Apollo 14 mission, 5 day report
Postflight report of Apollo 14 mission covering preflight experiments, launch, lunar EVA, and recovery
Source record↗
SEARCH · Engineering Papers
Results for “EVA”
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.
A study of telescope maintenance and updating in orbit
Large aperture telescope in-orbit maintainability packaging, examining optical systems replacement tolerances and astronauts EVA mode accessibility
Gratz, W.↗
Experiment D016: Power tool evaluation
Power tool evaluation was not attempted during the Gemini 11 mission because of the premature termination of the on-umbilical extravehicular activity (EVA). The experiment had been scheduled for the Gemini 8 mission, but early mission termination prevented completion of the experiment. However, the objective, equipment description, and experimental precedures are described briefly in this report.
Ettredge, V. L.↗
Apollo oxygen tank stratification analysis, volume 2
An analysis of flight performance of the Apollo 15 cryogenic oxygen tanks was conducted with the variable grid stratification math model developed earlier in the program. Flight conditions investigated were the CMP-EVA and one passive thermal control period which exhibited heater temperature characteristics not previously observed. Heater temperatures for these periods were simulated with the math model using flight acceleration data. Simulation results (heater temperature and tank pressure) compared favorably with the Apollo 15 flight data, and it was concluded that tank performance was nominal. Math model modifications were also made to improve the simulation accuracy. The modifications included the addition of the effects of the tank wall thermal mass and an improved system flow distribution model. The modifications improved the accuracy of simulated pressure response based on comparisons with flight data.
Barton, J. E.↗
University role in astronaut life support systems: Extravehicular guidance and stabilization in space
Two problem areas are reviewed: (1) the nature of and approach to the EVA mission and (2) the guidance and stabilization required of such a mission. The report indicates several broad areas in which additional research is needed to provide an advance to the state-of-the-art. Moreover, the research problems cited were chosen from among many as those most amenable to research and study in the university environment.
Vonrenner, L. C.↗
Preliminary geologic investigation of the Apollo 15 landing site
The Apollo 15 lunar module (LM) landed on the mare surface of Palus Putredinis on the eastern edge of the Imbrium Basin. The site is between the Apennine Mountain front and Hadley Rille. The objectives of the mission, in order of decreasing priority, were description and sampling of three major geologic features-the Apennine Front, Hadley Rille, and the mare. The greater number of periods of extravehicular activity (EVA) and the mobility provided by the lunar roving vehicle (ROVER) allowed much more geologic information to be obtained from a much larger area than those explored by previous Apollo crews. A total of 5 hours was spent at traverse station stops, and the astronauts transmitted excellent descriptions of the lunar surface while in transit between stations.
Swann, G. A.↗
Advanced extravehicular protective systems study, volume 1
An appraisal was made of advanced portable and emergency life support systems concepts for space station, space shuttle, lunar base, and Mars EVA missions. Specifications are given, and the methodology is described. Subsystem studies and systems integration efforts are summarized. Among the conclusions are the following: (1) For long duration missions, a configuration incorporating a regenerable CO2 control subsystem and a thermal control subsystem utilizing a minimum of expendables decreases the vehicle penalty of present configurations. (2) For shorter duration missions, a configuration incorporating an expendable water thermal control subsystem is the most competitive subsystem; regenerable CO2 control subsystems if properly developed are competitive with nonregenerable counterparts. (3) The CO2 reduction and oxygen reclamation withing the parent vehicle is only competitive when there are three or more parent vehicle resupply periods. (4) For long duration emergency systems of one hour or more, inherent redundancy within the primary configuration to provide emergency thermal control is the most competitive approach.
Sutton, J. G.↗
Apollo 16 (Descartes) landing site road log
The landing site traverse log is presented for the Apollo 16 mission. EVA's 1, 2, and 3 are included.
Boudette, E. L.↗
Apollo 15 Mission Report
A detailed discussion is presented of the Apollo 15 mission, which conducted exploration of the moon over longer periods, greater ranges, and with more instruments of scientific data acquisition than previous missions. The topics include trajectory, lunar surface science, inflight science and photography, command and service module performance, lunar module performance, lunar surface operational equipment, pilot's report, biomedical evaluation, mission support performance, assessment of mission objectives, launch phase summary, anomaly summary, and vehicle and equipment descriptions. The capability of transporting larger payloads and extending time on the moon were demonstrated. The ground-controlled TV camera allowed greater real-time participation by earth-bound personnel. The crew operated more as scientists and relied more on ground support team for systems monitoring. The modified pressure garment and portable life support system provided better mobility and extended EVA time. The lunar roving vehicle and the lunar communications relay unit were also demonstrated.
Source record↗
Safety in earth orbit study. Volume 2: Analysis of hazardous payloads, docking, on-board survivability
Detailed and supporting analyses are presented of the hazardous payloads, docking, and on-board survivability aspects connected with earth orbital operations of the space shuttle program. The hazards resulting from delivery, deployment, and retrieval of hazardous payloads, and from handling and transport of cargo between orbiter, sortie modules, and space station are identified and analyzed. The safety aspects of shuttle orbiter to modular space station docking includes docking for assembly of space station, normal resupply docking, and emergency docking. Personnel traffic patterns, escape routes, and on-board survivability are analyzed for orbiter with crew and passenger, sortie modules, and modular space station, under normal, emergency, and EVA and IVA operations.
Source record↗
On the moon with Apollo 15: A guidebook to Hadley Rille and the Apennine Mountains
Information is given in simple terms of the Apollo 15 lunar exploration and scientific equipment, to be used in conjunction with other material shown over commercial TV. The EVAs of the astronauts on the surface are divided into experiments and traverses. The landing site and experimental equipment are described, and life sketches are given of the crew.
Simmons, G.↗
Development and evaluation of thermoplastic street maintenance material
An all-weather permanent street patching material was investigated for flexible and rigid pavements. The economic, operational, and material requirements are discussed along with the results of field tests with various mixtures of EVA resins and asphalt. Cost analyses for thermoplastic patching methods are included.
Siemens, W. D.↗
Geosynchronous platform definition study. Volume 5: Geosynchronous platform synthesis
The development is described of the platform configurations, support subsystems, mission equipment, and servicing concepts. A common support module is developed; subsystem concepts are traded off; data relay, TDRS, earth observational, astro-physics, and advanced navigation and traffic control mission equipment concepts are postulated; and ancillary equipment required for delivery and on-orbit servicing interfaces with geosynchronous platforms is grossly defined. The general approach was to develop a platform concept capable of evolving through three on-orbit servicing modes: remote, EVA, and shirtsleeve. The definition of the equipment is to the assembly level. Weight, power, and volumetric data are compiled for all the platforms.
Source record↗
Apollo 17: At Taurus Littrow
A summation, with color illustrations, is presented on the Apollo 17 mission. The height, weight, and thrust specifications are given on the launch vehicle. Presentations are given on: the night launch; earth to moon ascent; separation and descent; EVA, the sixth lunar surface expedition; ascent from Taurus-Littrow; the America to Challenger rendezvous; return, reentry, and recovery; the scientific results of the mission; background information on the astronauts; and the future projects.
Anderton, D. A.↗
The Apollo 17 surface experiments.
Significant previous Apollo scientific results which influenced the selection of site for the Apollo 17 mission are reviewed. Apollo 17 assignments and equipment are characterized as an outgrowth of the preceding Apollo missions which is focused on the main problems of lunar form and origin. Details are given on the Apollo Lunar Surface Experiments Package (ALSEP) experiments, non-ALSEP experiments, the Lunar Seismic Profiling Experiment (LSPE), and the three periods of extravehicular activity (EVA) of Apollo 17.
Hinners, N. W.↗
Space Shuttle Orbiter ECLSS.
The Orbiter Environmental Control and Life Support System (ECLSS) provides the functions of atmosphere revitalization, crew life support, active thermal conditioning, and airlock support for EVA and docking activities. The ECLSS must satisfy the requirements of orbital missions with four to ten crewmembers and mission duration of a few hours to 30 days and the requirements associated with an atmospheric horizontal flight test program and ferry flight missions. The ECLSS development plan utilizes an ECLSS ground test article and thermal/vacuum testing to support the first horizontal flight test at the end of 1976. The ground testing and horizontal flight test program certify the Orbiter ECLSS for the first orbital flight in early 1978.
Stoll, O. T.↗
Traverse gravimeter experiment
The primary goal of the traverse gravimeter experiment (TGE) was to make relative gravity measurements at a number of sites in the Apollo 17 landing area and to use these measurements to obtain information about the geological substructure. A secondary goal was to obtain the value of the gravity at the landing site relative to an accurately known value on earth. Both these goals were successfully achieved by the experiment. A gravity tie has been obtained between the Taurus-Littrow landing site and the earth with an estimated accuracy of approximately 5 mgal. Relative gravity measurements that can be used to infer the substructure of the area have been obtained at stations visited during each period of extravehicular activity (EVA).
Talwani, M.↗
MSFC Skylab Kohoutek experiments mission evaluation
The Comet Kohoutek was documented by the Skylab 4 experiments' observations. The experiment concepts, hardware, operational performance and anomalies are discussed. Experiments which viewed the comet were mainly through the SAL and ATM, but some were handheld and EVA.
Source record↗