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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (1.933)
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  • 1
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    Stable direct adaptive control of linear infinite-dimensional systems using a command generator tracker approach (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The topics are presented in view graph form and include the following: an adaptive model following control; adaptive control of a distributed parameter system (DPS) with a finite-dimensional controller; a direct adaptive controller; a closed-loop adaptively controlled DPS; Lyapunov stability; the asymptotic stability of the closed loop; and model control of a simply supported beam.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 319-363
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  • 2
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    Rapid single-axis torque-bounded slewing of SCOLE configuration (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The first general research objective was to address control design challenges of the Spacecraft Control Laboratory Experiment (SCOLE) via the two stage approach: (1) slew the whole as if it were a rigid body about one Space Shuttle body axis each time using the onboard Reaction Control System (RCS) thrusters; and (2) damp out excited vibrations. The second objective was to examine the feasibility of applying the approach to shuttle-attached flexible space structures. The following was accomplished: (1) a standard bang-bang control technique was adapted; (2) a slew rate limit was imposed in the design; and (3) slew acceleration deviation was defined as the index of slew performance degradation.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 235-262
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  • 3
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    A modal model for SCOLE structural dynamics (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: Information on a modal model for the Spacecraft Control Laboratory (SCOLE) is given in viewgraph form. A partial differential equation model covering roll bending, pitch bending, torsion, shear forces, and bending moments is given.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 29-40
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  • 4
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    SCOLE dynamic analysis and frequency response using DISTEL software (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The distributed element dynamic analysis package DISTEL is used to analyze the NASA/Institute of Electrical and Electronics Engineers' Spacecraft Control Laboratory Experiment (SCOLE). In this configuration, the Space Shuttle motion is coupled to the motion of a large dish antenna through a Shuttle-deployed flexible mast of 40 m long. Due to the high asymmetry of the system, the motions about the different axes (roll, pitch, yaw) are severely coupled. A general purpose software like DISTEL is especially suited for this kind of analysis. Modal frequencies of the complete spacecraft and impulse response (modal gains) to excitations at different locations are obtained. Mode-shape plots of the deformations of the entire system are given. Finally, results obtained at NASA and at Purdue University are compared to those found by the European space technology center, ESTEC.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 41-86
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  • 5
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    A mathematical formulation for the control of the SCOLE configuration (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: A mathematical formulation for the control of the Spacecraft Control Laboratory Experiment (SCOLE) configuration is given. Two equivalent approaches, one using a functional equation and the other an abstract wave equation, are illustrated. Such a formulation can help in digital computer simulation to evaluate control laws, providing insight, and generating control laws.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 87-103
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  • 6
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    Equations of motion for control of the SCOLE laboratory experiment (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The objectives of this study are listed as follows: (1) to develop Lagrange's equations of motion for the shuttle antenna configuration in orbit; (2) to modify equations using the Lagrange multiplier method to develop equations of motion for the laboratory experiment; and (3) to discuss methods for simulation and control. The equations are presented in graph form.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 148-157
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  • 7
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    A mathematical problem and a Spacecraft Control Laboratory Experiment (SCOLE) used to evaluate control laws for flexible spacecraft. NASA/IEEE design challenge (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: Discussed here is a NASA program which was initiated to make direct comparisons of control laws for a mathematical problem. An experimental test item is being assembled under the cognizance of the Spacecraft Control Branch at Langley Research Center. The physical apparatus will consist of a softly supported dynamic model of an antenna attached to the Space Shuttle by a flexible beam. The control objective will include the task of directing the line of sight of the Shuttle/antenna configuration toward a fixed target, under conditions of noisy data, limited control authority, and random disturbances.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 1-27
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  • 8
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    Application of maximum entropy optimal projection design synthesis to the NASA Spacecraft Control Laboratory Experiment (SCOLE) (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The scope of this study covered steady-state, continuous-time vibration control under disturbances applied to the Space Shuttle and continuous-time models of actuators, sensors, and disturbances. Focus was on a clear illustration of the methodology, therefore sensor/actuator dynamics were initially ignored, and a finite element model of the NASA Spacecraft Control Laboratory Experiment (SCOLE) was conducted, including products of inertia and offset of reflector CM from the mast tip.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 364-392
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  • 9
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    Minimum time slew of the SCOLE configuration (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The motivation was to develop a control design and analysis methodology directly applicable to design concepts of flexible spacecraft of interest the the U.S. Navy and to provide a testbed for the evaluation of large space structure control techniques developed at the Naval Research Laboratory. The topics covered include the following: (1) a list of key concepts; (2) evaluation of the Spacecraft Control Laboratory Experiment (SCOLE) model with DISCOS; (3) baseline results, line of sight error vs. time; (4) general formulation of optimization; (5) geometric interpretation, projected eigenaxis; (6) closed loop control law; and (7) future directions.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 263-280
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  • 10
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    Modelling issues of the SCOLE control problem (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: Nonlinear and linear equations of motions were derived. The preliminary investigation consisted of model beam as truss structure, effects of truss structure on control design, and effects of reflector offset on control design. It was concluded that the offset of the reflector c.g. from the beam reflector attach point is dynamically significant. Also, truss effects may also significantly effect the performance of the controller if ignored. If the truss is included in the modeling of the NASA/SCOLE configuration, a practically implementable scheme is available to reduce the model order.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 133-147
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  • 11
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    Spacecraft Control Laboratory Experiment: Status report (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The Spacecraft Control Laboratory Experiment (SCOLE) will allow direct experimental comparison of competing control schemes for large flexible spacecraft structures. The experiment was designed to emulate the essential characteristics of a mathematical model design challenge which represents a Space Shuttle with a flexible mast and antenna attached. This experiment represents the third in a series of three flexible structure control experiments used by the Flight Dynamics and Control Division at LaRC. The key problem addressed by the facility is that flexible motion of the mast and antenna must be considered in the slewing and pointing control problems.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 393-404
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  • 12
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    Evaluation of on-line pulse control for vibration suppression in flexible spacecraft (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: The following topics are covered in view graph form: (1) pulse control strategy; (2) stability analysis and digital simulations; (3) digital/analog and analog/digital conversions, and analog simulation; and (4) experimental studies.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 281-318
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  • 13
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    Rapid torque-bounded line-of-sight pointing of SCOLE with a designer's choice of initial alignment (1984)
    In:  CASI
    Details
    Publikationsdatum: 2004-12-04
    Beschreibung: Researchers simplified the analytical expression of the line of sight (LOS) error, discovered and proved the independence of Euler angle Psi, calculated attitude angles corresponding to 0 degrees and 20 degrees LOS errors, determined choices of initial alignment, tailored the slew maneuvers for LOS pointing, simulated numerically the LOS pointing slew of the Spacecraft Control Laboratory Experiment (SCOLE), and evaluated the pointing performance.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 216-234
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  • 14
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    Systems/operations technology (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-03
    Beschreibung: The deliberations of the Systems/Operations Technology Panel are summarized. The first real question that arose was to develop an understanding of what systems/operations technology is. A relativelynew discipline in the NASA technology organization, necessitates the definition of the objectives. Two objectives were established: (1) to make new things possible, and (2) to make existing capabilities cost less or work better. Making new things possible is not really applicable in the case of a space station. Both Salyut 7 and Skylab indicate that space stations are possible with existing (not necessarily new) technology. There was a concern on the part of some of the penelists that work better might mean higher performance, and that is not necessarily the case at all. Work better may mean simply to provide better service to the users of the space station at lower cost. The panel felt this to be a more realistic viewpoint. As evidenced from interaction with users (and all of the contractors found this basically to be true), the users want low cost, no schedule constraints, and no hassles.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center Space Station Technol., 1983; p 1-24
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  • 15
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    Meteoroid damage to spacecraft (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The objective of this experiment is to obtain examples of meteoroid impact damage to typical spacecraft components, and by so doing to help establish design approaches to minimize meteoroid damage effects to future spacecraft. The results of the complete inspection of the LDEF will complement and extend the data obtained from specific meteoroid experiments flying in LDEF trays.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Long Duration Exposure Facility (LDEF); p 138
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  • 16
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    Measurements by the plasma diagnostics package on STS-3 (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A comprehensive set of measurements about the orbiter environment are provided by the plasma diagnostics package (PDP). Ion and electron particle densities, energies, and spatial distribution functions; ion mass for identification of particular molecular ion species; and magnetic fields, electric fields and electromagnetic waves over a broad frequency range are studied. Shuttle environmental measurements will be made both on the pallet and, by use of the remote manipulator system (RMS), the PDP will be maneuvered in and external to the bay area to continue environmental measurements and to carry on a joint plasma experiment with the Utah State University fast-pulsed electron generator. Results of orbiter environment EMI measurements and S-band field strengths as well as preliminary results from wake search operations indicating wake boundary identifiers are reported.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 8 p
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  • 17
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    Design and development of the ERBE data management system (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Earth radiation budget experiment (ERBE) software development approach is described. An iterative development approach was adopted which provides for three releases or versions of the processing system, each of increasing levels of complexity and solidity. The final release of the system will be used to process the flight data. The major phases for each iterative release consist of specifications developed in concert with the science team, preliminary design, subsystem reviews, coding, subsystem code walkthroughs, system testing, system documentation, and project status review.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 15 p
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  • 18
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    Outgassing: Its effects on spacecraft. Vibration damping materials (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The correlation of outgassing to the stability of the damping properties of polymer materials to be used in spacecraft structures is discussed. A test series was devised to obtain basic information from off-the-shelf damping materials. The test results could be considered as a guideline toward the application of these materials. Eight materials were selected to form a representative cross section of those polymers having both ready availability as commercial damping materials and desirable properties. A table indicates the temperatures at which peak damping occurs at 1 Hz and the type of beam specimen used in the vacuum exposure tests. These materials as a group cover the temperature range of -85 C to 38 C.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 25 p
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  • 19
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    Space shuttle (1975)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-10
    Beschreibung: The transportation cost associated with space materials processing were studied to determine the feasibility of space manufacturing. The assumptions use to determining the cost estimates for a 12 year planning period are listed, and the orbitor is described in terms of payloads. Shuttle operational costs, ground operational costs, and nonrecurring investment and development costs were analyzed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Econ. Analysis of Materials Processing in Space; p 8-39
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  • 20
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    Design development of the Apollo command and service module thrust vector attitude control systems (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-02
    Beschreibung: Development of the Apollo thrust vector control digital autopilot (TVC DAP) was summarized. This is the control system that provided pitch and yaw attitude control during velocity change maneuvers using the main rocket engine on the Apollo service module. A list of ten primary functional requirements for this control system are presented, each being subordinate to a more general requirement appearing earlier on the list. Development process functions were then identified and the essential information flow paths were explored. This provided some visibility into the particular NASA/contractor interface, as well as relationships between the many individual activities.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 63-82
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  • 21
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    IDEAS: A multidisciplinary computer-aided conceptual design system for spacecraft (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: During the conceptual development of advanced aerospace vehicles, many compromises must be considered to balance economy and performance of the total system. Subsystem tradeoffs may need to be made in order to satisfy system-sensitive attributes. Due to the increasingly complex nature of aerospace systems, these trade studies have become more difficult and time-consuming to complete and involve interactions of ever-larger numbers of subsystems, components, and performance parameters. The current advances of computer-aided synthesis, modeling and analysis techniques have greatly helped in the evaluation of competing design concepts. Langley Research Center's Space Systems Division is currently engaged in trade studies for a variety of systems which include advanced ground-launched space transportation systems, space-based orbital transfer vehicles, large space antenna concepts and space stations. The need for engineering analysis tools to aid in the rapid synthesis and evaluation of spacecraft has led to the development of the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) computer-aided design system. The ADEAS system has been used to perform trade studies of competing technologies and requirements in order to pinpoint possible beneficial areas for research and development. IDEAS is presented as a multidisciplinary tool for the analysis of advanced space systems. Capabilities range from model generation and structural and thermal analysis to subsystem synthesis and performance analysis.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 21 p
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  • 22
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    A facility for the simulation of low orbit atmospheric oxygen bombardment (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A molecular beam facility to simulate the space environment of a spacecraft at low orbit was designed with the intent of studying the effect on the properties of optical elements of oxygen atoms impacting at orbital velocity. The four-stage differentially pumped molecular beam facility includes a variety of oxygen atom beam sources which cover a wide range of velocities (1 km/sec to approximately 8 km/sec), in addition to the ultra-clean experimental environmental of an ultra-high vacuum chamber and an optical diagnostic set-up. The primary oxygen atom beam source used to obtain the 8 km/sec O atoms is an arc heated source. It consists of a modified commercially available plasma torch. The modifications include attachments which provide for a nozzle which is used to expand the atomic beam into the vacuum system, and exhaust channels to dispose of excess torch gas. The torch operates in the 'nontransferred' mode of operation, that is the electric arc is confined within the torch. A plasma is formed in helium by a dc arc. A small amount of O2 is injected downstream from the arc where it is thermally dissociated by the hot He into oxygen atoms. The high temperature and isentropic expansion give the oxygen atoms their velocity. Using seeded beam techniques, oxygen atom beams of approximately 3.5 and approximately 1.5 km/sec, respectively, are obtained.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 1 p
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  • 23
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    Space Shuttle preliminary. Contamination assessment from STS-1 and STS-2 (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A preliminary assessment of the space shuttle contamination environment was made using data from the first two orbital flight tests, STS-1 and STS-2. Data sources consisted of crew observations during flight, postflight vehicle inspection, and the induced environment contamination monitor which was used on STS-2 and consists of 10 instruments. These instruments are used to measure gas phase contaminants, particle population, humidity, and molecular deposition in the orbiter payload bay during ascent and descent and particle population, molecular deposition, and gas cloud during orbital flight. Results of the measurements described are presented in summary form and indicate low molecular deposition rates for both pressurized and orbital flight.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 21 p
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  • 24
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    Environmental test facilities used in Europe for ESA satellite programmes (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The structure of the European Space Agency (ESA) is described. The major test facilities used for ESA programs are described. Facility characteristics and special test methods are described.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 28 p
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  • 25
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    Education and training of personnel in space simulation (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: The training program and procedures developed and implemented at the space simulation laboratory at Martin Marietta Aerospace in Denver are discussed. The training of technicians and professionals as well as preparation for instructors is covered. Training manuals and their compilation are reported as applicable to the specific needs of the laboratory. The development of a space simulation course as part of the Martin Marietta Continuing Education Night School approaching space simulation from an academic viewpoint is presented. Finally, public relations tours of the facility as an informational/educational tool are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 5 p
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  • 26
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    Cryopump for large pulses of hydrogen (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A test involving a flow of hot hydrazine decomposition products at a rate of 13.6 g/s (0.03 lb/s) established the requirement to maintain pressure in an 11.9-m-(39 ft) diameter space chamber below 200 microns. The flow, 2/3 hydrogen and 1/3 nitrogen by volume, continued for several periods ranging from 3 to 15 min. The pressure requirement was necessary to minimize thermal effects of the gas on the test vehicle but was well beyond the capability of the existing facility pumps. Various methods of obtaining additional temporary jump capacity were considered. From these, the slugged-charcoal approach was selected as the quickest and least expensive method to implement.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 23 p
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  • 27
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    Spacecraft thermal balance testing using infrared sources (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A thermal balance test (controlled flux intensity) on a simple black dummy spacecraft using IR lamps was performed and evaluated, the latter being aimed specifically at thermal mathematical model (TMM) verification. For reference purposes the model was also subjected to a solar simulation test (SST). The results show that the temperature distributions measured during IR testing for two different model attitudes under steady state conditions are reproducible with a TMM. The TMM test data correlation is not as accurate for IRT as for SST. Using the standard deviation of the temperature difference distribution (analysis minus test) the SST data correlation is better by a factor of 1.8 to 2.5. The lower figure applies to the measured and the higher to the computer-generated IR flux intensity distribution. Techniques of lamp power control are presented. A continuing work program is described which is aimed at quantifying the differences between solar simulation and infrared techniques for a model representing the thermal radiating surfaces of a large communications spacecraft.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 26 p
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  • 28
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    Optical characterization of solar concentrator mirrors using the solar beam of the JPL 25-foot space simulator (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The Jet Propulsion Laboratory 25-foot space simulator with its 5.8-m (19-ft) diameter simulated solar beam provides an excellent facility for measuring the optical characteristics of parabolic solar concentrator panels and gores. The virtual source position and size were determined by using a single lamp of the 37 xenon 30-kW source array with only the center lens in the 19-channel optical mixer. This data was used to define the optical test geometry, and it allowed accurate measurement of focal length and surface deviations of the mirror under test. A flux distribution of a typical solar concentrator placed directly on the solar beam gives measurements of performance at the focal point of the parabolic surface.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center 12th Space Simulation Conf.; 19 p
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  • 29
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    Effects of antenna blockage on radio frequency performance of the microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Radio frequency scaled models of the microwave radiometer spacecraft suspended feed concept were tested to determine the effects of aperture blockage on the antenna radiation pattern. Contributors to the uncertainty of the test measurements were evaluated, and an estimate of the blockage effects was made for comparison with the test measurements. The gain loss budget associated with reflector performance characteristics (aperture blockage, surface reflectivity, reflector roughness, and defocus) was determined.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center The Microwave Radiometer Spacecraft; p 141-165
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  • 30
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    Systems design and analysis of the microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Systems design and analysis data were generated for microwave radiometer spacecraft concept using the Large Advanced Space Systems (LASS) computer aided design and analysis program. Parametric analyses were conducted for perturbations off the nominal-orbital-altitude/antenna-reflector-size and for control/propulsion system options. Optimized spacecraft mass, structural element design, and on-orbit loading data are presented. Propulsion and rigid-body control systems sensitivities to current and advanced technology are established. Spacecraft-induced and environmental effects on antenna performance (surface accuracy, defocus, and boresight off-set) are quantified and structured material frequencies and modal shapes are defined.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 69-94
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  • 31
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    Exceedance statistics of accelerations resulting from thruster firings on the Apollo-Soyuz mission (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Spacecraft acceleration resulting from firings of vernier control system thrusters is an important consideration in the design, planning, execution and post-flight analysis of laboratory experiments in space. In particular, scientists and technologists involved with the development of experiments to be performed in space in many instances required statistical information on the magnitude and rate of occurrence of spacecraft accelerations. Typically, these accelerations are stochastic in nature, so that it is useful to characterize these accelerations in statistical terms. Statistics of spacecraft accelerations are summarized.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 167-174
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  • 32
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    Contributions of orbital mechanics to conducting experiments in space (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Orbital mechanics as a discipline is principally concerned with solving the set of equations for analyzing the motion of a satellite under various conditions. This activity on the surface may not seem crucial to conducting experiments in space, but it provides insights into the way in which forces may influence these experiments. More directly, for experiments concerned with external targets, it provides predictions of the satellites's position and velcoity verus time, enabling extensive preflight planning and resulting in optimum use of on-orbit time.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 129-136
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  • 33
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    Spacecraft dynamic environments (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Zero-gravity conditions in Earth orbit cannot be obtained in the Shuttle Orbiter, however, through careful planning, the dynamic environment and its effects on experiments can be minimized. Futhermore, although the dynamic environment of the Shuttle Orbiter is to a large degree stochastics, it is possible to predict characteristics of this environments so that scientists and technologists can plan their experiments and mission managers can plan missions with a view toward minimizing the effects of spacecraft dynamics on experiments. Characteristics of the dynamic environment that might be predicted include typical and "worst case" values of vehicle acceleration for the anticipated acceleration sources, typical number of acceleration event, duration times of disctete acceleration events, bandwidth of acceleration time history, etc.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 115-120
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  • 34
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    Bootlace catenary concept for antenna shape control (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A preliminary design of the microwave radiometer spacecraft (MRS) using the bootlace catenary shaping concept was developed. The application of this radically different design for shape control of the antenna membrane was assessed and possible sources of inaccuracies and errors were investigated.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 205-213
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  • 35
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    Adaptive control system for large annular momentum control device (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A dual momentum vector control concept, consisting of two counterrotating rings (each designated as an annular momentum control device), was studied for pointing and slewing control of large spacecraft. In a disturbance free space environment, the concept provides for three axis pointing and slewing capabilities while requiring no expendables. The approach utilizes two large diameter counterrotating rings or wheels suspended magnetically in many race supports distributed around the antenna structure. When the magnets are energized, attracting the two wheels, the resulting gyroscopic torque produces a rate along the appropriate axis. Roll control is provided by alternating the radiative rotational velocity of the two wheels. Wheels with diameters of 500 to 800 m and with sufficient momentum storage capability require rims only a few centimeters thick. The wheels are extremely flexible; therefore, it is necessary to account for the distributed nature of the rings in the design of the bearing controllers. Also, ring behavior is unpredictably sensitive to ring temperature, spin rate, manufacturing imperfections, and other variables. An adaptive control system designed to handle these problems is described.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 169-187
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  • 36
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    Weight estimates and packaging techniques for the microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Estimates of total spacecraft weight and packaging options were made for three conceptual designs of a microwave radiometer spacecraft. Erectable structures were found to be slightly lighter than deployable structures but could be packaged in one-tenth the volume. The tension rim concept, an unconventional design approach, was found to be the lightest and transportable to orbit in the least number of shuttle flights.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 109-125
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  • 37
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    The microwave radiometer spacecraft. A design study: Executive summary (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A conceptual design was developed for a microwave radiometer spacecraft (MRS) using a large passive reflector, microwave radiometer, and advanced control concepts soil moisture mapping from microwave sensing for global crop forecasting. Mission requirements and tradeoffs were defined, and major subsystems (structural, electromagnetic surface, and attitude control) conceptually designed. An overview of the mission and a summary of the study results are presented.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 1-14
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  • 38
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    Acoustic and vibration environments for laboratory experiments in space (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The basic parameters of random noise and vibration are described, and typical environments for the launch phase and orbital operations are presented. For the latter, both acoustically induced and structure-borne, thruster-included vibration are addressed, using data obtained during the Skylab and Titan programs.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 188-195
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  • 39
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    Elastic body dynamics (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Most of the structural dynamics resources allocated to the Space Shuttle are concentrated on the flight events which result in critical structural loads and/or minimum control stability margins. Since these events are primarily sub-orbital, the data base of interest to those involved in orbital experimentation is somewhat limited. A brief discussion of available data is given. Although estimates of peak acceleration levels and the associated frequency spectrum in the payload bay due to thrusting of the various control system thrusters were made, the actual levels and time histories must be based on updated structural math models and a detailed knowledge of the input forcing functions.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 175-180
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  • 40
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    Interactions between spacecraft motions and the atmospheric cloud physics laboratory experiments (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: In evaluating the effects of spacecraft motions on atmospheric cloud physics laboratory (ACPL) experimentation, the motions of concern are those which will result in the movement of the fluid or cloud particles within the experiment chambers. Of the various vehicle motions and residual forces which can and will occur, three types appear most likely to damage the experimental results: non-steady rotations through a large angle, long-duration accelerations in a constant direction, and vibrations. During the ACPL ice crystal growth experiments, the crystals are suspended near the end of a long fiber (20 cm long by 200 micron diameter) of glass or similar material. Small vibrations of the supported end of the fiber could cause extensive motions of the ice crystal, if care is not taken to avoid this problem.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 34-35
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  • 41
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    Fuel optimal maneuvers for spacecraft with fixed thrusters (1982)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Several mathematical models, including a minimum integral square criterion problem, were used for the qualitative investigation of fuel optimal maneuvers for spacecraft with fixed thrusters. The solutions consist of intervals of "full thrust" and "coast" indicating that thrusters do not need to be designed as "throttleable" for fuel optimal performance. For the primary model considered, singular solutions occur only if the optimal solution is "pure translation". "Time optimal" singular solutions can be found which consist of intervals of "coast" and "full thrust". The shape of the optimal fuel consumption curve as a function of flight time was found to depend on whether or not the initial state is in the region admitting singular solutions. Comparisons of fuel optimal maneuvers in deep space with those relative to a point in circular orbit indicate that qualitative differences in the solutions can occur. Computation of fuel consumption for certain "pure translation" cases indicates that considerable savings in fuel can result from the fuel optimal maneuvers.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 21 p
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  • 42
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    Biaxial and electrostatic tensioning effects on thin membrane materials (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Thin membrane materials were subjected to biaxial and electrostatic tensioning loads to study techniques for maintaining surface smoothness of a thin membrane antenna. The basic mechanical and electrical setup for the tests is described and preliminary measurements of surface smoothness and surface deviation are presented.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 189-204
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  • 43
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    Effects of random distortions on the surface accuracy of a large antenna (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: The effects of random reflector distortions or irregularities on a reflector's radiation pattern are discussed. The importance of such surface deviations with respect to a radiometric reflector antenna is addressed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 137-140
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  • 44
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    Preliminary design of tetrahedral truss reflector structure (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A baseline structure proposed for the microwave radiometer spacecraft (MRS) reflector is a large graphite-epoxy truss. The truss structure was selected to provide adequate stiffness to minimize control problems and to provide a low-expansion 'strong back' on which to mount and control reflector mesh panels. Details of the structural members, joints and assembly concepts are presented, a concept for the reflector mesh surface is discussed, and preliminary estimates of the mass and structural natural frequencies of the reflector system are presented.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 95-107
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  • 45
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    Radiometer design concepts for large aperture microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Concepts involving active and passive microwave systems for soil-moisture monitoring are discussed. It is shown that the first major development efforts should be directed toward the simpler passive design concepts. Subsequently, five passive design concepts for a microwave radiometer spacecraft are outlined and compared. Some common technology needs, such as large space structures and controls, are shown to exist. Also, some peculiar technology needs are identified, such as complicated phasing networks, dielectric lenses, tapered illumination, and reflector-surface irregularity and distortion control techniques. More detailed studies to address these design concepts and assess the associated technology needs are recommended.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 43-49
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  • 46
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    High-resolution passive microwave imaging of the surface of the Earth (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The physics of passive microwave observations of the Earth and the system requirements for high-resolution imaging within this spectral band are summarized. High resolution is achieved in a straightforward manner by increasing the size of the primary antenna. However, with a single receiver, it is shown that the combination of high resolution and crosstrack scanning cannot produce images which have valuable geophysical content. The concept of a multiple receiver array located in the focal plane is presented as the only practical solution to the dilemma. Exploring this concept, system requirements are generated which, for the first order, appear to offer solutions to the problem.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Langley Research Center The Mirowave Radiometer Spacecraft; p 3-41
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  • 47
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    Mission definition for a large-aperture microwave radiometer spacecraft (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: An Earth-observation measurements mission is defined for a large-aperture microwave radiometer spacecraft. This mission is defined without regard to any particular spacecraft design concept. Space data application needs, the measurement selection rationale, and broad spacecraft design requirements and constraints are described. The effects of orbital parameters and image quality requirements on the spacecraft and mission performance are discussed. Over the land the primary measurand is soil moisture; over the coastal zones and the oceans important measurands are salinity, surface temperature, surface winds, oil spill dimensions and ice boundaries; and specific measurement requirements have been selected for each. Near-all-weather operation and good spatial resolution are assured by operating at low microwave frequencies using an extremely large aperture antenna in a low-Earth-orbit contiguous mapping mode.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 17-32
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  • 48
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    Cryogenic helium 2 systems for space applications (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Two cryogenic systems are described which will provide cooling for experiments to be flown on Spacelab 2 in the early 1980's. The first system cools a scanning infrared telescope by the transfer of cold helium gas from a separate superfluid helium storage dewar. The flexible design permits the helium storage dewar and transfer assembly to be designed independent of the infrared experiment. Where possible, modified commerical apparatus is used. The second cryogenic system utilizes a specially designed superfluid dewar in which a superfluid helium experiment chamber is immersed. Each dewar system employs a porous plug as a phase separator to hold the liquid helium within the dewar and provide cold gas to a vent line. To maintain the low vapor pressure of the superfluid, each system requires nearly continuous prelaunch vacuum pump service, and each will vent to space during the Spacelab 2 flight.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Spacecraft Thermal and Environ. Control Systems; p 507-515
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  • 49
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    Experimental control requirements for life sciences (1978)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The Life Sciences dedicated Spacelab will enable scientists to test hypotheses in various disciplines. Building upon experience gained in mission simulations, orbital flight test experiments, and the first three Spacelab missions, NASA will be able to progressively develop the engineering and management capabilities necessary for the first Life Sciences Spacelab. Development of experiments for these missions will require implementation of life-support systems not previously flown in space. Plant growth chambers, animal holding facilities, aquatic specimen life-support systems, and centrifuge-mounted specimen holding units are examples of systems currently being designed and fabricated for flight.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Spacecraft Thermal and Environ. Control Systems; p 467-472
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  • 50
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    Thermal integration of Spacelab experiments (1978)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The method of thermally integrating the experiments for Spacelab is discussed. The scientific payload consists of a combination of European and United States sponsored experiments located in the module as well as on a single Spacelab pallet. The thermal integration must result in accomodating the individual experiment requirements as well as ensuring that the total payload is within the Spacelab Environmental Control System (ECS) resource capability. An integrated thermal/ECS analysis of the module and pallet is performed in concert with the mission timeline to ensure that the agreed upon experiment requirements are accommodated and to ensure the total payload is within the Spacelab ECS resources.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Spacecraft Thermal and Environ. Control Systems; p 545-559
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  • 51
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    An assessment of thermal design procedures for Shuttle payloads (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: A review of the thermal design options for unmanned Shuttle payloads is presented. Because many future Shuttle payloads will have budgets and less time available for the definition of their thermal subsystems, simplified design procedures will be the most cost-effective. The thermal interface between an individual payload and the Orbiter is discussed. A simplified, modular thermal control system that will reduce the cost of providing thermal protection by minimizing both the initial procurement cost of any specialized hardware and the need for a detailed thermal interface analysis is described.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Spacecraft Thermal and Environ. Control Systems; p 481-486
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  • 52
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    Further development of the multipactor discharge electron source (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: A modification to the multipactor electron source used in the study of the behavior of spacecraft insulating materials is described. The electron accelerating system was included within the source, freeing the region between the source and the target of fields produced by the source electrodes.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 881-886
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    The Qualification of a large electron irradiation facility for telecommunication satellite differential charging simulation (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The definition and procurement program is presented for the set up of a test simulating an electron environment on a model of a communication satellite to study the degradation of the thermal insulation materials during electron bombardment.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 819-833
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  • 54
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    Secondary electron effects on spacecraft charging (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Calculations were conducted to determine the effects of electron-produced secondary electrons on the net charging current and the equilibrium voltage of spacecraft surfaces immersed in hot (keV) plasmas. The effects of secondary electrons produced by the primary plasma electrons were examined for aluminum, Teflon, Mylar, and Kapton. The results indicate that it is the primary electron energy region over which the secondary electrons are emitted (rather than the ratio of secondary to primary electrons) which determines the effectiveness of the secondary electrons in limiting the net charging current. While the electron-produced secondary electrons decreased the charging current, they had little effect upon the equilibrium voltages attained.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 756-768
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  • 55
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    Parameter dependence of equilibrium charging potentials (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Equilibrium surface potentials for slab configurations (representative e.g. of a large solar power satellite) are determined under extensive parametric variations of materials, solar exposure and substorm characteristics. The dependence of the charging process for dielectric surfaces on the various material response characteristics is described. The results are used as a guide to the material selection and design of large space systems to minimize dielectric breakdowns and reduce parasitic leakage currents on SPS.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA Lewis Res. Center Spacecraft Charging Technol., 1978; p 711-733
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  • 56
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    Thermal blanket metallic film groundstrap and second surface mirror vulnerability to arc discharges (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Available data on the geosynchronous orbit energetic plasma environment were examined, and a crude model was generated to permit an estimation to be made of the number of arc discharges per year to which a thermal blanket groundstrap would be subjected. Laboratory experiments and a survey of the literature on arc discharge characteristics were performed to define typical and worst case arc discharge current waveforms. In-air tests of different groundstrap configurations to a standardized test pulse were performed and a wide variability of durability values were found. A groundstrap technique, not used thus far, was found to be far superior than the others.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 657-681
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  • 57
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    Secondary emission effects on spacecraft charging: Energy distribution considerations (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: The conditions under which multiple valued solutions occur by computing the floating potential of an isolated eclipses surface on a geosynchronous orbit spacecraft were examined. Different approximations for the electron spectra during a geomagnetic substorm were used. The result indicates that if the incident electron flux has a Maxwellian energy distribution, the ratio of the secondary emitted current to the incident electron current is independent of the spacecraft potential. In this case a single value solution to the current equation occurs.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 747-755
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    Model for breakdown process in dielectric discharges (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: A heuristic model to explain the blowoff of charge during an electron-induced dielectric discharge is presented. It is proposed that blowoff of charge is initiated by a punchthrough or a flashover. The discharge time is assumed to be governed by an LC time constant where L is the inductance of the electrons flowing in the branches of the Lichtenberg figures at an electron range below the irradiated surface and C is the capacitance between the trapped electrons and the substrate for the discharged area. Experiments to verify that blowoff is a consequence of punchthrough or flashover and to measure the punchthrough current and the variation of discharge time with the sample area and thickness were conducted.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 704-710
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  • 59
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    Area scaling investigations of charging phenomena (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: The charging and discharging behavior of square, planar samples of silvered, fluorinated ethylene-propylene (FEP) Teflon thermal control tape was measured. The equilibrium voltage profiles scaled with the width of the sample. A wide range of discharge pulse characteristics was observed, and the area dependences of the peak current, charge, and pulse widths are described. The observed scaling of the peak currents with area was weaker than that previously reported. The discharge parameters were observed to depend strongly on the grounding impedance and the beam voltage. Preliminary results suggest that measuring only the return-current-pulse characteristics is not adequate to describe the spacecraft discharging behavior of this material. The seams between strips of tape appear to play a fundamental role in determining the discharging behavior. An approximate propagation velocity for the charge cleanoff was extracted from the data. The samples - 232, 1265, and 5058 square centimeters in area - were exposed at ambient temperature to a 1- to 2-nA/sq cm electron beam at energies of 10, 15, and 20 kilovolts in a 19-meter-long by 4.6-meter-diameter simulation facility at the Lewis Research Center.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 485-506
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  • 60
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    Plasma particle trajectories around spacecraft propelled by ion thrusters (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The thruster plasma is assumed to be described by a collimated energetic beam and a cloud of ionized thermal propellant produced by charge-exchange. A simple adiabatic model is used to describe the expansion of these neutral plasmas away from the source. As the pressure falls, shielding currents dissipate, and the geomagnetic field takes control of the particles. In low earth orbit, it is concluded that the vehicle easily outruns its thruster plasma. At geosynchronous altitude, the local electric fields around high voltage surfaces collect return current from the thermal plasma that appears to be limited only by the available space charge. Results appropriate to proposed electric propulsion missions and the solar power satellite are presented and operational considerations are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 419-436
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  • 61
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    Effect of parasitic plasma currents on solar-array power output (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Solar-array voltage-current curves are calculated by assuming the existence of parasitic loads that consist of local currents of charged particles collected by the array. Three cases of interest are calculated to demonstrate how the distribution and magnitude of parasitic currents affect output. Solar array performance degradation became significant when the total parasitic current plus the load current exceeded the short-circuit current. Approximate graphical methods were useful for many applications. Power loss, which was calculated by summing the product of parasitic current and the local potential, underestimated the loss in maximum power.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 358-375
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  • 62
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    Magnetic shielding of large high-power-satellite solar arrays using internal currents (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Present concepts for solar power satellites involve dimensions up to tens of kilometers and operating internal currents up to hundreds of kiloamperes. A question addressed is whether the local magnetic fields generated by these strong currents during normal operation can shield the array against impacts by plasma ions and electrons (and from thruster plasmas) which can cause possible losses such as power leakage and surface erosion. One of several prototype concepts was modeled by a long narrow rectangular panel 2 km wide and 20 km long. The currents flow in a parallel across the narrow dimension (sheet current) and along the edge (wire currents). The wire currents accumulate from zero to 100 kiloamp and are the dominant sources. The magnetic field is approximated analytically. The equations of motion for charged particles in this magnetic field are analyzed. The ion and electron fluxes at points on the surface are represented analytically for monoenergetic distributions and are evaluated.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 376-387
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  • 63
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    Spacecraft potential control on ISEE-1 (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Active control of the potential of the ISEE-1 satellite by the use of electron guns is reviewed. The electron guns contain a special cathode capable of emitting an electron current selectable between 10 to the -8th power and 10 to the -3rd power at energies from approximately .6 to 41 eV. Results obtained during flight show that the satellite potential can be stabilized at a value more positive than the normally positive floating potential. The electron guns also reduce the spin modulation of the spacecraft potential which is due to the aspect dependent photoemission of the long booms. Plasma parameters like electron temperature and density can be deduced from the variation of the spacecraft potential as a function of the gun current. The effects of electron beam emission on other experiments are briefly mentioned.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 256-267
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  • 64
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    Electron transport model of dielectric charging (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: A computer code (SCCPOEM) was assembled to describe the charging of dielectrics due to irradiation by electrons. The primary purpose for developing the code was to make available a convenient tool for studying the internal fields and charge densities in electron-irradiated dielectrics. The code, which is based on the primary electron transport code POEM, is applicable to arbitrary dielectrics, source spectra, and current time histories. The code calculations are illustrated by a series of semianalytical solutions. Calculations to date suggest that the front face electric field is insufficient to cause breakdown, but that bulk breakdown fields can easily be exceeded.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 209-238
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  • 65
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    Design, development, and flight of a spacecraft charging sounding rocket payload (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Results of the flight of the spacecraft charging sounding rocket payload are given. The payload was designed to create charging by the emission of both positive ions and electrons. The relationship between environmental parameters and changes in vehicle potential during periods of emission was also studied.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 80-90
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  • 66
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    Evolution of spacecraft attitude control concepts before 1952 (1977)
    In:  CASI
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    Publikationsdatum: 2006-01-16
    Beschreibung: The control of rotational motion of a spacecraft during its free flight regime is traced from pioneer space flight to the year 1952. Essentials of attitude control systems are reviewed and spin stabilization is examined. Other topics include passive stabilization and active closed loop control.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 156-169
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  • 67
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    F. Gomez Arias' rocket vehicle project (1977)
    In:  CASI
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    Publikationsdatum: 2006-01-16
    Beschreibung: Research done by Spanish pioneer rocket scientists in the 19th century was investigated with major emphasis placed on F. Gomez Arias' rocket vehicle project. Arias, considered the world's first designer of rocket propelled, manned aircraft, was interested in solving the problem of space navigation. Major concerns included ascent and direction of heavier-than-airmachines, as well as ascent and direction of balloons.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 176-185
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  • 68
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    Thermal/environmental control and life support system requirements for future space application (1978)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Thermal/environmental control systems concepts being considered for the power module and manned orbital facilities are described. To assure an economically viable program, the approach being pursued is utilization of existing hardware, where possible, and construction of orbital facilities in modular fashion to meet anticipated growth of space processing, astronomy, life science, solar/terrestrial observation, construction, etc. Configurations include Orbiter tended missions (Orbiter remains attached to orbiting facility) and freeflying manned or unmanned earth-orbiting facilities. Utilization of shuttle hardware, e. g., external tank, or the currently orbiting Skylab vehicle is being considered for orbital facilities. Studies include use of Spacelab hardware with a power module to permit extending on-orbit mission time beyond the capability of the current space transportation system. Power levels of 25 kW are being considered for the power module. Mission duration is not limited due to the modular approach and the concept of utilizing a logistics module to provide consumables' resupply capability to the orbital facility.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Spacecraft Thermal and Environ. Control Systems; p 575-582
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  • 69
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    Development of the Transient Pulse Monitor (TPM) for Scatha/P78-2 (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: An instrumentation system developed for the detection of electrical transients on space vehicles is presented. The pulse monitor measures the electron pulse environment on a spacecraft at synchronous altitude, and characterizes signals produced by arcing between differentially charged elements on the spacecraft.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 876-880
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  • 70
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    A combined spacecraft charging and pulsed X-ray simulation facility (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: A spacecraft charging simulation facility constructed to investigate the response of satellite materials in a typical geomagnetic substorm environment is described. The conditions simulated include vacuum, solar radiation, and substorm electrons. A nuclear threat environment simulation using a flash X ray generator is combined with the spacecraft charging facility. Results obtained on a solar cell array segment used for a preliminary facility demonstration are presented with a description of the facility.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 854-867
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    Investigation of electrostatic discharge phenomena on conductive and non-conductive solar reflectors (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: A sample composed of non conductive optical solar reflectors (OSR) was irradiated with low energy electrons at the DERTS facility to study the effects of charge build up on thermal control coating materials. The degration effects on this panel due to electrostatic discharges were investigated to find possible alternatives to limit the amount of damage. The following systems are evaluated: (1) non conductive OSR (non conductive adhesive) (2) non conductive OSR (conductive adhesive); and conductive OSR (conductive adhesive).
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol.; p 682-703
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  • 72
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    Effects of electron irradiation on large insulating surfaces used for European Communications Satellites (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Samples of aluminized Kapton used for passive thermal control on the VHF shield and the antenna dish of ESA's OTS satellite and its derivatives were subjected to an incident electron beam of 25 keV and irradiated for 8 hours at room temperature and at -173 C under a vacuum of the 10 to the minus 6 th power torr. Visual observations during electron irradiation, measurements of leakage current and discharge characteristics, and material degradation following completion of irradiation are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 570-586
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  • 73
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    Electric fields in irradiated dielectrics (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: An existing model for quantitatively predicting electric field build-up in dielectrics is used to demonstrate the importance of material parameters. Results indicate that electron irradiation will produce 10 to the 6th power V/cm in important materials. Parameters which can alter this build-up are discussed. Comparison to known irradiation induced dielectric charging experiments is discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 554-569
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  • 74
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    Interactions between spacecraft and the charged-particle environment (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Spacecraft-environment interactions are defined as the responses of a spacecraft surface to a charged-particle environment. This response can influence spacecraft system performance. Interactions can be divided into two broad categories: spacecraft passive, in which the environment acts on the spacecraft; and spacecraft active, in which the spacecraft causes the interaction. Passive interactions include the spacecraft-charging phenomenon. Active interactions include the relatively new interactions arising from the use of very large spacecraft and space power systems in future missions. To illustrate active interactions, a large power system operating at elevated voltages is considered. Possible interactions are described, available experimental data are reviewed, and the effect on power system performance is estimated.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 268-294
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  • 75
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    The calculation of spacecraft potential: Comparison between theory and observation (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: A simple charge balance model based on the work of DeForest was adapted for the calculation of spacecraft potentials. The model was calibrated with ATS 5 plasma data. Once calibrated, the model was used to calculate the time-varying potential that was observed as a spacecraft passes in and out of eclipse. Errors on the order of + or - 800 volts were observed over a range of 0 to -10,000 volts. Possible applications of the model to large space structures are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 239-255
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    Spacecraft charging results for the DSCS-3 satellite (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: Spacecraft charging results are presented for the DSCS-3 satellite for a severe geomagnetic substorm. Spacecraft charging results were obtained by the use of the electrostatic charging analysis program (ESCAP). The ESCAP computer code which can determine both the transient or steady state differential charging potentials was an engineering design tool that utilized a circuit theory approach to spacecraft charging. Using the ESCAP code, the steady state (static) differential potentials of the outer spacecraft surfaces and metallic structure were obtained for the DSCS-3 satellite when under the influence of a severe geomagnetic substorm during the local midnight-to-dawn quadrant of its geosynchronous orbital path. The results indicated that, in the steady state, most of the DSCS-3 outer surface materials will not achieve differential potentials large enough to produce an electrostatic discharge.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 158-178
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    Comparison of NASCAP predictions with experimental data (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The NASA charging analyzer program (NASCAP) is a three dimensional, finite element computer code capable of simulating the electrostatic charging of an arbitrary body either in a ground test tank or in the space environment. The code incorporated surface property parameters needed to simulate insulating and conducting materials. These parameters are being updated as required to bring the NASCAP predictions into correspondence with data from ground tests. NASCAP predictions are also being compared with data from the ATS 5 spacecraft. The significance of these results is discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 144-157
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  • 78
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    Description of the Space Test Program P78-2 spacecraft and payloads (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The P78-2 spacecraft and its payloads are designed to measure the environment at near synchronous altitude and the interactions of the environment on the spacecraft. A brief description of each payload is provided.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 4-10
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  • 79
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    Average plasma environment at geosynchronous orbit (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-12
    Beschreibung: The average plasma environment at geosynchronous orbit (GSO) is derived from a whole year's worth of plasma data obtained by the UCSD electrostatic electrometer on board ATS 5. The result is primarily intended for use as a general reference for engineers designing a large spacecraft to be flown at GSO. A simple mathematical formula using a 3rd order polynomial is found to be adequate for representing the yearly averaged particle energy spectrum from 70 to 41,000 eV under different geomagnetic conditions. Furthermore, correlation analyses with the geomagnetic planetary index Kp and with the auroral electrojet index AE were carried out in the hope that the ground observations of the geomagnetic field variations can be used to predict the plasma variations in space. Unfortunately, the results indicate that such forecasting is not feasible by use of these two popular geomagnetic parameters alone.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 23-37
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    Prediction of spacecraft potentials at geosynchronous orbit (1979)
    In:  CASI
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    Publikationsdatum: 2006-01-16
    Beschreibung: Two relatively straightforward techniques are outlined for determining spacecraft potentials in the limit of a 'thick sheath' surrounding the spacecraft. A statistical model of the various features of the geosynchronous environment based on ATS-5 and ATS-6 data and an analytic model capable of detailed simulation of the low energy geosynchronous environment are also discussed. The results from these two environmental models are then combined with the charging models in order to provide estimates of the relationships between the geomagnetic index and spacecraft potential. The results are compared with actual potential measurements from ATS-5 and ATS-6.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 104-118
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  • 81
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    Orbital environment dynamics (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: Diurnal density variations of the upper atmosphere are described. Temperature distribution above the thermopause were mapped and extremes of temperature variation over the 11-year solar cycle were determined. Day and nigth density profiles in the upper atmosphere at sunspot minimum and at a time of exceptionally high solar activity are presented.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 121-128
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  • 82
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    Design of the space shuttle digital autopilot and resulting dynamic environment (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: This compilation progresses through the development of the Space Shuttle phase plane controller form fundamental considerations. Quantitative insight regarding the nature of the dynamic environment aboard the Shuttle is provided.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 147-166
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  • 83
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    Attitude control of the space construction base: A modular approach (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A planar model of a space base and one module is considered. For this simplified system, a feedback controller which is compatible with the modular construction method is described. The systems dynamics are decomposed into two parts corresponding to base and module. The information structure of the problem is non-classical in that not all system information is supplied to each controller. The base controller is designed to accommodate structural changes that occur as the module is added and the module controller is designed to regulate its own states and follow commands from the base. Overall stability of the system is checked by Liapunov analysis and controller effectiveness is verified by computer simulation.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 35 p
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    Electromagnetic design of a microwave radiometer antenna system (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A preliminary electromagnetic (EM) design of a radiometric antenna system was developed for the microwave radiometer spacecraft mission. The antenna system consists of a large spherical reflector and an array of feed horns along a concentric circular arc in front of the reflector. The reflector antenna was sized to simultaneously produce 200 contiguous 1 km diameter footprints with an overall beam efficiency of 90 percent, and the feed horns and feed horn array were designed to monitor the radiation from the footprints.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 129-136
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    Evolution and design characteristics of the microwave radiometer spacecraft (1981)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: The evolution of the design of the microwave radiometer spacecraft from conception to preliminary design is described. Alternatives and tradeoff rationale are described, and the configuration and structural design features that were developed and refined during the design processes are presented for the three structural configurations studied (two geodesic trusses and a flexible catenary).
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: The Microwave Radiometer Spacecraft; p 51-66
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    Dynamic behavior of particles in spacecraft (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The behavior of particles relative to a spacecraft frame of reference was examined. Significant spatial excursions of particles in space can occur relative to the spacecraft frame of reference as a result of drag deceleration of the vehicle. These vehicle excursions tend to be large as time increases. Thus, if the particle is required to remain in a specified volume, constraints may be required. Thus, for example, in levitation experiments it may be extremely difficult to turn off the forces of constraint which keep the particles in a specified region. This means experiments which are sensitive to disturbances may be very difficult to perform if perturbation forces are required to be absent.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 137-146
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  • 87
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    Defining critical point experiments for a space laboratory (1981)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Three representative low-gravity experiments for a fluid near its liquid-vapor critical point are being defined. Two of these experiments require very careful measurements of properties of the fluid in thermodynamic equilibrium, while the third experiment is a series of optical observations of the phenomena which occur as a fluid is changed from one phase to two phases, either by cooling through the critical point, or by adiabatic expansion. There is concern that residual spacecraft motions may complicate the interpretation of the data from the proposed experiments. It is possible that the Spacelab environment will render certain desirable experiments impractical.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 11-17
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  • 88
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    TDRSS solar array arc discharge tests (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Solar array design guidelines for immunity to the geomagnetic substorm environment at geosynchronous altitudes are summarized. The preliminary design guidelines and recommended practices based on these test results are given. It is concluded that specific design and immunity verification problems on each spacecraft program have to be solved on an individual basis until the technology matures to an adequate level.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 834-852
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  • 89
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    Charging rates of metal-dielectric structures (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Metal plates partially covered by 0.01-centimeter-thick fluorinated ethylene-propylene (FEP) Teflon were charged in the Lewis Research Center's geomagnetic substorm simulation facility using 5-, 8-, 10-, and 12-kilovolt electron beams. Surface voltage as a function of time was measured for various initial conditions (Teflon discharged or precharged) with the metal plate grounded or floating. Results indicate that both the charging rates and the levels to which the samples become charged are influenced by the geometry and initial charge state of the insulating surfaces. The experiments are described and the results are presented and discussed. NASA charging analyzer program (NASCAP) models of the experiments have been generated, and the predictions obtained are described. Implications of the study results for spacecraft are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 507-523
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  • 90
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    Test results for electron beam charging of flexible insulators and composites (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Flexible solar-array substrates, graphite-fiber/epoxy - aluminum honeycomb panels, and thin dielectric films were exposed to monoenergetic electron beams ranging in energy from 2 to 20 keV in the Lewis Research Center's geomagnetic-substorm-environment simulation facility to determine surface potentials, dc currents, and surface discharges. The four solar-array substrate samples consisted of Kapton sheet reinforced with fabrics of woven glass or carbon fibers. They represented different construction techniques that might be used to reduce the charge accumulation on the array back surface. Five honeycomb-panel samples were tested, two of which were representative of Voyager antenna materials and had either conductive or nonconductive painted surfaces. A third sample was of Navstar solar-array substrate material. The other two samples were of materials proposed for use on Intelsat V. All the honeycomb-panel samples had graphite-fiber/epoxy composite face sheets. The thin dielectric films were 2.54-micrometer-thick Mylar and 7.62-micrometer-thick Kapton.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 457-484
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  • 91
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    Environmental interaction implications for large space systems (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Large Space Systems (LSS) comprise a new class of spacecraft, the design and performance of which may be seriously affected by a variety of environmental interactions. The special concerns associated with spacecraft charging and plasma interactions from the LSS designer's viewpoint are addressed. Survivability of these systems under combined solar U.V., particle radiation and repeated electrical discharges is of primary importance. Additional questions regard the character of electrical discharges over very large areas, the effects of high current/voltage systems and magnitude of induced structural disturbances. A concept is described for a large scale experiment platform.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 388-407
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  • 92
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    Plasma sheath effects and voltage distributions of large high-power satellite solar arrays (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Knowledge of the floating voltage configuration of a large array in orbit is needed in order to estimate various plasma-interaction effects. The equilibrium configuration of array voltages relative to space depends on the sheath structure. The latter dependence for an exposed array is examined in the light of two finite-sheath effects. One effect is that electron currents may be seriously underestimated. The other is that a potential barrier for electrons can occur, restricting electron currents. A conducting surface is assumed on the basis of a conductivity argument. Finite-sheath effects are investigated. The results of assuming thin-sheath and thick-sheath limits on the floating configuration of a linearly connected array are studied. Sheath thickness and parasitic power leakage are estimated. Numerically computed fields using a 3-D code are displayed in the thick-sheath limit.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 341-357
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  • 93
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    Status of materials characterization studies (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: In the context of the spacecraft charging technology investigation, studies were made to characterize the response of typical spacecraft surface materials to the charging environment. The objective is to obtain an understanding of the charging and discharging behavior of such materials for the reliable prediction of spacecraft response to charging environments and as a guide for the design of future spacecraft. Materials were characterized in terms of such basic properties as resistivity and secondary emission and in terms of charging and discharging behavior in simulated charging environments.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 437-456
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  • 94
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    Space environmental effects and the solar power satellite (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Some preliminary findings regarding the interactions between the space plasma at GEO and the Marshall Space Flight Center January 1978 baseline Satellite Power Systems (SPS) design are summarized. These include the following: (1) the parasitic load will be dominated by photoelectrons and will amount to about 34 MW; (2) material of higher conductivity than kapton should be used for the solar reflector substrate and the solar cell blanket support material; (3) the satellite structure and solar reflector should be tied electrically to midpoint voltage of each solar cell array; and (4) tests should be run on the proposed solar cell cover glass material (synthetic sapphire) to determine if breakdown is expected.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 408-418
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  • 95
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    Sheath effects observed on a 10 meter high voltage panel in simulated low earth orbit plasma (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: A large (1m x 10m) flat surface of conductive material was biased to high voltage (+ or - 3000 V) to simulate the behavior of a large solar array in low earth orbit. The model array was operated in a plasma environment of 1,000 to 1,000,000/cu cm, with sufficient free space around it for the resulting plasma sheaths to develop unimpeded for 5-10 meters into the surrounding plasma. Measurements of the resulting sheath thickness were obtained. The observed thickness varied approximately as V to the 3/4 power and N to the 1/2 power. This effect appears to limit total current leakage from the test array until sheath dimensions exceed about 1 meter. Total leakage current was also measured with the array.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 315-340
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  • 96
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    Plasma Interaction Experiment (PIX) flight results (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: An auxiliary payload package called PIX (plasma interaction experiment) was launched on March 5, 1978, on the LANDSAT 3 launch vehicle to study interactions between the space charged-particle environment and surfaces at high applied positive and negative voltages. Three experimental surfaces were used in this package: a plain disk to act as a control, a disk on a Kapton sheet to determine the effect of surrounding insulation on current collection, and a small solar-array segment to evaluate the effect of distributing biased surfaces among an array of insulators. Only half of the results from the 4 hours of PIX operations were recovered. The results did verify effects found in ground simulation testing. The results of this experiment are discussed in detail.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 295-314
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  • 97
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    ATS-5 and ATS-6 potentials during eclipse (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: The ATS 5 and ATS 6 data for spacecraft charging during eclipse conditions is analyzed. The ATS 5 and ATS 6 charged to voltages greater than 100 volts for about 55 percent of the eclipse periods examined. The mean spacecraft potential during eclipse was 2 keV for ATS 5, and the highest potential measured was 10 kilovolts. For ATS 6, the mean potential during eclipse was 4 keV, the highest potential measured 20 keV. The average measured spacecraft potentials for both ATS 5 and 6 depend approximately linearly upon Kp. This relationship is due mainly to the dependence of electron current density on Kp near midnight. Spacecraft potentials at geosynchronous orbit may, to a rough approximation, thus be inferred from ground-based measurements of Kp, the planetary 3-hour index.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 38-43
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  • 98
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    Modeling of the geosynchronous plasma environment (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: An analytic simulation of the geosynchronous environment in terms of local time and the daily A sub P index is presented. The simulation is compared with actual statistical data from approximately 50 days of ATS 5 plasma data and 50 days of ATS 6 plasma data. At low levels of activity the model adequately simulates the local time variations of the plasma parameters. At high values of geomagnetic activity, the predicted magnitudes of the plasma parameters agree with the statistical results but the effects of multiple injections are evident in both the data and the simulation, biasing the local time variations.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 11-22
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  • 99
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    Summary of the two year NASA program for active control of ATS-5/6 environmental charging (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Experiments conducted on the ATS 5 and ATS 6 which have demonstrated the feasibility of modifying or clamping the environmentally induced potential of these spacecraft are described. The results of these experiments indicate that a thermionic electron source is capable of replacing photo-emitted electrons during eclipse. However, the utility of this type of device is limited if its emission is suppressed by local electric fields. On the other hand, it is shown that a plasma source will not only serve as a substitute for photo-emitted electrons but will also suppress differential charging of isolated elements of the spacecraft which would tend to suppress electron emission. This later device is therefore capable of clamping the potential of a spacecraft without special considerations of its coupling to the ambient plasma.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: Spacecraft Charging Technol., 1978; p 44-58
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  • 100
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    An application of modern control theory to an elastic spacecraft (1976)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Results are presented to illustrate the application of established procedures of linear, quadratic, Gaussian optimal estimation and control to a spacecraft with dynamically significant elastic appendages. Interpretations are provided in both time domain and frequency domain, and conclusions are drawn for a wide class of problems of flexible spacecraft attitude control.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: ESA Dyn. and Control of Non-rigid Space Vehicles; 5 p
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