 16 data. When the laser results are compared with elevations on maps from the Aeronautical Chart and Information Center, differences of 2 kilometers over a few hundred kilometers are detected in the Mare Nubium and Mare Tranquillitatis regions. The Apollo 16 data alone would put a 2-kilometer bulge toward the earth; however, the combined data are best fit by a sphere of radius 1737.7 kilometers. The offset of the center of gravity from the optical center is about 2 kilometers toward the earth and 1 kilometer eastward. The polar direction parameters are not well determined.

Organics in APOLLO Lunar Samples

NASA Technical Reports Server (NTRS)

Allen, C. C.; Allton, J. H.

2007-01-01

One of many unknowns prior to the Apollo landings concerned the possibility of life, its remains, or its organic precursors on the surface of the Moon. While the existence of lunar organisms was considered highly unlikely, a program of biological quarantine and testing for the astronauts, the Apollo Command Modules, and the lunar rock and soil samples, was instituted in the Lunar Receiving Laboratory (LRL). No conclusive evidence of lunar organisms, was detected and the quarantine program was ended after Apollo 14. Analyses for organic compounds were also con-ducted. Considerable effort was expended, during lunar surface operations and in the LRL, to minimize and quantify organic contamination. Post-Apollo curatorial operations and cleaning minimize contamination from particulates, oxygen, and water but no longer specifically address organic contamination. The organic compounds measured in Apollo samples are generally consistent with known sources of contamination.

Flight evaluation of a computer aided low-altitude helicopter flight guidance system

NASA Technical Reports Server (NTRS)

Swenson, Harry N.; Jones, Raymond D.; Clark, Raymond

1993-01-01

The Flight Systems Development branch of the U.S. Army's Avionics Research and Development Activity (AVRADA) and NASA Ames Research Center developed for flight testing a Computer Aided Low-Altitude Helicopter Flight (CALAHF) guidance system. The system includes a trajectory-generation algorithm which uses dynamic programming and a helmet-mounted display (HMD) presentation of a pathway-in-the-sky, a phantom aircraft, and flight-path vector/predictor guidance symbology. The trajectory-generation algorithm uses knowledge of the global mission requirements, a digital terrain map, aircraft performance capabilities, and precision navigation information to determine a trajectory between mission waypoints that seeks valleys to minimize threat exposure. This system was developed and evaluated through extensive use of piloted simulation and has demonstrated a 'pilot centered' concept of automated and integrated navigation and terrain mission planning flight guidance. This system has shown a significant improvement in pilot situational awareness, and mission effectiveness as well as a decrease in training and proficiency time required for a near terrain, nighttime, adverse weather system.

X-Ray Computed Tomography of Tranquility Base Moon Rock

NASA Technical Reports Server (NTRS)

Jones, Justin S.; Garvin, Jim; Viens, Mike; Kent, Ryan; Munoz, Bruno

2016-01-01

X-ray Computed Tomography (CT) was used for the first time on the Apollo 11 Lunar Sample number 10057.30, which had been previously maintained by the White House, then transferred back to NASA under the care of Goddard Space Flight Center. Results from this analysis show detailed images of the internal structure of the moon rock, including vesicles (pores), crystal needles, and crystal bundles. These crystals, possibly the common mineral ilmenite, are found in abundance and with random orientation. Future work, in particular a greater understanding of these crystals and their formation, may lead to a more in-depth understanding of the lunar surface evolution and mineral content.

Space station data management system - A common GSE test interface for systems testing and verification

NASA Technical Reports Server (NTRS)

Martinez, Pedro A.; Dunn, Kevin W.

1987-01-01

This paper examines the fundamental problems and goals associated with test, verification, and flight-certification of man-rated distributed data systems. First, a summary of the characteristics of modern computer systems that affect the testing process is provided. Then, verification requirements are expressed in terms of an overall test philosophy for distributed computer systems. This test philosophy stems from previous experience that was gained with centralized systems (Apollo and the Space Shuttle), and deals directly with the new problems that verification of distributed systems may present. Finally, a description of potential hardware and software tools to help solve these problems is provided.

Autonomous docking ground demonstration

NASA Technical Reports Server (NTRS)

Lamkin, Steve L.; Le, Thomas Quan; Othon, L. T.; Prather, Joseph L.; Eick, Richard E.; Baxter, Jim M.; Boyd, M. G.; Clark, Fred D.; Spehar, Peter T.; Teters, Rebecca T.

1991-01-01

The Autonomous Docking Ground Demonstration is an evaluation of the laser sensor system to support the docking phase (12 ft to contact) when operated in conjunction with the guidance, navigation, and control (GN&C) software. The docking mechanism being used was developed for the Apollo/Soyuz Test Program. This demonstration will be conducted using the 6-DOF Dynamic Test System (DTS). The DTS simulates the Space Station Freedom as the stationary or target vehicle and the Orbiter as the active or chase vehicle. For this demonstration, the laser sensor will be mounted on the target vehicle and the retroflectors will be on the chase vehicle. This arrangement was chosen to prevent potential damage to the laser. The laser sensor system, GN&C, and 6-DOF DTS will be operated closed-loop. Initial conditions to simulate vehicle misalignments, translational and rotational, will be introduced within the constraints of the systems involved.

Orion Pad Abort 1 GN and C Design and Development

NASA Technical Reports Server (NTRS)

Medina, Edgar A.; Stachowiak, Susan J.

2010-01-01

The first flight test of the Orion Abort Flight Test project is scheduled to launch in Spring 2010. This flight test is known as Pad Abort 1 (PA-1) and it is intended to accomplish a series of flight test objectives, including demonstrating the capability of the Launch Abort System (LAS) to propel the Crew Module (CM) to a safe distance from a launch vehicle during a pad abort. The PA-1 Flight Test Article (FTA) is actively controlled by a guidance, navigation, and control (GN&C) system for much of its flight. The purpose of this paper is to describe the design, development, and analysis of the PA-1 GN&C system. A description of the technical solutions that were developed to meet the challenge of satisfying many competing requirements is presented. A historical perspective of how the Orion LAV compares to the Apollo Launch Escape Vehicle (LEV) design will also be included.

Video Guidance Sensor for Surface Mobility Operations

NASA Technical Reports Server (NTRS)

Fernandez, Kenneth R.; Fischer, Richard; Bryan, Thomas; Howell, Joe; Howard, Ricky; Peters, Bruce

2008-01-01

Robotic systems and surface mobility will play an increased role in future exploration missions. Unlike the LRV during Apollo era which was an astronaut piloted vehicle future systems will include teleoperated and semi-autonomous operations. The tasks given to these vehicles will run the range from infrastructure maintenance, ISRU, and construction to name a few. A common task that may be performed would be the retrieval and deployment of trailer mounted equipment. Operational scenarios may require these operations to be performed remotely via a teleoperated mode,or semi-autonomously. This presentation describes the on-going project to adapt the Automated Rendezvous and Capture (AR&C) sensor developed at the Marshall Space Flight Center for use in an automated trailer pick-up and deployment operation. The sensor which has been successfully demonstrated on-orbit has been mounted on an iRobot/John Deere RGATOR autonomous vehicle for this demonstration which will be completed in the March 2008 time-frame.

Prime crew of Apollo/Saturn Mission 204 prepares for water egress training

NASA Image and Video Library

1966-10-27

S66-58501 (27 Oct. 1966) --- The prime crew of the first manned Apollo Space Flight, Apollo/Saturn (AS) mission 204, is suited up aboard the NASA Motor Vessel Retriever (MVR) in preparation for Apollo water egress training in the Gulf of Mexico. Left to right, are astronauts Edward H. White II, senior pilot; Virgil I. Grissom, command pilot; and Roger B. Chaffee, pilot.

Apollo 9 Lunar Module in lunar landing configuration

NASA Technical Reports Server (NTRS)

1969-01-01

View of the Apollo 9 Lunar Module, in a lunar landing configuration, as photographed form the Command/Service Module on the fifth day of the Apollo 9 earth-orbital mission. The landing gear on the 'Spider' has been deployed. Lunar surface probes (sensors) extend out from the landing gear foot pads. Inside the 'Spider' were Astronauts James A. McDivitt, Apollo 9 commander; and Russell L. Schweickart, lunar module pilot.

Vertical view of Apollo 16 landing site located Descartes area lunar nearside

NASA Technical Reports Server (NTRS)

1971-01-01

A vertical view of the Apollo 16 landing site located in the Descartes area lunar nearside. The overlay indicates the location of the proposed touchdown point for the Apollo 16 Lunar Module. Descartes is located west of the Sea of Nectar and southwest of the Sea of Tranquility. This photograph was taken with a 500mm lens camera from lunar orbit by the Apollo 14 crew.

View of Apollo 17 lunar rock sample no. 72415,0

NASA Image and Video Library

1972-01-18

S73-16198 (December 1972) --- A close-up view of Apollo 17 lunar sample number 72415,0 which was brought back from the Taurus-Littrow landing site by the Apollo 17 crewmen. This sample is a brecciated dunite clast weighing a little over 32 grams (about 1.14 ounces). This sample was collected at station 2 (South Massif) during the second Apollo 17 extravehicular activity (EVA).

Apollo experience report: Mission planning for lunar module descent and ascent

NASA Technical Reports Server (NTRS)

Bennett, F. V.

1972-01-01

The premission planning, the real-time situation, and the postflight analysis for the Apollo 11 lunar descent and ascent are described. A comparison between premission planning and actual results is included. A navigation correction capability, developed from Apollo 11 postflight analysis was used successfully on Apollo 12 to provide the first pinpoint landing. An experience summary, which illustrates typical problems encountered by the mission planners, is also included.

Crew Members - First Manned Apollo Flight - Unmanned Mission Launch - Cape

NASA Image and Video Library

1968-01-22

S68-18700 (22 Jan. 1968) --- Two prime crew members of the first manned Apollo space flight were present at Cape Kennedy for the launch of the Apollo V (LM-1/Saturn 204) unmanned space mission. On left is astronaut Walter M. Schirra Jr.; and on right is astronaut R. Walter Cunningham. In background is the Apollo V stack at Launch Complex 37 ready for launch.

Saturn Apollo Program

NASA Image and Video Library

1975-07-01

SA-210 Apollo-Soyuz Test Project (ASTP) awaits the launch scheduled on July 15, 1975 on the launch pad at the Kennedy Space Center, the ASTP mission with astronauts Thomas Stafford, Vance Brand, and Donald "Deke" Slayton. The Saturn IB, developed under the direction of the Marshall Space Flight Center (MSFC), launched five manned Earth-orbital missions between 1968 and 1975: Apollo 7, Skylab 2, Skylab 3, Skylab 4, and the Apollo-Soyuz Test Project .

Navigating Space by the Stars

NASA Image and Video Library

2018-06-19

A tool that has helped guide sailors across oceans for centuries is now being tested aboard the International Space Station as a potential emergency navigation tool for guiding future spacecraft across the cosmos. The Sextant Navigation investigation tests use of a hand-held sextant aboard the space station. Sextants have a telescope-like optical sight to take precise angle measurements between pairs of stars from land or sea, enabling navigation without computer assistance. NASA’s Gemini missions conducted the first sextant sightings from a spacecraft, and designers built a sextant into Apollo vehicles as a navigation backup in the event the crew lost communications from their spacecraft. Jim Lovell demonstrated on Apollo 8 that sextant navigation could return a space vehicle home. Astronauts conducted additional sextant experiments on Skylab. Read more about the Sextant experiment happening aboard the space station: https://www.nasa.gov/mission_pages/station/research/news/Sextant_ISS HD Download: https://archive.org/details/jsc2018m000418_Navigating_Space_by_the_Stars

Navigating Space by the Stars - 16x9

NASA Image and Video Library

2018-06-18

A tool that has helped guide sailors across oceans for centuries is now being tested aboard the International Space Station as a potential emergency navigation tool for guiding future spacecraft across the cosmos. The Sextant Navigation investigation tests use of a hand-held sextant aboard the space station. Sextants have a telescope-like optical sight to take precise angle measurements between pairs of stars from land or sea, enabling navigation without computer assistance. NASA’s Gemini missions conducted the first sextant sightings from a spacecraft, and designers built a sextant into Apollo vehicles as a navigation backup in the event the crew lost communications from their spacecraft. Jim Lovell demonstrated on Apollo 8 that sextant navigation could return a space vehicle home. Astronauts conducted additional sextant experiments on Skylab. Read more about the Sextant experiment happening aboard the space station: https://www.nasa.gov/mission_pages/station/research/news/Sextant_ISS HD Download: https://archive.org/details/jsc2018m000418_Navigating_Space_by_the_Stars

Kennedy Space Center's Command and Control System - "Toasters to Rocket Ships"

NASA Technical Reports Server (NTRS)

Lougheed, Kirk; Mako, Cheryle

2011-01-01

This slide presentation reviews the history of the development of the command and control system at Kennedy Space Center. From a system that could be brought to Florida in the trunk of a car in the 1950's. Including the development of larger and more complex launch vehicles with the Apollo program where human launch controllers managed the launch process with a hardware only system that required a dedicated human interface to perform every function until the Apollo vehicle lifted off from the pad. Through the development of the digital computer that interfaced with ground launch processing systems with the Space Shuttle program. Finally, showing the future control room being developed to control the missions to return to the moon and Mars, which will maximize the use of Commercial-Off-The Shelf (COTS) hardware and software which was standards based and not tied to a single vendor. The system is designed to be flexible and adaptable to support the requirements of future spacecraft and launch vehicles.

Blunt Body Aerodynamics for Hypersonic Low Density Flows

NASA Technical Reports Server (NTRS)

Moss, James N.; Glass, Christopher E.; Greene, Francis A.

2006-01-01

Numerical simulations are performed for the Apollo capsule from the hypersonic rarefied to the continuum regimes. The focus is on flow conditions similar to those experienced by the Apollo 6 Command Module during the high altitude portion of its reentry. The present focus is to highlight some of the current activities that serve as a precursor for computational tool assessments that will be used to support the development of aerodynamic data bases for future capsule flight environments, particularly those for the Crew Exploration Vehicle (CEV). Results for aerodynamic forces and moments are presented that demonstrate their sensitivity to rarefaction; that is, free molecular to continuum conditions. Also, aerodynamic data are presented that shows their sensitivity to a range of reentry velocities, encompassing conditions that include reentry from low Earth orbit, lunar return, and Mars return velocities (7.7 to 15 km/s). The rarefied results obtained with direct simulation Monte Carlo (DSMC) codes are anchored in the continuum regime with data from Navier-Stokes simulations.

Six degree of freedom FORTRAN program, ASTP docking dynamics, users guide

NASA Technical Reports Server (NTRS)

Mount, G. O., Jr.; Mikhalkin, B.

1974-01-01

The digital program ASTP Docking Dynamics as outlined is intended to aid the engineer using the program to determine the docking system loads and attendant vehicular motion resulting from docking two vehicles that have an androgynous, six-hydraulic-attenuator, guide ring, docking interface similar to that designed for the Apollo/Soyuz Test Project (ASTP). This program is set up to analyze two different vehicle combinations: the Apollo CSM docking to Soyuz and the shuttle orbiter docking to another orbiter. The subroutine modifies the vehicle control systems to describe one or the other vehicle combinations; the rest of the vehicle characteristics are changed by input data. To date, the program has been used to predict and correlate ASTP docking loads and performance with docking test program results from dynamic testing. The program modified for use on IBM 360 computers. Parts of the original docking system equations in the areas of hydraulic damping and capture latches are modified to better describe the detail design of the ASTP docking system.

Lunar near-surface shear wave velocities at the Apollo landing sites as inferred from spectral amplitude ratios

NASA Technical Reports Server (NTRS)

Horvath, P.; Latham, G. V.; Nakamura, Y.; Dorman, H. J.

1980-01-01

The horizontal-to-vertical amplitude ratios of the long-period seismograms are reexamined to determine the shear wave velocity distributions at the Apollo 12, 14, 15, and 16 lunar landing sites. Average spectral ratios, computed from a number of impact signals, were compared with spectral ratios calculated for the fundamental mode Rayleigh waves in media consisting of homogeneous, isotropic, horizontal layers. The shear velocities of the best fitting models at the different sites resemble each other and differ from the average for all sites by not more than 20% except for the bottom layer at station 14. The shear velocities increase from 40 m/s at the surface to about 400 m/s at depths between 95 and 160 m at the various sites. Within this depth range the velocity-depth functions are well represented by two piecewise linear segments, although the presence of first-order discontinuities cannot be ruled out.

Experience of modeling relief of impact lunar crater Aitken based on high-resolution orbital images

NASA Astrophysics Data System (ADS)

Mukhametshin, Ch R.; Semenov, A. A.; Shpekin, M. I.

2018-05-01

The paper presents the author’s results of modeling the relief of lunar Aitken crater on the basis of high-resolution orbital images. The images were taken in the frame of the “Apollo” program in 1971-1972 and delivered to the Earth by crews of “Apollo-15” and “Apollo-17”. The authors used the images obtained by metric and panoramic cameras. The main result is the careful study of the unusual features of Aitken crater on models created by the authors with the computer program, developed by “Agisoft Photoscan”. The paper shows what possibilities are opened with 3D models in the study of the structure of impact craters on the Moon. In particular, for the first time, the authors managed to show the structure of the glacier-like tongue in Aitken crater, which is regarded as one of the promising areas of the Moon for the forthcoming expeditions.

Apollo Lunar Sample Integration into Google Moon: A New Approach to Digitization

NASA Technical Reports Server (NTRS)

Dawson, Melissa D.; Todd, nancy S.; Lofgren, Gary E.

2011-01-01

The Google Moon Apollo Lunar Sample Data Integration project is part of a larger, LASER-funded 4-year lunar rock photo restoration project by NASA s Acquisition and Curation Office [1]. The objective of this project is to enhance the Apollo mission data already available on Google Moon with information about the lunar samples collected during the Apollo missions. To this end, we have combined rock sample data from various sources, including Curation databases, mission documentation and lunar sample catalogs, with newly available digital photography of rock samples to create a user-friendly, interactive tool for learning about the Apollo Moon samples

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.

Bulk, rare earth, and other trace elements in Apollo 14 and 15 and Luna 16 samples.

NASA Technical Reports Server (NTRS)

Laul, J. C.; Wakita, H.; Showalter, D. L.; Boynton, W. V.; Schmitt, R. A.

1972-01-01

Measurement of 24 and 34 bulk, minor, and trace elements in lunar specimens by instrumental and radiochemical neutron activation analysis shows greater Al2O3, Na2O, and K2O abundances and higher TiO2, FeO, MnO and Cr2O3 depletions in Apollo 14 soil samples as compared to Apollo 11 samples and to most of Apollo 12 samples. The uniform abundances in 14230 core tube soils and three other Apollo 14 soils indicate that the regolith is uniform to at least 22 cm depth and within about 200 m from the lunar module.

Computers in Public Broadcasting: Who, What, Where.

ERIC Educational Resources Information Center

Yousuf, M. Osman

This handbook offers guidance to public broadcasting managers on computer acquisition and development activities. Based on a 1981 survey of planned and current computer uses conducted by the Corporation for Public Broadcasting (CPB) Information Clearinghouse, computer systems in public radio and television broadcasting stations are listed by…

Astronaut John Young ingresses Apollo spacecraft command module in training

NASA Image and Video Library

1968-07-05

S68-40875 (5 July 1968) --- Astronaut John W. Young, Apollo 7 backup command module pilot, ingresses Apollo Spacecraft 101 Command Module during simulated altitude runs at the Kennedy Space Center's Pad 34.

INFLIGHT - APOLLO X

NASA Image and Video Library

1969-05-25

S69-34969 (24 May 1969) --- Astronaut Thomas P. Stafford, Apollo 10 commander, is seen in this color reproduction taken from a telecast made by the color television camera aboard the Apollo 10 spacecraft during its trans-Earth journey home.

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.

KSC-2014-3250

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- Apollo astronauts and their families receive a briefing in one of the remodeled firing rooms in the Launch Control Center at NASA's Kennedy Space Center in Florida. The facility's firing rooms were used to conduct the Saturn V countdowns during the Apollo Program. The tour followed a ceremony renaming the refurbished Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Second from left is Apollo 11 moonwalker Buzz Aldrin and former astronaut Jim Lovell, a member of the Apollo 8 and Apollo 13 crews, standing next to him, at center. The ceremony was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Buzz Aldrin landed in the moon's Sea of Tranquility on July 20, 1969, aboard the lunar module Eagle. 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/Kevin O'Connell

Apollo 12 crewmembers during geological field trip

NASA Image and Video Library

1969-10-24

S69-55662 (10 Oct. 1969) --- Astronauts Alan L. Bean (left) and Charles Conrad Jr., the two crewmen of the Apollo 12 lunar landing mission who are scheduled to participate in two lengthy periods of extravehicular activity (EVA) on the lunar surface, are pictured during a geological field trip and training at a simulated lunar surface area near Flagstaff, Arizona. Here Conrad, the Apollo 12 commander, gets a close look through hand lens at the stratigraphy (study of strata or layers beneath the surface) of a man-dug hole, while Bean, the Apollo 12 mission's lunar module pilot, looks on. The topography in this area, with several man-made modifications, resembles very closely much of the topography found on the lunar surface. While Conrad and Bean explore the lunar surface (plans call for Apollo 12 spacecraft to land in the Sea of Storms), astronaut Richard F. Gordon Jr., command module pilot for the Apollo 12 mission, will remain with the Command and Service Modules (CSM) in lunar orbit. The Apollo 12 mission is scheduled to lift off from Cape Kennedy on Nov. 14, 1969.

Saturn Apollo Program

NASA Image and Video Library

1971-01-31

In the launch control center at Kennedy Space Flight Center (KSC), Walter J. Kapryan, Director of Launch Operations (center), discusses an aspect of the Apollo 14 flight with Marshall Space Flight Center’s (MSFC) Dr. Rocco A. Petrone, Apollo Program Director (right). The Apollo 14, carrying a crew of three astronauts: Mission commander Alan B. Shepard Jr., Command Module pilot Stuart A. Roosa, and Lunar Module pilot Edgar D. Mitchell, lifted off from launch complex 39A at KSC on January 31, 1971. It was the third manned lunar landing, the first manned landing in exploration of the lunar highlands, and it demonstrated pinpoint landing capability. The major goal of Apollo 14 was the scientific exploration of the Moon in the foothills of the rugged Fra Mauro region. The extravehicular activity (EVA) of astronauts Shepard and Mitchell included setting up an automated scientific laboratory called Apollo Lunar Scientific Experiments Package (ALSEP), and collecting a total of about 95 pounds (43 kilograms) of Moon rock and soil for a geological investigation back on the Earth. Apollo 14 safely returned to Earth on February 9, 1971.

Petrographic and petrological study of lunar rock materials

NASA Technical Reports Server (NTRS)

Winzer, S. R.

1976-01-01

Samples returned from Apollo 14 (14171, 14305, 14319), Apollo 15 (15255), Apollo 16 (61175, 67455), and Apollo 17 (77215) were studied optically and selected polished sections by SEM/Microprobe. Splits and separates from 77215, 67455, 61175 and 15255 were prepared; 77215 and 67455 were analyzed for major, minor and LIL trace elements. The data indicate that 77215, a noritic breccia clast found in the Station7 boulder, is a norite cumulate similar to and probably derived from the same body as 78235. The Apollo 17 boulders are found to be part of the same melt sheet, which was formed by a major impact event, possibly Serenitatis, about 4 B. Y. ago. The Apollo 14 and 16 breccias are polymict, their clast populations indicating quite different provenance. The Apollo 14 breccias are possibly the result of multiple impacts, while the other breccias studied appear to have been formed by single impacts. ANT suite clasts included in 61175 are, for the most part, granulites resulting from subsolidus recrystallization of norites, anorthosites or gabbros. This metamorphism appears to have occurred prior to the impact event forming 61175.

Asymmetrical booster ascent guidance and control system design study. Volume 1: Summary. [space shuttle development

NASA Technical Reports Server (NTRS)

Williams, F. E.; Lemon, R. S.; Jaggers, R. F.; Wilson, J. L.

1974-01-01

Dynamics and control, stability, and guidance analyses are summarized for the asymmetrical booster ascent guidance and control system design studies, performed in conjunction with space shuttle planning. The mathematical models developed for use in rigid body and flexible body versions of the NASA JSC space shuttle functional simulator are briefly discussed, along with information on the following: (1) space shuttle stability analysis using equations of motion for both pitch and lateral axes; (2) the computer program used to obtain stability margin; and (3) the guidance equations developed for the space shuttle powered flight phases.

Asymmetrical booster ascent guidance and control system design study. Volume 5: Space shuttle powered explicit guidance. [space shuttle development

NASA Technical Reports Server (NTRS)

Jaggers, R. F.

1974-01-01

An optimum powered explicit guidance algorithm capable of handling all space shuttle exoatospheric maneuvers is presented. The theoretical and practical basis for the currently baselined space shuttle powered flight guidance equations and logic is documented. Detailed flow diagrams for implementing the steering computations for all shuttle phases, including powered return to launch site (RTLS) abort, are also presented. Derivation of the powered RTLS algorithm is provided, as well as detailed flow diagrams for implementing the option. The flow diagrams and equations are compatible with the current powered flight documentation.

Optimal guidance with obstacle avoidance for nap-of-the-earth flight

NASA Technical Reports Server (NTRS)

Pekelsma, Nicholas J.

1988-01-01

The development of automatic guidance is discussed for helicopter Nap-of-the-Earth (NOE) and near-NOE flight. It deals with algorithm refinements relating to automated real-time flight path planning and to mission planning. With regard to path planning, it relates rotorcraft trajectory characteristics to the NOE computation scheme and addresses real-time computing issues and both ride quality issues and pilot-vehicle interfaces. The automated mission planning algorithm refinements include route optimization, automatic waypoint generation, interactive applications, and provisions for integrating the results into the real-time path planning software. A microcomputer based mission planning workstation was developed and is described. Further, the application of Defense Mapping Agency (DMA) digital terrain to both the mission planning workstation and to automatic guidance is both discussed and illustrated.

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.

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

The Moon: What Have the Apollo Missions Taught Us? Part II: The View from Apollo.

ERIC Educational Resources Information Center

McKeever, S. W. S.

1980-01-01

Summarizes scientific findings resulting from the Apollo missions, including lunar rocks and soil, age determination, and the moon's interior, evolution, and origin. Indicates experiments for future lunar research. (SK)

INFLIGHT - APOLLO X

NASA Image and Video Library

1969-05-25

S69-34968 (24 May 1969) --- Astronaut Eugene A. Cernan, Apollo 10 lunar module pilot, is seen in this color reproduction taken from a telecast made by the color television camera aboard the Apollo 10 spacecraft during its trans-Earth journey home.

Launch of Apollo 8 lunar orbit mission

NASA Image and Video Library

1968-12-21

S68-56001 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center, at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (Just after ignition)

KSC-2009-4187

NASA Image and Video Library

2009-07-16

CAPE CANAVERAL, Fla. – The Apollo/Saturn V Center at NASA's Kennedy Space Center in Florida is filled with guests gathered to hear about the Apollo 11 launch and landing in July 1969 from eight Apollo astronauts: . The event is part of NASA's 40th Anniversary of Apollo Celebration. Participating are CNN correspondent, who moderated, Buzz Aldrin, Walt Cunningham, Edgar Mitchell, Al Worden, Charlie Duke, Vance Brand, Gerald Carr and Bruce McCandless. Photo credit: NASA/Kim Shiflett

NASA-marks 5th anniversary of first lunar landing

NASA Technical Reports Server (NTRS)

1974-01-01

The accomplishments of the Apollo 11 Flight are presented as a tribute to the fifth anniversary of the first landing on the moon. The document contains: (1) a general description of the Apollo 11 Flight, (2) Presidential statements, (3) Apollo historical summary, (4) Apollo mission facts, (5) information on astronauts who are no longer in the program, and (6) transcripts of the landing sequence and first extravehicular activities on the moon.

Where No Man Has Gone Before: A History of Apollo Lunar Exploration Missions

NASA Technical Reports Server (NTRS)

Compton, William David

1988-01-01

This book is a narrative account of the development of the science program for the Apollo lunar landing missions. It focuses on the interaction between scientific interests and operational considerations in such matters as landing site selection and training of crews, quarantine and back contamination control, and presentation of results from scientific investigations. Scientific exploration of the moon on later flights, Apollo 12 through Apollo 17 is emphasized.

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.

MISSION CONTROL CENTER (MCC) - MSC - during Apollo 16

NASA Image and Video Library

1972-05-08

S72-37009 (20 April 1972) --- NASA officials gather around a console in the Mission Operations Control Room (MOCR) in the Mission Control Center (MCC) prior to the making of a decision whether to land Apollo 16 on the moon or to abort the landing. Seated, left to right, are Dr. Christopher C. Kraft Jr., Director of the Manned Spacecraft Center (MSC), and Brig. Gen. James A. McDivitt (USAF), Manager, Apollo Spacecraft Program Office, MSC; and standing, left to right, are Dr. Rocco A. Petrone, Apollo Program Director, Office Manned Space Flight (OMSF), NASA HQ.; Capt. John K. Holcomb (U.S. Navy, Ret.), Director of Apollo Operations, OMSF; Sigurd A. Sjoberg, Deputy Director, MSC; Capt. Chester M. Lee (U.S. Navy, Ret.), Apollo Mission Director, OMSF; Dale D. Myers, NASA Associate Administrator for Manned Space Flight; and Dr. George M. Low, NASA Deputy Administrator. Photo credit: NASA

MISSION CONTROL CENTER (MCC) - APOLLO 16 - MSC

NASA Image and Video Library

1972-05-08

S72-37010 (20 April 1972) --- NASA officials gather around a console in the Mission Operations Control Room (MOCR) in the Mission Control Center (MCC) prior to the making of a decision whether to land Apollo 16 on the moon or to abort the landing. Seated, left to right, are Dr. Christopher C. Kraft Jr., Director of the Manned Spacecraft Center (MSC), and Brig. Gen. James A. McDivitt (USAF), Manager, Apollo Spacecraft Program Office, MSC; and standing, left to right, are Dr. Rocco A. Petrone, Apollo Program Director, Office Manned Space Flight (OMSF), NASA HQ.; Capt. John K. Holcomb (U.S. Navy, Ret.), Director of Apollo Operations, OMSF; Sigurd A. Sjoberg, Deputy Director, MSC; Capt. Chester M. Lee (U.S. Navy, Ret.), Apollo Mission Director, OMSF; Dale D. Myers, NASA Associate Administrator for Manned Space Flight; and Dr. George M. Low, NASA Deputy Administrator. Photo credit: NASA

NASA Officials in MCC to decide whether to land Apollo 16 or cancel landing

NASA Technical Reports Server (NTRS)

1972-01-01

NASA Officials gather around a console in the Mission Operations Control Room (MOCR) in the Mission Control Center (MCC) prior to the making of a decision whether to land Apollo 16 on the moon or to abort the landing. Seated, left to right, are Dr. Christopher C. Kraft Jr., Director of the Manned Spacecraft Center (MSC), and Brig. Gen. James A. McDivitt (USAF), Manager, Apollo Spacecraft Program Office, MSC; and standing, left to right, are Dr. Rocco A. Petrone, Apollo Program Director, Office Manned Space Flight (OMSF), NASA HQ.; Capt. John K. Holcolmb (U.S. Navy, Ret.), Director of Apollo Operations, OMSF; Sigurd A. Sjoberg, Deputy Director, MSC; Capt. Chester M. Lee (U.S. Navy, Ret.), Apollo Mission Director, OMSF; Dale D. Myers, NASA Associate Administrator for Manned Space Flight; and Dr. George M. Low, NASA Deputy Administrator.

KSC-2011-5962

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, Apollo 11 Commander Neil Armstrong speaks to the invited guests. In the background is a model of the Lunar Module, part of the lander portion of the Apollo spacecraft. 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

KSC-2014-3244

NASA Image and Video Library

2014-07-21

CAPE CANAVERAL, Fla. -- Apollo astronauts and their families tour the Vehicle Assembly Building, the facility in which Apollo's Saturn V rockets were processed at NASA's Kennedy Space Center in Florida. The tour followed a ceremony renaming the refurbished Operations and Checkout Building for Apollo 11 astronaut Neil Armstrong, the first person to set foot on the moon. Leading the way through the transfer aisle, from left, are Apollo astronaut Jim Lovell, Neil's former wife Janet, Neil's granddaughter Lily, and Apollo 11 moonwalker Buzz Aldrin. The ceremony was part of NASA's 45th anniversary celebration of the Apollo 11 moon landing. As the world watched, Neil Armstrong and Buzz Aldrin landed in the moon's Sea of Tranquility on July 20, 1969, aboard the lunar module Eagle. 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 1 Tribute Opening

NASA Image and Video Library

2017-01-27

Former Gemini and Apollo astronaut Tom Stafford speaks during the opening of the tribute exhibition to the Apollo 1 astronauts who perished in a fire at the launch pad on Jan. 27, 1967, during training for the mission. The tribute highlights the lives and careers of astronauts Gus Grissom, Ed White II and Roger Chaffee who were lost during the fire. The tribute at the Apollo/Saturn V Center at NASA's Kennedy Space Center opened Jan. 27, 2017, 50 years after the crew of three was lost. It features numerous items recalling the lives of the three astronauts. The tribute also includes the three-part hatch to the spacecraft itself, the first time any part of the Apollo 1 spacecraft has been displayed publicly. A version of the hatch after it was redesigned is also showcased as an example of improvements NASA made throughout the agency and to the Apollo spacecraft that would later carry astronauts to the moon.

Apollo 1 Tribute

NASA Image and Video Library

2017-01-24

A gateway featuring the Apollo 1 mission logo over the moon is shown inside the new tribute to the crew of Apollo 1 who perished in a fire at the launch pad on Jan. 27, 1967, during training for the mission. Astronauts Gus Grissom, Ed White II and Roger Chaffee were lost during the fire. The tribute at the Apollo/Saturn V Center at NASA's Kennedy Space Center opened Jan. 27, 2017, 50 years after the crew of three was lost. It features numerous items recalling the lives of the three astronauts. The tribute also includes the three-part hatch to the spacecraft itself, the first time any part of the Apollo 1 spacecraft has been displayed publicly. A version of the hatch after it was redesigned is also showcased as an example of improvements NASA made throughout the agency and to the Apollo spacecraft that would later carry astronauts to the moon.

Apollo 1 Tribute

NASA Image and Video Library

2017-01-24

A redesigned hatch for an Apollo spacecraft is shown inside the new tribute to the crew of Apollo 1 who perished in a fire at the launch pad on Jan. 27, 1967, during training for the mission. Astronauts Gus Grissom, Ed White II and Roger Chaffee were lost during the fire. The tribute at the Apollo/Saturn V Center at NASA's Kennedy Space Center opened Jan. 27, 2017, 50 years after the crew of three was lost. It features numerous items recalling the lives of the three astronauts. The tribute also includes the three-part hatch to the spacecraft itself, the first time any part of the Apollo 1 spacecraft has been displayed publicly. The version of the hatch after it was redesigned was also showcased as an example of improvements NASA made throughout the agency and to the Apollo spacecraft that would later carry astronauts to the moon.

Apollo: a community resource for genome annotation editing

PubMed Central

Ed, Lee; Nomi, Harris; Mark, Gibson; Raymond, Chetty; Suzanna, Lewis

2009-01-01

Summary: Apollo is a genome annotation-editing tool with an easy to use graphical interface. It is a component of the GMOD project, with ongoing development driven by the community. Recent additions to the software include support for the generic feature format version 3 (GFF3), continuous transcriptome data, a full Chado database interface, integration with remote services for on-the-fly BLAST and Primer BLAST analyses, graphical interfaces for configuring user preferences and full undo of all edit operations. Apollo's user community continues to grow, including its use as an educational tool for college and high-school students. Availability: Apollo is a Java application distributed under a free and open source license. Installers for Windows, Linux, Unix, Solaris and Mac OS X are available at http://apollo.berkeleybop.org, and the source code is available from the SourceForge CVS repository at http://gmod.cvs.sourceforge.net/gmod/apollo. Contact: elee@berkeleybop.org PMID:19439563

Apollo 1 Tribute

NASA Image and Video Library

2017-01-24

An Apollo spacecraft mockup marks the capstone of the new tribute to the crew of Apollo 1 who perished in a fire at the launch pad on Jan. 27, 1967, during training for the mission. The tribute highlights the lives and careers of astronauts Gus Grissom, Ed White II and Roger Chaffee who were lost during the fire. The tribute at the Apollo/Saturn V Center at NASA's Kennedy Space Center opened Jan. 27, 2017, 50 years after the crew of three was lost. It features numerous items recalling the lives of the three astronauts. The tribute also includes the three-part hatch to the spacecraft itself, the first time any part of the Apollo 1 spacecraft has been displayed publicly. A version of the hatch after it was redesigned is also showcased as an example of improvements NASA made throughout the agency and to the Apollo spacecraft that would later carry astronauts to the moon.

Apollo 1 Tribute

NASA Image and Video Library

2017-01-24

The three-part hatch that was in place on the Apollo 1 spacecraft is shown in a tribute to the crew of Apollo 1 who perished in a fire at the launch pad on Jan. 27, 1967, during training for the mission. This is the first time any part of the Apollo 1 spacecraft has been displayed publicly. The tribute highlights the lives and careers of astronauts Gus Grissom, Ed White II and Roger Chaffee who were lost during the fire. The tribute at the Apollo/Saturn V Center at NASA's Kennedy Space Center opened Jan. 27, 2017, 50 years after the crew of three was lost. It features numerous items recalling the lives of the three astronauts. A version of the hatch after it was redesigned is also showcased as an example of improvements NASA made throughout the agency and to the Apollo spacecraft that would later carry astronauts to the moon.

Apollo: a community resource for genome annotation editing.

PubMed

Lee, Ed; Harris, Nomi; Gibson, Mark; Chetty, Raymond; Lewis, Suzanna

2009-07-15

Apollo is a genome annotation-editing tool with an easy to use graphical interface. It is a component of the GMOD project, with ongoing development driven by the community. Recent additions to the software include support for the generic feature format version 3 (GFF3), continuous transcriptome data, a full Chado database interface, integration with remote services for on-the-fly BLAST and Primer BLAST analyses, graphical interfaces for configuring user preferences and full undo of all edit operations. Apollo's user community continues to grow, including its use as an educational tool for college and high-school students. Apollo is a Java application distributed under a free and open source license. Installers for Windows, Linux, Unix, Solaris and Mac OS X are available at http://apollo.berkeleybop.org, and the source code is available from the SourceForge CVS repository at http://gmod.cvs.sourceforge.net/gmod/apollo.

Saturn Apollo Program

NASA Image and Video Library

1971-01-31

Stuart A. Roosa, Apollo 14 Command Module pilot, undergoes a final space suit check prior to liftoff. The Apollo 14, carrying a crew of three astronauts: Roosa; Alan B. Shepard, Jr., Mission Commander; and Edgar D. Mitchell, Lunar Module pilot, lifted off from launch complex 39A at KSC on January 31, 1971. It was the third manned lunar landing, the first manned landing in exploration of the lunar highlands, and it demonstrated pinpoint landing capability. The major goal of Apollo 14 was the scientific exploration of the Moon in the foothills of the rugged Fra Mauro region. The lunar surface extravehicular activity (EVA) of astronauts Shepard and Mitchell included setting up an automated scientific laboratory called Apollo Lunar Scientific Experiments Package (ALSEP), and collecting a total of about 95 pounds (43 kilograms) of Moon rock and soil for a geological investigation back on the Earth. Apollo 14 safely returned to Earth on February 9, 1971.

Project Logic Handbook: Computer Literacy through BASIC.

ERIC Educational Resources Information Center

Huber, Leonard; And Others

This handbook for teachers offers guidance on introducing computer literacy into elementary and secondary classrooms. It includes a list of computer concepts exemplified by each step in learning to write programs in BASIC Programming Language and the objectives for the elementary and secondary activities; suggestions for using computers in…

U.S. Army weapon systems human-computer interface style guide. Version 2

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

Avery, L.W.; O`Mara, P.A.; Shepard, A.P.

1997-12-31

A stated goal of the US Army has been the standardization of the human computer interfaces (HCIs) of its system. Some of the tools being used to accomplish this standardization are HCI design guidelines and style guides. Currently, the Army is employing a number of HCI design guidance documents. While these style guides provide good guidance for the command, control, communications, computers, and intelligence (C4I) domain, they do not necessarily represent the more unique requirements of the Army`s real time and near-real time (RT/NRT) weapon systems. The Office of the Director of Information for Command, Control, Communications, and Computers (DISC4),more » in conjunction with the Weapon Systems Technical Architecture Working Group (WSTAWG), recognized this need as part of their activities to revise the Army Technical Architecture (ATA), now termed the Joint Technical Architecture-Army (JTA-A). To address this need, DISC4 tasked the Pacific Northwest National Laboratory (PNNL) to develop an Army weapon systems unique HCI style guide, which resulted in the US Army Weapon Systems Human-Computer Interface (WSHCI) Style Guide Version 1. Based on feedback from the user community, DISC4 further tasked PNNL to revise Version 1 and publish Version 2. The intent was to update some of the research and incorporate some enhancements. This document provides that revision. The purpose of this document is to provide HCI design guidance for the RT/NRT Army system domain across the weapon systems subdomains of ground, aviation, missile, and soldier systems. Each subdomain should customize and extend this guidance by developing their domain-specific style guides, which will be used to guide the development of future systems within their subdomains.« less

Apollo Spacecraft 012 Command/Service Module being moved to Operations bldg

NASA Technical Reports Server (NTRS)

1967-01-01

Transfer of Apollo Spacecraft 012 Command/Service Module for mating to the Saturn Lunar Module Adapter No. 05 in the Manned Spacecraft Operations bldg. S/C 012 will be flown on the Apollo/Saturn 204 mission.

Astronaut Vance Brand at controls of Apollo Command Module

NASA Technical Reports Server (NTRS)

1975-01-01

Astronaut Vance D. Brand, command module pilot of the American ASTP crew, is seen at the controls of the Apollo Command Module during the joint U.S.-USSR Apollo Soyuz Test Project (ASTP) docking in Earth orbit mission.

Astronaut John Young during final suiting operations for Apollo 10 mission

NASA Technical Reports Server (NTRS)

1969-01-01

A technician attaches hose from test stand to spacesuit of Astronaut John W. Young, Apollo 10 command module pilot, during final suiting operations for the Apollo 10 lunar orbit mission. Another technician makes adjustment behind Young.

Apollo rocks, fines and soil cores

NASA Astrophysics Data System (ADS)

Allton, J.; Bevill, T.

Apollo rocks and soils not only established basic lunar properties and ground truth for global remote sensing, they also provided important lessons for planetary protection (Adv. Space Res ., 1998, v. 22, no. 3 pp. 373-382). The six Apollo missions returned 2196 samples weighing 381.7 kg, comprised of rocks, fines, soil cores and 2 gas samples. By examining which samples were allocated for scientific investigations, information was obtained on usefulness of sampling strategy, sampling devices and containers, sample types and diversity, and on size of sample needed by various disciplines. Diversity was increased by using rakes to gather small rocks on the Moon and by removing fragments >1 mm from soils by sieving in the laboratory. Breccias and soil cores are diverse internally. Per unit weight these samples were more often allocated for research. Apollo investigators became adept at wringing information from very small sample sizes. By pushing the analytical limits, the main concern was adequate size for representative sampling. Typical allocations for trace element analyses were 750 mg for rocks, 300 mg for fines and 70 mg for core subsamples. Age-dating and isotope systematics allocations were typically 1 g for rocks and fines, but only 10% of that amount for core depth subsamples. Historically, allocations for organics and microbiology were 4 g (10% for cores). Modern allocations for biomarker detection are 100mg. Other disciplines supported have been cosmogenic nuclides, rock and soil petrology, sedimentary volatiles, reflectance, magnetics, and biohazard studies . Highly applicable to future sample return missions was the Apollo experience with organic contamination, estimated to be from 1 to 5 ng/g sample for Apollo 11 (Simonheit &Flory, 1970; Apollo 11, 12 &13 Organic contamination Monitoring History, U.C. Berkeley; Burlingame et al., 1970, Apollo 11 LSC , pp. 1779-1792). Eleven sources of contaminants, of which 7 are applicable to robotic missions, were identified and reduced; thus, improving Apollo 12 samples to 0.1 ng/g. Apollo sample documentation preserves the parentage, orientation, and location, packaging, handling and environmental histories of each of the 90,000 subsamples currently curated. Active research on Apollo samples continues today, and because 80% by weight of the Apollo collection remains pristine, researchers have a reservoir of material to support studies well into the future.

Ares V: Progress Toward Unprecedented Heavy Lift

NASA Technical Reports Server (NTRS)

Sumrall, Phil

2010-01-01

Every major examination of America s spaceflight capability since the Apollo program has highlighted and reinforced the need for a heavy lift vehicle for human exploration, science, national security, and commercial development. The Ares V is NASA s most recent effort to address this gap and provide the needed heavy lift capability for NASA and the nation. An Ares V-class heavy lift capability is important to supporting beyond earth orbit (BEO) human exploration. Initially, that consists of exploration of the Moon vastly expanded from the narrow equatorial Apollo missions to a global capability that includes the interesting polar regions. It also enables a permanent human outpost. Under the current program of record, both the Ares V and the lunar exploration it enables serve as a significant part of the technology and experience base for exploration beyond the Moon, including Mars, asteroids, and other destinations. The Ares V is part of NASA s Constellation Program architecture. The Ares V remains in an early stage of concept development, while NASA focused on development of the Ares I crew launch vehicle to replace the Space Shuttle fleet. However, Ares V development has benefitted from its commonality with Ares I, the Shuttle, and contemporary programs on which its design is based. The Constellation program is currently slated for cancellation under the proposed 2011 federal budget, pending review by the legislative branch. However, White House guidance on its 2011 budget retains funding for heavy lift research. This paper will discuss progress to date on the Ares V and its potential utility to payload users.

Apollo 13 - Mission Control Console

NASA Image and Video Library

1970-04-15

S70-35096 (16 April 1970) --- As the problem-plagued Apollo 13 crewmen entered their final 24 hours in space, several persons important to the mission remained attentive at consoles in the Mission Operations Control Room of the Mission Control Center at Manned Spacecraft Center. Among those monitoring communications and serving in supervisory capacities were these four officials from National Aeronautics and Space Administration Headquarters, Washington, D.C.: (from left) Thomas H. McMullen, Office of Manned Space Flight, who served as Shift 1 mission director; Dale Myers, associate administrator, Manned Space Flight; Chester M. Lee of the Apollo Program Directorate, OMSF, Apollo 13 mission director; and Dr. Rocco A. Petrone, Apollo program director, OMSF.

Apollo Program Summary Report: Synopsis of the Apollo Program Activities and Technology for Lunar Exploration

NASA Technical Reports Server (NTRS)

1975-01-01

Overall program activities and the technology developed to accomplish lunar exploration are discussed. A summary of the flights conducted over an 11-year period is presented along with specific aspects of the overall program, including lunar science, vehicle development and performance, lunar module development program, spacecraft development testing, flight crew summary, mission operations, biomedical data, spacecraft manufacturing and testing, launch site facilities, equipment, and prelaunch operations, and the lunar receiving laboratory. Appendixes provide data on each of the Apollo missions, mission type designations, spacecraft weights, records achieved by Apollo crewmen, vehicle histories, and a listing of anomalous hardware conditions noted during each flight beginning with Apollo 4.

Apollo Block I Spacesuit Development and Apollo Block II Spacesuit Competition

NASA Technical Reports Server (NTRS)

McBarron, Jim

2013-01-01

Jim McBarron has over 40 years of experience with the U.S. Air Force pressure suit and NASA spacesuit development and operations. As a result of his experience, he shared his significant knowledge about the requirements and modifications made to the Gemini spacesuit, which were necessary to support the Apollo Block I Program. In addition, he provided an overview of the Apollo Block II Spacesuit competition test program conducted by the NASA Manned Spacecraft Center. Topics covered included the program's chronology; competition test program ground rules, scoring details, and final test results; and the implementation of resulting modifications to the Apollo Spacesuit Program. He concluded his presentation by identifying noteworthy lessons learned.

SNM1B/Apollo in the DNA damage response and telomere maintenance

PubMed Central

Schmiester, Maren; Demuth, Ilja

2017-01-01

hSNM1B/Apollo is a member of the highly conserved β-CASP subgroup within the MBL superfamily of proteins. It interacts with several DNA repair proteins and functions within the Fanconi anemia pathway in response to DNA interstrand crosslinks. As a shelterin accessory protein, hSNM1B/Apollo is also vital for the generation and maintenance of telomeric overhangs. In this review, we will summarize studies on hSNM1B/Apollo's function, including its contribution to DNA damage signaling, replication fork maintenance, control of topological stress and telomere protection. Furthermore, we will highlight recent studies illustrating hSNM1B/Apollo's putative role in human disease. PMID:28430596

SNM1B/Apollo in the DNA damage response and telomere maintenance.

PubMed

Schmiester, Maren; Demuth, Ilja

2017-07-18

hSNM1B/Apollo is a member of the highly conserved β-CASP subgroup within the MBL superfamily of proteins. It interacts with several DNA repair proteins and functions within the Fanconi anemia pathway in response to DNA interstrand crosslinks. As a shelterin accessory protein, hSNM1B/Apollo is also vital for the generation and maintenance of telomeric overhangs. In this review, we will summarize studies on hSNM1B/Apollo's function, including its contribution to DNA damage signaling, replication fork maintenance, control of topological stress and telomere protection. Furthermore, we will highlight recent studies illustrating hSNM1B/Apollo's putative role in human disease.

Apollo: Giving application developers a single point of access to public health models using structured vocabularies and Web services

PubMed Central

Wagner, Michael M.; Levander, John D.; Brown, Shawn; Hogan, William R.; Millett, Nicholas; Hanna, Josh

2013-01-01

This paper describes the Apollo Web Services and Apollo-SV, its related ontology. The Apollo Web Services give an end-user application a single point of access to multiple epidemic simulators. An end user can specify an analytic problem—which we define as a configuration and a query of results—exactly once and submit it to multiple epidemic simulators. The end user represents the analytic problem using a standard syntax and vocabulary, not the native languages of the simulators. We have demonstrated the feasibility of this design by implementing a set of Apollo services that provide access to two epidemic simulators and two visualizer services. PMID:24551417

Apollo: giving application developers a single point of access to public health models using structured vocabularies and Web services.

PubMed

Wagner, Michael M; Levander, John D; Brown, Shawn; Hogan, William R; Millett, Nicholas; Hanna, Josh

2013-01-01

This paper describes the Apollo Web Services and Apollo-SV, its related ontology. The Apollo Web Services give an end-user application a single point of access to multiple epidemic simulators. An end user can specify an analytic problem-which we define as a configuration and a query of results-exactly once and submit it to multiple epidemic simulators. The end user represents the analytic problem using a standard syntax and vocabulary, not the native languages of the simulators. We have demonstrated the feasibility of this design by implementing a set of Apollo services that provide access to two epidemic simulators and two visualizer services.

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.

76 FR 23824 - Guidance for Industry: “Computer Crossmatch” (Computerized Analysis of the Compatibility Between...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-28

... the Compatibility Between the Donor's Cell Type and the Recipient's Serum or Plasma Type... Crossmatch' (Computerized Analysis of the Compatibility between the Donor's Cell Type and the Recipient's... donor's cell type and the recipient's serum or plasma type. The guidance describes practices that we...

77 FR 3779 - Guidance for Industry on Product Name Placement, Size, and Prominence in Advertising and...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-25

...), broadcast media promotion (e.g., television advertisements, radio advertisements), and electronic and computer-based promotional labeling and advertisements, such as Internet promotion, social media, emails... guidance pertain to product names in traditional print media promotion (e.g., journal ads, detail aids...

Effects of Metacognitive Guidance on Critical Thinking Disposition

ERIC Educational Resources Information Center

Akyüz, Halil Ibrahim; Samsa Yetik, Serap; Keser, Hafize

2015-01-01

The present study investigated the effect of metacognitive guidance in an online learning environment on the students' critical thinking competency. The research was carried out using experimental design with pretest-posttest control groups. The research group of the study consisted of 60 students studying at Computer and Educational Teaching…

A Computing based Simulation Model for Missile Guidance in Planar Domain

NASA Astrophysics Data System (ADS)

Chauhan, Deepak Singh; Sharma, Rajiv

2017-10-01

This paper presents the design, development and implementation of a computing based simulation model for interceptor missile guidance for countering an anti-ship missile through a navigation law. It investigates the possibility of deriving, testing and implementing an efficient variation of the PN and RPN laws. A new guidance law [true combined proportional navigation (TCPN) guidance law] that combines the strengths of both the PN and RPN and has a superior capturability in a specified zone of interest is presented in this paper. The presented proportional navigation (PN) guidance law is modeled in a two dimensional planar engagement model and its performance is studied with respect to a varying navigation ratio (N) that is dependent on the `heading error (HE)' and missile lead angle. The advantage of varying navigation ratio is: if N' > 2, Vc > 0, Vm > 0, then the sign of navigation ratio is determined by cos (ɛ + HE) and for cos (ɛ + HE) ≥ 0 and N > 0, the formulation reduces to that of PN and for cos (ɛ + HE) < 0 and N < 0, the formulation reduces to that of RPN. Hence, depending upon the values of cos (ɛ + HE) the presented navigation guidance strategy is shuffled between the PN navigation ratio and the RPN navigation ratio. The theoretical framework of TCPN guidance law is implemented in two dimensional setting of parameters. An important feature of TCPN is the HE and the aim is to achieve lower values of the heading error in simulation. The presented results in this paper show the efficiency of simulation model and also establish that TCPN can be an accurate guidance strategy that has its own range of application and suitability.

Launch of Apollo 8 lunar orbit mission

NASA Image and Video Library

1968-12-21

S68-56050 (21 Dec. 1968)--- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 is the first manned Saturn V launch. (water in foreground, seagulls)

Seismometer reading viewed in ALSEP Room in Misson Control during Apollo 17

NASA Technical Reports Server (NTRS)

1972-01-01

The seismometer readings from the impact made by the Apollo 17 Saturn S-IVB stage when it struck the lunar surface are viewed in the ALSEP Room in the Misson Control Center at Houston by Dr. Maurice Ewing, professor of geophysics of the Universtiy of Texas at Galveston. The seismic tracings are from sensings made by seismometers of Apollo Lunar Surface Experiments Packages left on the Moon during earlier Apollo lunar landing missions.

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, NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft 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, Apollo 11 crew members, Buzz Aldrin, Neil Armstrong, and Michael Collins. 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, Former NASA Astronaut and U.S. Senator John Glenn 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 NASA Mission Control creator and former NASA Johnson Space Center director Chris Kraft, Apollo 11 crew members, Buzz Aldrin, Neil Armstrong, and Michael Collins. 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 the first human landing on the Moon, Apollo 11 Astronaut Neil Armstrong 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)

APOLLO XII - ART CONCEPT - COMMAND MODULE

NASA Image and Video Library

1969-11-10

S69-58005 (10 Nov. 1969) --- An artist's concept of the Apollo 12 Command Module's (CM) interior, with the command module pilot at the controls. The Apollo 12 Lunar Module (LM) and a portion of the lunar surface are seen out of the window. Astronaut Richard F. Gordon Jr. will maneuver the Apollo 12 Command and Service Modules (CSM) in lunar orbit while astronauts Charles Conrad Jr., commander, and Alan L. Bean, lunar module pilot, explore the moon.

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, participates in water egress training in the Gulf of Mexico. In hatch of the Apollo egress trainer (command module) is Astronaut Walter M. Schirra Jr., Sitting in life raft are Astronauts Walter Cunningham (on left) and Donn F. Eisele. A team of Manned Spaceflight Center swimmers assisted with the training exercise. The inflated bags were used to upright the trainer prior to egress.

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, participates in water egress training in the Gulf of Mexico. Left to right, are Astronauts Walter M. Schirra Jr. (stepping into life raft); Donn F. Eisele, and Walter Cunningham. They have just egressed the Apollo Command Module Boilerplate 1102, and are awaiting helicopter pickup. Inflated bags were used to upright the boilerplate. Manned Spaceflight Center swimmers assisted in the training exercise.

KSC-2012-1846

NASA Image and Video Library

2012-02-17

Apollo/Saturn Program: In January 1962, NASA initiated development of the large launch vehicle for the Project Apollo manned lunar flights. The Saturn V configuration comprised the S-IC first stage, the S-II second stage and the S-IVB third stage, all integrated and stacked in the Vehicle Assembly Building. The first manned Apollo spacecraft launched on the mighty Saturn V was Apollo 8 on December 21, 1968. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

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.

Astronaut John Young displays drawing of Snoopy

NASA Technical Reports Server (NTRS)

1969-01-01

Astronaut John W. Young, Apollo 10 command module pilot, displays drawing of Snoopy in this color reproduction taken from the fourth telecast made by the color television camera aboard the Apollo 10 spacecraft. When this picture was made the Apollo 10 spacecraft was about half-way to the moon, or approximately 112,000 nautical miles from the earth. Snoopy will be the code name of the Lunar Module (LM) during Apollo 10 operations when the LM and CM are separated.

Apollo 17 preliminary science report. [Apollo 17 investigation of Taurus-Littrow lunar region

NASA Technical Reports Server (NTRS)

1973-01-01

An analysis of the Apollo 17 flight is presented in the form of a preliminary science report. The subjects discussed are: (1) Apollo 17 site selection, (2) mission description, (3) geological investigation of landing site, (4) lunar experiments, (5) visual flight flash phenomenon, (6) volcanic studies, (7) mare ridges and related studies, (8) remote sensing and photogrammetric studies, and (9) astronomical photography. Extensive photographic data are included for all phases of the mission.

Apollo 8 crew shown during intravehicular activity during mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Frank Borman, commander, is shown during intravehicular activity on the Apollo 8 lunar orbit mission. This still print was made from movie film taken by an on-board 16mm motion picture camera (56531); Astronaut William A. Anders, lunar module pilot, is shown during intravehicular activity on the Apollo 8 lunar orbit mission (56532); Astronaut James A. Lovell Jr., command module milot, is shown during intravehicular activity on the Apollo 8 lunar orbit mission (56533).

LAUNCH - APOLLO VII - KSC

NASA Image and Video Library

1968-10-11

S68-48666 (11 Oct. 1968) --- The Apollo 7/Saturn IB space vehicle is launched from the Kennedy Space Center's Launch Complex 34 at 11:03 a.m. (EDT), Oct. 11, 1968. Apollo 7 (Spacecraft 101/Saturn 205) is the first of several manned flights aimed at qualifying the spacecraft for the half-million-mile round trip to the moon. Aboard the Apollo spacecraft are astronauts Walter M. Schirra Jr., commander; Donn F. Eisele, command module pilot; and Walter Cunningham, lunar module pilot.

Astronauts Stafford and Brand at controls of Apollo Command Module

NASA Technical Reports Server (NTRS)

1975-01-01

Two American ASTP crewmen, Astronauts Thomas P. Stafford (foreground) and Vance D. Brand are seen at the controls of the Apollo Command Module during the joint U.S.-USSR Apollo Soyuz Test Project (ASTP) docking in Earth orbit mission.

Astronaut Donn Eisele photographed during Apollo 7 mission

NASA Image and Video Library

1968-10-20

AS07-04-1600 (20 Oct. 1968) --- Astronaut Donn F. Eisele, Apollo 7 command module pilot, smiles through a heavy growth of beard as he is photographed during a momentary pause on the ninth day of the Apollo 7 mission.

Lunar map showing traverse plans for Apollo 14 lunar landing mission

NASA Image and Video Library

1970-09-01

This lunar map shows the traverse plans for the Apollo 14 lunar landing mission. Areas marked include Lunar module landing site, areas for the Apollo Lunar Surface Experiment Package (ALSEP) and areas for gathering of core samples.

Apollo 40th Anniversary Morning Television

NASA Image and Video Library

2009-07-19

Apollo 12 astronaut Alan Bean responds to a question during a live television interview on Monday, July 20, 2009, at NASA Headquarters in Washington. Bean was lunar module pilot on Apollo 12, man's second lunar landing. Photo Credit: (NASA/Paul E. Alers)

Virtual Microscope Views of the Apollo 11, 12, and 15 Lunar Samples

NASA Technical Reports Server (NTRS)

Gibson, E. K.; Tindle, A. G.; Kelley, S. P.; Pillinger, J. M.

2017-01-01

The Apollo virtual microscope is a means of viewing, over the Internet, polished thin sections of every rock in the Apollo lunar sample collections. It uses software that duplicates many of the functions of a petrological microscope.

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

Singer Chaka Khan performs 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)

Kennedy Center Salute To Apollo

NASA Image and Video Library

2009-07-17

The audience applauds 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)

Apollo experience report: Lunar module landing radar and rendezvous radar

NASA Technical Reports Server (NTRS)

Rozas, P.; Cunningham, A. R.

1972-01-01

A developmental history of the Apollo lunar module landing and rendezvous radar subsystems is presented. The Apollo radar subsystems are discussed from initial concept planning to flight configuration testing. The major radar subsystem accomplishments and problems are discussed.

Apollo 15 30-day failure and anomaly listing report

NASA Technical Reports Server (NTRS)

1971-01-01

The significant anomalies that occurred during the Apollo 15 mission are discussed. The five major areas are command and service modules, lunar module, scientific instrument module experiments, Apollo lunar surface experiment package and associated equipment, and government furnished equipment.

Mineralogy and cooling history of magnesian lunar granulite 67415

NASA Technical Reports Server (NTRS)

Takeda, Hiroshi; Miyamoto, Masamichi

1993-01-01

Apollo granulite 67415 was investigated by mineralogical techniques to gain better understanding of cooling histories of lunar granulities. Cooling rates were estimated from chemical zoning of olivines in magnesian granulitic clasts by computer simulation of diffusion processes. The cooling rate of 10 deg C/yr obtained is compatible with a model of the granulite formation, in which the impact deposit was cooled from high temperature or annealed, at the depth of about 25 m beneath the surface.

Guidance and Control System for an Autonomous Vehicle

DTIC Science & Technology

1990-06-01

implementing an appropriate computer architecture in support of these goals is also discussed and detailed, along with the choice of associated computer hardware and real - time operating system software. (rh)

21 CFR 803.14 - How do I submit a report electronically?

Code of Federal Regulations, 2014 CFR

2014-04-01

... submissions include alternative reporting media (magnetic tape, disc, etc.) and computer-to-computer communication. (b) If your electronic report meets electronic reporting standards, guidance documents, or other...

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

Restoration of the Apollo Heat Flow Experiments Metadata

NASA Technical Reports Server (NTRS)

Nagihara, S.; Stephens, M. K.; Taylor, P. T.; Williams, D. R.; Hills, H. K.; Nakamura, Y.

2015-01-01

Geothermal heat flow probes were deployed on the Apollo 15 and 17 missions as part of the Apollo Lunar Surface Experiments Package (ALSEP). At each landing site, the astronauts drilled 2 holes, 10-m apart, and installed a probe in each. The holes were 1- and 1.5-m deep at the Apollo 15 site and 2.5-m deep at the Apollo 17 sites. The probes monitored surface temperature and subsurface temperatures at different depths. At the Apollo 15 site, the monitoring continued from July 1971 to January 1977. At the Apollo 17 site, it did from December 1972 to September 1977. Based on the observations made through December 1974, Marcus Langseth, the principal investigator of the heat flow experiments (HFE), determined the thermal conductivity of the lunar regolith by mathematically modeling how the seasonal temperature fluctuation propagated down through the regolith. He also determined the temperature unaffected by diurnal and seasonal thermal waves of the regolith at different depths, which yielded the geothermal gradient. By multiplying the thermal gradient and the thermal conductivity, Langseth obtained the endogenic heat flow of the Moon as 21 mW/m(exp 2) at Site 15 and 16 mW/m(exp 2) at Site 17.

Mapping the Apollo 17 landing site area based on Lunar Reconnaissance Orbiter Camera images and Apollo surface photography

NASA Astrophysics Data System (ADS)

Haase, I.; Oberst, J.; Scholten, F.; Wählisch, M.; Gläser, P.; Karachevtseva, I.; Robinson, M. S.

2012-05-01

Newly acquired high resolution Lunar Reconnaissance Orbiter Camera (LROC) images allow accurate determination of the coordinates of Apollo hardware, sampling stations, and photographic viewpoints. In particular, the positions from where the Apollo 17 astronauts recorded panoramic image series, at the so-called “traverse stations”, were precisely determined for traverse path reconstruction. We analyzed observations made in Apollo surface photography as well as orthorectified orbital images (0.5 m/pixel) and Digital Terrain Models (DTMs) (1.5 m/pixel and 100 m/pixel) derived from LROC Narrow Angle Camera (NAC) and Wide Angle Camera (WAC) images. Key features captured in the Apollo panoramic sequences were identified in LROC NAC orthoimages. Angular directions of these features were measured in the panoramic images and fitted to the NAC orthoimage by applying least squares techniques. As a result, we obtained the surface panoramic camera positions to within 50 cm. At the same time, the camera orientations, North azimuth angles and distances to nearby features of interest were also determined. Here, initial results are shown for traverse station 1 (northwest of Steno Crater) as well as the Apollo Lunar Surface Experiment Package (ALSEP) area.

Apollo: Learning From the Past, For the Future

NASA Technical Reports Server (NTRS)

Grabois, Michael R.

2009-01-01

This paper shares an interesting and unique case study of knowledge capture by the National Aeronautics and Space Administration (NASA), an ongoing project to recapture and make available the lessons learned from the Apollo lunar landing project so that those working on future projects do not have to "reinvent the wheel". NASA's new Constellation program, the successor to the Space Shuttle program, proposes a return to the Moon using a new generation of vehicles. The Orion Crew Vehicle and the Altair Lunar Lander will use hardware, practices, and techniques descended and derived from Apollo, Shuttle and the International Space Station. However, the new generation of engineers and managers who will be working with Orion and Altair are largely from the decades following Apollo, and are likely not well aware of what was developed in the 1960s. In 2006 a project at NASA's Johnson Space Center was begun to find pertinent Apollo-era documentation and gather it, format it, and present it using modern tools for today's engineers and managers. This "Apollo Mission Familiarization for Constellation Personnel" project is accessible via the web from any NASA center for those interested in learning "how did we do this during Apollo?"

Apollo: Learning From the Past, For the Future

NASA Technical Reports Server (NTRS)

Grabois, Michael R.

2010-01-01

This paper shares an interesting and unique case study of knowledge capture by the National Aeronautics and Space Administration (NASA), an ongoing project to recapture and make available the lessons learned from the Apollo lunar landing project so that those working on future projects do not have to "reinvent the wheel". NASA's new Constellation program, the successor to the Space Shuttle program, proposes a return to the Moon using a new generation of vehicles. The Orion Crew Vehicle and the Altair Lunar Lander will use hardware, practices, and techniques descended and derived from Apollo, Shuttle and the International Space Station. However, the new generation of engineers and managers who will be working with Orion and Altair are largely from the decades following Apollo, and are likely not well aware of what was developed in the 1960s. In 2006 a project at NASA's Johnson Space Center was begun to find pertinent Apollo-era documentation and gather it, format it, and present it using modern tools for today's engineers and managers. This "Apollo Mission Familiarization for Constellation Personnel" project is accessible via the web from any NASA center for those interested in learning "how did we do this during Apollo?"