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At least 577 records · Page 32

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NASA NTRS1982

Design concepts and cost studies for magnetic suspension and balance systems

The application of superconducting magnets for suspension and balance of wind tunnel models was studied. Conceptual designs are presented for magnetic suspension and balance system (MSBS) configurations compatible with three high Reynolds number cases representing specified combinations of test conditions and model sizes. Concepts in general met initially specified performance requirements such as duty cycle, force and moment levels, model angular displacement and positioning accuracy with nominal design requirements for support subsystems. Other performance requirements, such as forced model sinusoidal oscillations, and control force magnitude and frequency, were modified so as to alleviate the magnitude of magnet, power, and cryogenic design requirements.

Bloom, H. L.↗

NASA NTRS1981

Materials Experiment Carrier Thermal Control System study

The Materials Experimental Carrier (MEC) vehicle currently under study at NASA-Marshall Space Flight Center presents unique power and heat rejection problems to the 25 kW Power System (PS). In order to determine how these requirements can best be met on both the Power System and MEC vehicle, Thermal Control System Trade Studies were conducted. The results of these trade studies indicated total weight to orbit would be minimized for multiple MEC launches by centralized radiators on the Power System. A split loop arrangement of Power System Thermal Control Subsystem, with separate loops for payload and PS heat rejection, appeared favorable from these trades. FC72 fluid was recommended for the high temperature MEC heat transport loop.

Fleming, M.↗

NASA NTRS1981

Cost and performance projections for SPS photovoltaic blankets

An estimate, based on optimistic projections of current technology, is given for the specific power of photovoltaic blankets which might be achieved if the SPS concept was to be implemented. A simultaneous consideration of cost and technical requirements is used to identify key blanket technologies which must be developed for this reference system. The terrestrial photovoltaic experience coupled with new technology is used to develop cost estimates for the blanket, assuming an annual demand of 5 GW and a manufacturing industry dedicated to blanket production. The results indicate that blanket specific power goals may be exceeded, but there is little prospect that the cost goals can be met. This argues for a reconsideration of the photovoltaic option based on more expensive but higher performance blankets.

Scott-Monck, J. A.↗

NASA NTRS1981

NASA tracking and data acquisition in the 1990's - Support for low earth orbit missions

Requirements related to increases in data volume for missions projected for the 1990's could be met by increasing the number of satellites in the Tracking and Data Relay Satellite System (TDRSS) constellation or by providing a new tracking and data acquisition satellite system having greater capacity (gigabits), increased reliability, and more direct user-to-relay connectivity. The program to develop the heir to TDRSS for the 1990's, has been defined as Tracking and Data Acquisition System (TDAS). A description is presented of the system architectural considerations which have to be studied in order to develop a cost effective TDAS. Attention is given to basic TDAS design parameters, TDAS spacecraft architectures, system considerations, technology considerations, and TDAS constellation options involving 2, 3, and 4 satellites.

Schwartz, J. J.↗

NASA NTRS1980

ESTL tracking and data relay satellite /TDRSS/ simulation system

The Tracking Data Relay Satellite System (TDRSS) provides single access forward and return communication links with the Shuttle/Orbiter via S-band and Ku-band frequency bands. The ESTL (Electronic Systems Test Laboratory) at Lyndon B. Johnson Space Center (JSC) utilizes a TDRS satellite simulator and critical TDRS ground hardware for test operations. To accomplish Orbiter/TDRSS relay communications performance testing in the ESTL, a satellite simulator was developed which met the specification requirements of the TDRSS channels utilized by the Orbiter. Actual TDRSS ground hardware unique to the Orbiter communication interfaces was procured from individual vendors, integrated in the ESTL, and interfaced via a data bus for control and status monitoring. This paper discusses the satellite simulation hardware in terms of early development and subsequent modifications. The TDRS ground hardware configuration and the complex computer interface requirements are reviewed. Also, special test hardware such as a radio frequency interference test generator is discussed.

Kapell, M. H.↗

NASA NTRS1981

Gravity, lignification, and land plant evolution

Vascular plants began their occupation of the wetlands interfacing both terrestrial and marine environments at some point in early Paleozoic time. Chemical differences between green algae and vascular land plants are mainly related to an abundance of lignins in the land plants. Answers to questions relating to the phylogeny and adaptive significance of the lignins must depend on experiments and observations using contemporary plant material. A summary is provided of a series of such observations. It is found that the differences between modern Chlorophyta and vascular land plants cannot be explained in full on the basis of lignification alone. Nevertheless, the data point to the emergence of the primitive land populations into an oxygen-rich terrestrial world where the need for mechanical support and water conservation could be met by a single aerobic biochemical process connected to essential aromatic amino acids likely to be found in every cell

Siegel, S. M.↗

NASA NTRS1982

Space Shuttle Orbiter - Reusable surface insulation flight performance

The first two flights of the Space Shuttle Orbiter have provided the initial data required for operational certification of the Thermal Protection System (TPS). The flight performance characteristics of the TPS reusable surface insulation (RSI) will be discussed. The discussion will be based on post-flight inspections of the RSI and post-flight interpretations of the flight instrumentation data. The flights to date indicate that the thermal and mechanical design requirements for the RSI system were met or exceeded.

Dotts, R. L.↗

NASA NTRS1982

Unusual structure of the dayside low-latitude magnetopause energetic electron layer

An analysis of high time resolution energetic electron data from an ISEE 1 spacecraft crossing of the magnetopause on Nov. 6, 1977 is presented. Low-energy proton measurements were taken with an ultralow energy and charge analyzer and energetic electron measurements were made with an ultralow energy wide-angle telescope (ULEWAT). Electrons were observed in four rate channels between 75 and 1300 keV and particle angular distributions are provided. The ecliptic was scanned by the particle angular detector as the spacecraft rotated at 19.7 rpm. Trapped energetic electrons were found to drift from dusk to dawn by way of the midnight sector. The electrons which started at midnight met the magnetopause at the dawnside, were entrained on the field lines, and resulted in a filamentary small-scale structure. A diffusion time scale across the magnetosheath was determined to be a few seconds, and electrons diffused tailward or into the interplanetary medium

Scholer, M.↗

NASA NTRS1982

Conversion of acoustic energy by lossless liners

The Blokhintzev acoustic energy equation is applied to a two-dimensional duct containing a uniform flow with a finite length lining. It is shown that the difference of the incident and outgoing acoustic energy differs in general from the energy dissipated in the liner, the difference being related to the displacements at the liner's edges. It is shown that in the case of a locally reacting lossless liner for frequencies below the first cut-off frequency and for low Mach number acoustic energy is generated if the flow and the incident sound wave are in the same direction and is absorbed if these two directions are opposite unless special edge conditions are met. Furthermore it is shown under the same conditions that the ratio of the reflection coefficient at finite flow velocity to the reflection coefficient at vanishing velocity is to first order in Mach number independent of the liner characteristics. A numerical calculation confirms these predictions at least for mass-like linear admittance.

Moehring, W.↗

NASA NTRS1982

Friction estimation technique for Galileo scan platform control

A friction estimation technique has been developed for the scan platform control of the Galileo spacecraft. The purpose of the estimation is to reduce the impact of friction in the scan platform actuator on the pointing performance of the scan platform so that tight pointing requirements can be met. The estimator operates by comparing the actual behavior of the platform with the expected behavior and attributing the difference to the presence of friction. The estimator is coupled with a proportional-integral-derivative controller to generate a control torque for the scan platform actuator. Since the algorithm will be implemented on an onboard digital computer, a stability analysis of the estimator-controller in discrete time is presented. The performance of the design is demonstrated by a sample slew test case.

Chodas, J. L.↗

NASA NTRS1982

Recommended satellite imagery capabilities for disaster management

This study explores the role that satellite imaging systems might play in obtaining information needed in the management of natural and manmade disasters. Information requirements which might conceivably be met by satellite were identified for over twenty disasters. These requirements covered pre-disaster mitigation and preparedness activities, disaster response activities, and post-disaster recovery activities. The essential imaging satellite characteristics needed to meet most of the information requirements are 30 meter (or finer) spatial resolution, frequency of observations of one week or less, data delivery times of one day or less, and stereo, synoptic all-weather coverage of large areas in the visible, near infrared, thermal infrared and microwave bands. Of the current and planned satellite systems investigated for possible application to disaster management, Landsat-D and SPOT appear to have the greatest potential during disaster mitigation and preparedness activities, but all satellites studied have serious deficiencies during response and recovery activities. Several strawman concepts are presented for a satellite system optimized to support all disaster management activities.

Richards, P. B.↗

NASA NTRS1982

Preliminary risk benefit assessment for nuclear waste disposal in space

This paper describes the recent work of the authors on the evaluation of health risk benefits of space disposal of nuclear waste. The paper describes a risk model approach that has been developed to estimate the non-recoverable, cumulative, expected radionuclide release to the earth's biosphere for different options of nuclear waste disposal in space. Risk estimates for the disposal of nuclear waste in a mined geologic repository and the short- and long-term risk estimates for space disposal were developed. The results showed that the preliminary estimates of space disposal risks are low, even with the estimated uncertainty bounds. If calculated release risks for mined geologic repositories remain as low as given by the U.S. DOE, and U.S. EPA requirements continue to be met, then no additional space disposal study effort in the U.S. is warranted at this time. If risks perceived by the public are significant in the acceptance of mined geologic repositories, then consideration of space disposal as a complement to the mined geologic repository is warranted.

Rice, E. E.↗

NASA NTRS1982

Analysis and design of a standardized control module for switching regulators

Three basic switching regulators: buck, boost, and buck/boost, employing a multiloop standardized control module (SCM) were characterized by a common small signal block diagram. Employing the unified model, regulator performances such as stability, audiosusceptibility, output impedance, and step load transient are analyzed and key performance indexes are expressed in simple analytical forms. More importantly, the performance characteristics of all three regulators are shown to enjoy common properties due to the unique SCM control scheme which nullifies the positive zero and provides adaptive compensation to the moving poles of the boost and buck/boost converters. This allows a simple unified design procedure to be devised for selecting the key SCM control parameters for an arbitrarily given power stage configuration and parameter values, such that all regulator performance specifications can be met and optimized concurrently in a single design attempt.

Lee, F. C.↗

NASA NTRS1982

Development of the Ultraviolet Imaging Telescope for the OSS-3 experiment complement

The areas of scientific interest addressed by the Ultraviolet Imaging Telescope (UIT) as part of the OSS-3 (Office of Space Science) experiment complement and the use of the Space Shuttle to make possible extended observations impose constraints in the optical, mechanical, and thermal design areas which are significantly more difficult than those encountered with sounding rocket payloads. Yet, in order that the UIT be cost-effective, it has been designed using the technology proven in the prior sounding rocket flights as a basis. The UIT had its beginnings in a series of eleven Goddard Space Flight Center sounding rocket payloads dating from 1973. Optically and mechanically it is derived from the 13-inch telescope of Rocket 26.008. Its detector design is related to that of Rocket 25.017, launched in 1977. Rocket 27.062, to be launched in 1982, will be the second flight of the 15-inch telescope serving as the direct prototype of the UIT. This evolution of the UIT from the rocket payload configuration, the nature of the new design requirements, and the manner in which the requirements were met are discussed.

Oliver, J. A.↗

NASA NTRS1982

STRAP V - Higher accuracy, lower drift attitude control system

The STRAP V system was developed to provide higher accuracy and lower limit cycle fine pointing (+ or - 7 arcseconds) in all three axes at targets which cannot be tracked by startrackers or solar trackers. The system provides an increase in pointing performance over that obtainable with the STRAP IV (1) Attitude Control System (ACS). The STRAP IV concept of third axis updates is utilized to reduce pointing errors, using the flight-proven STRAP III (2) system as a first stage. Flight aspect photographs and telemetry records show that the STRAP V objectives have been met. The STRAP IV major error contributors have been significantly reduced and the tracking flexibility has been increased with only minor error contributions. Attention is given to the basic STRAP III control modes, major STRAP IV system error sources, tuned restrained inertial gyros (TRIGs), the programmable sequence timer, the STRAP V control box, third axis update, system gyro alignments, and STRAP V operational capabilities.

Budney, T. J.↗

NASA NTRS1982

Development of advanced high-temperature heat flux sensors

Various configurations of high temperature, heat flux sensors were studied to determine their suitability for use in experimental combustor liners of advanced aircraft gas turbine engines. It was determined that embedded thermocouple sensors, laminated sensors, and Gardon gauge sensors, were the most viable candidates. Sensors of all three types were fabricated, calibrated, and endurance tested. All three types of sensors met the fabricability survivability, and accuracy requirements established for their application.

Atkinson, W. H.↗

NASA NTRS1979

Energy efficient engine. Flight propulsion system preliminary analysis and design

The characteristics of an advanced Flight Propulsion System (FPS) suitable for introduction in the late 1980's to early 1990's, were defined. It was determined that NASA goals for efficiency, environmental considerations, and economics could be met or exceeded with the possible exception of NOx emission. In evaluating the FPS, all aspects were considered including component design, performance, weight, initial cost, maintenance cost, engine-system integration (including nacelle), and aircraft integration considerations. In terms of the NASA goals, the current FPS installed specific fuel consumption was reduced 14.2% from that of the CF6-50C reference engine. When integrated into an advanced, subsonic, study transport, the FPS produced a fuel-burn savings of 15 to 23% and a direct operating cost reduction of 5 to 12% depending on the mission and study-aircraft characteristics relative to the reference engine.

Johnston, R. P.↗

NASA NTRS1982

The Rayleigh curve as a model for effort distribution over the life of medium scale software systems

It is noted that previous investigations into the applicability of Rayleigh curve model to medium scale software development efforts have met with mixed results. The results of these investigations are confirmed by analyses of runs and smoothing. The reasons for the models' failure are found in the subcycle effort data. There are four contributing factors: uniqueness of the environment studied, the influence of holidays, varying management techniques and differences in the data studied.

Picasso, G. O.↗