Facility engineering and operations
Flight project support for Surveyor III, Lunar Orbiter, Pioneer VII, and Mariner IV MISSIONS, facility construction and equipment for deep space network, and system reliability
MISSION PLANNING↗
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Results for “System reliability”
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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Development of multiple source - multiple low voltage converter-regulator power supply with automatic failure sensing and redundant switching Final report, 30 Jun. 1966 - 30 Jul. 1967
Development of failure sensing switching circuitry for electrical power system reliability during extended space missions
Jenson, K. J.↗
EBW firing unit and detonator compatibility investigation.
EBW firing unit-detonator interface compatibility measured to determine total system reliability for randomly paired production units
Amicone, R. G.↗
System concepts for a liquid mercury cathode thruster.
Solar electric propulsion for space missions, evaluating modularized ion propulsion systems to determine effect of electric isolation on system reliability, weight, etc
Kami, S.↗
System for computing operational probability equations
SCOPE system computes an expression relating the probability of system success to the probabilities of success of its components. It is especially designed for complex system reliability studies.
Ryan, K. E.↗
Information science
Information processing techniques and systems reliability by coding, digital designed methods, retrieval, and communication
Ash, R. B.↗
Approximate intervals and tests for products and ratios of binomial probabilities
Approximate confidence interval and tests for products and ratios of binomial probabilities with application in investigating and comparing system reliabilities
Walsh, J. E.↗
Fault-tolerant computer design for space shuttle
Application of redundancy techniques for improved computer system reliability
Goodman, I.↗
Survey of aircraft electrical power systems
Areas investigated include: (1) load analysis; (2) power distribution, conversion techniques and generation; (3) design criteria and performance capabilities of hydraulic and pneumatic systems; (4) system control and protection methods; (5) component and heat transfer systems cooling; and (6) electrical system reliability.
Lee, C. H.↗
Evaluation of spacecraft boom deployment dynamics by combined analysis and testing.
Discussion of the deployment of multiple hinged booms from the IMP-I satellite, which is a good example of the use of the combined analysis and testing approach for preflight system reliability evaluation. The procedures used for test and evaluation of the booms are described, and problems encountered and results achieved are considered. Analytical methods, using a digital computer program, and functional test operation with the best possible environmental simulation, were both applied to the problem and comparisons between analytical and test results were made to evaluate their validity and to reveal the effects of errors and imperfections. There is a synergistic advantage in the combined approach in that mutual comparison gives better evaluation of both analysis and test results than independent study of either. An appendix presents some results of a later and as yet incomplete test program involving the IMP-H satellite.
Lang, W. E.↗
Technical report analysis and design: Study of solid rocket motors for a space shuttle booster, volume 2, book 1, supplement 1
An analysis and design effort was conducted as part of the study of solid rocket motor for a space shuttle booster. The 156-inch-diameter, parallel burn solid rocket motor was selected as its baseline because it is transportable and is the most cost-effective, reliable system that has been developed and demonstrated. The basic approach was to concentrate on the selected baseline design, and to draw from the baseline sufficient data to describe the alternate approaches also studied. The following conclusions were reached with respect to technical feasibility of the use of solid rocket booster motors for the space shuttle vehicle: (1) The 156-inch, parallel-burn baseline SRM design meets NASA's study requirements while incorporating conservative safety factors. (2) The solid rocket motor booster represents a cost-effective approach. (3) Baseline costs are conservative and are based on a demonstrated design. (4) Recovery and reuse are feasible and offer substantial cost savings. (5) Abort can be accomplished successfully. (6) Ecological effects are acceptable.
Source record↗
Tracking and data relay satellite system configuration and tradeoff study. Volume 1: Summary. Part 2: Final Report, 22 August 1972 - 1 April 1973
A Tracking and Data Relay Satellite System (TDRSS) concept for service of low, medium, and high data rate user spacecraft has been defined. During the study, four TDRS dual spin stabilized configurations (contractual requirement) were designed; two are compatible with Delta 2914, one with Atlas Centaur, and one with space shuttle launches. A summary of the study and the salient results are presented. The topics included are: (1) TDRSS operations, (2) telecommunications service performance, telecommunications service equipment, (3) TDRS configurations and their design characteristics, and (4) TDRS system reliability.
Source record↗
Materials interactions between the thermoelectric converter and the 5kwe reactor system
The integration of a compact thermoelectric converter with a 5-kwe reactor system is described. Material interaction uncertainties study is also presented. This includes degradation of the required austenitic - refractory metal transition joint during operation at high temperatures; loss of corrosion resistance; embrittlement by the presence of hydrogen; and loss of design margin by transport of interstitial elements. Analysis and limited experimental evidence indicate that these potential materials interactions can be adequately controlled. Group 5-2 refractory metals can be utilized without unacceptable adverse effect on system reliability.
Ferry, P. B.↗
Insulation commonality assessment (phase 1). Volume 2: Section 7.0 through 16.0
The heat transfer characteristics of various materials used for the thermal insulation of spacecraft are discussed. Techniques for conducting thermal performance analysis, structural performance analysis, and dynamic analysis are described. Processes for producing and finishing the materials are explained. The methods for determining reliability, system safety, materials tests, and design effectiveness are explained.
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Computer-aided communication satellite system analysis and optimization
The capabilities and limitations of the various published computer programs for fixed/broadcast communication satellite system synthesis and optimization are discussed. A satellite Telecommunication analysis and Modeling Program (STAMP) for costing and sensitivity analysis work in application of communication satellites to educational development is given. The modifications made to STAMP include: extension of the six beam capability to eight; addition of generation of multiple beams from a single reflector system with an array of feeds; an improved system costing to reflect the time value of money, growth in earth terminal population with time, and to account for various measures of system reliability; inclusion of a model for scintillation at microwave frequencies in the communication link loss model; and, an updated technological environment.
Stagl, T. W.↗
Systems design study of the Pioneer Venus spacecraft. Volume 2. Preliminary program development plan
The preliminary development plan for the Pioneer Venus program is presented. This preliminary plan treats only developmental aspects that would have a significant effect on program cost. These significant development areas were: master program schedule planning; test planning - both unit and system testing for probes/orbiter/ probe bus; ground support equipment; performance assurance; and science integration Various test planning options and test method techniques were evaluated in terms of achieving a low-cost program without degrading mission performance or system reliability. The approaches studied and the methodology of the selected approach are defined.
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Review of Kaufman thruster development at the Lewis Research Center - 1973
Work on Kaufman thruster development completed during the years 1971 and 1972 is reviewed. Thrusters tested have ranged in size from 2.5-cm to 150-cm diameters, in thrust from 0.4 to 4300 mN, and in power from 0.03 to 203 kW. A 2.5-cm thruster was briefly tested and found to have surprisingly high thruster efficiency. Emphasis is placed on thruster system reliability and lifetime as previous work has increased thruster efficiency to a high level. Work also proceeds on definition of thruster-spacecraft interactions. Major R&D efforts are directed at present into two areas of thruster size: a 5-cm to 8-cm diameter thruster to be used for station keeping and attitude control of geosynchronous spacecraft; and a 30-cm diameter thruster to be used for primary propulsion in a 3- to 7-thruster array for solar electric propulsion of interplanetary spacecraft.
Kerslake, W. R.↗
Real time solar magnetograph Skylab mission Atlas
An atlas of all magnetic field observations made during the Skylab missions with the Real Time Solar Magnetograph system located at the Marshall Space Flight Center is presented. Also included are a description of the system and its operation; an outline of the data reductions performed; and a discussion of probable errors, noise, magnetic sensitivity, and system reliability.
Hagyard, M. J.↗