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  • Other Sources  (2,113)
  • NASA Technical Reports  (2,113)
  • INSTRUMENTATION AND PHOTOGRAPHY  (1,039)
  • ASTRONOMY  (734)
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  • NASA Technical Reports  (2,113)
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  • 1
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    Radiography (1973)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Radiography is discussed as a method for nondestructive evaluation of internal flaws of solids. Gamma ray and X-ray equipment are described along with radiographic film, radiograph interpretation, and neutron radiography.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nondestructive Testing; p 63-99
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  • 2
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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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  • 3
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    Ultraviolet spectrometer experiment (1973)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The original scientific objectives and the achieved results are discussed. The upper atmosphere was found to have a variable temperature, with a mean exospheric temperature of 325 K; composed predominantley of CO2. Measurements of hydrogen and ozone are analyzed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Mariner Mars 1971 Proj., Vol. 5; p 53-61
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  • 4
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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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  • 5
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    Zodiacal light photography (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Polarized and red- and blue-filter photographs of zodiacal light obtained by Apollo 17 are analyzed. Attempts were made to identify the cause of subtle change in the observed light and determine the dust composition of the light. A comparison of red and blue images indicates such changes may be caused by particle size distribution and range, number of particles along any given line of sight, particle surface characteristics including dielectric compared to metallic properties, and variations of the parameters as a function of distance from the sun.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Apollo 17 Prelim. Sci. Rept.; 3 p
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  • 6
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    Effect of photogrammetric reading error on slope-frequency distributions (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The effect of reading error on two hypothetical slope frequency distributions and two slope frequency distributions from actual lunar data in order to ensure that these errors do not cause excessive overestimates of algebraic standard deviations for the slope frequency distributions. The errors introduced are insignificant when the reading error is small and the slope length is large. A method for correcting the errors in slope frequency distributions is presented and applied to 11 distributions obtained from Apollo 15, 16, and 17 panoramic camera photographs and Apollo 16 metric camera photographs.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center Apollo 17 Prelim. Sci. Rept.; 9 p
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  • 7
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    Near-terminator and earthshine photography (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Photographic results obtained during the Apollo 17 flight for the near terminator and earthshine conditions are discussed. Lunar surface photographs taken in the vicinity of the sunshine terminator provide important information that is not obtained on photographs taken at higher sun evaluation angles. Earthshine photography also provides data on low relief, crater morphology, and small scale structures. Examples of photographs of the lunar surface taken under both conditions are provided.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center Apollo 17 Prelim. Sci. Rept.; 7 p
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  • 8
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    Analysis of the dynamics and frequency spectrum synthesis of an optical-mechanical scanning device (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: A two-coordinate optical-mechanical scanning device (OMSD), the operating unit of which is a scanning disk, with directional and focusing optics and a board, on which the data carrier is placed, is examined. The disk and board are kinematically connected by a transmission mechanism, consisting of a worm and complex gear drive and a tightening screw-nut with correcting device, and it is run by a synchronous type motor. The dynamic errors in the system depend, first, on irregularities in rotation of the disk, fluctuations in its axis and vibrations of the table in the plane parallel to the plane of the disk. The basic sources of the fluctuations referred to above are residual disbalance of the rotor and other rotating masses, the periodic component of the driving torque of the synchronous motor, variability in the resistance, kinematic errors in the drive and other things. The fluctuations can be transmitted to the operating units through the kinematic link as a flexural-torsional system, as well as through vibrations of the housing of the device.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 301-305
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  • 9
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    Experimental research on aerostatic suspensions (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: Suspensions for carrying out experimental investigations, for the purpose of studying a number of problems in dynamics and stability of a suspended cylindrical body at various dynamic loads were investigated in the work. The results of the experimental investigations served as a basis for building a stand with a variable resonator. The experimental stand for suspension of cylindrical object, with a comparatively high natural free vibration frequency in the vertical direction, coinciding with the axis of the suspended object, is distinguished by the possibility of regulating the size of the clearance and is intended for carrying out preliminary experimental studies, for the purpose of selection of optimum aerostatic suspension parameters.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 289-291
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  • 10
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    Measurement of the vibration of structures with a three-component vibration sensor (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The effects of transverse waves and longitudinal displacements on transverse displacements in a plate are studied using a three component vibration sensor. Limitations of using the sensor in such measurements are: (1) sensor connection to the plate leads to changes in transverse displacement points on the plate surface, (2) the sensor has a finite magnitude of selectivity with respect to vibrations in the direction of the different channel axes, (3) longitudinal displacements of plate surface create restrictions on relative sensitivity of sensor to longitudinal-transverse waves, and (4) tranverse displacement of plate surface during longitudinal wave propagation also creates a restriction on sensor sensitivity to transverse waves.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 190-192
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  • 11
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    Vibrational sensitivity of a measuring instrument and methods of increasing the accuracy of its determinations (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The properties and peculiarities of two groups of measuring systems reacting to vibrations are discussed. Specifically, results of the action of a three dimensional, cophasal, monoharmonic vibration on the linear system of a measuring instrument was analyzed. Data are also given on the connection between vibration sensitivity and vibration resistance for instruments, methods for estimating vibration resistance, and formulas for expressing test results of vibration resistance. Experimental data are also given for decreasing errors in nonlinear systems during vibrations.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 188-189
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  • 12
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    New principles of construction of electromechanical vibration inducers (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: Electromechanical vibration inducers with high reliability and low noise level were created to study premature operating losses in their support bearings. An investigation was also made of the feasibility of developing stable synchronous operation of two vibrational inducers, rigidily fastened to a solid body with and without flexible suspension.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 176-178
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  • 13
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    The use of correlation receiving systems for detection of noise sources at short distances (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The use of a directional receiving system to detect noise sources masked by isotropic noise field interference at distances comparable with the distance between the two receivers, was discussed. Wide band noise was also examined. Results indicate the following limitations must be considered when using the method: (1) the system is directional only in the plane of the base, (2) directional power of the system is impaired with a decrease in the bandwidth of the noise source spectrum, (3) the system does not permit unambiguous determination of the direction to noise sources, located on both sides of the base line, and (4) the system has a comparatively low output signal-to-noise ratio.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 171-175
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  • 14
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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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  • 15
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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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  • 16
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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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  • 17
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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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  • 18
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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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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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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  • 24
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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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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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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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  • 30
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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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    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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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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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  • 36
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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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  • 37
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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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  • 38
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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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  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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    The use of film actinometry in low intensity ultraviolet irradiation measurement (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: High resolution film was used to measure solar ultraviolet irradiation at a wavelength of 254 nanometers between energy levels of 3 x 10 to the minus 7 power and 130 x 10 to the minus 7 power joules (3 and 130 ergs). The results imply that the film recorded exposure to energy levels from 2.5 to 13 times the expected values. These high values are being evaluated for the influences of other factors that could affect the recorded values.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center Proc. of the Microbial Response to Space Environ. Symp.; p 155-168
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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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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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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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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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  • 58
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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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    Cuvette loading and unloading procedures (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: The cuvettes for the flight hardware used in the Microbial Response to Space Environment Experiment (M191) were loaded with the biological test systems according to the methods described. After the flight, the experiment package was returned and dismantled. Then, the individual cuvettes were removed from the hardware and unloaded according to the procedures described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center Proc. of the Microbial Response to Space Environ. Symp.; p 41-48
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    Description of the microbial ecology evaluation device, flight equipment, and ground transporter (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: Exposure of test systems in space required the fabrication of specialized hardware termed a Microbial Ecology Evaluation Device that had individual test chambers and a complex optical filter system. The characteristics of this device and the manner in which it was deployed in space are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Proc. of the Microbial Response to Space Environ. Symp.; p 21-39
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    Electrical and acoustical resonances of vibrators (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The basic sources of vibration in electrical machines are identified as: (1) unbalanced masses of the rotor, (2) condition of the bearings, and (3) the electromagnetic field gap. Methods for improving the vibration characteristics of electrical machines are proposed. A mathematical model is developed for calculating the damping elements located between the bearings and the mounts.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 235-238
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    A silicon vidicon camera for slow scan operation (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A silicon vidicon camera was designed, built, and tested to determine its potential for use aboard future Mariner spacecraft. Slow scan operation is made possible by cooling the vidicon to -40 C. Cooling is achieved by a simple thermal condition path between the vidicon and a radiator mounted on top of the camera head. The camera was successfully operated under simulated space flight conditions and has survived vibration designed to simulate the launch of a Mariner spacecraft. A description of the camera and its operation along with the results of the testing is presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 27-36
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  • 63
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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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  • 64
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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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  • 65
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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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    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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  • 67
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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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  • 68
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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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  • 69
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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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  • 70
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    Solar corona photography (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: An analysis was made of Apollo 17 solar corona photographs in an effort to identify coronal streamers observed from earth. The photographs corroborate earth based observations; moreover, visual observations made by the Apollo crew indicate clearly identifiable streamers which extend to approximately 100 solar radii.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Apollo 17 Prelim. Sci. Rept.; 3 p
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  • 71
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    Apollo 17 laser altimeter (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The performance and operation of the Apollo 17 laser altimeter after several modifications are discussed. Functions of the instrument include precise altitude measurement of the CSM above the lunar surface, and measurement of broad scale topographic relief around the entire circumference of the moon.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Apollo 17 Prelim. Sci. Rept.; 4 p
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  • 72
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    Repeatability of elevation measurements: Apollo photography (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Sun elevation angle effects on repeatability, using Apollo 15 photographs are analyzed and results extended to slope related effects. Preliminary results indicate repeatibility of elevation measurement is related to contrast in the stereoscopic image.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center Apollo 17 Prelim. Sci. Rept.; 6 p
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  • 73
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    Photographic summary (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The photographic objectives of the Apollo 17 mission are discussed. The photographic requirements are divided into lunar surface photographs and orbital photographic tasks. The cameras used during the mission are listed and a general description of the tasks for which each was used is provided. Examples of photographs taken during lunar orbit and on the lunar surface are included. The cameras used and the photographic coverage obtained during specific phases of the mission are reported.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Apollo 17 Prelim. Sci. Rept.; 32 p
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  • 74
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    Identification of a mechanical vibration system (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The actual values of the parameters of a precision instrument assembly vibration system are determined according to experimental amplitude-frequency characteristics. The assembly is considered as a complex mechanical vibrating system, consisting of elements with concentrated and distributed parameters. A calculation procedure was compiled.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 36-37
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  • 75
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    Automatic measuring device for octave analysis of noise (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: An automatic decoder is described that counts noise levels by pulse counters and forms audio signals proportional in duration to the total or to one of the octave noise levels. Automatic ten fold repetition of the measurement cycle is provided at each measurement point before the transition to a new point is made.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 25-27
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    Use of the mathematical modelling method for the investigation of dynamic characteristics of acoustical measuring instruments (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The schematic diagram of a noise measuring device is presented that uses pulse expansion modeling according to the peak or any other measured values, to obtain instrument readings at a very low noise error.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 10-12
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  • 77
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    System for automated measurement of full-scale noises and vibrations (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: On-line devices are described for measuring the electrical spectrum of a signal in the presence of full scale noise and vibrations. The system includes a set of parallel filters with detectors at the filtration channel outlet. A reciprocal spectral density matrix is used to process the information contained in the interacting signals from various noise and vibration sources.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 3-6
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  • 78
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    Multiple-point unit for remote automatic spectral analysis (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: An experimental model of a mechanical spectrometer is reported that permits vibration measurements at 297 points on a mechanical device and processes this information by digital computer for automatic printout.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 1-2
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  • 79
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    Photogrammetric evaluation of Mariner 9 photography (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Some attempts to produce, with an AP/C analytical plotter, stereo models using Mariner 9 pictures are reported. The first attempt using geometrically uncorrected mission test video system (MTVS) imagery failed; the second, using corrected reduced data record (RDR) pictures also failed, probably because they were reconstructed through a vidicon display which introduces additional distortion. By using images obtained from RDR tape data through the Optronics Photowrite device, models were successfully obtained.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Mariner Mars 1971 Proj., Vol. 4; p 587-592
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    Mariner 9 ultraviolet spectrometer experiment: Mars atomic oxygen 1304-Angstrom emission (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Selected results are presented for a considerable quantity of Mariner 9 1304-A data for the first 100 revolutions from both the bright limb and disk of Mars. The limb data suggest that the exospheric temperature is less than it was in 1969 when Mariners 6 and 7 encountered the planet. Similar (O) concentrations (0.5 to 1%) are derived for a temperature of about 300 K. Structure in the limb profiles below 200 km suggests the possibility that about 0.2 kR of the observed approximately 0.8 kR near 150 km is due to dissociative excitation of CO2. Significant differences in selected limb profiles suggest that local as well as random variations in (O) occur.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Mariner Mars 1971 Proj., Vol. 4; p 355-368
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    Mariner 9 ultraviolet spectrometer experiment: Seasonal variation of ozone on Mars (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: On Mars, the Mariner observations show a twenty-fold variation in the amount of ozone, depending on the presence or absence of another minor constituent, water vapor, in the atmosphere. In the evolution of earth's primitive atmosphere, the formation of an ozone layer may have played an important role in the prebiotic chemistry that took place on the surface. The seasonal formation and disappearance of ozone in the contemporary Martian atmosphere may be of consequence in any prebiotic chemistry that may be occurring there.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Mariner Mars 1971 Proj., Vol. 4; p 369-372
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  • 82
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    Passive microwave images of lake ice (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-26
    Description: Photographic data and microwave emission images from the Great Lake ice formation are compared for their applicability to commercial shipping interests. A synoptic view of the microwave radiation from the lake area ice shows a large variation in brightness temperature. The snow ice appears to have the highest microwave brightness temperatures, whereas the thick clear ice shows up some 30 degrees kelvin colder, and the thin clear ice is colder still with a 1.55 cm radiation.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Significant Accomplishments in Sci.; p 187-189
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  • 83
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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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    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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    A new method of measurement of tension on a moving magnetic tape (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The possibility of no-contact measurement of the tension on a moving magnetic tape, assuming the tape is uniform, is discussed. A scheme for calculation of the natural frequency of transverse vibrations of magnetic tape is shown. Mathematical models are developed to show the relationships of the parameters. The method is applicable to the analysis of accurate tape feed mechanisms design.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 229-231
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  • 86
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    Method of accounting for instrumental distortions during observation of signals (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: A method is proposed for accounting for instrumental distortions in linear systems with known dynamic characteristics.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 193-194
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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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  • 88
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    Low frost-point humidity generator (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A low frost-point humidity generator has been developed at NBS to provide a capability for calibration, testing, and research at very low levels of water vapor content in such gases as atmospheric air, carbon dioxide and nitrogen. The generator produces frost points from -30 to -100 C at ambient pressures from 500 to 200,000 pascals (0.005 to 2 atm.). This is equivalent to mixing ratios of 4 micrograms to 51 grams of water vapor per kilogram of dry air and to vapor pressures of .0014 to 38 pascals. The generated test gas can be fed to a test chamber with independent temperature control between +25 and -100 C. The uncertainty of the frost point in the test chamber is estimated not to exceed 0.05 deg C.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Research; vol. 77A
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  • 89
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    Hot-wire coil probe for high-speed flows (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Small-diameter-wire coil probes developed for use in a hypersonic helium tunnel are discussed. The springlike properties of the coil minimize strain-gauge effects, and allow to use a higher length-to-diameter ratio for a given flow. In addition, the coil is more rugged for sudden flow changes, and since it can be mounted straight across the support tips, there is less support interference in cross flows. In addition to measuring fluctuating quantities in a boundary layer, the probes were used with a constant temperature anemometer for measuring mean mass flow profiles, and with a constant current anemometer for measuring mean total temperature profiles.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 11; Dec. 197
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  • 90
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    Increase in transmittance of unbacked aluminum filters exposed to RF or dc discharges in oxygen (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Results of an experimental study of the effect of discharges in oxygen on the oxide thickness and transmittance of aluminum filters. The studies were performed by exposing the filters to RF discharges and dc glow discharges in oxygen. In all experiments except one in which an aluminum ring was used as the cathode an increase in the transmittance of the filters is noted. It is thus demonstrated that the transmittance of aluminum filters increases on exposure to electrical discharges in oxygen, although it is not certain whether this phenomenon is caused by atomic oxygen.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 12; Dec. 197
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  • 91
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    Performance characteristics of proximity focused ultraviolet image converters (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Performance characteristics of Bendix type BX 8025-4522 proximity focused image tubes for UV to visible light conversion are presented. Quantum efficiency, resolution, background, geometric distortion, and environmental test results are discussed. The converters use magnesium fluoride input windows with Cs-Te photocathodes and P-11 phosphors on fiber optic output windows.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 12; Dec. 197
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  • 92
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    Molecular beam techniques applied to mass spectrometric thermospheric density measurements (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 44; Oct. 197
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  • 93
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    Use of LEED, Auger emission spectroscopy and field ion microscopy in microstructural studies (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
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  • 94
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    Skylab's photographic workhorse (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: There are ten Data Acquisition Cameras (DAC) aboard the Skylab workshop, and one additional is aboard each of the three command modules that ferry astronauts to Skylab. These cameras will transport approximately 40,000 feet of 16-mm film at frame rates from time exposures to 24 frames per second (fps). The heart of the 16-mm DAC system is a unique sequence camera. Approximately 80% of the Skylab 16-mm film will be exposed at 2 fps to maximize data acquisition time and remain within spacecraft return weight limitations. Of the approximately 225 accessories, the most unique item is the 400-foot magazine system.-
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Spectra; 7; Dec. 197
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  • 95
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    Evaluation of Raman scattering as a sensor of temperature and molecular density (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The performance of the Raman scattering technique for the remote monitoring of temperature and molecular number density in various wind tunnel and engine testing facilities has been experimentally evaluated. Temperature measurements were made by monitoring the pure rotational spectrum of nitrogen and the rotational branch separations of nu2 of CF4 for temperatures in the range 300 to 1000 K. These measurements yielded an average error of 2.6 and 7.6%, respectively, for temperature measurements at pressures near 1 atm. Molecular number density measurements with 20% error could be made at densities as low as 3.5 times 10 to the 22-nd power per cu m by monitoring the 6 to 8 rotational transition of nitrogen, 3.5 times 10 to the 23-rd power per cu m by monitoring the Q-branch of the fundamental vibrational transition of nitrogen, and 7 times 10 to the 22-nd power per cu m by monitoring the nu1 fundamental vibrational transition of CF4.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Spectroscopy; 27; Nov
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  • 96
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    Preparation of ultra small samples for optical and microprobe analysis (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper describes a simple but satisfactory new method for the preparation of tiny, varied and specialized specimens for electron or ion-microprobe analysis developed over the past five years. Microtektites, individual chondrules, single grains, blebs from lunar samples and meteoritic minerals have been prepared by this technique. A description of the preparation of these usually difficult samples from the initial mounting through the various polishing steps to their final polish is presented in detail. The procedures used to prevent any contamination of these specimens by the polishing agents and to prevent cross contamination to the other samples used for geochronology studies are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Meteoritics; 8; Sept. 30
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  • 97
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    A diode-quad bridge circuit for use with capacitance transducers (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 44; Oct. 197
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  • 98
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    Heterodyne frequency measurements and frequency calibration standards for tunable diode lasers (1983)
    In:  Other Sources
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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.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 99
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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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  • 100
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    Camera/photometer results (1983)
    In:  Other Sources
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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.
    Keywords: SPACE TRANSPORTATION
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