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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.

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NASA NTRS1971

Simple mass distribution for the lunar potential.

A set of twenty-one point masses gravitationally equivalent to the L1 lunar potential model is presented. By construction, the equivalence is valid only in a region of space 'sampled' by Apollo spacecraft. That region is taken to be a finite, torus-shaped shell. When used in place of the L1 model for Apollo 12 lunar orbit determination, the solution set gives spacecraft positions identical to within about 100 m. The solution is developed in two steps: first the L1 potential is examined to determine favorable mass locations, and then the mass values are computed to force an optimum matching of the L1 potential. Therefore the solution set is 'artificial.' It is related to the moon's actual mass distribution only in its similar gravitational effects in a limited region of space.

Levie, S. L., Jr.↗
NASA NTRS1974

Apollo experience report: Test and checkout

The problem areas encountered during the development of the acceptance testing and preflight checkout requirements and procedures for Apollo spacecraft are discussed. Recommendations are given for cases in which methods used in the Apollo program are considered to apply to future space flight programs.

Mechelay, J. E.↗
NASA NTRS1963

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

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

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NASA NTRS1974

Development of the Apollo Control Network

Description of activities associated with photogrammetric reduction of photography and support data gathered by Apollo spacecraft in lunar orbit. The aim of these activities is to combine all data from Apollo 15, 16, and 17 missions for the purpose of forming a unified control system on the moon called the Apollo Control Network. The status of efforts at reduction of data from each of these missions is summarized along with a proposed scheme for combining the three missions in a simultaneous reduction. Plans to expand the network by use of Apollo oblique mapping photography are also discussed, and the results of an oblique triangulation test are evaluated.

Hassell, J. R.↗
NASA NTRS1971

Spacecraft cryogenic gas storage systems

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

Rysavy, G.↗
NASA NTRS1976

Faster Finances

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.

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NASA NTRS1972

Comments on the figure of the moon from Apollo landmark tracking.

The selenographic positions of the observed lunar features are solved for, or estimated directly from, angular measurements made from the orbiting spacecraft (Apollo missions 8, 10, 11, 12, 14, and 15) to the landmark, using least-squares techniques. It appears that the radius values derived from the Apollo landmark data provide some proof of the existence of a displacement between the center of figure and center of mass of the moon along the earth-moon line. In addition, all three components of the estimated crater locations should be useful toward establishing a selenodetic reference system for interpreting or reducing earth-based observation data.

Wollenhaupt, W. R.↗
NASA NTRS2009

Orbital Debris Quarterly News, Volume 13, Issue 4

Although NASA has conducted research on orbital debris since the 1960s, the NASA Orbital Debris Program Office is now considered to have been established in October 1979, following the recognition by senior NASA officials of orbital debris as a space environmental issue and the allocation by NASA Headquarters Advanced Programs Office to the Lyndon B. Johnson Space Center (JSC) of funds specifically dedicated for orbital debris investigations. In the 30 years since, the NASA Orbital Debris Program Office has pioneered the characterization of the orbital debris environment and its potential effects on current and future space systems, has developed comprehensive orbital debris mitigation measures, and has led efforts by the international aerospace community in addressing the challenges posed by orbital debris. In 1967 the Flight Analysis Branch at the Manned Spacecraft Center (renamed the Lyndon B. Johnson Space Center in 1973) evaluated the risks of collisions between an Apollo spacecraft and orbital debris. Three years later the same group calculated collision risks for the forthcoming Skylab space station, which was launched in 1973. By 1976, the nucleus of NASA s yet-to-be-formed orbital debris research efforts, including Andrew Potter, Burton Cour-Palais, and Donald Kessler, was found in JSC s Environmental Effects Office, examining the potential threat of orbital debris to large space platforms, in particular the proposed Solar Power Satellites (SPS).

Liou, Jer-Chyi↗
NASA NTRS2014

The Max Launch Abort System - Concept, Flight Test, and Evolution

The NASA Engineering and Safety Center (NESC) is an independent engineering analysis and test organization providing support across the range of NASA programs. In 2007 NASA was developing the launch escape system for the Orion spacecraft that was evolved from the traditional tower-configuration escape systems used for the historic Mercury and Apollo spacecraft. The NESC was tasked, as a programmatic risk-reduction effort to develop and flight test an alternative to the Orion baseline escape system concept. This project became known as the Max Launch Abort System (MLAS), named in honor of Maxime Faget, the developer of the original Mercury escape system. Over the course of approximately two years the NESC performed conceptual and tradeoff analyses, designed and built full-scale flight test hardware, and conducted a flight test demonstration in July 2009. Since the flight test, the NESC has continued to further develop and refine the MLAS concept.

Gilbert, Michael G.↗
NASA NTRS1975

The gravity and shape of the moon

This review discusses the current knowledge of the gravity and geometry of the moon, and their implications as to lunar structure. Measurements pertaining to the gravity field are, first and foremost, Doppler tracking of spacecraft that have orbited the moon, but also the laser ranging from the earth to the moon and the gravity meters and accelerometers landed with the Apollo spacecraft. Measurements pertaining to the geometry include (1) those related to the shape: the metric photography and laser altimeters on Apollo 15, 16, and 17; the electromagnetic sounder on Apollo 17; the landmark tracking from earlier Apollo orbiters; and occupations, plus (2) measurements related to the orientation: the laser ranging and interferometry from the earth. The review does not cover determinations of topography from photography taken for geologic or landing reconnaissance purposes. The discussion of tectonic implications is limited to inferences of a quantitative nature. The emphasis is on work since 1970; see Kaula [1969, 1971] for reviews of earlier work.

William M. Kaula↗
NASA NTRS2008

Apollo Lesson Sampler: Apollo 13 Lessons Learned

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

Interbartolo, Michael A.↗
NASA NTRS1971

Development of nonflammable potting compounds for spacecraft

The requirements for nonflammable potting compounds for use in spacecraft electric and electronic equipment are discussed. The development of a suitable nonflammable compound is described. Flammability testing and acceptance criteria for Apollo spacecraft are presented. The dielectric properties of various ceramic materials used as conformal coatings are examined.

Kline, H. F.↗
NASA NTRS1974

Apollo experience report: Problem reporting and corrective action system

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

Adams, T. J.↗
NASA NTRS1972

Apollo experience report: Thermal protection from engine-plume environments

Portions of the combined Apollo spacecraft (the command and service module and the lunar module) are subjected to the impingement of hot exhaust gases from the various propulsion systems of the modules. The configurations of the vehicles and the sources of impinging engine plumes are described. A typical Apollo mission is outlined. Protection and design-verification methods are discussed. Finally, recommendations are made for future spacecraft programs.

Taylor, J. T.↗
NASA NTRS1972

Reliability history of the Apollo guidance computer

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

Hall, E. C.↗