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  • Weitere Quellen  (513)
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  • 1
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    Space flight experience with the Shuttle Orbiter control system (1983)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-17
    Beschreibung: Experience gained through the Shuttle Orbital Flight Test program has matured the engineering understanding of the Shuttle on-orbit control system. The geneology of the control systems (called digital autopilots, or DAPs, and used by the Shuttle for on-orbit operations) is reviewed, the flight experience gained during the flight test program is examined within the context of preflight analysis and test results, and issues for the operational phase of the Shuttle, including constraints upon both operations and analysis still required to increase confidence in the Shuttle's ability to handle capabilities not experienced during the flight test program are addressed. Two orbital autopilots have resulted from computer memory and time constraints on a flight control system, with many different, flight phase unique requirements. The transition DAP, used for insertion and deorbit, has more active sensors and redundancy but a less complex data processing scheme excluding state estimation with fewer choices of operational mode.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 949-967
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  • 2
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    Reduced order control design for large space structures: A communication satellite example (1983)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-16
    Beschreibung: Large flexible communication satellite controller design is considered. The satellite that was developed for a "straw man' was configured as an offset fed paraboloid with a set of masts and booms that carry the antenna. The controllers were both a boom and mast actuator and a set of two degree of freedom actuators at the antenna to move it in order to satisfy both line of sight and defocus control.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 625-648
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  • 3
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    A large antenna system flight experiment (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The design and development of large antenna systems are discussed. The validation objectives and techniques of the structural behavior of the system are outlined along with studies of the dynamics, deployment, and unpacking. The validation of flexible control and system performance are also considered.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 1021-1027
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  • 4
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    SADE: A space experiment to demonstrate structural assembly (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Structural Assembly and Demonstration Experiment (SADE) demonstrates that the Shuttle is a suitable base for space construction; this includes a test of the Shuttle's control system to determine its performance when a long attached truss or beam is extended from the bay. Examples of Shuttle-related systems that will receive special attention are the RMS, the lighting system, and the crew assembly capabilities. A second purpose is to determine the extent to which the assembly results from the Neutral Buoyancy Simulator can be used to forecast the results of space assembly is determined. Finally, the SADE truss design will be validated by measuring the performance of the deployment, the special connectors, and the assembly methods.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 1027-1036
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  • 5
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    MAST space research flight experiment (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The MAST flight experiments comprise a research program focusing on major LSS issues for which it is deemed necessary to test, measure, and validate techniques and concepts in the space environment. The MAST Shuttle attached test articles are transported to space by the STEP experiment carrier and are compatible with STEP interfaces in all configurations. As the experiments require no particular orbit and the operational timeliness needed for mission performance are not extensive, it is forseen that the STEP/MAST combination could provide an attractive repetitive element within the Shuttle mixed cargo manifesting process. Using the STEP experiment carrier and a retractable reusable test article allows repetitive flight research to the extent that the STEP is able to be manifested on a regular basis. Since this research program examines generic phenomena, maximum emphasis is placed upon information quality and the fidelity with which the phenomena model emulates the LSS issue.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 1007-1019
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  • 6
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    SAFE II: Large systems space plasma evaluation experiment (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A shuttle flight experiment, the purpose of which is to obtain space data on the interaction of a high voltage solar array with the ambient space plasma is addressed. This flight experiment is a reflight of the solar array flight experiment, SAFE, except that three active solar array panels, electron release devices and plasma diagnostics are added. This experiment, SAFE 2, evaluates power loss due to parasitic current collected by the solar array, arcing on the solar array and perturbations to the plasma which may increase power loss and disturb plasma and charged particle science acquisition.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 991-1006
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  • 7
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    Safe on-orbit experiment for measurement of large structures dynamics (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Solar Array Flight Experiment (SAFE) on-orbit experiment for measurement of large structures dynamics consists of a dynamic sensing system designed to record and analyze the dynamic characteristics of the SAFE. The early availability of the SAFE and its basic large space structure characteristics make it a logical candidate for verification of the sensing system and the evaluation technique. The characteristics of the solar array which place it well within the generic class of large space structures are: (1) large size, (2) low natural frequencies, (3) mechanical complexity of its extendable/retractable mast, and (4) the inability to dynamically test in the Earth's atmosphere and in one g. The fourth characteristic is due to its size, air damping dominance of the blanket, and structural instability in one g. The specific characteristics of the solar array are shown and the applicability to large space structures is illustrated.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 981-989
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  • 8
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    Space Technology Experiment Platform (STEP). A Shuttle-borne support facility for structures, structural dynamics, and control technology flight experiments (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Space Transportation System (STS) is used for technology experiments in space. The Space Technology Experiment Platform (STEP) is a Shuttle-borne experiment support facility for use by structures, structural dynamics, and controls technology flight experiments. STEP represents a key element in the commitment to STS utilization. The STEP concept and definition process is discussed, and the results obtained to date on the configuration and function capability are summarized, and preliminary schedule information is presented.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 969-980
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  • 9
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    A robot in space as a large space structures control experiment (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The control systems design issues for large space structures can be addressed by a robotics experiment which defines a teleoperator or a robot or uses the RMS. The robotics control demonstration brings the large space structures control technology to an effective state of readiness and provides a useful robot when the experiment is finished. Three major options in such an experiment are the RMS, a flexible arm that is going to be put on the Shuttle for other reasons, or a dexetrous manipulator or teleoperator.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 941-947
    Format: text
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  • 10
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    The need for space flight experiments and testing in the development of large space antenna systems technology (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Flight experiments for large space antennas are discussed. A history of flight experimentation in the manned spacecraft program, space shuttle development, and planetary spacecraft is presented. Large space antenna systems are defined, and the needs for flight experiments justified.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 923-940
    Format: text
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  • 11
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    A survey of near-field testing methods for large aperture antennas and future trends (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: In recent years, a near-field antenna measurements have progressed from theoretical concepts to a wide variety of operational measurement systems. The current status of this work is summarized and its possible application to large space antennas is discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 877-897
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  • 12
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    Near-field measurement facility plans at Lewis Research Center (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The direction of future antenna technology will be toward antennas which are large, both physically and electrically, will operate at frequencies up to 60 GHz, and are non-reciprocal and complex, implementing multiple-beam and scanning beam concepts and monolithic semiconductor devices and techniques. The acquisition of accurate antenna performance measurements is a critical part of the advanced antenna research program and represents a substantial antenna measurement technology challenge, considering the special characteristics of future spacecraft communications antennas. Comparison of various antenna testing techniques and their relative advantages and disadvantages shows that the near-field approach is necessary to meet immediate and long-term testing requirements. The LeRC facilities, the 22 ft x 22 ft horizontal antenna boresight planar scanner and the 60 ft x 60 ft vertical antenna boresight plant scanner (with a 60 GHz frequency and D/lamdba = 3000 electrical size capabilities), will meet future program testing requirements.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 899-922
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  • 13
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    Development of improved analytical models for mesh reflector surfaces (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Several methods for computing the reflection coefficients from mesh surfaces are discussed. Some methods mentioned have severe limitations, and the spectral approach appears to be the most attractive alternative. In spite of some inherent problems, the solutions obtained with this method will offer not only the reflection coefficients but also the currents carried on the mesh. This would allow separation of the power lost to resistive terms from that due to transmission loss. Overall, good results and rapid convergence should be obtained from this method when proper care is applied.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 867-876
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  • 14
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    The effects of mesh reflecting surfaces upon radiometric measurements (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Reflector antennas with mesh surfaces have been used in ground and space applications primarily for communication systems. How the requirements for mesh surface reflectors are different for microwave radiometric applications is indicated, a method of measuring the anticipated small dissipation losses of gold-plated mesh using a radiometer system is proposed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 853-866
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  • 15
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    Large space antenna communications systems: Integrated Langley Research Center/Jet Propulsion Laboratory development activities. 3: Jet Propulsion Laboratory activities (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The portion of JPL antenna R/D work that is performed cooperatively with Langley Research Center in support of the demonstration and evaluation of the 15-m unfurlable antenna. The activities that will be performed during FY 83 and FY 84 are also indicated.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 833-851
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  • 16
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    Large space antenna communications systems: Integrated Langley Research Center/Jet Propulsion Laboratory development activities. 2: Langley Research Center activities (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The electromagnetic analysis activities at the Langley Research Center are resulting in efficient and accurate analytical methods for predicting both far- and near-field radiation characteristics of large offset multiple-beam multiple-aperture mesh reflector antennas. The utilization of aperture integration augmented with Geometrical Theory of Diffraction in analyzing the large reflector antenna system is emphasized.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 815-832
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  • 17
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    Large space antenna communications systems: Integrated Langley Research Center/Jet Propulsion Laboratory technology development activities. 1: Introduction (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Jet Propulsion Laboratory and the Langley Research Center have been developing technology related to large space antennas (LSA) during the past several years. The need for a communication system research program became apparent during the recent studies for the Land Mobile Satellite System. This study indicated the need for additional research in (1) electromagnetic analysis methods, (2) design and development of multiple beam feed systems, and (3) the measurement methods for LSA reflectors.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 809-814
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  • 18
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    Scanning beam antenna conceptual design for 20/30 GHz satellite systems (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The configuration described is one of four antenna system configurations developed using a variety of monolithic microwave integrated circuit module arrangements and optical systems. A parametric analysis is expected to produce a data base for the selection of design points for a variety of applications. Soon to be accomplished is the design concept of the active (lens) array, which will take into consideration such factors as, coupling effects, the space-fed power divider network design, input bias and control layout, investigation of thermal distribution, and analysis of module failure (graceful degradation).
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 767-795
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  • 19
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    Multimission advanced configuration (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The proposed multimission configuration reduces the number of reflectors present on the spacecraft and their related supporting structure (masts, booms) and at the same time divides the feed system from the reflector system for possible maintenance and/or payload substitution. This implies: An antenna system that is split into two parts: (1) the reflector with the platform (2) the feed subsystem with the payload. Reuse of the same reflector at different frequencies (to achieve this, the reflector system will use additional components, i.e., frequency sensitive subreflectors (FSS)). In case of in-orbit refurbishment or maintenance, the reflector system may remain in orbit with the platform. The presence of the FSS allows separation of the focal position sufficiently for the multiple-contoured beam applications required by future missions. There are two of these reflectors (one for TX function, one for RV deployed) on the east and west sides of the spacecraft, and the solar panels are on the north and south sides. The payloads are aligned along the yaw axis. Apart from the size, this configuration looks like a conventional spacecraft.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 797-807
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  • 20
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    INTELSAT 6 antenna system design and development (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: An overview of INTELSAT VI is presented.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 743-765
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  • 21
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    Results of studies at Langley Research Center on the control of large space systems (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A control moment gyro, an integrated power/attitude control system, and distributed adaptive control are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 2; p 721-742
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  • 22
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    Practical approaches to the design of control systems for large space structures (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Future space systems, flexible spacecraft, modular control, design-test-revise cycle, and control technique verification are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 709-719
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  • 23
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    Shape determination/identification for large space antennas (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: An integrated hardware/software system, SHADES, for shape determination and identification; a three dimensional multipoint sensor; multipoint sensor data; batch processing; and scanning algorithms are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 687-708
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  • 24
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    Computer analysis and ground testing of large space systems control strategies (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: High and low authority control integration; analytical studies, test model, disturbance rejection, LSS control, Toysat experiment, control hardware, slim beam test, plate experiments, and truss experimental results are presented.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 665-686
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  • 25
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    Current status of system identification methodology (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Large space structures, system identification, model formulation, experimental design, model order and structure determination, parameter estimation, reduced order modeling, and closed loops are considered.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 649-664
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  • 26
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    Enabling technologies for large precision space systems (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Modeling accuracy, system identification, control law design methodology, sensors and actuators, and avionics are addressed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 601-624
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  • 27
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    Control of large space antennas (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The NASA large space antenna missions, the performance requirements, and the resulting control technology requirements are summarized.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 583-608
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  • 28
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    Inflated antennas (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Inflatable space antennas are discussed. A brief history of inflatable structures is given. Several antenna configurations are described. The antenna configuration consisting of a thin film cone and parabolic held to the proper shape by internal pressure is discussed in detail.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 545-574
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  • 29
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    Box truss development and applications (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The development and applications of a box truss design for large space antennas are discussed. A kinematic model with a mesh reflector was constructed. A prototype cube is described. Details of fabrication are given.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 527-544
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  • 30
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    Electrostatically figured membrane reflectors: An overview (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Electrostatically figured membrane reflectors (EFMR) are described. Static and dynamic models were developed and verified. The models were used to develop control systems capable of stabilizing EFMR instabilities and providing EFMR disturbance rejection. Expected reflector figure diameter to surface tolerance ratios are given.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 575-582
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  • 31
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    Status of deployable geo-truss development (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The development of a deployable geo-truss spacetenna reflector is discussed. The design of the antenna is discussed. The proof of concepts development program is described.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 513-526
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  • 32
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    Survey of deployable antenna concepts (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Deployable space antenna concepts are surveyed. Precision reflector antennas, stiffened membrane antennas, truss antennas, infrared antennas, and electrostatically figured membrane reflectors are described.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 381-422
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  • 33
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    Hoop/column antenna development program (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The development of the hoop/column spacetenna reflector is discussed. Schedules, mission configurations, systems compatibility, deployment sequence, cable development, and ground model fabrication and assembly are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 469-512
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  • 34
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    Wrap-rib antenna concept development overview (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The wrap rib antenna design of a parabolic reflector large space antenna is discussed. Cost estimates, design/mission compatibility, deployment sequence, ground based tests, and fabrication are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 423-468
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  • 35
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    Manned assembly of space structures (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: This presentation will describe some results which have been obtained and the experiments which have been conducted in the Marshall Space Flight Center's Neutral Buoyancy Facility (MSFC NBF). The MSFC NBF is a tank of water 40 feet deep and 70 feet in diameter. Presently there is a mockup of the Orbiter payload bay at the bottom. There also is a Remote Manipulator System at the edge of the tank.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 285-300
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  • 36
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    NASA/USAF research in structural dynamics (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Research in the structural dynamics of large space structures is discussed. The problems of structural response are emphasized. Dynamic modeling, structural members, finite element techniques, axial loads, and vibration tests are among the topics discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 301-344
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  • 37
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    Structures for large precision reflectors (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The design and fabrication of a highly accurate large aperture infrared reflecting telescope is discussed. The structural concept is an off axis Cassegrainian design with a focal length equal to the aperture diameter. Thermal shielding, peak heat fluxes, cooling rates, active control tasks, and deployment sequence are discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 361-380
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  • 38
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    Advances in structural concepts (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A number of different structural concepts are currently under development as a means of placing large structures in orbit. Three commonly considered concepts are described. The radial rib structure and the hoop-column structure have undergone considerable early development because of their seeming potential for providing a reliably deployable reflector surface. In the present paper, attention is focused on truss structures which historically have been widely used in ground based structures because of their inherent simplicity, versatility, and high stiffness.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 257-284
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  • 39
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    Spacecraft material applications: Long-term stability questions (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: An examination of the materials concerns for a variety of spacecraft components shows that long-term stability within the space environments is a major issue in the design of large space antenna systems. This survey paper will review some of the more recent work on the effect of space environment on (1) thin films, (2) structural composites, and (3) thermal control materials. Degradation in thermal-mechanical and optical properties associated with atmospheric and trapped particles and ultraviolet light will be highlighted. Finally, the dimensional instability associated with microcracking during thermal cycling will be examined and a methodology for estimating thermal fatigue effects from results of mechanical fatigue tests will be presented.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 241-256
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  • 40
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    A summary of mission and system performance requirements for large space antennas (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Mission definition studies and system analyses have been described for a number of potential civilian missions and a few military missions. In this paper, an attempt is made to summarize the most formidable mission and system performance requirements for large space antennas. The emphasis will be on the civilian systems; only those aspects of military mission and system requirements that are unclassified are included.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 201-212
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  • 41
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    Spacecraft materials research: A NASA perspective (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: This paper reviews NASA's spacecraft materials research program. This is a multicenter program and includes research in the following areas: space environmental effects on materials, low expansion composites, fatigue and fracture of composites, thermal control coatings, and contamination. Research to date has concentrated on current graphite-reinforced composites and polymer systems, and developing analytical models to explain observed changes in mechanical, physical, and optical properties. As a result of these research efforts, new experimental facilities have been developed to simulate the space environment and measure the observed property changes. Chemical and microstructural analyses have also been performed to establish damage mechanisms and the limits for accelerated testing. The implications of these results on material selection and system performance are discussed, and additional research needs and opportunities in the area of tougher resin/matrix and metal/matrix composites are identified.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 213-240
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  • 42
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    Large space systems auxiliary propulsion requirements (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: To meet the needs of a variety of civilian and military missions objectives large space systems (LSS) will become a greater percentage of our orbiting hardware. These LSS's will be transported to low Earth orbit (LEO) by the space transportation system (STS Shuttle). Concurrently, for LSS missions to orbit higher than LEO, the predominant mission scenario is that the LSS will be deployed or assembled in LEO and then transferred to a higher orbit. In support of the LSS concepts, the Office of Aeronautics and Space Technology (OAST) has sponsored studies to determine LSS mission propulsion requirements. Since the fall of 1979, the Boeing Aerospace Company, under contract to NASA and Lewis Research Center, has been studying the disturbance forces and torques that will be experienced by LSS, and they have identified some of the associated auxiliary propulsion systems (APS) requirements. This presentation provides an insight into the results of some of the APS studies, focusing primarily on the APS requirements of single Shuttle launchable LSS's.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 175-200
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  • 43
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    Systems design and comparative analysis of large antenna concepts (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Conceptual designs are evaluated and comparative analyses conducted for several large antenna spacecraft for Land Mobile Satellite System (LMSS) communications missions. Structural configurations include trusses, hoop and column and radial rib. The study was conducted using the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) system. The current capabilities, development status, and near-term plans for the IDEAS system are reviewed. Overall capabilities are highlighted. IDEAS is an integrated system of computer-aided design and analysis software used to rapidly evaluate system concepts and technology needs for future advanced spacecraft such as large antennas, platforms, and space stations. The system was developed at Langley to meet a need for rapid, cost-effective, labor-saving approaches to the design and analysis of numerous missions and total spacecraft system options under consideration. IDEAS consists of about 40 technical modules efficient executive, data-base and file management software, and interactive graphics display capabilities.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 157-174
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  • 44
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    A 15-meter deployable aperture microwave radiometer (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Large Antenna Multifrequency Microwave Radiometer (LAMMR) was a 4-meter-diameter mechanically scanned (at 1 rps) antenna operating at frequencies from 4.3 to 36 GHz. This LAMMR system was scheduled to fly on the National Oceanic Satellite System (NOSS) in 1986 to measure sea surface temperature and wind speed along with several other atmospheric and sea ice parameters. The LAMMR was limited to a 4-meter solid reflector to stay within the Shuttle/NOSS launch volume and to operate with radiometric precision up to 36.5 GHz. Under the 4-meter aperture constraint, LAMMR could not meet the user resolution requirement for sea surface temperature (25 km minimum, 50 km goal) in an RFI free band, i.e., 4.3 GHz. This study explores the feasibility of meeting this requirement goal with a 15-meter mechanically scanned deployable reflector. Two other research objectives can also be studied by adding one active (approximately 5 GHz) and two additional passive (1.4 and 6.4 GHz) channels to investigate soil moisture and precipitation profiles over land. These two objectives are closely related because the precipitation is the source of the soil moisture in unirrigated regions, and the soil moisture changes between samples (2/day) could indicate that precipitation may have occurred while the sensor was not in view.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 131-156
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  • 45
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    Earth observation system: Spacecraft design (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Earth Observation Satellite (EOS) was a study funded by NASA Langley Research Center. The study was a system investigation of the total spacecraft integration with its major subsystems and sensors. Mission optimization and ranking using various sensors was also an objective of the contract. Integrating the spacecraft and major subsystems with the large microwave radiometer was done, essentially making the radiometer a free-flyer without an external spacecraft. Another program objective was to provide design and analysis data on microwave radiometer satellites augmented with additional Earth, ocean, and atmospheric sensors. A top-down systems approach resulted in a detailed design integrating subsystems and sensors into the microwave support structure. An important objective of the program was to identify technology needs for Earth observation satellites. The definition and understanding of these design drivers are critical in order to set priorities for future EOS work.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 105-130
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  • 46
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    Antenna technology for orbital Very Long Baseline Interferometry (VLBI) (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Since it is not economically feasible to construct steerable antennas much larger than 100 meters on Earth (400 meters for fixed telescopes), radio interferometry became a very useful technique for high resolution astronomy observations of quasars, galactic nuclei, and interstellar hydroxyl (OH) and water vapor (H2O) masers. The subsystems necessary to do the space VLBI experiment appear are available but require space qualifications. There are several 50-meter antenna concepts that could be used. Certainly there are problems to be solved. Feed positioning with respect to reflector, pointing such a large structure to accuracy indicated, and integration into the Shuttle control system are all significant engineering challenges. However, there are no problems that are insurmountable in the latter part of this decade.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 61-80
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  • 47
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    Pushbroom radiometry and its potential using large space antennas (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Electromagnetic radiation is emitted by matter which was heated to a temperature above absolute zero. The amount of blackbody radiation in the microwave frequency region of interest (10 to the 8th power f 10 to the 10th power Hz) emitted by matter can be determined from the Rayleigh-Jeans approximation to Planck's Radiation Law. The amount of electromagnetic radiation from matter which is not a blackbody is a function of the emissivity of the material. The emissivity is a factor less than unity and is a function of several parameters including chemical composition, temperature, frequency, surface characteristics, and viewing angle. A radiometer is an instrument which detects and provides a measure of the electromagnetic radiation being emitted by a material or surface area within the radiometer's antenna beamwidth. Microwave radiometers provide the capability for remote measurements from Earth orbits of geophysical parameters. These measurements will require the use of a microwave imaging radiometer using a large aperture deployable antenna with multiple beams in a pushbroom mode to achieve high spatial resolution and large swath width.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Large Space Antenna Systems Technol., Pt. 1; p 81-104
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  • 48
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    Large deployable reflector: An infrared and submillimeter orbiting observatory (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Large Deployable Reflector (LDR) is to be a dedicated astronomical observatory in space. It will operate in the 1 mm to 30 micron wavelength region where the Earth's atmospheric opacity makes ground-based observations nearly impossible. The primary mirror will be 20 m in diameter, made up of 37 individual segments. The reflector will be actively controlled to provide an overall surface accuracy of less than or approximately 2 microns. The LDR will be placed in orbit by the Space Shuttle and revisited at approximately 2 year intervals during its 10 year lifetime.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 53-60
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  • 49
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    Satellite systems requirements for land mobile communications (1983)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: The system design objective is to provide a satellite link through a gateway station, connecting mobile users in areas not served by a terrestrial cellular system to the switched telephone network (STN). The proposed frequency allocation comprises a pair of 10-MHz bands in the 806-890 MHz range specified by the 1979 World Administrative Radio Conference (WARC) for land-mobile satellite service (LMSS). The satellite design is constrained by projected STS capability with an upper stage of the wide-body Centaur or Integral Propulsion System (IPS) type. For the latter (a TRW design), the payload is limited to approximately 10,400 lb. The design is to be based on 1990's technology, with initial operating capability scheduled for 1995. The satellite should be designed for a 7-year life. Mobile-unit compatibility with cellular system specifications is desirable, if consistent with other system requirements.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 29-46
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  • 50
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    Large spaceborne antenna technology: A system perspective (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Land Mobile Satellite System (LMSS) is a communication system which provides radio communication to a large group of users within a vast geographical area (e.g. communications to and from mobile vehicles anywhere within the U.S.). Such radio communication may be in the form of radio telephone, paging, dispatch, or data transmission. The intended applications of LMSS range from emergency medical to disaster relief, from law enforcement to truck dispatch. By providing service to vast rural areas, LMSS compliments the current terrestrial service in the metropolitan areas and hence provides for a nationally ubiquitous coverage.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 1-16
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  • 51
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    Land mobile satellite system requirements (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A Land Mobile Satellite System (LMSS) provides voice, data and related communications services to moving vehicles and persons. Communications between the mobiles and satellite are in the 806-890 MHz band. The satellite translates these signals to a ""fixed services band'' such as 14/12 GHz band (Ku-band), and communicates in this band with fixed terminals called gateways. The gateways are located at convenient places such as telephone switches (which provide entry into the national telephone system), dispatcher headquarters, computer centers, etc. Communications are therefore principally mobile to fixed. A third communications link, also at Ku-band, is needed between the satellite and a single fixed ground station. This link provides satellite command, telemetry and ranging and also provides a network control function. The latter, through a common signalling system, receives requests and assigns channel slots, and otherwise controls, monitors and polices the network and collects billing information.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 17-28
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  • 52
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    Thermal analysis considerations for large space structures (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-11
    Beschreibung: A number of issues and needs relative to thermal analysis of large space structures and space stations are discussed. Some indications of trends in the Langley thermal-structural analysis research program consistent with the issues and needs are also presented. The main heat transfer mechanism in space is radiation; consequently, there is a need for a strong thrust on improved radiation analysis capability. Also the important interactions among temperatures, deformations, and controls need to be accounted for. Finite element analysis capability seems to be lagging behind lumped-parameter capability or heat pipe analysis. The Langley plan will include improving radiation analysis capability, evaluating the errors involved in certain approximate analysis and modeling techniques for large space trusses, and continuing the development of integrated thermal-structural finite elements with an emphasis on radiation heat transfer. Work will be initiated to develop finite element analysis techniques for heat pipes. Finally, optimization research activities will be oriented toward methods to design flexible orbiting structures to account for thermal and thermal deformation requirements.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Modeling Analysis, and Optimization Issues for Large Space Struct.; p 123-147
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  • 53
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    Assessment of current state of the art in modeling techniques and analysis methods for large space structures (1983)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-11
    Beschreibung: Advances in continuum modeling, progress in reduction methods, and analysis and modeling needs for large space structures are covered with specific attention given to repetitive lattice trusses. As far as continuum modeling is concerned, an effective and verified analysis capability exists for linear thermoelastic stress, birfurcation buckling, and free vibration problems of repetitive lattices. However, application of continuum modeling to nonlinear analysis needs more development. Reduction methods are very effective for bifurcation buckling and static (steady-state) nonlinear analysis. However, more work is needed to realize their full potential for nonlinear dynamic and time-dependent problems. As far as analysis and modeling needs are concerned, three areas are identified: loads determination, modeling and nonclassical behavior characteristics, and computational algorithms. The impact of new advances in computer hardware, software, integrated analysis, CAD/CAM stems, and materials technology is also discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Modeling Analysis, and Optimization Issues for Large Space Struct.; p 5-32
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  • 54
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    A computational approach to the control of large-order structures (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: The independent modal space control (IMSC) method is described and compared with the coupled controls method. Although the coupled controls require fewer actuators, the IMSC provides: larger choice of control techniques, including nonlinear control; lower computational effort; lower computer storage requirement; lower control energy; provable robustness; and actuator location flexibility.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 99-112
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  • 55
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    Structural modelling and control design under incomplete parameter information: The maximum-entropy approach (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: A stochastic structural control model is described. In contrast to the customary deterministic model, the stochastic minimum data/maximum entropy model directly incorporates the least possible a priori parameter information. The approach is to adopt this model as the basic design model, thus incorporating the effects of parameter uncertainty at a fundamental level, and design mean-square optimal controls (that is, choose the control law to minimize the average of a quadratic performance index over the parameter ensemble).
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 73-96
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  • 56
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    Analysis and testing of large space structures (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: Considerations and approaches to the ground testing of large space structures are discussed. The large size combined with the loading due to gravity makes testing of the complete structure difficult. Gravitational stiffening, suspension effects, virtual air mass, preloads, and air damping alter the dynamic characteristics. Low resonant frequencies and high modal densities within the frequency range of interest combine with small motions and accelerations to make testing difficult. Mechanism complexities and nonlinearities associated with space-erected/assembled structures cause structural complexity regardless of other considerations. Ground test approaches include scale models, element and substructure tests, and structural linearization. Analytical approaches are also discussed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 113-122
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  • 57
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    Control of large space structures: Status report on achievements and current problems (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: The objectives, state-of-the-art, and problems of large space structures control are outlined. The general objectives range from basic deployment and maneuvering, where some vibration modes may be suppressed, to disturbance rejection for very high performance imaging applications. The controls selected generally must produce some combination of eigenvalue/eigenvector and loads modification in order to achieve the mission objectives. An experiment illustrating the dynamic control of a suspended circular plate is described. Analysis methods used in system modelling, signal processing, and process control and monitoring are discussed. Sensor and actuator performance are assessed.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 55-72
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  • 58
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    Optimal large-angle maneuvers with vibration suppression (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: Some methods and applications which determine optimal maneuver controls are overviewed. The main aspects of optimal control theory are summarized and the essential ideas involved in a class of methods ('continuation' or 'homotopy' methods) which are useful in solving the resulting two-point boundary value problems are discussed. Several low dimensioned, nonlinear maneuvers of multiple rigid-body configurations using optimal momentum transfer are discussed. Several linear and nonlinear flexible-body maneuvers are then presented and include distributed controls, vibration suppression/arrest, and computational issues. Finally, the key problem areas in which future research appears most urgent are identified.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 177-215
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  • 59
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    Algorithm development for the control design of flexible structures (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: The critical problems associated with the control of highly damped flexible structures are outlined. The practical problems include: high performance; assembly in space, configuration changes; on-line controller software design; and lack of test data. Underlying all of these problems is the central problem of modeling errors. To justify the expense of a space structure, the performance requirements will necessarily be very severe. On the other hand, the absence of economical tests precludes the availability of reliable data before flight. A design algorithm is offered which: (1) provides damping for a larger number of modes than the optimal attitude controller controls; (2) coordinates the rate of feedback design with the attitude control design by use of a similar cost function; and (3) provides model reduction and controller reduction decisions which are systematically connected to the mathematical statement of the control objectives and the disturbance models.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 151-176
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  • 60
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    Recent developments in thermal analysis of large space structures (1983)
    In:  CASI
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    Publikationsdatum: 2006-04-11
    Beschreibung: A numerical procedure for analysis of shadowed space heating of sparse structures, SSQ, is discussed. The SSQ program avoids inordinate computational complexity by confining attention to a single elemental location on a structural member of interest throughout an entire orbital period, proceeding then to similar treatment of individual alternate locations. The procedure considers a spacecraft in circular orbit and assumes fixed-Earth orientation of the spacecraft. Shadow orientation and interval duration, merged shadows, and computation of solar heat flux and thermal response are addressed. The output options of the SSQ FORTRAN 5 program and its efficiency are discussed. Application of the system to the analysis of a parabolic expandable truss antenna is considered.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 33-54
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    Solution adaptive grid generation (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Langley Research Center, Theoretical Aerodynamics Contractors' Workshop, Volume 2; p 651-68
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  • 62
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    Navier-Stokes solution for quasi-three dimensional flow (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Langley Research Center, Theoretical Aerodynamics Contractors' Workshop, Volume 1; p 329-33
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  • 63
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    Vectorized, implicit Navier-Stokes solver for 2-D incompressible flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Langley Research Center, Theoretical Aerodynamics Contractors' Workshop, Volume 1; p 273-31
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  • 64
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    Clebsch velocity decomposition for rotational conical flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Langley Research Center, Theoretical Aerodynamics Contractors' Workshop, Volume 1; p 183-19
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  • 65
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    Influence of convection on the growth of crystals from solution (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Beschreibung: This is a review of the influence of convection on the growth of crystals from solution. The growth rate is increased by convection up to the point where interface kinetics becomes rate controlling. Compositional inhomogeneity and morphological instability (inclusion formation) are probably worse for gentle convection than for either no convection or for vigorous stirring. Stirring, particularly of crystal suspensions, can cause an orders of magnitude increase in the rate of formation of new crystals. This is called 'secondary nucleation'.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Crystal Growth (ISSN 0022-0248); 65; 133-142
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  • 66
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    The production of turbulent stress in a shear flow by irrotational fluctuations (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Attention is given to the way in which external turbulence affects an initially turbulence-free region in which there is a mean velocity gradient. External turbulence induces irrotational fluctuations in the sheared region which interact with the shear to produce rotational velocity fluctuations and mean Reynolds stresses. Since the actual front between the initial external turbulence and the shear flow is a randomly contorted surface, the turbulence near the front is intermittent, and is presently included in the form of a simple statistical model. In wind tunnel tests, turbulent shear stress was found to grow from zero to significant values in the interaction region. Observed stress magnitude and extent agrees with predictions, and it is concluded that turbulent stresses can be produced by irrotational fluctuations in a region of mean shear.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Fluid Mechanics (ISSN 0022-1120); 137; 307-329
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  • 67
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    Viscous thermocapillary convection at high Marangoni number (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A liquid, contained in a quarter plane, undergoes steady motion due to thermocapillary forcing on its upper boundary, a free surface separating the liquid from a passive gas. The rigid vertical sidewall has a strip whose temperature is elevated compared with the liquid at infinity. A boudnary-layer analysis is performed that is valid for large Marangoni numbers M and Prandtl numbers P. It is found that the Nusselt number N for the horizontal heat transport satisfies N proportional to min (M to the 1 2/7/power, M to the 1 1/5/power, M to the 1 1/10/power) Generalizations are discussed.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Fluid Mechanics (ISSN 0022-1120); 135; 175-188
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  • 68
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    Stagnation-point ablation of carbonaceous flat disks. II Experiment (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Six flat-disk models made of carbon-carbon and carbon-phenolic materials were launched in an argon-filled track-range facility to test ablation characteristics in a radiation-dominated, massive-blowing environment. The shock standoff distances deduced from the shadowgraphs agree with theoretical predictions during the earlier portion of the flight, while the wall temperatures determined by the image-converter photographs agree with predictions during the later portion. The measured surface recessions exceed the calculated values by about 60 percent for carbon-phenolic and 30 percent for carbon-carbon. The discrepancies are attributed to spallation. The measured char thicknesses agree with theoretical predictions.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA Journal (ISSN 0001-1452); 21; 1748-175
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  • 69
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    Continuation in a parameter - Experience with viscous and free surface flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The results of modifications in continuation methods applied to obtain solutions to the Navier-Stokes systems of equations for incompressible, two-dimensional, steady flows are reported. It is shown that parameter continuation permits prediction of accurate, initial estimates for iterative processing of nonlinear finite difference and finite element equations of motions. The new parameter steps are derived from values of the preceding parameter steps. The accuracy of the estimates is ensured with appropriate choices of the step size. The continuation predictor/iterative corrector is demonstrated to trace the branches of parameter space along which steady flow states are found, and techniques are available for tracing multiply branching paths. The techniques are applied to solving the Navier-Stokes equations for flow through a rotating square channel, the formation of a falling liquid curtain, and gyrostatic equilibria of rotating cylindrical drops.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
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  • 70
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    Modeling of transient two-component flow using a four-point implicit method (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The four-point, centered implicit scheme that is extensively used in open channel flow simulation is shown to be applicable to rapid and slow pressure transient problems in conduits with nearly single phase and two-phase flows. It is only necessary to choose the proper weighting factor value, theta, of the Courant number. For rapid pressure transients such as waterhammer, the implicit method can yield reasonable results with limited numerical dispersion and attenuation if theta is only slightly greater than the critical value of 0.5. For slower pressure gradients in single and two-phase flows, reasonable numerical solutions may be achieved for Courant number values as high as 20.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
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  • 71
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    The production of turbulent stress in a shear flow by irrotational fluctuations (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: This paper examines, both theoretically and experimentally, the effect produced by irrotational fluctuations, associated with a nearby turbulent field, in a region where the turbulence is initially very low but where there is a mean shear. Calculations are based on rapid distortion theory and experiments use linearized hot wire anemometers in an open circuit wind tunnel. Turbulent shear stress is observed to grow from zero to significant values in the interaction region. The magnitude and extent of this observed shear stress agree reasonably well with predictions of the analysis, when intermittency effects are included. It is concluded that turbulent stresses can be produced by irrotational fluctuations in a region of mean shear and that this effect can be estimated using rapid distortion theory if the overall strain ratio is not large.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
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  • 72
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    A modified Dodge algorithm for the parabolized Navier-Stokes equations and compressible duct flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A revised version of Dodge's split-velocity method for numerical calculation of compressible duct flow was developed. The revision incorporates balancing of mass flow rates on each marching step in order to maintain front-to-back continuity during the calculation. The (checkerboard) zebra algorithm is applied to solution of the three dimensional continuity equation in conservative form. A second-order A-stable linear multistep method is employed in effecting a marching solution of the parabolized momentum equations. A checkerboard iteration is used to solve the resulting implicit nonlinear systems of finite-difference equations which govern stepwise transition. Qualitative agreement with analytical predictions and experimental results was obtained for some flows with well-known solutions. Previously announced in STAR as N82-16363
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: International Journal for Numerical Methods in Fluids (ISSN 0271-2091); 3; 493-506
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  • 73
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    Accuracy of approximations to the Navier-Stokes equations (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The systems of truncated differential equations that have been proposed to reduce the complexity and large computational costs of solutions to the full Navier-Stokes equations are considered. These systems are computationally efficient and capture all the physically relevant behavior. The systems follow a certain hierarchy: (1) the classical boundary-layer equations with specified edge properties (usually the streamwise pressure distribution); (2) the coupled boundary-layer/inviscid equations; (3) the so-called thin-layer equations that discard streamwise diffusion; and (4) the Navier-Stokes equations. Consideration is given to each of these approximations applied to an incompressible, laminar-separating flow at low and moderate Reynolds numbers. It is pointed out that for any flow or region of flow for which viscous-inviscid interaction effects are small, classical boundary-layer equations will provide a satisfactory description of the viscous flow at a fraction of the computational cost of any higher approximations.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA Journal (ISSN 0001-1452); 21; 1759
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  • 74
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    Growth of Goertler vortices in compressible boundary layers along curved surfaces (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-19
    Beschreibung: An investigation of the growth of the three-dimensional, counter-rotating, longitudinal type vortices is considered in two-dimensional laminar compressible boundary-layer flow. The basic approximation of the disturbance equations that includes the terms due to boundary layer growth is considered and solved numerically. These terms are shown to have large local effects near the neutral stability region. The study shows that the instability of the boundary layer with respect to the three-dimensional vortices sets in at higher Goertler number as Mach number increases. Also the maximum amplitude ratio of the vortices is reduced by about 20 percent as Mach number increases from 0 to 5.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Engineering and Applied Sciences (ISSN 0191-9539); 2; 3, 19; 213-238
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  • 75
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    Direct launch using the electric rail gun (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The concept explored involves using a large single stage electric rail gun to achieve orbital velocities. Exit aerodynamics, launch package design and size, interior ballistics, system and component sizing and design concepts are treated. Technology development status and development requirements are identified and described. The expense of placing payloads in Earth orbit using conventional chemical rockets is considerable. Chemical rockets are very inefficient in converting chemical energy into payload kinetic energy. A rocket motor is relatively expensive and is usually expended on each launch. In addition specialized and expensive forms of fuel are required. Gun launching payloads directly to orbit from the Earth's surface is a possible alternative. Guns are much more energy efficient than rockets. The high capital cost of the gun installation can be recovered by reusing it over and over again. Finally, relatively inexpensive fuel and large quantities of energy are readily available to a fixed installation on the Earth's surface.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: APL The 1983 JANNAF Propulsion Meeting, Vol. 1; p 51-56
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  • 76
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    The 1986 launch of the Galileo spacecraft via the Space Transportation System (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Beginning with the Galileo spacecraft launch, deep space payloads will be launched via the Space Shuttle. This change from the previous use of expendable launch vehicles will introduce large changes in procedures and data flow configurations for both the flight project and the Deep Space Network during the launch period. The planned Galileo launch period sequence of events and telemetry and command data flow configurations are described.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: The Telecommun. and Data Acquisition Rept.; p 186-199
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  • 77
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    Finite element calculation of buoyancy-driven convection near a melt/solid phase boundary (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Two iterative schemes based on the mixed finite element method are developed for analyzing steady natural convection in a melt adjacent to its solid phase. The simplest method decouples the calculation of the field variables and the shape of the melt/solid interface into two interlocked iterations that are performed successively. The second method uses Newton's iteration to solve simultaneously for both types of unknowns and has a quadratic convergence rate. Results for a model problem of melt and solid in a cylindrical ampoule show the Newton algorithm to be a factor of three more efficient.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
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    Exospheric cleaning of the Earth Radiation Budget solar radiometer during solar maximum (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Anomalous behavior of the Earth Sensor Assemblies (ESA) had been observed on the Defense Meteorological Satellite Program (DMSP) 5D/1 satellites and the Tiros-N satellite. The present investigation is concerned with the reasons for the observed phenomena. Degradation of the Earth Radiation Budget (ERB) solar channels and the Solar Backscatter Ultraviolet and Total Ozone Mapping Spectrometer (SBUV/TOMS) diffuser plate is attributed to transmission or reflection loss originating from the growth of an organic film by photolytic polymerization. Simultaneous degradation of the ESA interference filter coated lenses facing the flight direction and the recovery of the ERB solar channels on Nimbus 6 and 7 is caused by a reaction with the increase in the exospheric atmospheric density caused by solar maximum.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
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  • 79
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    Multiple-grid convergence acceleration of viscous and inviscid flow computations (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A multiple-grid algorithm for use in efficiently obtaining steady solution to the Euler and Navier-Stokes equations is presented. The convergence of a simple, explicit fine-grid solution procedure is accelerated on a sequence of successively coarser grids by a coarse-grid information propagation method which rapidly eliminates transients from the computational domain. This use of multiple-gridding to increase the convergence rate results is substantially reduced work requirements for the numerical solution of a wide range of flow problems. Computational results are presented for subsonic and transonic inviscid flows and for laminar and turbulent, attached and separated, subsonic viscous flows. Work reduction factors as large as eight, in comparison to the basic fine-grid algorithm, were obtained. Possibilities for further performance improvement are discussed. Previously announced in STAR as N83-21847
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Applied Mathematics and Computation (ISSN 0096-3003); 13; 375-398
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    Effect of variable thermal conductivity on isotherms in Bridgman growth (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A change in thermal conductivity associated with melting or solidification can have a profound influence on the isotherms near the solidification interface if the material is being directionally solidified in an ampoule whose walls carry a substantial portion of the heat. This analysis was prompted by a recent discovery that the thermal conductivity of Hg(1-x)CD(x)Te increased dramatically as the material is heated above the solidus curve. An illustrative example is shown in which the sample is approximated as an infinite cylinder with constant but diffferent thermal properties in the solid and melt. The boundary conditions are fixed on the surface by a conductive ampoule in a two-zone Bridgman furnace with an adiabatic region separating the two zones. The effect of the adiabatic zone in this case is to intensify the curvature of the interface rather than to lessen it.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Crystal Growth (ISSN 0022-0248); 61; Apr
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    Analysis of coolant entrance boundary shape of porous region to control cooling along exit boundary (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A cooled porous region has a plane surface exposed to a specified spatially varying heat flux. The coolant leaves the region through this surface, and it is desired to control the flow distribution to maintain a specified uniform surface temperature. This is accomplished by having the coolant entrance surface shaped to provide in the region the necessary variation of path length and, hence, flow resistance. The surface shape at the coolant entrance is found by solving a Cauchy boundary value problem. An exact solution is obtained that will deal with a wide variety of heating distributions for both two- and three-dimensional shapes.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: ASME, Transactions, Journal of Heat Transfer (ISSN 0022-1481); 105; Aug. 198
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    The IRAS project organisation and mission operations (1983)
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    Publikationsdatum: 2011-08-18
    Beschreibung: The project organisation of IRAS is described, showing the tasks assigned to each project group during post-launch operations. The satellite is described, emphasizing the detectors. In the task division, the role of the U.S. is to construct the telescope and survey instrument, launch the satellite, process final science data for the survey instrument, and provide certain standard satellite items. The Netherlands construct the spacecraft and three additional instruments, integrates and tests the overall satellite, and designs and participates in the development of the operational system. The U.K. provides the operational control center and primary tracking station, generates a system for preliminary science analysis of the survey data, provides housekeeping analysis software and science data distribution software, and staffs the control center operations. The teams involved in mission planning and operations, and their roles, are identified, and a block diagram of the operations organisation is presented.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: vol. 36; Jan. 198
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  • 83
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    Numerical solutions for spin-up from rest in a cylinder (1983)
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    Publikationsdatum: 2011-08-18
    Beschreibung: A set of three-dimensional flow-field data for the region around a cylinder impulsively spun-up from rest was derived with a numerical model based on the Navier-Stokes equations. Laser-Doppler anemometer data in the azimuthal direction was employed to test the model predictions, and data was developed for a flowfield with Ekman numbers from 9.18/1,000,000 to 9.18/10,000. The contributions of inviscid and viscous terms were determined as functions of radius and time. It was found that immediately after start-up viscous diffusion is the dominant factor, which is replaced by nonlinear radial advection. The Coriolis force dominates in the later stages of spin-up. The inward radial flow is a maximum near the front, where the vertical velocity is small, but features strong radial gradients, as it does at the edge of the Ekman layer.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Fluid Mechanics; 127; Feb. 198
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    Procedure for generating ground wind environments for Shuttle liftoff studies (1983)
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    Publikationsdatum: 2011-08-18
    Beschreibung: Ground-wind environments for Monte Carlo simulations of Space Shuttle liftoff at KSC are developed. Input parameters include randomly selected 18.3-m-altitude peak wind speed (from which mean wind profile and turbulence intensity are calculated), randomly selected mean wind direction, and longitudinal and lateral turbulence components obtained from the Shuttle-simulation turbulence tapes (SSTT: Tatom et al., 1982). The steps in the simulation of turbulence time histories and horizontal wind fields are listed. It is found that separate statistical analysis of each hour-season pair, applying data on the time fraction of occurrence of peak winds and wind directions at KSC, will be necessary to interpret simulation results consistently.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Spacecraft and Rockets (ISSN 0022-4560); 20; July-Aug
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    The evolution of Tollmien-Schlichting waves near a leading edge (1983)
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    Publikationsdatum: 2011-08-18
    Beschreibung: The method of matched asymptotic expansions is used to study the generation of Tollmien-Schlichting waves by free-stream disturbances incident on a flat-plate boundary layer. Near the leading edge, the motion is governed by the unsteady boundary-layer equation, while farther downstream it is governed (to lowest order) by the Orr-Sommerfeld equation with slowly varying coefficients. It is shown that there is an overlap domain where the Tollmien-Schlichting wave solutions to the Orr-Sommerfeld equation and appropriate asymptotic solutions of the unsteady boundary-layer equation match, in the matched-asymptotic-expansion sense. The analysis explains how long-wavelength free-stream disturbances can generate Tollmien-Schlichting waves of much shorter wavelength. It also leads to a set of scaling laws for the asymptotic structure of the unsteady boundary layer.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Fluid Mechanics; 127; Feb. 198
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    Systems and operations - Living with complexity and growth (1983)
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    Publikationsdatum: 2011-08-18
    Beschreibung: Since the space station concept currently being developed by NASA calls for system updates and additions over a period of at least ten years following launch, attention must be given to the interfaces between station elements. Efforts have begun to develop generic fault detection, isolation, and correction techniques that could simplify on-orbit operations, maintenance and repair. An integrated hydrogen-oxygen system has been identified as the feature promising the greatest reduction in resupply costs. Scavenging excess fuel from the Space Shuttle's internal and external tanks, and using leftover Shuttle payload for fluid tankage, could supply hydrogen and oxygen for consumption in the form of propellants, fuel cell electricity, and life support gases. Advancements in cryogenic fluid management and storage technology are the keys to the design of this integrated system. Attention is given to the Interactive Design and Evaluation of Advanced Spacecraft computer-aided design and analysis system, which allows system engineers to study the integration problems presented by 40 technical modules.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Astronautics and Aeronautics; 21; Mar. 198
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  • 87
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    Sparger system for MMH-helium vents (1983)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Based on a calculated vent flow rate and MMH concentration, a TI-59 program was run to determine total sparger hole area for a given sparger inlet pressure. Hole diameter is determined from a mass transfer analysis in the holding tank to achieve complete capture of MMH. In addition, based on oxidation kinetics and vapor pressure data, MMh atmospheric concentrations are determined 2 ft above the holding tank.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: The 1983 NASA(ASEE Summer Faculty Fellowship Research Program Research Reports; 17 p
    Format: application/pdf
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  • 88
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    An analysis of cryotrap heat exchanger performance test data (400 area) and recommendations for a system to handle Apollo RCS engines (1983)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The current arrangement of a Platecoil heat exchanger which uses LN2 on the inside of parallel tubes, in counter flow to the test cell engine exhaust gases which are drawn through a box surrounding the plates by the existing vacuum blowers is examined. As a result of inadequate performance and special test data it was decided to redesign the system to accommodate an Apollo RCS engine.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: The 1983 NASA(ASEE Summer Faculty Fellowship Research Program Research Reports; 15 p
    Format: application/pdf
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  • 89
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    Jet array impingement heat transfer characteristics (1983)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Two dimensional arrays of circular air jets impinging on a heat transfer surface parallel to the jet orifice plate are considered. The jet flow, after impingement, is constrained to exit in a single direction along the channel formed by the jet orifice plate and the heat transfer surface. In addition to the crossflow which originates from the jets following impingement, an initial crossflow is present which approaches the array through an upstream extension of the channel. The configurations considered are intended to model the impingement cooled midchord region of gas turbine airfoils in cases where an initial crossflow is also present. A major objective is determination of the effect of initial crossflow air temperature relative to jet array air temperature on impingement surface heat fluxes.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 117-128
    Format: application/pdf
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  • 90
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    Coolant passage heat transfer with rotation. A progress report on the computational aspects (1983)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Turbine airfoils are subjected to increasingly higher heat loads which escalate the cooling requirements in order to satisfy life goals for the component materials. If turbine efficiency is to be maintained, however, cooling requirements should be as low as possible. To keep the quantity of cooling air bounded, a more efficient internal cooling scheme must be developed. One approach is to employ airfoils with multipass cooling passages that contain devices to augment internal heat transfer while limiting pressure drop. Design experience with multipass cooling passage airfoils has shown that a surplus of cooling air must be provided as a margin of safety. This increased cooling air leads to a performance penalty. Reliable methods for predicting the internal thermal and aerodynamic performance of multipass cooling passage airfoils would reduce or eliminate the need for the safety margin of surplus cooling air. The objective of the program is to develop and verify improved analytical methods that will form the basis for design technology which will result in efficient turbine components with improved durability without sacrificing performance. The objective will be met by: (1) establishing a comprehensive experimental data base that can form the basis of an empirical design system; (2) developing computational fluid dynamic techniques; and (3) analyzing the information in the data base with both phenomenological modeling and mathematical modeling to derive a suitable design and analysis procedure.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 111-116
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  • 91
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    A Feasibility Study of Electromagnetic De-Spin System for Earth Orbiting Satellites (1983)
    In:  CASI
    Details
    Publikationsdatum: 2014-09-11
    Beschreibung: This investigation is a feasibility study of electromagnetic satellite de-spin systems based on induced eddy-currents in the satellite by an external dc magnetic field. Two concepts have been investigated: (1) one based on a large diameter coil positioned around the satellite such that the axis of the satellite rotation is in the plane of the coil; and (2) a magnet, either permanent or electromagnet, positioned close to the satellite by the orbiter RMS. A comparison is made of the two concepts by varying the appropriate parameters with a view to reduce the de-spin time to a reasonable value. Design parameters for the magnets and the coil are indicated.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: Alabama Univ. Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 33 p
    Format: text
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  • 92
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    A Study of Accretion in Compact Sources: Disk Precession and Jet Helicity (1983)
    In:  CASI
    Details
    Publikationsdatum: 2014-09-11
    Beschreibung: The effect of adiabatic expansion on the propagation and growth of helical twisting on a supersonic jet is investigated. Cooling of the jet material increases the jet's Mach number and increases the jet's density relative to that of the external medium. This has the effect of decreasing the maximum rate of growth and increasing the maximally unstable wavelength relative to the jet's radius. Propagation effects cause the wavelength of helical waves to change at a rate different from that of the maximally unstable wavelength with the result that the characteristic wavelength of helical twisting is not equal to this wavelength. The most rapidly growing helical wave will have a wavelength as much as a factor of 2 different from the instantaneous maximally unstable wavelength.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 39 p
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  • 93
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    A Numerical Investigation of the Multiple Vortex Phenomenon: Vortex Number and Structure as a Function of Swirl Ratio (1983)
    In:  CASI
    Details
    Publikationsdatum: 2014-09-12
    Beschreibung: A numerical investigation of the multiple vortex phenomenon (MVP) for tornado like flows is conducted to determine the conditions for when a vortex becomes unstable and divides into smaller subsidiary vortices, as well as to determine the structure of these vortices. A three dimensional numerical model developed by Rotunno (1983) is utilized which has been demonstrated to successfully simulate MVP with properties observed both in natural as well as laboratory tornado like vortices. The MVP is generated for several swirl ratio conditions in order to determine the number of vortices generated for those flow configurations. These results are then compared to experimental measurements to validate the numerical model. The number of vortices produced is consistent with observational results made in the Purdue tornado vortex chamber. Furthermore, horizontal and vertical cross sections are taken through the vortices to determine the structure of MVP. Preliminary results indicate that tangential velocities within these smaller asymmetric vortices increase by 20% over values observed in a single axisymmetric vortex at the same swirl ratio.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Alabama Univ. Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 28 p
    Format: text
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  • 94
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    A comparative study of time-marching and space-marching numerical methods (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Menees (1981) has conducted an evaluation of three different flowfield codes for the Jupiter entry conditions. However, a comparison of the codes has been made difficult by the fact that the three codes use different solution procedures, different computational mesh sizes, and a different convergence criterion. There are also other differences. For an objective evaluation of the different numerical solution methods employed by the codes, it would be desirable to select a simple no-blowing perfect-gas flowfield case for which the turbulent models are well established. The present investigation is concerned with the results of such a study. It is found that the choice of the numerical method is rather problem dependent. The time-marching and the space-marching method provide both comparable results if care is taken in selecting the appropriate mesh size near the body surface.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA Journal; 21; Jan. 198
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  • 95
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    On the structure of wall-bounded turbulent flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The variable-interval time-averaging (VITA) technique developed by Blackwelder and Kaplan is applied to data obtained from large-eddy simulation of turbulent channel flow in an investigation of the organized structures associated with the bursting phenomenon in the near-wall region. Conditionally averaged velocities, shear stress, pressure, and vorticity are discussed in conjunction with the bursting phenomenon detected by the VITA technique. The conditionally averaged pressure reveals that the ejection process is associated with a localized adverse pressure gradient. In the plane perpendicular to the flow direction, the conditionally averaged vorticity field indicates that a pair of counterrotating streamwise vorticity is being lifted through the ejection process. Previously announced in STAR as N83-17832.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Physics of Fluids (ISSN 0031-9171); 26; Aug. 198
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  • 96
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    Coherent structures - Reality and myth (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Large-scale coherent structures (CS) in turbulent shear flows are characterized, reviewing recent theoretical and experimental investigations. The use of computers as a research tool and the flow-visualization experimental technique are introduced, CS are defined, the history of their discovery is traced, and their main characteristics are listed. Topics discussed and illustrated include the initial condition of the free shear layer, triple and double decomposition, topological features of CS, detection and eduction of CS, phase alignment via cross correlation, induced versus natural structures, the bursting phenomenon, turbulent spot, streaks, bursting frequency, the axisymmetric mixing layer, vortex pairing in an axisymmetric jet, CS and jet noise, broadband noise amplification via pure-tone excitation, CS interaction in a plane-jet near field, the Taylor hypothesis applied to CS, negative production, and the validity of the Reynolds-number similarity hypothesis. It is found that the coherent Reynolds stress, vorticity, and production are not much greater than the time-averaged values for fully developed flows with significant incoherent turbulence, suggesting that the importance of CS may have been exaggerated in some recent studies.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Physics of Fluids (ISSN 0031-9171); 26; 2816-285
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  • 97
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    Stagnation-point ablation of carbonaceous flat disks. I Theory (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: The process of ablation is calculated for the stagnation region of a flat disk in a radiation-dominated, massive-blowing environment produced in a ballistic range filled with argon. Flow environments are determined by solving the boundary-layer equations while radiative transfer is calculated through a line-by-line spectral computation. The resulting wall heat-transfer rates are coupled with an existing material's response code to determine surface recession and char thickness. The calculation is performed for six 5-cm-diam models made of carbon-phenolic and carbon-carbon composite launched in the Track-G facility at the Arnold Engineering Development Center. Significant surface recessions are predicted to occur for these models due mostly to radiative heating.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA Journal (ISSN 0001-1452); 21; 1588-159
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  • 98
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    A spectral numerical method for the Navier-Stokes equations with applications to Taylor-Couette flow (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A new spectral method for solving the incompressible Navier-Stokes equations in a plane channel and between concentric cylinders is presented. The method uses spectral expansions which inherently satisfy the boundary conditions and the continuity equation and yield banded matrices which are efficiently solved at each time step. In addition, the number of dependent variables is reduced, resulting in a reduction in computer memory requirements. Several test problems have been computed for the channel flow and for flow between concentric cylinders, including Taylor-Couette flow with axisymmetric Taylor vortices and wavy vortices. In all cases, agreement with available experimental and theoretical results is very good.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Journal of Computational Physics (ISSN 0021-9991); 52; 524-544
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  • 99
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    Numerical computation of transonic flow governed by the full-potential equation (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: Basic concepts associated with the numerical solution of elliptic partial differential equations are introduced, and procedures used to solve the full potential equation for transonic flow fields are discussed. Governing equations, classical relaxation schemes and concepts regarding transonic, full potential equation algorithms are covered. The equation transformation and grid generation procedures; full potential spatial differencing schemes; full potential iteration schemes, emphasizing convergence acceleration; and three dimensional applications are presented.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Von Karman Inst. for Fluid Dynamics Computational Fluid Dyn., Vol. 2; 110 p
    Format: text
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    A modified Dodge algorithm for the parabolized Navier-Stokes equations and compressible duct flows (1983)
    In:  Other Sources
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    Publikationsdatum: 2011-08-18
    Beschreibung: A revised version of Dodge's split-velocity method for numerical calculation of compressible duct flow has been developed. The revision incorporates balancing of massflow rates on each marching step in order to maintain front-to-back continuity during the calculation. Qualitative agreement with analytical predictions and experimental results has been obtained for some flows with well-known solutions.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
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