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  • Other Sources  (429)
  • ENERGY PRODUCTION AND CONVERSION  (243)
  • LAUNCH VEHICLES AND SPACE VEHICLES  (186)
  • Cell & Developmental Biology
  • General Chemistry
  • 1980-1984  (429)
  • 1945-1949
  • 1915-1919
  • 1983  (429)
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  • 1980-1984  (429)
  • 1945-1949
  • 1915-1919
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  • 1
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    Space flight experience with the Shuttle Orbiter control system (1983)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2009-11-16
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 2; p 941-947
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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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 2; p 923-940
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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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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).
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: An overview of INTELSAT VI is presented.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: A control moment gyro, an integrated power/attitude control system, and distributed adaptive control are discussed.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: Future space systems, flexible spacecraft, modular control, design-test-revise cycle, and control technique verification are discussed.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: Large space structures, system identification, model formulation, experimental design, model order and structure determination, parameter estimation, reduced order modeling, and closed loops are considered.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: Modeling accuracy, system identification, control law design methodology, sensors and actuators, and avionics are addressed.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: The NASA large space antenna missions, the performance requirements, and the resulting control technology requirements are summarized.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: Deployable space antenna concepts are surveyed. Precision reflector antennas, stiffened membrane antennas, truss antennas, infrared antennas, and electrostatically figured membrane reflectors are described.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 285-300
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    NASA/USAF research in structural dynamics (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 301-344
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    Structures for large precision reflectors (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 361-380
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    Advances in structural concepts (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 241-256
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    A summary of mission and system performance requirements for large space antennas (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 201-212
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    Spacecraft materials research: A NASA perspective (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 175-200
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    Systems design and comparative analysis of large antenna concepts (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 157-174
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    A 15-meter deployable aperture microwave radiometer (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 131-156
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    Earth observation system: Spacecraft design (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 105-130
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    Antenna technology for orbital Very Long Baseline Interferometry (VLBI) (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 81-104
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    Large deployable reflector: An infrared and submillimeter orbiting observatory (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 53-60
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    Satellite systems requirements for land mobile communications (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 29-46
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    Large spaceborne antenna technology: A system perspective (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 1-16
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    Land mobile satellite system requirements (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 17-28
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    Thermal analysis considerations for large space structures (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Modeling Analysis, and Optimization Issues for Large Space Struct.; p 123-147
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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
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 99-112
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    Structural modelling and control design under incomplete parameter information: The maximum-entropy approach (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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).
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 73-96
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    Analysis and testing of large space structures (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 113-122
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    Control of large space structures: Status report on achievements and current problems (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 55-72
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    Optimal large-angle maneuvers with vibration suppression (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 177-215
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    Algorithm development for the control design of flexible structures (1983)
    In:  CASI
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: 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
    Details
    Publication Date: 2006-04-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Modeling Analysis, and Optimization Issues for Large Space Struct.; p 33-54
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    Sheet silicon cell/module technology (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The cost involved in the performance of the standard operations for the manufacture of silicon wafers is insignificant in the case of space photovoltaics applications. It is, however, a decisive factor with respect to terrestrial applications of silicon photovoltaic devices. In 1975, a program was, therefore, begun to develop low cost silicon solar arrays for terrestrial applications. The goal was silicon-based photovoltaic (PV) modules ready for installation at a selling price of $0.50/watt (1975 dollars). Sheet and ribbon silicon growth held out the promise of reduced cost through continuous operation, high material throughput, high material utilization efficiency, and a product whose shape lent itself to the assembly of high packing density modules. Attention is given to ribbon growth technologies, sheet technology generic problems, and ribbon cell and module technology status. It is concluded that the potential for crystalline ribbon silicon appears to be better today than ever before.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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    Investigation of energy management strategies for photovoltaic systems - A predictive control algorithm (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The present investigation is concerned with the formulation of energy management strategies for stand-alone photovoltaic (PV) systems, taking into account a basic control algorithm for a possible predictive, (and adaptive) controller. The control system controls the flow of energy in the system according to the amount of energy available, and predicts the appropriate control set-points based on the energy (insolation) available by using an appropriate system model. Aspects of adaptation to the conditions of the system are also considered. Attention is given to a statistical analysis technique, the analysis inputs, the analysis procedure, and details regarding the basic control algorithm.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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    Discharge characteristics of a simulated solar cell array (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Measurements of the transient characteristics associated with the discharge of a simulated solar array are presented. A capacitively coupled probe is used to measure the discharge current, and antennas are used to measure the electromagnetic radiation. Discharges were observed at low surface voltages and several modes of discharge were observed. The maximum discharge current is found to be 0.2 A. This value is several orders of magnitude higher than that reported by previous measurements. Experimental evidence suggests that the inverted voltage gradient is a very likely triggering mechanism for solar array discharges.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: IEEE Transactions on Nuclear Science (ISSN 0018-9499); NS-30; 4311-431
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    Direct launch using the electric rail gun (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: APL The 1983 JANNAF Propulsion Meeting, Vol. 1; p 51-56
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    The 1986 launch of the Galileo spacecraft via the Space Transportation System (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: The Telecommun. and Data Acquisition Rept.; p 186-199
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    An overview of the Goldstone Energy Systems study (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A systems planning methodology was developed for analyzing and synthesizing Deep Space Network (DSN) energy systems. The resultant product, the Deep Space Network Planning and Analysis Methodology supports DSN energy planning evaluations. It addresses a broad spectrum of tradeoff and dispatching scenarios. It evaluates a variety of energy generation configurations and also includes a capability to evaluate conservation measures.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: The Telecommun. and Data Acquisition Rept.; p 135-141
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    Efficient computerized model for dynamic analysis of energy conversion systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: In searching for the optimum parameters that minimize the total life cycle cost of an energy conversion system, various combinations of components are examined and the resulting system performance and associated economics are studied. The systems performance and economics simulation computer program (SPECS) was developed to fill this need. The program simulates the fluid flow, thermal, and electrical characteristics of a system of components on a quasi-steady state basis for a variety of energy conversion systems. A unique approach is used in which the set of characteristic equations is solved by the Newton-Raphson technique. This approach eliminates the tedious iterative loops which are found in comparable programs such as TRNSYS or SOLTES-1. Several efficient features were also incorporated such as the centralized control and energy management scheme, and analogous treatment of energy flow in electrical and mechanical components, and the modeling of components of similar fundamental characteristics using generic subroutines. Initial tests indicate that this model can be used effectively with a relatively small number of time steps and low computer cost.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: The Telecommun. and Data Acquisition Rept.; p 161-176
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  • 68
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    Performance simulation of the JPL solar-powered distiller. Part 1: Quasi-steady-state conditions (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A 37.85 cu m (10,000 gallons) per year (nominal) passive solar powered water distillation system was installed and is operational in the Venus Deep Space Station. The system replaced an old, electrically powered water distiller. The distilled water produced with its high electrical resistivity is used to cool the sensitive microwave equipment. A detailed thermal model was developed to simulate the performance of the distiller and study its sensitivity under varying environment and load conditions. The quasi-steady state portion of the model is presented together with the formulas for heat and mass transfer coefficients used. Initial results indicated that a daily water evaporation efficiency of 30% can be achieved. A comparison made between a full day performance simulation and the actual field measurements gave good agreement between theory and experiment, which verified the model.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: The Telecommun. and Data Acquisition Rept.; p 142-160
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  • 69
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    Single cell performance studies on the FE/CR Redox Energy Storage System using mixed reactant solutions at elevated temperature (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Experimental studies in a 14.5 sq cm single cell system using mixed reactant solutions at 65 C are described. Systems were tested under isothermal conditions, i.e., reactants and the cell were at the same temperature. Charging and discharging performance were evaluated by measuring watt-hour and coulombic efficiencies, voltage-current relationships, hydrogen evolution and membrane resistivity. Watt-hour efficiencies ranged from 86 percent at 43 ma/sq cm to 75 percent at 129 ma/sq cm with corresponding coulombic efficiencies of 92 percent and 97 percent, respectively. Hydrogen evolution was less than 1 percent of the charge coulumbic capacity during charge-discharge cycling. Bismuth amd bismuth-lead catalyzed chromium electrodes maintained reversible performance and low hydrogen evolution under normal and adverse cycling conditions. Reblending of the anode and cathode solutions was successfully demonstrated to compensate for osmotic volume changes. Improved performance was obtained with mixed reactant systems in comparison to the unmixed reactant systems. Previously announced in STAR as N83-25042
    Keywords: ENERGY PRODUCTION AND CONVERSION
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    The DOE photovoltaics program (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The considered program of the U.S. Department of Energy (DOE) has the objective to provide federal support for research and development work related to photovoltaics. According to definitions of policy in 1981, a strong emphasis is to be placed on long-term, high-risk research and development that industry could not reasonably be expected to perform using their own funds. Attention is given to the program structure, the photovoltaics program management organization, the advanced research and development subprogram, the collector research and development subprogram, flat-plate collectors, concentrator collectors, and the systems research and technology subprogram.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 71
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    Silicon material technology status (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Silicon has been the basic element for the electronic and photovoltaic industries. The use of silicon as the primary element for terrestrial photovoltaic solar arrays is projected to continue. The reasons for this projection are related to the maturity of silicon technology, the ready availability of extremely pure silicon, the performance of silicon solar cells, and the considerable present investment in technology and manufacturing facilities. The technologies for producing semiconductor grade silicon and, to a lesser extent, refined metallurgical grade silicon are considered. It is pointed out that nearly all of the semiconductor grade silicon is produced by processes based on the Siemens deposition reactor, a technology developed 26 years ago. The state-of-the-art for producing silicon by this process is discussed. It is expected that efforts to reduce polysilicon process costs will continue.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 72
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    Systems approach to walk-off problems for dish-type solar thermal power systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 'Walk-off' in a dish-type solar thermal power system is a failure situation in which the concentrator remains fixed while the spot of concentrated sunlight slowly moves across the face of the receiver. The intense local heating may damage the receiver and nearby equipment. Passive protection has advantages in minimizing damage, but in a fully passive design the receiver must be able to withstand full solar input with no forced fluid circulation during the walk-off. An active walk-off emergency subsystem may include an emergency detrack or defocus mechanism or sun-blocking device, emergency power, sensors and logic to detect the emergency and initiate protective action, and cooling or passive protection of emergency and non-emergency components. Each of these elements is discussed and evaluated in the paper.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 73
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    Exospheric cleaning of the Earth Radiation Budget solar radiometer during solar maximum (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
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  • 74
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    Plasma-enhanced CVD silicon nitride antireflection coatings for solar cells (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Multilayer plasma-enhanced chemical vapor deposition (PECVD) silicon nitride antireflection coatings were deposited on space quality silicon solar cells. Preliminary experiments indicated that multilayer coatings decreased the total reflectance of polished silicon from 35 percent to less than 3 percent over the spectral range 0.4-1.0 micron. The solar cell energy conversion efficiency was increased from an average of 8.84 percent to an average of 12.63 percent.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Solar Energy (ISSN 0038-092X); 31; 4, 19; 1983
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  • 75
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    Whirl flutter analysis of a horizontal-axis wind turbine with a two-bladed teetering rotor (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Whirl flutter and the effect of pitch-flap coupling on teetering motion of a wind turbine were investigated. The equations of motion are derived for an idealized five-degree-of-freedom mathematical model of a horizontal-axis wind turbine with a two-bladed teetering rotor. The model accounts for the out-of-plane bending motion of each blade, the teetering motion of the rotor, and both the pitching and yawing motions of the rotor support. Results show that the design is free from whirl flutter. Selected results are presented indicating the effect of variations in rotor support damping, rotor support stiffness, and pitch-flap coupling on pitching, yawing, teetering, and blade bending motions. Previously announced in STAR as N82-23707
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Solar Energy (ISSN 0038-092X); 31; 2, 19; 1983
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  • 76
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    Thermal behavior of laboratory models of honeycomb-covered solar ponds (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Laboratory experiments were conducted to provide insight into the technical feasibility of honeycomb-covered solar ponds. Cooling tests using honeycomb panels of various materials and geometries showed that a 5.7-cm-thick one-tier panel insulated as effectively as a 10-cm fiberglass slab. Heating tests demonstrated that a model pond covered with a polycarbonate panel boiled upon 16 hours of continuous exposure to a 150-W spotlight. Analysis of the experimental data indicates positively that honeycomb-covered solar ponds can be expected to perform satisfactorily, and that larger-scale outdoor tests should be conducted to provide a more realistic assessment and a more refined performance estimate.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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    The IRAS project organisation and mission operations (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: vol. 36; Jan. 198
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  • 78
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    Expected cycle life vs. depth of discharge relationships of well-behaved single cells and cell strings (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The present investigation is concerned with the factors which might influence the cycle life vs. depth of discharge relationship, taking into account the rate of loss of cell capacity, the amount of excess capacity built into the cells, and the penalty in capacity loss resulting from the use of deep depths of discharge. 'First principles' are used to develop a cell life model for somewhat arbitrary conditions. This model is then used to estimate the cycle life vs. depth of discharge relationships for 'well behaved' cells. The stochastic variations associated with groupings of single cells are then introduced to the battery pack cycle life model. The term 'well behaved' cell is used to describe a single cell which does not suffer any abrupt failure mode during the course of its operation. It gradually loses capacity for any number of the usual reasons at a rate which is the product of the fractional depth of discharge and a factor which is characteristic of the cell under consideration.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Electrochemical Society, Journal (ISSN 0013-4651); 130; May 1983
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  • 79
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    Systems and operations - Living with complexity and growth (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 80
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    Solar concentrator degradation in Low Earth Orbit (LEO) (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of parabolically or spherically-shaped mirrors is being considered in order to increase the solar energy intensity on solar cells. Their use will significantly decrease the size and number of the cells needed for a particular application, hence the total array cost. Questions arise, however, regarding the long-term (five to ten years) efficiency of these devices. Performance degradation of the mirror surfaces might result from known hostile elements in the low earth orbit (LEO) environment (150-350 nautical miles). The degradation issue is addressed in light of present knowledge of this environment. The following characteristics of the LEO environment are identified for study: (1) the vacuum of space; (2) sputtering by the residual atoms and particles in space; (3) solar electromagnetic radiation; (4) contamination of the mirror surface; (5) atomic oxygen interactions with the surface; (6) bombardment of the surface by meteoroids; and (7) irradiation of the surface by ionizing particles (protons). Using the best available information for the magnitudes of the necessary quantities, a mathematical analysis was carried out, where possible, to determine the degradation in reflectance or other loss caused by each characteristic. Otherwise, reasonable estimates are made of corresponding losses, based on already published data.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Johnson (Lyndon B.) Space Center The 1983 NASA/ASEE Summer Faculty Fellowship Research Program Research Reports; NASA. Johnson (Lynd
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  • 81
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    Laser assisted deposition (1983)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Applications of laser-based processing techniques to solar cell metallization are discussed. Laser-assisted thermal or photolytic maskless deposition from organometallic vapors or solutions may provide a viable alternative to photovoltaic metallization systems currently in use. High power, defocused excimer lasers may be used in conjunction with masks as an alternative to direct laser writing to provide higher throughput. Repeated pulsing with excimer lasers may eliminate the need for secondary plating techniques for metal film buildup. A comparison between the thermal and photochemical deposition processes is made.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: JPL Proc. of the Flat-Plate Solar Array Res. Forum on Photovoltaic Metallization Systems; p 317-332
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  • 82
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    Metallization with generic metallo-organic inks (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use and fabrication of metallo-organic films are discussed. Metallo-organic compounds are ones in which a metal is linked to a long chain carbon ligand through a hetero atom such as O, S, N, P or As. Films formed by the thermal decomposition of these metallo-organics are called MOD films. In order that the products of decomposition contain only CO2, H2O, and in rare cases nitrogen compounds, and to avoid S containing products, the use of a set of metallo-organic compounds for ink fabrication where the linking hetero atom was oxygen was pioneered. These links were made from commercially available carboxylates, or synthesized from commonly available reagents. The processing is described and the molecular design criteria are given. The particular carboxylates or amine carboxylates selected were the octoates or neodecanoates, and they are described.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: JPL Proc. of the Flat-Plate Solar Array Res. Forum on Photovoltaic Metallization Systems; p 277-300
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  • 83
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    Solar cell metallization: Historical perspective (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Solar cell metallization design requirements are discussed. Space applications and terrestrial applications are considered. Cost factors are discussed in relation to design analysis.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: JPL Proc. of the Flat-Plate Solar Array Res. Forum on Photovoltaic Metallization Systems; p 9-18
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  • 84
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    Economic implications of current systems (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The primary goals of this study are to estimate the value of R&D to photovoltaic (PV) metallization systems cost, and to provide a method for selecting an optimal metallization method for any given PV system. The value-added cost and relative electrical performance of 25 state-of-the-art (SOA) and advanced metallization system techniques are compared.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Proc. of the Flat-Plate Solar Array Res. Forum on Photovoltaic Metallization Systems; p 19-33
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  • 85
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    A Feasibility Study of Electromagnetic De-Spin System for Earth Orbiting Satellites (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-11
    Description: 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.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Alabama Univ. Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 33 p
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  • 86
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    Photovoltaic power - An important new energy option (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A review of photovoltaic (PV) power technology is presented with an emphasis of PV as an economical and technically feasible alternative source of energy. The successful completion of the development and transfer of emerging low-cost technologies into a fully commercialized status are identified as the means to the realization of this option's full potential. The DOE National Photovoltaics Program, a significant sponsor of PV R&D, expects both flat-plate and concentrator collectors to meet established cost targets. Citing the DOE large flat-plate grid-connected system project of the Sacramento Municipal Utility District, current technology modules priced at near $5/Wp (1983 dollars) are steadily reducing costs. A recent DOE study suggests that PV-generated electricity produced at a 30-year levelized cost of 15 cents per kWh would represent a viable energy supply alternative for the nation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Mechanical Engineering (ISSN 0025-6501); 105; 16-23
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  • 87
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    TOPEX watershed coming in oceanography (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The NASA Ocean Topography Experiment (TOPEX) will use precision radar altimetry to determine topographic features of the global oceans from which currents may be deduced. TOPEX will coincide with the World Ocean Circulation Experiment (WOCE), which will be conducted at the end of this decade and shall involve ships, fixed and drifting buoys, aircraft observations, and satellite remote sensing, to resolve fundamental questions about the flow of water in the global ocean. TOPEX will contribute to WOCE the measurement of satellite height above the sea surface, and the precise radial position above a reference ellipsoid for the earth. The combination of these two measurements with the marine geoid yields the topographic data sought. Three years of topographic data, together with conventional oceanographic data and theoretical ocean models, will be needed to derive the mean and variable components of ocean circulation.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; 60-62
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  • 88
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    Harnessing surface plasmons for solar energy conversion (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: NASA research on the feasibility of solar-energy conversion using surface plasmons is reviewed, with a focus on inelastic-tunnel-diode techniques for power extraction. The need for more efficient solar converters for planned space missions is indicated, and it is shown that a device with 50-percent efficiency could cost up to 40 times as much per sq cm as current Si cells and still be competitive. The parallel-processing approach using broadband carriers and tunable diodes is explained, and the physics of surface plasmons on metal surfaces is outlined. Technical problems being addressed include phase-matching sunlight to surface plasmons, minimizing ohmic losses and reradiation in energy transport, coupling into the tunnels by mode conversion, and gaining an understanding of the tunnel-diode energy-conversion process. Diagrams illustrating the design concepts are provided.
    Keywords: ENERGY PRODUCTION AND CONVERSION
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    Thermoelectric energy conversion with solid electrolytes (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The alkali metal thermoelectric converter (AMTEC) is a device for the direct conversion of heat to electrical energy. The sodium ion conductor beta-double prime-alumina is used to form a high-temperature regenerative concentration cell for elemental sodium. An AMTEC of mature design should have an efficiency of 20 to 40 percent, a power density of 0.5 kilowatt per kilogram or more, no moving parts, low maintenance requirements, high durability, and efficiency independent of size. It should be usable with high-temperature combustion, nuclear, or solar heat sources. Experiments have demonstrated the feasibility of the AMTEC and confirmed the theoretical analysis of the device. A wide range of applications from aerospace power to utility power plants appears possible.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Science (ISSN 0036-8075); 221; Sept. 2
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  • 90
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    Analysis of the interaction of an electron beam with back surface field solar cells (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: In this paper the short circuit current Isc induced by the electron beam of a scanning electron microscope in a back surface field solar cell will be determined theoretically. It will be shown that, in a configuration used previously for solar cells with an ohmic back surface, the Isc gives a convenient means for estimating the back surface recombination velocities and thus the quality of back surface field cells. Numerical data will be presented applicable to a point source model for the electron-hole pair generation.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Applied Physics (ISSN 0021-8979); 54; July 198
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  • 91
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    Dish concentrators for solar thermal energy (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 03, p. 397, Accession no. A82-14001
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: (ISSN 0146-0412)
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  • 92
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    Solar thermal technologies - Potential benefits to U.S. utilities and industry (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Solar energy systems were investigated which complement nuclear and coal technologies as a means of reducing the U.S. dependence on imported petroleum. Solar Thermal Energy Systems (STES) represents an important category of solar energy technologies. STES can be utilized in a broad range of applications servicing a variety of economic sectors, and they can be deployed in both near-term and long-term markets. The net present value of the energy cost savings attributable to electric utility and IPH applications of STES were estimated for a variety of future energy cost scenarios and levels of R&D success. This analysis indicated that the expected net benefits of developing an STES option are significantly greater than the expected costs of completing the required R&D. In addition, transportable fuels and chemical feedstocks represent a substantial future potential market for STES. Due to the basic nature of this R&D activity, however, it is currently impossible to estimate the value of STES in these markets. Despite this fact, private investment in STES R&D is not anticipated due to the high level of uncertainty characterizing the expected payoffs. Previously announced in STAR as N83-10547
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Energy (ISSN 0146-0412); 7; July-Aug
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  • 93
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    Correlation of solar cell electrical properties with material characteristics of silicon cast by the ubiquitous crystallization process (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Solar cells were fabricated using a conservative 'baseline' process on 1-3 Omega-cm p-type silicon from ingots cast by the ubiquitous crystallization process. Conversion efficiencies of the cells were measured, as well as spectral response and minority carrier diffusion length. Adjacent slices from the same ingot were studied for their grain size, dislocation distribution, and impurity distribution. Cell performance was related to the observed structural features, as well as to the chemical structure of the ingot.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Electrochemical Society, Journal (ISSN 0013-4651); 130; June 198
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  • 94
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    Space platforms (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The expanded scientific capabilities available by interfacing an orbital, free-flying experiments platform with Shuttle tending are outlined. The platform would be lifted to orbit by the Shuttle, and modularly increased in size on subsequent flights. Science packages could be left on the 26,000 lb space platform for up to six months. Component sections would include electrical and thermal control systems, berthing ports for payloads and an Orbiter, and an attitude control, communications, and data handling subsection. A 12 kW solar array would furnish power, and interconnect with Spacelab would further enhance the operations range. All berthed science packages would have individual pointing ability and grapples for the Orbiter RMS. Eventual evolution to include facilities for a human crew and a 25 kW solar array is projected.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: ; vol. 25
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  • 95
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    Configuration selection study for isolated loads (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 06, p. 900, Accession no. A82-18223)
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 96
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    Deployment of a spin parachute in the altitude region of 260,000 ft (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 01, p. 17, Accession no. A82-10418)
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
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  • 97
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    Optimization of dish solar collectors (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Methods for optimizing parabolic dish solar collectors and the consequent effects of various optical, thermal, mechanical, and cost variables are examined. The most important performance optimization is adjusting the receiver aperture to maximize collector efficiency. Other parameters that can be adjusted to optimize efficiency include focal length, and, if a heat engine is used, the receiver temperature. The efficiency maxima associated with focal length and receiver temperature are relatively broad; it may, accordingly, be desirable to design somewhat away from the maxima. Performance optimization is sensitive to the slope and specularity errors of the concentrator. Other optical and thermal variables affecting optimization are the reflectance and blocking factor of the concentrator, the absorptance and losses of the receiver, and, if a heat engine is used, the shape of the engine efficiency versus temperature curve. Performance may sometimes be improved by use of an additional optical element (a secondary concentrator) or a receiver window if the errors of the primary concentrator are large or the receiver temperature is high. Previously announced in STAR as N83-19224
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Energy (ISSN 0146-0412); 7; 684-694
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  • 98
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    Limits to solar power conversion efficiency with applications to quantum and thermal systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An analytical framework is presented that permits examination of the limit to the efficiency of various solar power conversion devices. Thermodynamic limits to solar power efficiency are determined for both quantum and thermal systems, and the results are applied to a variety of devices currently considered for use in space systems. The power conversion efficiency for single-threshold energy quantum systems receiving unconcentrated air mass zero solar radiation is limited to 31 percent. This limit applies to photovoltaic cells directly converting solar radiation, or indirectly, as in the case of a thermophotovoltaic system. Photoelectrochemical cells rely on an additional chemical reaction at the semiconductor-electrolyte interface, which introduces additional second-law demands and a reduction of the solar conversion efficiency. Photochemical systems exhibit even lower possible efficiencies because of their relatively narrow absorption bands. Solar-powered thermal engines in contact with an ambient reservoir at 300 K and operating at maximum power have a peak conversion efficiency of 64 percent, and this occurs for a thermal reservoir at a temperature of 2900 K. The power conversion efficiency of a solar-powered liquid metal magnetohydrodydnamic generator, a solar-powered steam turbine electric generator, and an alkali metal thermoelectric converter is discussed.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: Journal of Energy (ISSN 0146-0412); 7; 581-588
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  • 99
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    Pore size engineering applied to the design of separators for nickel-hydrogen cells and batteries (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Pore size engineering in starved alkaline multiplate cells involves adopting techniques to widen the volume tolerance of individual cells. Separators with appropriate pore size distributions and wettability characteristics (capillary pressure considerations) to have wider volume tolerances and an ability to resist dimensional changes in the electrodes were designed. The separators studied for potential use in nickel-hydrogen cells consist of polymeric membranes as well as inorganic microporous mats. In addition to standard measurements, the resistance and distribution of electrolyte as a function of total cell electrolyte content were determined. New composite separators consisting of fibers, particles and/or binders deposited on Zircar cloth were developed in order to engineer the proper capillary pressure characteristics in the separator. These asymmetric separators were prepared from a variety of fibers, particles and binders. Previously announced in STAR as N83-24571
    Keywords: ENERGY PRODUCTION AND CONVERSION
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  • 100
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    Test results of a ten cell bipolar nickel-hydrogen battery (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A ten cell bipolar nickel hydrogen 6.5 ampere-hour battery demonstrated over 2000 low earth orbit cycles at an 80 percent depth-of-discharge. Charge/discharge cyclic ampere-hour and watt-hour efficiencies of 88 and 76 percent, respectively, observed. Peak power capability was determined at 1.1 kW. A 10C discharge rate yields 83 percent of the nominal stark capacity to the 1.0 volt cut off in just under 6 minutes. Previously announced in STAR as N83-26253
    Keywords: ENERGY PRODUCTION AND CONVERSION
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