Reliability and quality assurance guideline for government-furnished equipment control
Guidelines for positive control of government furnished equipment for manned spacecraft
SEARCH · Engineering Papers
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.
Guidelines for positive control of government furnished equipment for manned spacecraft
Terrestrial environment /climatic/ criteria guidelines for use in NASA space vehicles and associated equipment development with major emphasis on Kennedy Space Center launch area
Guidelines for design, selection, and use of magnetic heads and tape for unattended satellite tape recorders
Guidelines are presented on probable precipitation extremes and characteristics, applicable for NASA space vehicles and associated equipment development. Information is provided on probability of rainfall rates, drop size, drop rate of fall, associated wind speeds with rainfall, snow loads, hail, laboratory test simulation, and rain erosion.
A consolidation of natural environment data is presented for use as design criteria guidelines in space and planetary exploration vehicle development programs. In addition to information in the disciplinary areas of aeronomy, radiation, geomagnetism, astrodynamic constants, and meteoroids for the earth's environment above 90 kilometers, interplanetary space, and the planetary environments, the upper atmosphere model currently recommended for use at MSFC is discussed in detail.
Lightning has always been of concern for aerospace vehicle ground activities. The unexpected triggering of lightning discharges by the Apollo 12 space vehicle shortly after launch and the more recent repeated lightning strikes to the launch umbilical tower while the Apollo 15 space vehicle was being readied for launch have renewed interest in studies of atmospheric electricity as it relates to space vehicle missions. The material presented reflects some of the results of these studies with regard to updating the current criteria guidelines.
A technical analysis of a portion of the advanced missions safety study is presented. The potential hazards introduced when experimental equipment is carried aboard the Earth Orbit Shuttle are identified. Safety guidelines and requirements for eliminating or reducing these hazards are recommended.
Injector design guidelines are provided for gas/liquid propellant systems. Information was obtained from a 30-month applied research program encompassing an analytical, design, and experimental effort to relate injector design parameters to simultaneous attainment of high performance and component (injector/thrust chamber) compatibility for gas/liquid space storable propellants. The gas/liquid propellant combination studied was FLOX (82.6% F2)/ ambient temperature gaseous methane. Design criteria that provide for simultaneous attainment of high performance and chamber compatibility are presented for both injector types. Parametric data are presented that are applicable for the design of circular coaxial and like-doublet injectors that operate with design parameters similar to those employed. However, caution should be exercised when applying these data to propellant combinations whose elements operate in ranges considerably different from those employed in this study.
The educational programs for public administration were studied to develop guidelines for meeting the requirements of public service in the 1980's. The current state of education for public service is discussed along with a prospective view of the service over the next decade. Criteria for evaluating graduate programs are presented.
The problem of experiment design is defined as an information system consisting of information source, measurement unit, environmental disturbances, data handling and storage, and the mathematical analysis and usage of data. Based on today's concept of effective computability, general guidelines for the definition of the relevant information content in data classes are derived. The lack of a universally applicable information theory and corresponding mathematical or system structure is restricting the solvable problem classes to a small set. It is expected that a new relativity theory of information, generally described by a universal algebra of relations will lead to new mathematical models and system structures capable of modeling any well defined practical problem isomorphic to an equivalence relation at any corresponding level of abstractness.
Guidelines are provided on probable climatic extremes and terrestrial environment data applicable to space vehicle and associated equipment design and development. Operational criteria for ground support sites are emphasized.
The Day-Night Noise Level, which takes tonal content, duration, and number of operations into account, and penalizes night-time noise, is found to be the best available index for rating community annoyance caused by aircraft. A Day-Night level of 60 for communities with ambient noise levels up to 58 dBA, and a level of 2 dBA higher than the ambient for communities where it is above 58 dBA, is proposed as acceptable. Evaluation of a large transport helicopter showed that the guidelines do not impose severe economic penalties on helicopter operations.
The present work outlines the general concept as to how natural environment guidelines will be developed for Space Shuttle activities. The following six categories that might need natural environment support are single out: development tests; preliminary operations and prelaunch; launch to orbit; orbital mission and operations; deorbit, entry, and landing; ferry flights. An example of detailed event requirements for decisions to launch is given. Some artist's conceptions of proposed launch complexes at Kennedy Space Center and Vandenberg AFB are shown.
Handbook provides specific guidelines related to ceramic multilayer circuit fabrication in terms of packaging density and interconnection methods, guiding the designer from initial stages of ceramic multilayer interconnection and artwork generation through test pattern utilization, assembly operations, and final inspection and test procedures.
The properties of organic adhesives were studied to acquire an adequate information base to generate a guideline document for the selection of adhesives for use in high reliability hybrid microcircuits. Specific areas covered include: (1) alternate methods for determining the outgassing of cured adhesives; (2) effects of long term aging at 150C on the electrical properties of conductive adhesives; (3) effects of shelf life age on adhesive characteristics; (4) bond strengths of electrically conductive adhesives on thick film gold metallization, (5) a copper filled adhesive; (6) effects of products outgassed from cured adhesives on device electrical parameters; (7) metal migration from electrically conductive adhesives; and (8) ionic content of electrically insulative adhesives. The tests performed during these investigations are described, and the results obtained are discussed in detail.
Guidelines are presented for the preparation of illustrated talks which are audience oriented and which are aimed at the efficient transfer of technical information. Early decisions concerning the required number of slides are helpful in initial planning for a good quality talk. Detailed considerations are: the establishment of limited objectives, selection of appropriate slide material, development of a text which is well coordinated with the slides, and accurate timing.
General guidelines are given for the design of diffusers, contractions, corners, and the inlets and exits of non-return tunnels. A system of equations, reflecting the current technology, has been compiled and assembled into a computer program (a user's manual for this program is included) for determining the total pressure losses. The formulation presented is applicable to compressible flow through most closed- or open-throat, single-, double-, or non-return wind tunnels. A comparison of estimated performance with that actually achieved by several existing facilities produced generally good agreement.
A very broad mission objective was established; i.e., manned circumlunar flight and return to earth. It is implicit that the Saturn will be the primary propulsion system for this mission. The following attempts to: (1) define the objective so as to achieve as much capability in the vehicle as possible; (2) draw on Mercury experience to provide broad guidelines for vehicle performance and safety; (3) provide flexibility in the vehicle capability in the event that the manned lunar mission is proved to be subject to unacceptable risk in the target time period; and (4) indicate problem areas where work appears to be particularly needed.