Search NASA⌕ Search

SEARCH · Search NASA

Results for “Apollo”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 595 records · Page 33
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Apollo 16 time and motion study

A time and motion study is presented of astronaut lunar surface activity on Apollo 16 which consists of five distinct analyses: an evaluation of lunar mobility, a comparison of task performance in 1-g training and lunar EVA, a study of metabolic costs and adaptation, a discussion of falls, and retrieval of fallen objects. Two basic mobility patterns, the hop or canter and the traditional walking gait, were consistently utilized in longer traverses. The metabolic rates associated with these two mobility types, each used by a different astronaut, were relatively equivalent. The time to perform tasks on the lunar surface was significantly longer (on the order of 70%) than the time to perform the same tasks during the last 1-g training session. These results corroborated the findings on Apollo 15 and were not significantly different from them. There was general improvement in lunar EVA performance upon repetition of tasks. Metabolic rate (BTU/hr.) and metabolic cost (BTU) decreased over successive EVAs. Specifically, the metabolic rate associated with riding the lunar roving vehicle (LRV) decreased by approximately 18% from EVA 1 to EVA 2 and by 15% from EVA 2 to EVA 3.

Kubis, J. F.↗
NASA NTRS1972

Dynamic analysis of Apollo-Salyut/Soyuz docking

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.

Schliesing, J. A.↗
NASA NTRS1973

Apollo experience report: Launch escape propulsion subsystem

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

Townsend, N. A.↗
NASA NTRS1973

Apollo experience report: Spacecraft heating environment and thermal protection for launch through the atmosphere of the earth

The techniques that were used to define the aerothermodynamic environment of the Apollo spacecraft during the boost phase and to predict the structural temperatures of the spacecraft are discussed. The wind-tunnel and radiant-heating tests that were used to support the analytical predictions are discussed. The analytical predictions are discussed. The accuracy of the boost-phase heating-analysis techniques is shown by comparing the techniques with flight data. The analytical techniques for predicting heating characteristics and structural temperatures of the spacecraft were adequate for predicting the temperatures of the Apollo spacecraft during the boost phase.

Dotts, R. L.↗
NASA NTRS1973

Apollo experience report: Power generation system

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

Bell, D., III↗
NASA NTRS1973

Apollo experience report: The problem of stress-corrosion cracking

Stress-corrosion cracking has been the most common cause of structural-material failures in the Apollo Program. The frequency of stress-corrosion cracking has been high and the magnitude of the problem, in terms of hardware lost and time and money expended, has been significant. In this report, the significant Apollo Program experiences with stress-corrosion cracking are discussed. The causes of stress-corrosion cracking and the corrective actions are discussed, in terminology familiar to design engineers and management personnel, to show how stress-corrosion cracking can be prevented.

Johnson, R. E.↗
NASA NTRS1972

An investigation to improve selenodetic control on the lunar limb utilizing Apollo 15 trans-earth photography

A study is made using actual metric photography taken by Apollo 15 after the trans earth injection when the spacecraft left the lunar orbit. After measurements on 12 frames were reduced for 11 known control and unknown points on the eastern limb, a least squares adjustment program provided the simultaneous solution for the selected points. The results indicate an improvement in selenodetic control may be achieved over a limited portion of the lunar limb; however, the solution could be further improved by strengthening the geometry of intersecting rays through additional observations of the same area using film from the succeeding Apollo missions.

Riotte, W.↗
NASA NTRS1972

Dynamic mass modeling and geophysical analysis of lunar maria based on Apollo tracking data

A series of lunar gravity analyses were carried out using unified S-band tracking network data obtained from Apollos 8, 10, 11, 12, 14, and 15. The progress obtained to date is summarized as it relates to the estimation of lunar mass distributions and their geologic interpretation. The analyses reported are of two distinct types. The first type consists of data obtained at two ranges of altitude to estimate the total mass associated with various lunar features employing a point mass assumption. The second type consists of detailed analyses of Apollo 14 tracking data.

Strange, W. E.↗
NASA NTRS1973

Apollo experience report: Flight instrumentation calibration

Three types of instrumentation-calibration data were used in the Apollo Program to provide the correct engineering data for tests and mission support. The command and service module instrumentation-component procurement specifications required individual-component calibration, and calibration data for these individual components (conventional-calibration data) were always used for mission data support. A mean standard type of calibration data derived from a statistical sampling of conventional-calibration data was used for test and checkout during the latter part of the Apollo Program. The lunar module instrumentation procurement specification permitted the use of standard-calibration data. These data were applicable to similarly instrumented measurements. The definition, merit, and application of each type of data are discussed.

Demoss, J. F.↗
NASA NTRS1972

Apollo window meteoroid experiment

The Apollo window meteoroid experiment is described which uses the Apollo command module heat shield window surfaces to obtain information about the flux of meteoroids with masses of 10 to the minus 7th power g and less; to examine the residue and the morphology of the craters produced by these meteoroid; to obtain information regarding the dynamic and physical properties of the meteoroids; and to discover possible correlations with the lunar-rock-crater studies. Photographs are included.

Cour-Palais, B. G.↗
NASA NTRS1972

Photogeology. Part A: Relative ages of some near-side and far-side terra plains based on Apollo 16 metric photography

Relative age measurements were made for 14 light plains areas, using 30X enlargements of Apollo 16 metric camera photography. Results indicate that: (1) Crater morphology and frequency studies consistently indicate that the Fra Mauro Formation has received 2.5 to 3 times as much impact flux as the Cayley Formation. (2) Crater counts and relative age dating indicate that the Cayley Formation is only slightly older than the oldest mare units. (3) Assuming the rubidium-strontium ages of Apollo 14 basalt breccias give minimum age for Fra Mauro Formation, the Cayley Formation must have been generated throughout a period of less than 100 million years, approximately 3.8 to 3.9 billion years ago. (4) The Cayley Formation ages obtained on the near side and far side are the same, indicating a synchrony throughout the moon in these units. (5) The linear relationship as predicted by the small impact erosion model between net accumulated flux and the maximum diameter of a crater that could be eroded below recognition is confirmed.

Soderblom, L. A.↗
NASA NTRS1973

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

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

Gilbert, D. W.↗
NASA NTRS1973

Apollo Experience Report: Command and Service Module Reaction Control Systems

The reaction control systems of the Apollo command and service module were developed and modified between July 1961 and July 1969. The successful development of these systems, as part of the Apollo Program, was the result of extensive testing, retesting, and modifications of the hardware to ensure system capability and intrasystem compatibility.

Taeuber, Ralph J.↗
NASA NTRS1973

Apollo experience report: Evolution of the rendezvous-maneuver plan for the lunar-landing missions

The evolution of the nominal rendezvous-maneuver plan for the lunar landing missions is presented along with a summary of the significant development for the lunar module abort and rescue plan. A general discussion of the rendezvous dispersion analysis that was conducted in support of both the nominal and contingency rendezvous planning is included. Emphasis is placed on the technical developments from the early 1960's through the Apollo 15 mission (July to August 1971), but pertinent organizational factors also are discussed briefly. Recommendations for rendezvous planning for future programs relative to Apollo experience also are included.

Alexander, J. D.↗
NASA NTRS1973

Apollo experience report: Reliability and quality assurance

The reliability of the Apollo spacecraft resulted from the application of proven reliability and quality techniques and from sound management, engineering, and manufacturing practices. Continual assessment of these techniques and practices was made during the program, and, when deficiencies were detected, adjustments were made and the deficiencies were effectively corrected. The most significant practices, deficiencies, adjustments, and experiences during the Apollo Program are described in this report. These experiences can be helpful in establishing an effective base on which to structure an efficient reliability and quality assurance effort for future space-flight programs.

Sperber, K. P.↗
NASA NTRS1973

Apollo experience report: Spacecraft structural windows

The window structural design and verification experience is presented for the Apollo command and lunar modules. This report presents window design philosophy, design criteria, hardware description, and qualification and acceptance test programs and discusses the problems encountered and solutions developed in these areas. The structural characteristics of glass are not generally well understood by designers. The optics and instrument glass covers were not considered to be structural components and thus were not normally subjected to the design, qualification, and acceptance standards necessary to preclude failures. These two factors contributed significantly to window problems on both Apollo spacecraft.

Pigg, O. E.↗
NASA NTRS1973

Apollo experience report: Postflight testing of command modules

Various phases of the postflight testing of the command modules used in the Apollo Program are presented. The specific tasks to be accomplished by the task force recovery teams, the National Aeronautics and Space Administration Lyndon B. Johnson Space Center, (formerly the Manned Spacecraft Center) and the cognizant contractors/subcontractors are outlined. The means and methods used in postflight testing and how such activities evolved during the Apollo Program and were tailored to meet specific test requirements are described. Action taken to resolve or minimize problems or anomalies discovered during the flight, the postflight test phase, or mission evaluation is discussed.

Hamilton, D. T.↗
NASA NTRS1972

Engineering potential for lunar missions after Apollo.

The need for continuing post-Apollo lunar research is defined by outlining problems in stellar, planetary, biological, and social evolution which require specific studies of the moon. Engineering capabilities existing immediately after the Apollo program are described in the areas of launch vehicles and spacecraft, lunar surface mobility, instrumentation, and communications.

Burke, J. D.↗