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  • Other Sources  (2,024)
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  • 1
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    Si:Bi array detectors and astronomical applications of the Goddard 10 micron camera (1983)
    In:  CASI
    Details
    Publication Date: 2004-12-04
    Description: An improved 4 to 18 micron array camera system was developed at NASA Goddard SFC for astronomical photometry, using an Aerojet Electro Systems Corp. 16 x 16 Si:Bi accumulation mode charge injection device (AMCID) which could be suitable for eventual low-background spaceflight applications. An astronomical observing program using this device was carried out as a collaboration between NASA Goddard (Infrared and Radio Astronomy Branch and Micro Electronics Branch), the Harvard/Smithsonian Center for Astrophysics, and Steward Observatory of the University of Arizona. In 1983 the camera system was revised, and a new Aeroject Si:Bi array with 16 x 16 active pixels was obtained from NASA/Ames Research Center as part of a new scientific collaboration between the Ames and Goddard infrared array research groups. The 16 x 16 device had sufficiently good sensitivity, uniformity and noise characteristics to be used for successful observations at the Mt. Lemmon 60 and 61 inch telescopes in May 1983. Complete laboratory characterization of the 16 x 16 array was carried out in summer of 1983. Initial results indicate that this detector has sensitivity and noise characteristics comparable to other devices from the same generation of Aerojet arrays.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Ames Research Center, Infrared Detector Technology Workshop; 12 p
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  • 2
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    The High Resolution Spectrograph for the Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: The High Resoltuion Spectrograph (HRS) in conjunction with the Space Telescope (ST), extends ultraviolet astronomical spectroscopy to higher spectra, spatial, and time resolutions than previously achieved, as well as to fainter and more distant celestial objects. Other significant advances inherent in the instrument are high photometric accuracy and efficient operation via exposure meter control and real time rejection of bad data. These capabilities are provided to accomplish the scientific programs of the HRS investigation definition team, which concern the interstellar medium, stellar winds, and evolutionary aspects of stellar atmosphere studies; the determination of chemical abundances relevant to stellar evolution; the investigation of quasars and Seyfert galaxy nuclei; and the analysis of the atmospheres of solar system objects, including comets.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 76-105
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  • 3
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    Reflections on the Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The significance of the Space Telescope for the advancement of astronomy and astrophysics is described. The current state of knowledge in astronomy and cosmology is summarized and unanswered questions in those fields discussed. The rapid evolution of modern astronomy and the need for systematic observations are stressed.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 121-134
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  • 4
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    Astrometric observations with the Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Astrometry with the Space Telescope (ST) is performed using one of the fine guidance sensors (FGS). The FGS, which is based on a pair of Koester's prism interferometers, one for each axis, is capable of measuring the position of one object relative to another with an accuracy of 0.002 arcseconds. Astrometric Data Reduction Software (ADRS) available to the astrometric user of ST is described. The kinds of problems the space telescope astrometry team plans to investigate using ST are discussed.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 114-120
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  • 5
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    The wide field/planetary camera (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A wide site of potential astronomical and solar system scientific studies using the wide field planetary camera on space telescope are described. The expected performance of the camera as it approaches final assembly and testing is also detailed.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 28-39
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  • 6
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    European astronomy and the Space Telescope: The Space Telescope European Coordinating Facility (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The role of the European Coordinating Facility is described. European participation in the Space Telescope Science Institute and the relation of Space Telescope to ground-based astronomy in Europe are discussed.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 16-19
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  • 7
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    Approach and landing characteristics of the space shuttle orbiter Learned, Pt. 1 p 637-651 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The first five Space Shuttle orbiter landng during the Orbital Flight Test program are analyzed with respect to the unique requirement to perform routine experience during the Approach and Landing Tests is also considered. Results are presented on energy control, handing qualities, and landing distance.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons (SEE N84-10115 01-16)
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  • 8
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    Space shuttle descent flight control design requirements and experiments Learned, Pt. 1 p 617-628 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Some of the lessons learned during the development of the Space Shuttle descent flight control system (FCS) are reviewed. Examples confirm the importance for requirements definition, systems level analyses, and testing. In sounding these experiences may have implication for future designs or suggest the discipline required in this engineering art.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons (SEE N84-10115 01-16)
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  • 9
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    Shuttle ascent GN&C postflight results (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The key features of the ascent and Guidance navigation, and control (GN and C) system are discussed. How well this system performed during the orbital flight test program is examined. Flight results are compared with preflight predictions and postflight reconstructions. Variations from expected performance are identified as well as flight-to-flight trends. The most notable variation was the lofted trajectory observed on the Space Transportation System 1 flight. The lessons learned from the orbital flight test program are being used to enhance the overall system performance for future Shuttle flights. Several of the planned GN and C system enhancements are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 1; p 581-594
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  • 10
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    The application of aerodynamic uncertainties in the design of the entry trajectory and flight control system of the space shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The process used in the application of aerodynamic uncertainties for the design and verification of the Space Shuttle Orbiter Entry Flight Control System is presented. The uncertainties were used to help set center of gravity, angle of attack and dynamic pressure lateral control divergence parameter as well as C sub n sub beta dynamic were instrumental in setting these placards.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 1; p 595-616
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  • 11
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    Lateral-directional stability investigation of the space shuttle orbiter at Mach 6 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Lateral-directional aerodynamic data and oil-flow visualization results are pesented from four tests (conducted in two facilities using three models) which were designed to verify the hypersonic aerodynamics of the Space Shuttle orbiter at M=6. Comparisons of measured lateral-directional stability data and oil-flow results between the tests show excellent agreement, especially considering the nonuniform, unpredictable flow which occurs in the vicinity of the vertical tail. Results ere shown to be sensitive to Reynolds number with the higher Reynolds number cases producing more stable values and also showing good agreement with flight values. The results also show that the effects of Reynolds number, angle of attack, and angle of sideslip on the lateral-directional stability of future entry configuration should be carefully assessed for non-linearities.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 1; p 525-548
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  • 12
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    Predicted and flight test results of the performance, stability and control of the space shuttle from reentry to landing (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Aerodynaic performance, stability and control data obtained from the first five reentries of the Space Shuttle orbiter are given. Flight results are compared to pedicted data from Mach 26.4 to Mach 0.4. Differences between flight and predicted data as well as probable causes for the discrepancies are given.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 1; p 509-524
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  • 13
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    Stability and control over the supersonic and hypersonic speed range (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The performance and aerodynamic characteristics of the Space Shuttle Columbia are analyzed over the speed range from Mach 2 to 26 using flight data taken from the first five Space Transportation System flights. These data are used to reconstruct the entry trajectory, calculate vehicle performance, and estimate lateral stability and control derivatives including those assocated with the onboard Reaction Control System. The trajectory reconstruction process is discussed in its relationship to the determination of the vehicle flight characteristics. Vehicle performance results are presented which show that lift and drag were generally overpredicted by 3 percent and that the life-to-drag ratio was underpredicted by 1 percent. Anomalies in pitching-moment trim characteristics are shown and noted to be due to real-gas and Mach-number effects. Lateral stability and control derivatives estimated using programmed test input maneuvers are corrected with preflight predictions and are usually within the uncertainties associated with the predictions. The lateral reaction-control system effectiveness is evaluated.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 1; p 473-508
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  • 14
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    Minimum testing of the space shuttle orbiter for stability and control derivatives (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A unique approach has been developed for stability and control derivative testing of the Space Shuttle orbiter during entry. Shuttle Program requirements have necessitated a minimum of testing. Therefore, flight tests concentrate on potential control problem areas predicted from wind tunnel data as well as anomalies discovered during flight testing. The object is to use the test data to remove center of gravity (cg), angle of attack, and elevon placards which are a function of these potential control problems. To ensure successful aerodynamic extraction from a minimum of testing, the following special measures have been taken. Exact maneuvers are designed preflight on Shuttle simulators. These maneuvers are duplicated and implemented during the flight by onboard software. An onboard instrumentation system was designed especially for aerodynamic parameter identification. State-of-the-art techniques are used in extracting aerodynamics.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 1; p 447-472
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  • 15
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    Approach to establishing the effect of aeroelasticity on aerodynamic characteristics of the space shuttle orbiter (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The static aeroelastic effects on the longitudinal stability and elevon/aileron effectiveness of the space transportation system (STS) Space Shuttle orbiter were estimated by a simplified approach called the elevon torsional stiffness (ETS) method. This method employs rigid model wind tunnel test results to predict aeroelastic effects. Lateral/directional stability and rudder effectiveness were based on results of a wind tunnel test in which a flexible tail model was used. Comparisons with selective flight data are made in this paper. Results of correlations with flight data (although limited at the present time) verify the predicted aeroelastic effects for the orbiter. The orbiter's structural characteristics are such that the effects of aeroelasticity, whether estimated using analytical techniques or simplified methods, do not appear to affect the vehicle performance to any great extent. The large amount of scatter in the flight-extracted data made verification of the aeroelastic corrections very difficult. Generally, the simplified elevon torsional stiffness method provided better correlation with flight test results than he analytical method and reduced the verification effort and cost.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 413-446
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  • 16
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    Analysis of shuttle oscillation in the Mach Number = 1.7 to Mach Number = 1.0 range (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The first five flights of the Space Transportation System (STS) have exhibited unexpected lateral oscillations in the Mach Number = 1.7 to Mach Number = 1.0 region of the descent trajectory. These oscillations can be split into two parts: a predominantly rolling oscillation referred to as the quarter hertz motion and a long-priod, large-amplitude oscillation in sideslips, roll rate, and yaw rate. These motions are analyzed in this paper in order to determine their source and the mechanism driving them. They will first be examined to determine how much of the motion can be explained using the set of equations that contain linear aerodynamic parameters. Then differences between measured moments and those calculated using linear aerodynamics which are considered to be due to unmodeled moments will be exained. Possible error sources such as not inluding nonlinear aerodynamics in the vehicle model, measurement errors, and the effect of pressure gradients will be considered. Based on these analyses, conclusions as to the nature and cause of the Shuttle lateral oscillations will be drawn.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Part 1; p 397-412
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  • 17
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    Space shuttle orbiter reaction control subsystem flight data anomalies (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Shuttle orbiter vehicle flight data obtained during operation of the reaction control subsystem (RCS) were compared with predictions derived from RCS wind tunnel test data. This paper reviews the derivation of the wind tunnel data base and discusses how it was used to predict the full-scale RCS effects. Flight and predicted data comparisons include the lateral and directional aerodynamic effects of firing the side jets, longitudinal aerodynamics for pitch jets, and lateral aerodynamics for roll jets. Flight data anomalies resulting from wind tunnel limitations in representing portions of the entry flight trajectory are presented. The cause of each data anomaly is described, as well as a requirement for additional technical analysis to establish RCS effect simulation parameters that can be used to update jet effect technology.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons earned, Part 1; p 381-396
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  • 18
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    Explanation of the hypersonic longitudinal stability problem: Lessons learned (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Inviscid and viscous CFD codes have been applied to a modified Space Shuttle orbiter geometry to investigate differences between preflight aerodynamic predictions and aerodynamic data from hypersonic reentry flight. Flow field solutions were obtained for wind tunnel conditions and flight conditions to assess Mach number, real-gas, and viscous effects on the reentry aerodynamics of the orbiter. Based on the CFD studies, a methodology model has been developed to (1) extrapolate wind tunnel data to flight conditions and (2) calculate a DCM for use with the Aerodynamic Design Data Book. Comparisons are made with selected flight data. Results of the study indicate that the differences between flight and pre-STS-1 predictions of hypersonic pitching moment are primarily due the to Mach number and real-gas effects.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 347-381
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  • 19
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    A review of preflight estimates of real-gas effects on space shuttle aerodynamic characteristics (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Preflight estimates of the hypersonic aerodynamic characteristics of the Shuttle orbiter were based on a diverse series of research studies using state of the art techniques developed by basic research in the 60's and 70's. Real-gas viscous calculations on simple shapes that were used to evaluate correlation parameters indicated that real-gas effects reduce aerodynamic forces and moments. Inviscid calculations on winged lifting shapes indicated reduced forces and a slight nose-up pitch resulted because of real-gas effects. Analysis of the extensive wind tunnel data base indicated viscous correlation parameters provided the most appropriate extrapolation technique for estimating flight aerodynamics. Variations because of changes in the ratio of specific heats, which was the only available experimental tool for evaluating real-gas effects, indicated that reduced loads and nose-up pitching moments would occur at high altitudes and Mach numbers but that the values would not exceed the tolerances and variations established about the aerodynamic design data book values derived from viscous correlations. During STS-1, nose-up pitching moments exceeded the established variations.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Part 1; p 309-346
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  • 20
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    Space shuttle entry longitudinal aerodynamic comparisons of flights 1-4 with preflight predictions (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Space Shuttle orbiter flight test program has required the aerodynamicist to take a new approach in determining flight characteristics. A conventional flight test program of slowly and cautiously approaching more severe flight conditions was not possible with the orbiter. On the first four orbital flights, The orbiter entered the atmosphere at approximately Mach 29 and decelerated through the Mach range (the subsonic portion of flight had also been flown by another orbiter vehicle during the Approach and Landing Test Program). Certification for these flights was achieved by an extensive wind tunnel test and analysis program. The initial series of flights of the orbiter were heavily instrumented for the purpose of obtaining accurate aerodynamic data. The flight data derived from the entry Mach range provided comparisons between flight and wind tunnel derived predicted data in the areas of both aerodynamic performance and longitudinal trim.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 283-308
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  • 21
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    Space shuttle orbiter venting: Lessons learned (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The orbiter vent system provides dedicated vent areas to permit the gases trapped inside the vehicle to escape during accent. The same vent system also repressurizes the vehicle during entry. The vent system is one of six systems that constitutes the purge, vent and drain subsystem. The orbiter active vent system has been very adaptable to the changing requirements that have occurred during the development of the Space Shuttle orbiter. Good correlation has been obtained between predicted and measured compartment pressures during the orbital flight test (OFT) program. An investigation of the flight data showed that the difference between preflight prediction and the measured values were primarily due to the difference between the baseline external pressures, which was based on subscale wind tunnel test data, and the actual vehicle local external pressures measured during the flight. The current predictions are based on flight derived vent port pressure coefficients since the wind tunnel data does not adequately define the orbiter ascent pressure environment.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 231-258
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  • 22
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    Development of space shuttle ignition overpressure environment and correlation with flight data (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Space Transportation (STS) launch vehicles are more complex than other launch vehicles. A comprehensive analysis of the lift-off event is required so that the responses of the vehicle and payloads can be predicted. The transient overpressure induced by ignition of the solid rocket motors (SRM's) is one of the critical design factors assessed for lift-off. The STS-1 ignition overpressure design environment was developed from 6.4-percent scale-model tests in which the Tomahawk solid rocket motors were used to simulate the start-up process of the SRM's. The overpressures measured during STS-1 lift-off were much more severe than predicted. The reasons for this anomaly are discussed in this paper. The 6.4-percent scale model was redesigned and used as a tool to develop an effective ignition overpressure suppression system for STS-2 and subsequent flights. Also presented are advancements in subscale-model simulation and theoretical understanding of this transient overpressure phenomenon that led to the successful development of the fix.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 259-282
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  • 23
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    Ascent air data system results from the space shuttle flight test program (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The ascent air data system of the Space Shuttle consists of a simple biconic spike probe on the nose of the external tank. Pressure measurements were calibrated in a wind tunnel to obtain vehicle attitude and speed (relative to the air) and dynamic pressure. The wind tunnel test data analysis and the calibration are discussed in terms of test problems and calibration parameter formulation. The flight pressures are traced from telemetry data to final air data products. Analysis of the flight results showed that static pressure could not be accurately determined at the higher Mach numbers (above approx. 2.0). By replacing static pressure with data from a postflight estimated trajectory the ascent air data system performance met the user requirements. Lessons learned are enumerated, the most important being the need for a thorough systems integration effort.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 187-231
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  • 24
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    Shuttle launch debris: Sources, consequences, solutions (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Following the first space shuttle flight, the shuttle program established a team to identify and eliminate sources of debris which had caused serious damage to the orbiter thermal protection tiles. An approach was developed for debris identification which involved pre- and post-flight vehicle and pad inspections, analytic assessment of debris transport and impact phenomena, and analysis of various photographic records of the flight. Debris sources identified by this approach were classified as being either hazards to flight or sources of damage which increased vehicle refurbishment costs without having any safety implications. As a result of this assessment, all known hazardous debris sources on the launch vehicle and pad were eliminated; other sources are being removed in a cost effective manner as appropriate.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 159-186
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  • 25
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    Techniques for assessment of ascent aerodynamic characteristics of the space shuttle launch system (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: In order to investigate the impact of ascent element aerodynamics on the flight constraints of the Space Shuttle, a system of programs was developed which allowed the assessment of wind-tunnel data, the extraction of aerodynamic coeffients, the identification of critical structural load indicators and their margins, the calculation of mission-unique shaping parameters and the evaluation of prelaunch wind measurements.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 79-94
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  • 26
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    Supersonic loads due to shuttle-orbiter/external-tank attachment structures (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A large variety of tests were conducted during development of the Space Shuttle to determine the strength, fatigue, and thermal characteristics of the thermal-protection system of the orbiter. The research and analysis carried out to accurately define and simulate the flow characteristics immediately ahead of the external tank attachment structures are described. The highest known acoustic pressure loads occur in these regions and tests to insure the ability of the titles to withstand these acoustic loads, plus those due to pressure gradient, were thought necessary. First flight-critical wind tunnel tests were therefore conducted in the Langley 8-Foot Transonic Pressure Tunnel (8-Ft. TPT), which simulated the time histories of Shuttle ascent loads on tile arrays bonded to structures which accurately duplicated those of the Shuttle. The time-varying free stream conditions were provided by controlling the deflection angle history of diffuser spoiler flaps in an automated way. Time histories of the critical load parameters imposed on the tile arrays in the tunnel are compared with those expected in flight.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Part 1; p 95-138
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  • 27
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    Shuttle booster separation aerodynamics (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A wind tunnel test program of some complexity was used to define the aerodynamic forces exerted on the space shuttle solid rocket boosters and orbiter/external tank during staging. In these tests, problems associated with the use of up to three models in close proximity and with the need to simulate high pressure separation motor plumes were handled in a unique and effective manner. A new method was developed for efficiently organizing data which is a function of a large number of independent variables. Data derived from the test program drastically reduced previous estimates of aerodynamic uncertainties and allowed certification of the separation system at the design maximum staging dynamic pressure. Reduction of flight data has implicitly verified the staging aerodynamics data base and its associated uncertainties.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 139-158
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  • 28
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    Aerodynamic analysis of the loft anomaly observed on orbital flight tests of the space shuttle (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The loft anomaly observed during the launch phase of the orbital flight tests (OFT) of the Space Shuttle is described and evidence that the loft anomaly resulted from previously unobserved aerodynamic phenomena is presented. The anomaly was that the altitude at staging was higher than anticipated. The anticipated altitude profile was predicted on wind tunnel test results that did not accurately simulate the flow between the orbiter vehicle and external tank and did not adequately simulate the engine plumes and thus the base pressures. An analogy is used to relate the flow between the orbiter and external tank to the flow in a two dimensional channel. Plume simulation is identified as a major goal during wind tunnel testing, and a wind tunnel test that was conducted to provide the best possible representation of the plume effect on the channel flow field is described.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 59-78
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    Launch vehicle aerodynamic flight test results (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The aerodynamic flight test procedures and results for the Space Shuttle orbiter are presented. The aerodynamic characteristics used in testing were determined from flights STS-1 and through STS-4. Normal force and pitching moment were different than predicted, suggesting an unanticipated aerodynamic force acting upward on the end of the orbiter. However, lateral-directional aerodynamic characteristics were in good management with good predictions. The flight measured aerodynamics are repeatable and show good correlation with angle of attack and angle of sideslip.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 41-58
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    Plume base flow simulation technology (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A combined analytical/empirical approach was studied in an effort to define the plume simulation parameters for base flow. For design purposes, rocket exhaust simulation (i.e., plume simulation) is determined by wind tunnel testing. Cold gas testing was concluded to be a cost and schedule effective data base of substantial scope. The results fell short of the target, although work conducted was conclusive and advanced the state of the art. Comparisons of wind tunnel predictions with Space Transportation System (STS) flight data showed considerable differences. However, a review of the technology program data base has yielded an additional parameter that may correlate flight and cold gas test data. Data from the plume technology program and the NASA test flights are presented to substantiate the proposed simulation parameters.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 1-18
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    Launch vehicle aerodynamic data base development comparison with flight data (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The aerodynamic development plan for the Space Shuttle integrated vehicle had three major objectives. The first objective was to support the evolution of the basic configuration by establishing aerodynamic impacts to various candidate configurations. The second objective was to provide continuing evaluation of the basic aerodynamic characteristics in order to bring about a mature data base. The third task was development of the element and component aerodynamic characteristics and distributed air loads data to support structural loads analyses. The complexity of the configurations rendered conventional analytic methods of little use and therefore required extensive wind tunnel testing of detailed complex models. However, the ground testing and analyses did not predict the aerodynamic characteristics that were extracted from the Space Shuttle flight test program. Future programs that involve the use of vehicles similar to the Space Shuttle should be concerned with the complex flow fields characteristics of these types of complex configurations.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 19-36
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    Space shuttle launch vehicle aerodynamic uncertainties: Lessons learned (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The chronological development and evolution of an uncertainties model which defines the complex interdependency and interaction of the individual Space Shuttle element and component uncertainties for the launch vehicle are presented. Emphasis is placed on user requirements which dictated certain concessions, simplifications, and assumptions in the analytical model. The use of the uncertainty model in the vehicle design process and flight planning support is discussed. The terminology and justification associated with tolerances as opposed to variations are also presented. Comparisons of and conclusions drawn from flight minus predicted data and uncertainties are given. Lessons learned from the Space Shuttle program concerning aerodynamic uncertainties are examined.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 37-40
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    Unsteady environments and responses of the shuttle combined loads orbiter test (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Both separate and combined wind tunnel and vibration shaker tests were conducted on two structural panels representative of the Shuttle orbiter in the NASA LaRC 8-foot transonic pressure tunnel to determine the effects of combined loads on the thermal protection system (TPS). The primary objective of this test was to provide a combined full-scale load environment and realistic time history of the dynamic pressures, Mach numbers (through transonic), and dynamic structural responses of these panels. The panels were selected from orbiter locations where interactive load sources such as aerodynamic shock waves, turbulent boundary layers, strut-induced vorticity, and substrate deformation combined to provide high bonding loads between the TPS and the orbiter structure. The test panels were highly instrumented with static and dynamic pressure gages, accelerometers, deflectometers, strain gages, Schileren and high speed photography, and special instrumentation necessary to determine TPS/structure interface loads and tile motions. Two test specimens of each orbiter panel were utilized. Both were high-fidelity representations of the selected orbiter location.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 157-163
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    Buffet loads on shuttle thermal-protection-system tiles (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Results of wind-tunnel and acoustic tests to investigate buffet loads on Shuttle Thermal-Protection-System (TPS) tiles are given. Also described is the application of these results to the prediction of tile buffet loads for the first shuttle flight into orbit. The wind-tunnel tests of tiles were conducted at transonic and supersonic Mach numbers simulating flow regions on the Orbiter where shock waves and boundary-layer separations occur. The acoustic tests were conducted in a progressive wave tube at an overall sound pressure level (OASPL) approximately equal to the maximum OASPL measured during the wind-tunnel tests in a region of flow separation. The STS-1 buffet load predictions yielded peak tile stresses due to buffeting that were as much as 20 percent of the total stress for the design-load case when a shock wave was on a tile.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 147-153
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    Dynamic and static modeling of the shuttle orbiter's thermal protection system (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The dynamic and static analysis methods used to model the nonlinear structural behavior of the Shuttle Orbiter's tile/pad thermal protection system are discussed. The structural evaluation of the tile/pad system is complicated by the nonlinear stiffening, hysteresis and viscosity exhibited by the pad material. Application of the analysis to square tiles subject to sinusoidal and random excitation is presented along with appropriate test data. Correlation is considered good. In order to treat the stress analysis of thousands of individual tiles, a nonlinear static analysis was developed which utilizes equivalent static loads derived from the dynamic environment. Tensile stress at the bondline is examined in thousands of unique tiles.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 127-145
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  • 36
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    The development and verification of shuttle orbiter random vibration test requirements (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The unique space shuttle vehicle size, weight, and configuration gave rise to problems in determining vibration requirements and in verifying structural integrity for anticipated mission environments. The applications of large-scale vibration testing played a prominent part in qualifying the shuttle for its intended missions. Severe vibration excitation from rocket engines, aerodynamic noise, and onboard equipment are expected on each shuttle flight. Scale-model wind tunnel and rocket firing tests, as well as full-size rocket engine tests were relied on to define the random forcing functions. The determination of structural response to these environments is described as well as evaluations of measured flight data and comparison with predicted design and test criteria.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 71-80
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  • 37
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    Space shuttle solid rocket booster reentry and decelerator system loads and dynamics (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Recovery of the space shuttle solid rocket boosters required development of a heavy duty large decelerator subsystem. Successful recovery of the first launch pair of boosters demonstrated the adequacy of the design. Flight data consisting of accelerometers and parachute attach point loads provide a basis for evaluation of the decelerator subsystem performance. These results are summarized and compared to preflight predictions.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 2; p 27-33
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  • 38
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    Remote orbital servicing system concept (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Increased applications of automation technology identified as necessary for NASA to carry out its missions within the constraints of future funding and available physical resources are described. A concept for a Remote Orbital Servicing System (ROSS) based on present teleoperator and robotics technology is presented. A single servicer design compatible with three specified spacecraft, capable of performing service to the same extent as manned extravehicular activity, controlled from a ground control station, and using currently available technology is conceptualized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 104-119
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  • 39
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    Open cherry picker simulation results (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The simulation program associated with a key piece of support equipment to be used to service satellites directly from the Shuttle is assessed. The Open Cherry Picker (OCP) is a manned platform mounted at the end of the remote manipulator system (RMS) and is used to enhance extra vehicular activities (EVA). The results of simulations performed on the Grumman Large Amplitude Space Simulator (LASS) and at the JSC Water Immersion Facility are summarized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 17 p
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  • 40
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    Satellite retrieval and servicing operations with proximity operations modules (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The concept of manned and unmanned proximity modules (POM) to assist the Orbiter in retrieval, servicing, and emergency operations of orbiting payloads is discussed. An unmanned POM, capable of examining or capturing and returning to the Orbiter large satellites which are station-keeping at distances up to one kilometer from the Orbiter, is presented and its design features defined. Also presented is the concept of a manned POM which is capable of capturing and maneuvering smaller payloads in or about the Orbiter payload bay. The manned POM also serves as a free flying work station used to support satellite servicing and provide a back-up to Orbiter situations when the remote manipulator is inoperative.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 21 p
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  • 41
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    Design objectives of the multimission modular spacecraft (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Servicing economics for LANDSAT are examined. The following objectives of the multimission modular spacecraft are outlined: retrieval; multimission capability; standard flight support system; standard hardware; repair and refurbishment on orbit; instrument replacement; standard ground support system; and standard software.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 168-199
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  • 42
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    Spacecraft automatic umbilical system (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: A conceptual definition of an appropriate berthing technique and a prototype design of an automatic umbilical system suitable for use with payloads carried by the Space Shuttle are presented. A four-element berthing system is described. This concept consists of a set of four remote manipulator system (RMS)-type end-effector capture/tie-down devices on the power system and corresponding RMS-type grapple fittings on the payload. In operation, the RMS maneuvers the payload to a position where the four grapple fittings can be snared within the end-effectors and then secured to the power system. The concept takes advantage of mechanisms and operating techniques developed for attaching the RMS to a payload. Although the umbilical installation is attached to the docking interface structure, its operation is independent and it must comply with a set of primary requirements specified by Marshall Space Flight Center (MSFC), which is presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 39 p
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  • 43
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    Advanced service equipment (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Orbiter-based service equipment needs/usage are identified by considering a broad spectrum of on-orbit operational scenarios associated with three primary mission events: initial launch, revisits, and Earth return. Nominal and alternate modes of operation, contingency situations (as remote manipulator system inoperative), and Orbiter close proximity operations are included. Satellite classes considered are direct delivery and servicing of the orbiter, low Earth orbiter/propulsion, sorties and DOD, geosatellites, and planetary and other satellites.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 1-28
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  • 44
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    The Space Shuttle orbiter payload retention systems (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 216-227
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  • 45
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    Characteristics of the handling and positioning aid (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The handling and positioning aid which (HPA) provides a wide range of adjustable work stations both inboard and outboard of the cargo bay is discussed. It can assist with berthing and docking, it is robust, stiff, has a simple control system, and is modular. An articulated arm version of HPA employed in a typical servicing mission is shown. Mounted on a base frame that spans the Orbiter cargo bay, the 6 m arm is long enough to hold the satellite being serviced and keep its solar array clear of the Orbiter radiators. By adjusting the length and angle of the support platform mast, and rotating the tip of the HPA arm, almost every item on the satellite can be reached. Spares and change-out units can be brought to and from the work site by the RMS, which is controlled from the aft flight deck. The fore and aft position of the base frame can be changed between Orbiter flights and this, together with the 5 degrees of freedom (DOF) of the long arm, allows work sites to be chosen that meet the clearance, reach and vision requirements of many missions. Flight article activities are shown are shown above the dashed horizontal line and Development Test Article (DTA) work below. Flight article requirements and concepts and the design of the DTA are developed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 15 p
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  • 46
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    Space operations center applications of satellite service equipment (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Satellite servicing requirements for a continuously manned Space Operations Center (SOC) are discussed. Applications for Orbiter developed service equipment are described, together with representative satellite servicing operations for use on SOC. These services cover the full mission cycle from orbital deployment to on-orbit maintenance/repair and, eventually, removal from orbit. An orbiting base, such as the SOC, can provide many of the same services at less cost than the Space Shuttle transportation system.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 14 p
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  • 47
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    The High Speed Photometer for the Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: An overview of the high speed photometer (HSP), its optics and detectors, its electronics, its mechanical structure, and some observational considerations are presented. The capabilities and limitations of the HSP are outlined.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 106-113
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  • 48
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    The Faint Object Camera (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Faint Object Camera fully exploits the spatial resolution capability of the Space Telescope on the very faintest detectable objects over a broad wavelength range. A full complement of filters, objective prisms and polarizers, a choice of coronograhic masks, and a variety of scan formats extend the scientific versatility of the direct imaging mode. In addition, the Faint Object Camera provides the unique facility of long-slit spectroscopy to Space Telescope observers.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 40-54
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  • 49
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    Low-Earth orbit satellite servicing economics (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Servicing economics of low Earth orbit satellites were studied. The following topics are examined: the economic importance of the repair missions; comparison of mission cost as opposed to satellite modulation transfer functions over a 10 year period; the effect of satellite flight rate change due to changes in satellite failure rate; estimated satellite cost reduction with shuttle operation projects from the 1960's to the 1970's; design objectives of the multimission modular spacecraft; and the economic importance of the repair mission.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; p 150-167
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  • 50
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    Servicing costs for representative service missions (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: User cost for three satellite services were assessed. The three missions are: advanced X-ray astrophysics facility (AXAF) revisit; upper atmosphere research satellite (UARS) revisit: and solar maximum mission (SMM) Earth return. Service scenarios for the missions to identify service equipment needs and on orbit usage were developed. The AXAF revisit is a service mission involving a contamination sensitive satellite. Following servicing and checkout, the spacecraft is redeployed from the orbiter. The total user charges for revisit missions is from 5 to 10% less than the cost to build and relaunch a replacement satellite. It is indicated that satellite servicing from the Orbiter is cost effective.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Satellite Serv. Workshop, Vol. 2; 11 p
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  • 51
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    Determination of the efficiency of a proportional counter for detecting X-rays (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A parallel beam of X-rays (approximately monoenergetic) passing through a rectangular slit and scattering from two flat mirrors comprise the X-ray test. The two mirrors are arranged in a periscope geometry so that the final reflected beam is parallel to the incident beam but displaced laterally by given amount. One of the detectors used to intercept the reflected X-rays is a one dimensional gas-filled proportional counter which is sensitive to the position (in 1 dimension) at which the X-rays are incident within its detecting "window". The total length of the anode wire of the proportional counter is 120 mm and this length can be divided electronically into a maximum of 1,024 parts. Hence, the output of an experimental run would be the number of incident X-rays that registered on each of the 1,024 channels. Each channel would represent an X-ray at a different spatial location and, hence, at a different scattering angle. In order to look at a wider range of scattering angles, the detector is placed on an optical table which can be rotated.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 6 p
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  • 52
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    Performance of the continuous flow diffusion chambers (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A brief comparative description is made of the chambers. Overall, comparisons for the various types of experiments - monodisperse, polydisperse and ambient aerosol - showed agreement among these chambers to within 15% in most cases. A careful analysis of the results indicated that a proper accounting of certain parameters would bring about much closer agreement among four of these instruments.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Third Intern. Cloud Condensation Nuclei Workshop; p 79-84
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  • 53
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    A new SPS antenna design to reduce grating lobes (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: In the Solar Power Satellite system, the antenna's misalignment will produce well defined grating lobes. These gratings lobe peaks occur every 440 km and are potentially hazardous to the environment. One way to suppress these peaks is to phase control every power module. The cost due to the increase in receiving electronics and processors, however, could prove to be prohibitive. A new design of the antenna involving the addition of two broad gaps, one along the x axis and another along the y axis is proposed. The gap distance is exactly one half of the distance between the center of two neighboring subarrays. Calculation of far field radiation patterns shows that the design reduces grating lobe peaks without sacrificing power in the main lobe.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The 1981 NASA(ASEE Summer Fac. Fellowship Program; 14 p
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  • 54
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    A preliminary study of the particulate fallout from the space shuttle (STS-1) (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Prediction of acid fallout and the dry deposition of Al2O2 was the objective of this investigation. Sampling was done at the Kennedy Space Center in Florida. The models available were not appropriate and the data available was negligible. Thus, a bimodal particle distribution was assumed normalized to the few existing data points and used as a foundation for a crude zeroth order approximation for the acid fallout. In addition, a settling spectrum for the Al2O3 particles was devised as a table look-up since the graphs in the literature at first pass could not be fitted with reasonable analytic functions. Consulting services were rendered to researchers. Special emphasis was placed on improving current techniques and adding LIDAR (Light Radar). Suggestions for future studies are made.
    Keywords: SPACE TRANSPORTATION
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 8 p
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  • 55
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    Astronomical capabilities of the Faint Object Spectrograph on Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Examples of scientific observing programs planned with the Faint Object Spectrograph on Space Telescope are presented. An overview of the spectrograph design and operation is presented. The expected astronomical performance of the instrument is described in some detail.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 55-75
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  • 56
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    The Space Telescope Observatory (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The history of the observatory is briefly described, as is the overall system design. The principal design features that are important to the scientific user are described. The present status of preparation for launch in the spring of 1985 is summarized.
    Keywords: ASTRONOMY
    Type: Space Telescope Science Inst. The Space Telescope Obs.; p 20-27
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  • 57
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    Science operations with Space Telescope (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The operation, instrumentation, and expected contributions of the Space Telescope are discussed. Space Telescope capabilities are described. The organization and nature of the Space Telescope Science Institute are outlined, including the allocation of observing time and the data rights and data access policies of the institute.
    Keywords: ASTRONOMY
    Type: The Space Telescope Obs.; p 1-15
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  • 58
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    Miniature voice output communication aid (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: COMMUNICATIONS AND RADAR
    Type: NASA Technol. Appl. Team; p 20
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  • 59
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    Atmospheric attenuation for correlated satellite communication ground sites (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Link margin estimates are calculated for 30/20 GHz satellite communication systems employing closely-spaced (4 to 100 km) 'dual diversity' switched ground sites. The link margin estimates are based on a new analysis in which the bivariate rain attenuation density function for two correlated ground sites is modelled by an exponential density function. The results of the exponential density function analysis enable derivation of a direct relation between rain margin estimates and probability of exceedance (link availability). Margins typically in the range 2 to 12 dB are calculated for various ground site separations and summarized for seven city locations and five satellite orbit positions over the U.S. The results can be easily extended to other EHF satellite frequencies and other locations.
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    Effects of ISI and satellite channel nonlinearity on Viterbi demodulation/decoding (1983)
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    Publication Date: 2011-08-18
    Description: It is shown that, for convolutionally coded transmission over bandwidth-constrained channels, a mere reversal of the switching direction at the encoder output produces a change in the system bit error probability performance. This change is significant when the Viterbi demodulator/decoder is matched to the total channel memory and is more significant for linear channels than for nonlinear ones. The reversal of switching direction is a simple demonstration of the fact that the well-known optimum codes for the linear AGWN channel are no longer necessarily optimum for a bandwidth-constrained channel with or without the addition of channel nonlinearity. It is concluded that potentially significant performance improvement can be obtained by matching the encoder (through the appropriate choice of tap weights and modulo-2 summers) to the channel in addition to matching the demodulator/decoder to the channel for a given encoder.
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    Heterodyne frequency measurements and frequency calibration standards for tunable diode lasers (1983)
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    Publication Date: 2011-08-18
    Description: New frequency calibration tables are required to keep abreast of the resolution attainable by currently available tunable lasers. One key to the generation of tables with requisite accuracy involves accurate heterodyne frequency measurements; another key consists of reliable fitting and analysis. Coordinated activity in NBS involves selection of suitable molecular calibration candidates, their frequency measurement and analysis, and dissemination of the results in the form of frequency calibration tables. Current status of these efforts is described.
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    Optogalvanic photodetachment spectroscopy (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A new extension to optogalvanic spectroscopy, in which electrons detached from negative ions formed in the discharge are observed as a function of incident laser wavelength, has been developed. The determination of the electron affinities of I(-) and Cl(-) atomic ions is described. The potential of the technique for studying the spectroscopy of molecular negative ions is also discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal de Physique (ISSN 0449-1947); 44; C7-461 t
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    Camera/photometer results (1983)
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    Publication Date: 2011-08-18
    Description: Camera/photometer systems have been constructed for analyzing particulate contamination on STS-2. The systems contained two 16-mm photographic cameras to make stereoscopic observation of contaminant particles and the background. During the STS-2 mission, 102 photographic exposures were obtained under conditions suitable for recording particulate contamination. Attention is given to a breakdown of STS-2 camera/photometer data with the number of particles observed per frame, a correlation of observed contamination with mission elapsed time broken into 5-hr segments, and a correlation of observed contamination with onboard spacecraft events.
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    Induced Environment Contamination Monitor (IECM), air sampler - Results from the Space Transport System (STS-2) flight (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An investigation involving sampling the rapidly changing environment of the Shuttle cargo bay is considered. Four time-integrated samples and one rapid acquisition sample were collected to determine the types and quantities of contaminants present during ascent and descent of the Shuttle. The sampling times for the various bottles were controlled by valves operated by the Data Acquisition and Control System (DACS) of the IECM. Many of the observed species were found to be common solvents used in cleaning surfaces. When the actual volume sampled is taken into account, the relative mass of organics sampled during descent is about 20 percent less than during ascent.
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    Nd:YAG holographic interferometer for aerodynamic research (1983)
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    Publication Date: 2011-08-18
    Description: A holographic interferometer system has been installed in the NASA Ames 2- by 2-Foot Transonic Wind Tunnel. The system incorporates a modern 10 pps, Nd:YAG pulsed laser which provides reliable operation and is easy to align. The spatial filtering requirements of the unstable resonator beam are described, as well as the integration of the system into the existing schlieren system. A two-plate holographic interferometer is used to reconstruct flow field data. For static wind tunnel models, the single exposure holograms are recorded in the usual manner; however, for dynamic models such as oscillating airfoils, synchronous laser hologram recording is used.
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    Mission analysis techniques for attached Shuttle payloads (1983)
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 24, p. 3746, Accession no. A82-48063
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 597-602
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  • 67
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    Space Shuttle entry longitudinal aerodynamic comparisons of flight 2 with preflight predictions (1983)
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 10, p. 1557, Accession no. A82-24655
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 518-523
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  • 68
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    Detection of silicate emission features in the 8- to 13-micron spectra of main belt asteroids (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A presentation is given of 8.0-13.0 micron spectra (Delta lambda/lambda = 0.02-0.03) for six main belt asteroids, which range from 58 to 220 km in diameter and sample the five principal taxonomic classes (C, S, M, R and E). Narrow, well-defined silicate emission features are present on two of the asteroids, the C-type 19 Fortuna and the M-type 21 Lutetia. No comparable emission features are observed on the S-types 11 Parthenope and 14 Irene, the R-type 349 Dembowska or the E-type 64 Angelina.
    Keywords: ASTRONOMY
    Type: Icarus (ISSN 0019-1035); 56; 393-397
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  • 69
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    Space Shuttle progress report (1982)
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    Publication Date: 2011-08-18
    Description: The Shuttle flight test plan is detailed, together with the results of tests of the flight control system (FCS). The initial Columbia flights carried 13,000 lb of instrumentation, and will be replaced with a 97 lb package during subsequent flights when further data are desired. The flight test program, besides gathering aerodynamic data, was heavily concerned with the perormance of the SSME (near-nominal), the thermal protection system (the performance and reusability have been demonstrated), and the data processing system (ground verification tests vindicated). Ascent has been nominal, as have orbital maneuvers, and descent roll/yaw has proven smoother than other high performance aircraft. Accelerometers and crewmembers have not been able to sense the smoothness of reentry RCS-controlled maneuvers. The manual controls are noted to serve only in off-nominal situations. The STS is concluded to be a basically sound vehicle, assuring a routine American presence in space.
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    Low gain and steerable vehicle antennas for communications with land mobile satellite (1982)
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    Publication Date: 2011-08-18
    Description: Current development activities at JPL for ground mobile vehicle antennas to be used with the Land Mobile Satellite Service (LMSS) system are described. Both low gain and electronically steerable high gain type antennas are discussed in terms of their design concept and RF performance. For the low gain type, three classes of antennas are under various stages of development. These are the crossed-drooping dipole, quadrifilar helix, and microstrip patch designs. The antennas are intended to provide circularly-polarized radiation with a minimum of 3-dB gain in the angular region from 19 degrees to 60 deg from the horizon in elevation plane and with an omnidirectional pattern in azimuthal plane. For the electronically steerable high gain type, circularly-polarized microstrip patch phased arrays formed on a planar surface and on the surface of a truncated cone are under study. The arrays are intended to provide a minimum of 12 dB gain in the same angular region in elevation plane at all azimuthal angles. This coverage is accomplished by scanning the high gain pencil beam in both elevation and azimuthal directions. Both types of antennas are to transmit at 821-831 MHz band and to receive at 866-876 MHz band. They must be of low cost design and reasonably conformal to the vehicle.
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    Concept for advanced satellite communications and required technologies (1982)
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    Publication Date: 2011-08-18
    Description: The advanced communications technology satellite (ACTS) program of NASA is aimed at the development of high risk technologies that will enable exploiting higher frequency bands and techniques for improving frequency reuse. The technologies under development include multiple beam spacecraft antennas, on-board switching and processing, RF devices and components and advanced earth stations. The program focus is on the Ka-band (30/20 GHz) as the implementing frequency since it has five times the bandwidth of either the C- or Ku-bands. However, the technology being developed is applicable to other frequency bands as well and will support a wide range of future communications systems required by NASA, other Government agencies and the commercial sector. An overview is presented of an operational 30/20 GHz satellite system that may evolve. How the system addresses service requirements is discussed, and the technology required and being developed is considered. Previously announced in STAR as N83-11210
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    The evolution of the infrared emission from the Type II supernova 1980k in NGC 6946 - The dust formation model (1983)
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    Publication Date: 2011-08-18
    Description: The paper presents 1-4 micron photometry of supernova 1980 k in NGC 6946 obtained over a period of 1 year following the outburst. During the period between 1980 November 1 and December 19, the infrared emission probably originated from the extended atmosphere of the expanding star. The JHKL colors and a 1.3-2.6-micron spectrum observed during this period correspond to those of a blackbody with an average temperature of about 5000 K. Observations around 1981 May 31 showed that the supernova developed an infrared excess after 1980 December. This infrared excess persisted through 1981 October and is consistent with the appearance of thermal emission from about 700 to 900 K dust in addition to a hotter photosphere. The similarity of this behavior to that of the infrared evolution of some novae suggests that dust formation may be occurring in the supernova ejecta. The hypothesis, that the emission arises from preexisting grains in a circumstellar shell which are heated by the supernova outburst, is also consistent with the data.
    Keywords: ASTRONOMY
    Type: Astrophysical Journal, Part 1 (ISSN 0004-637X); 274; 168-174
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  • 73
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    Differential absorption lidar technique for measurement of the atmospheric pressure profile (1983)
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    Publication Date: 2011-08-18
    Description: A new two-wavelength lidar technique for remotely measuring the pressure profile using the trough absorption region between two strong lines in the oxygen A band is described. The theory of integrated vertical path, differential ranging, and horizontal-path pressure measurements is given, with methods to desensitize and correct for temperature effects. The properties of absorption troughs are described and shown to reduce errors due to laser frequency jitter by up to two orders of magnitude. A general analysis, including laser bandwidth effects, demonstrates that pressure measurements with an integrated-vertical-path technique are typically fifty times more accurate than with a differential ranging technique. Simulations show 0.1-0.3 percent accuracy for ground and Shuttle-based pressure-profile and surface-pressure experiments.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics (ISSN 0003-6935); 22; 3759-377
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  • 74
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    Ultraviolet and optical studies of binaries with luminous cool primaries and hot companions. III - Reticon radial velocities (1983)
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    Publication Date: 2011-08-18
    Description: Radial velocities for 72 stars, most of them known or suspected binaries with F - K giant-supergiant primaries, are derived from Reticon spectra in the region 6005-6235 A at a scale of 7 km/s per diode. Cross-correlation of the spectra normally produces results accurate to better than 1.0 km/s. Eight new radial velocity variables are found (HR 2786, R Pup, HR 3291, HR 4451, HD 114520, HR 5667, HR 7014, and Nu1 Sgr). Improved orbits are determined for 15 known spectroscopic binaries, and provisional orbits are obtained for seven new spectroscopic binaries.
    Keywords: ASTRONOMY
    Type: Astrophysical Journal Supplement Series (ISSN 0067-0049); 53; 553-571
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    Infrared observations of RS CVn stars (1983)
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    Publication Date: 2011-08-18
    Description: The paper presents infrared photometry of the RS CVn binary stars AR Lac (1.2-10 microns) and MM Her (1.2-3.5 microns) as they egressed from their primary and secondary eclipses; of the eclipsing systems RS CVn and Z Her at maximum light (1.2-10 microns) and of the non-eclipsing systems UX Ari and HR 1099 (1.2-10 microns). An analysis of these and published V data based on flux ratio diagrams (linear analogues of color-color diagrams) shows that G and K stars supply the infrared light of these systems. In AR Lac, the combined light of a G5-K0 subgiant and either a late F dwarf or an early F subgiant can account for the observed visual and infrared light curves. None of these systems shows infrared emission from circumstellar matter. This result is simply understood: dust grains would not be expected to form in the physical conditions surrounding the subgiant, and the corona and chromosphere (whose properties have been deduced from spectroscopic X-ray observations) should not produce appreciable infrared emission.
    Keywords: ASTRONOMY
    Type: Royal Astronomical Society, Monthly Notices (ISSN 0035-8711); 205; 859-873
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  • 76
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    Ultraviolet high-resolution spectroscopy from the Space Telescope (1983)
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    Publication Date: 2011-08-18
    Description: The High Resolution Spectrograph is one of five scientific instruments which will be part of the Space Telescope observatory. The spectrograph was designed to take advantage of the imaging and pointing capabilities of the telescope to obtain ultraviolet spectra with spectral resolution comparable to large, ground-based coudeinstruments. Some of the results of the ground-based testing program will be described, along with applications of these properties to future science programs.
    Keywords: ASTRONOMY
    Type: Astronomical Society of the Pacific, Publications (ISSN 0004-6280); 95; 543-549
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  • 77
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    Space Shuttle/high energy upper stage capabilities for the 1990's (1982)
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    Publication Date: 2011-08-18
    Description: Possible performance gains and cost reductions available through the evolution of succeedingly larger unmanned, and then manned, orbital transfer vehicles (OTV) as Shuttle upper stages are projected. Future missions could include delivery of 10,000 lb to GEO, planetary missions in the 2000-12,000 lb class, 30-42 ft payloads in the 5000-10,000 lb class, and manned and unmanned satellite servicing by the turn of the century. The vehicles could evolve from the Centaur F vehicle through stages of all-propulsive configurations to aerobraked, fully reusable vehicles. Reusability introduces cost savings and the ability to make plane changes. Furthermore, aerobraking will double the payload capability for round trip journeys to GEO, bringing costs down to $7000/lb.
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    An advanced generation land mobile satellite system and its critical technologies (1982)
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    Publication Date: 2011-08-18
    Description: A conceptual design for a Land Mobile Satellite System (LMSS) for the 1990s is presented. LMSS involves small tranceivers accessing satellites directly, with ground reception through small car-top antennas. The satellite would have a large antenna and blanket coverage areas in the UHF. The call may originate from a home, be carried by wire to a gateway, transmitted to satellite on the S-band, converted to UHF on the satellite, and transmitted to the vehicle. The system design is constrained by the number of users in an area during the busiest hours, Shuttle storage, controllability factors, and the total area served. A 55-m antenna has been selected, with 87 spot beams and two 10 MHz UHF bands in the 806-890 MHz band. A 17 dB interbeam isolation level is required, implying that sufficient sub-bands can be generated to assure 8265 total channels. The mobile satellite (MSAT) would have an 83 m mast lower segment, a 34 m upper segment, and a second, 10 m antenna made of a deployable mesh. Various antenna function modes are considered.
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    Theoretical studies of the effects of grain noise on photographic stellar astrometry and photometry (1983)
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    Publication Date: 2011-08-18
    Description: A method of incorporating the effects of photographic emulsion grain noise into digital image centering algorithms is presented which improves the accuracy of the derived stellar positions and magnitudes. Theoretical formulae are then derived for the limiting error of the center, and the photometric parameters. For IIIa-J, this error is 0.2-0.3 mu for bright unsaturated images, which agrees quite well with measurements made with the Yale PDS microdensitometer. It is expected that, with further improvements in the positional accuracy of the PDS, it should be possible to reach the emulsion grain noise limit, providing that emulsion shifts or other large scale errors do not dominate. It is also shown that, with appropriate trimming, marginal distribution image centering algorithms can yield an accuracy only slightly poorer than that obtained with two-dimensional distributions.
    Keywords: ASTRONOMY
    Type: Astronomical Journal (ISSN 0004-6256); 88; 1683-168
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  • 80
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    Airborne detection of oceanic turbidity cell structure using depth-resolved laser-induced water Raman backscatter (1983)
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    Publication Date: 2011-08-18
    Description: Airborne laser-induced, depth-resolved water Raman backscatter is useful in the detection and mapping of water optical transmission variations. This test, together with other field experiments, has identified the need for additional field experiments to resolve the degree of the contribution to the depth-resolved, Raman-backscattered signal waveform that is due to (1) sea surface height or elevation probability density; (2) off-nadir laser beam angle relative to the mean sea surface; and (3) the Gelbstoff fluorescence background, and the analytical techniques required to remove it. When converted to along-track profiles, the waveforms obtained reveal cells of a decreased Raman backscatter superimposed on an overall trend of monotonically decreasing water column optical transmission.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics (ISSN 0003-6935); 22; 3778-378
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  • 81
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    Differential versus limiter-discriminator detection of narrow-band FM (1983)
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    Publication Date: 2011-08-18
    Description: The error probability performance of differential detection of narrow-band FM is determined and compared with the analogous results for limiter-discriminator detection of the same modulation. It is shown that over a large class of benign and hostile environments, e.g., Gaussian IF filter, AWGN, partial-band noise jamming, the differential detector offers no theoretical performance advantage over the limiter-discriminator receiver with integrate-and-dump postdetection filtering.
    Keywords: COMMUNICATIONS AND RADAR
    Type: IEEE Transactions on Communications (ISSN 0090-6778); COM-31; 1227-123
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  • 82
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    TDM/FM/FDMA - A modulation technique for multiple-beam satellites which precludes cochannel interference and allows non-uniform geographic distribution of user channels (1982)
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    Publication Date: 2011-08-18
    Description: The technique outlined in this paper is intended to eliminate the problems of cochannel interference and uniform geographic distribution of user channels which arise in conventional designs for a multiple spot beam communication satellite to serve mobile telephony users across the CONUS. By time multiplexing FM/FDMA signal ensembles so that only those beams operating on distinct frequency subbands are allowed to transmit concurrently, cochannel interference arising from simultaneous frequency subband reuse is precluded. Thus, time disjoint frequency reuse is accomplished over a repetitive sequence of fixed time slots. By assigning different size subbands to each time slot, a market of nonuniform users can be accommodated. The technique results in a greatly simplified antenna feed system design for the satellite, at a cost of imposing the need for time slot synchronization on the mobile FM receivers whose ability for rejecting adjacent channel interference is somewhat diminished.
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  • 83
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    An improved celestial radio reference frame: JPL 1982-4 (1983)
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    Publication Date: 2011-08-18
    Description: In the development of a celestial radio reference frame, there are now over 100 sources whose relative positions are known with an average uncertainty less than 5 milliarcseconds. These sources are fairly uniformly distributed over the celestial sphere north of -40 deg declination. Their positions are expressed in the new IAU system. This presentation describes the analysis involved in obtaining these results, as well as future plans for linking this system to the JPL planetary ephemerides.
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  • 84
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    Control of large space antennas based on electromagnetic-structural models (1983)
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    Publication Date: 2011-08-18
    Description: A general approach to the optimal control of large space antennas based on their RF/structural characteristics is described. The approach consists of defining a cost functional based on the degradation of the RF performance of the antenna and using the structural model as the dynamic system. The method is applied to the design of an optimal controller for a 55-m, wrap-rib offset-fed antenna. The controller's goal is to minimize the variations of the peak electric field of the antenna due to feed displacements.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 181-194
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  • 85
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    Single point random modal test technology application to failure detection (1982)
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    Publication Date: 2011-08-18
    Description: Frequency response function data, normally acquired as a data base for use in development of empirically based mode shapes, has additional utility. Comparison and analysis of frequency response function data sets obtained prior to and after environmental tests of an Orbiter body flap have enabled identification of structural damage that was not detected by conventional visual, X-ray, and ultrasonic inspections. The analyses and conclusions reported demonstrate that specific damaged areas within a relatively complex structure identified on a timely basis.
    Keywords: SPACE TRANSPORTATION
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., No. 52. Part 4; p 25-31
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  • 86
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    Space Shuttle and TDRSS telecommunications system interfaces (1982)
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    Publication Date: 2011-08-18
    Description: The telecommunications system interfaces between the spacecraft and the space shuttle, and between the spacecraft and the Tracking and Data Relay Satellite System (TDRSS) are discussed. The payload/shuttle/ground communications network, principle end-to-end link configurations, and requirements for attached and detached payloads are addressed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 557-596
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  • 87
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    Telecommunications performance analysis and monitoring software (1982)
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    Publication Date: 2011-08-18
    Description: The computer software used for telecommunications performance analysis and monitoring is discussed. The utilization of the TPAP analysis program for the Viking 1975 project and the Voyager 1977 project is described. The functional and design requirements for the successor system, TPAS, are also given.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 491-516
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  • 88
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    Radio frequency selection and interference prevention (1982)
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    Publication Date: 2011-08-18
    Description: The bands available for deep-space communications, and the choice of particular mission frequencies are discussed. The more general susceptibility of deep-space Earth stations to various kinds of interference is then presented. An associated topic is the development of protection criteria that specify maximum allowable levels of interference. Next, the prediction of interference from near-Earth satellites is described, with particular emphasis on the problems and uncertainties of such predictions. Finally, a brief description of other activities aimed at the prevention or avoidance of interference to deep-space radio communications is given.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 517-555
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  • 89
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    Spacecraft antennas (1982)
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    Publication Date: 2011-08-18
    Description: A tutorial description is given for spacecraft antennas used for deep-space-to-Earth communication. Radiation pattern parameters, pointing errors, pointing and polarization loss, and noise characteristics are discussed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 413-460
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  • 90
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    Spacecraft radio frequency subsystem (1982)
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    Publication Date: 2011-08-18
    Description: The historical background for the development of the planetary (RFS) is reviewed, and the performance capabilities of the various functional subassemblies are described. The flight radio frequency subsystem is a valid component for the three spacecraft telecommunications functions of tracking, command, and telemetry. It is the radio and the signal processing equipment residing in the spacecraft that interfaces with the control & data subsystem and performs two-way communications with the Earth-based Deep Space Network. The RFS consists of all the elements for RF reception, demodulation, modulation, and transmission, including those for command detection and telemetry modulation.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 383-412
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  • 91
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    Command system (1982)
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    Publication Date: 2011-08-18
    Description: The Multimission Command (MMC) System is described. The major components within the MMC System are discussed, with the emphasis on the telecommunication-related implementations. Two versions of the spacecraft command detection system (the Viking heritage command detector and the NASA standard command detector) are discussed in detail. The former prevails in the existing flight projects and the latter will likely be adopted by the missions of the near future. The preparation of design control tables for the control of command link performance between deep space stations and the spacecraft is also discussed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 343-381
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  • 92
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    Receiver design and performance characteristics (1982)
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    Publication Date: 2011-08-18
    Description: The basic design, principles of operation, and characteristics of deep space communications receivers are examined. In particular, the basic fundamentals of phase-locked loop and Costas loop receivers used for synchronization, tracking, and demodulation of phase-coherent signals in residual carrier and suppressed carrier systems are addressed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telcommun. Systems Eng.; p 49-121
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  • 93
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    Special characteristics of digital modulations (1982)
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    Publication Date: 2011-08-18
    Description: The importance of the bandwidth required for transmitting the chosen signaling or modulation technique in evaluating efficiency of a communication system is noted. The direct relation between bandwidth and the power spectral density (PSD) of the signaling scheme makes efficient analytical methods for calculating the PSD essential to specifying the spectral occupancy of the transmission channel. Several techniques for calculating the PSD of synchronous data pulse streams are reviewed.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 23-47
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  • 94
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    Telecommunications systems design (1982)
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    Publication Date: 2011-08-18
    Description: The general configuration of deep space telecommunication systems is reviewed with regard to the design criteria necessary to insure the integrity of the system's telemetry, command, and tracking functions. The signal to noise spectral density ratios that characterize telecommunications performance are defined in terms of the link parameters. For design control, a statistical approach to predict link performance and to assess its uncertainty is described.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Deep Space Telecommun. Systems Eng.; p 1-22
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  • 95
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    Submillimetre astronomy from space platforms (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The scientific need and the technical feasibility of a 10-m class far infrared telescope in space were studied and culminated in the recommendation of the large deployable reflector (LDR). The scientific considerations for such a project are described and the general characteristics of LDR are derived. A scientific program culminating in LDR is suggested.
    Keywords: ASTRONOMY
    Type: ESA The Sci. Importance of Submillimetre Observations ap 91-96 (SEE N83-22034 11-88)
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  • 96
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    DSN ground communications facility (1983)
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    Publication Date: 2011-08-18
    Description: A functional description of the GCF and its relationships with other elements of the DSN and NASCOM is presented together with development objectives and goals and comments on implementation activites in support of flight projects.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Rept.; p 200-209
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  • 97
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    MV-3 communication subsystem (1983)
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    Publication Date: 2011-08-18
    Description: The operational mobile VLBI data acquisition system (MV-3) requires that a voice link be established between the mobile data system and a fixed site. A communications subsystem was incorporated in the MV-3 design which consists of HF radio, VHF mobile radio telephone and conventional land line telephone. The HF antenna design was optimized for short and long range transmission using both inverted V and yagi antennas mounted on a self-supporting telescoping mast.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Rept.; p 210-219
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  • 98
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    S-band aperture efficiency of the DSS 13 26-meter antenna with the S-X common aperture feed (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Measurements of the S-band performance of the DSS 13 26-meter antenna, equipped with the second generation S-X common aperture feed, are reported. Aperture efficiency and overall antenna gain results are compared with predicted values. The elevation dependence of the aperture efficiency is reported.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Rept.; p 89-94
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  • 99
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    Antenna arraying performance for deep space telecommunications systems (1983)
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    Publication Date: 2011-08-18
    Description: Antenna arraying is a crucial Deep Space Network technique in maximizing the science return of planetary and comet encounters. The equations which describe the total figure of merit for a multiple system of arrayed antennas are developed. An example is given for three Canberra DSN antennas and the Parkes 64-m antenna to be arrayed for the Voyager 2 Uranus flyby.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Rept.; p 83-88
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  • 100
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    VLBI collimation tower technique for time-delay studies of a large ground station communications antenna (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A need for an accurate but inexpensive method for measuring and evaluating time delays of large ground antennas for VLBI applications motivated the development of the collimation tower technique. Supporting analytical work which was performed primarily to verify time delay measurement results obtained for a large antenna when the transmitter was at a collimation distance of 1/25 of the usual far field criterion is discussed. Comparisons of theoretical and experimental results are also given.
    Keywords: COMMUNICATIONS AND RADAR
    Type: The Telecommun. and Data Acquisition Rept.; p 20-29
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