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  • Other Sources  (1,015)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (1,015)
  • 1980-1984  (1,015)
  • 1
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    Stable direct adaptive control of linear infinite-dimensional systems using a command generator tracker approach (1984)
    In:  CASI
    Details
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2004-12-04
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2006-04-03
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 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
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Long Duration Exposure Facility (LDEF); p 138
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  • 16
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    IDEAS: A multidisciplinary computer-aided conceptual design system for spacecraft (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: 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.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 21 p
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  • 17
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    Erectable beam experiment (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: The erectable beam applicability to the MAST/STEP experiment is summarized. High manual assembly rates were demonstrated in neutral buoyancy tests and it is suggested that use of an erectable beam would eliminate extension/retraction complexity associated with deployable beams. The erectable beam assembly aid is easily adaptable to general truss configurations and structural appendages could be accommodated with the use of actuators. The ACCESS flight experiment precedes MAST by 2 to 3 years and will provide mature, space proven assembly/disassembly technology on which to base the MAST experiment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: STEP Expt. Requirements; p 121-134
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  • 18
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    Dual structural-control optimization of large space structures (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A new approach is proposed for solving dual structural-control optimization problems for high-order flexible space structures where reduced-order structural models are employed. For a given initial structural dessign, a quadratic control cost is minimized subject to a constant-mass constraint. The sensitivity of the optimal control cost with respect to the stuctural design variables is then determined and used to obtain successive structural redesigns using a contrained gradient optimization algorithm. This process is repeated until the constrained control cost sensitivity becomes negligible. A numerical example is presented which demonstrates that this new approach effectively addresses the problem of dual optimization for potentially very high-order structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 28 p
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  • 19
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    Large inflated-antenna system (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: It is proposed that for inflatable antenna systems, technology feasibility can be demonstrated and parametric design and scalability (scale factor 10 to 20) can be validated with an experiment using a 16-m-diameter antenna attached to the Shuttle. The antenna configuration consists of a thin film cone and paraboloid held to proper shape by internal pressure and a self-rigidizing torus. The cone and paraboloid would be made using pie-shaped gores with the paraboloid being coated with aluminum to provide reflectivity. The torus would be constructed using an aluminum polyester composite that when inflated would erect to a smooth shell that can withstand loads without internal pressure.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: STEP Expt. Requirements; p 311-324
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  • 20
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    Deployable beam flight experiment (MAST) (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: Improvement of technology of space systems control is discussed. Future space systems such as large antennas or a space station may have dimensions on the order of 30 m to 200 m, yet their basic structures may be relatively lightweight and flexible, making ground tests for loads, controls analyses, and design verifications questionable if not impossible. Abandoning the extensive ground test and analysis verification program that led to the success of previous spacecraft is not a sensible option; making it meaningful using current technology will require inefficient, ultraconservative structure and control designs. New test methods are outlined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: STEP Expt. Requirements; p 103-120
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  • 21
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    The 55-meter-structure flight experiment (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: The verification and demonstration of the structural performance related parameters for large flexible space structures are discussed. The objectives are to verify the deployment repeatability of static surface contour, to demonstrate the feasibility of in-flight static shape correction, to verify predicted shape in a zero gravity thermal environment, to determine zero gravity structural dynamic characteristics, and to verify the instrumentation and excitation system for in-flight measurements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center STEP Expt. Requirements; p 301-310
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  • 22
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    Large deployable antenna flight experiment for the Space Technology Experiments Platform (STEP) (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: Spaceborne experiments to test the deployment reliability of large space antennas are discussed. Retraction, reflector surface tolerance, thermal distortion, electromagnetic performance, and dynamic controls are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: STEP Expt. Requirements; p 279-300
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  • 23
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    Integrated Power/Attitude Control System (IPACS) technology experiment (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: An experiment is proposed that will perform the tasks associated with the control and energy storage/power generation functions attendant to space operations. It was shown in past studies that the integration of these functions into one system can result in significant weight, volume, and cost savings. The Integrated Power/Attitude Control System (IPACS) concept is discussed. During orbit day, power is derived from the solar cell arrays and, after appropriate conditioning, is used to operate the spacecraft subsystems, including the control system. In conventional approaches, a part of the collected solar energy is stored in a bank of batteries to permit operation of the vehicle's systems during orbit night. In the IPACS concept, the solar energy is stored in the spinning flywheels of the control system in the form of kinetic energy. During orbit night, the wheels are despun and, through the use of a wheel-shaft mounted generator, power is generated for the onboard subsystems. Operating these flywheels over a 50-percent speed variation permits the extraction of 75 percent of the stored energy while at the same time preserving 50 percent of the momentum capacity for control of the vehicle. Batteries can therefore be eliminated and significant weight and volume savings realized.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: STEP Expt. Requirements; p 231-240
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  • 24
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    The STEP/STACBEAM experiment technology development for very large solar array deployers (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-03
    Description: The Stacking Triangular Articulated Compact Beam (STACBEAM) is discussed with reference to structural testing experiments afforded by ground simulation and the Space Technology Experiments Platform (STEP). The STACBEAM lends itself to a deployment technique which offers a radical improvement in flexible blanket solar array technology. A system for deployment and support of a solar array blanket is described which consists of the blanket, its containment structure, the support structure and its deployer, the blanket stiffening battens, and the deployable boom standoffs. In operation, the blanket is pulled out and supported by the STACBEAM which packages next to the folded blanket. Since the STACBEAM does not rotate during extension, complete control of the blanket is maintained during extension. Deployment of this system occurs one bay at a time in a sequential manner. The deployer provides sufficient rigidity so that beam stiffness is not degraded during the deployment process.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center STEP Expt. Requirements; p 135-146
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  • 25
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    Innovative method for the thermal cycling of large spacecraft systems (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The use of low cost, off the shelf prefabricated enclosures for spacecraft system thermal cycling applications was indicated. The enclosures are erected in the satellite integration areas without disturbing the test article, electrical test set, or RF interfaces. They are assembled by metal clad, modular urethane panels. These panels are self supporting, and are locked and sealed to each other on assembly. Penetrations for interconnecting cables, coaxial and waveguide services; and temperature conditioning inlet and outlet ducts are easily incorporated where required. The facility and its advantages and intrinsic benefits are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 13th Space Simulation Conf.; p 8-20
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  • 26
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    Earth orbiter into planetary orbiter - What's the problem? (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A recent series of competitive design studies appears to have yielded positive results about the efficacy of adapting earth-orbiting spacecraft to perform planetary missions. The purpose of this paper is twofold: (1) to show the intrinsic attributes required to adapt an earth orbiter into a Martian orbiter compatible with the scientific requirements, and (2) to show the minimum requisite changes needed to make the adaptation. It is shown that major deficiencies of such conversion for earth-orbiting satellites lie in the not-unexpected inability of its telecommunications system to operate at Martian distances and its lack of an autonomous recovery system from anomalous performance. Since these deficiencies can be overcome without too great a financial or schedule penalty, the study shows that the adaptation can be made cost effectively.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 32; 199-209
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  • 27
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    The next generation of reentry vehicles: NASA's view (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The term reentry vehicle is used in the broad sense. The vehicles addressed include not only those that return from orbit to the Earth's surface, but also aeroassisted orbit transfer vehicles that use aerodynamic forces generated during atmospheric passes to achieve orbital changes with a smaller expenditure of energy than is required for an all-propulsion vehicle. Advanced reusable launch vehicles with special emphasis on system concepts and the influence of advanced technology on entry vehicle configuration are considered. Three categories of orbital transfer vehicles discussed: synergetic plane-change vehicles, planetary aerocapture vehicles, and LEO to GEO orbital transfer vehicles. While the orbital transfer and planetary vehicles are quite different from conventional winged Earth entry vehicles, synergetic plane change and high cross-range Earth entry vehicles have many similarities. Finally, a possible scenario for the development of the next generation of reentry vehicles is presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Von Karman Inst. for Fluid Dynamics Hypersonic Aerothermodyn.; 95 p
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  • 28
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    Application of fracture mechanics on the Space Shuttle (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: During the design stages of the shuttle orbiter, fracture-mechanics concepts were applied extensively to the highly stressed areas of the structure. This was the first space program to require a comprehensive fracture mechanics approach to prevent structural failures from crack or crack-like defects. As anticipated, some difficult problems were encountered. This paper briefly describes some of them together with the procedure used for fracture control on the orbiter. It is believed that the principles and methods as presented herein can serve as an example of fracture control for aerospace and other industries.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 29
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    Reduction of root-mean-square error in faceted space antennas (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA Journal (ISSN 0001-1452); 22; 1679-168
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  • 30
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    Maintenance of contamination sensitive surfaces on board long-term space vehicles (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: In the current age, highly sensitive instruments are being flown on spacecraft, and questions of contamination have become important. The present investigation is concerned with the available approaches which can provide long-term protection for contamination sensitive surfaces. Aspects and sources of spacecraft contamination are examined, taking into account materials outgassing, particulates, propulsion system interaction, overboard venting, man-made and cosmic debris, and atomic oxygen/ambient atmosphere interaction. Suitable protection approaches provided by current technology are discussed, giving attention to aperture covers, a possibility for a retractable cover design, gaseous purges, options for prolonging the lifetime of the thermal control system, and plume shields. Some new possibilities considered are related to an early warning system for excessive amounts of contamination, a molecular/wake shield, and the use of atomic oxygen.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Environmental Sciences (ISSN 0022-0906); 19-21
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  • 31
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    An on-orbit experiment for dynamics and control of large structures (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Attention is given to the definition of the on-orbit dynamic testing that is currently being planned for the flight of a large solar array test article, the Solar Array Flight Experiment (SAFE 1), which consists of a coilable longeron mast that deploys a large solar array blanket. Also discussed is the design of an additional experiment employing this structure in conjunction with a two- or three-axis gimbal system, in order to demonstrate control techniques applicable to such large structures. SAFE 1 experiment objectives, hardware, software, and the experimental operations foreseen are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 554-562
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  • 32
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    The evolution of small payload carrier systems (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design of a bridge-like structure to span the Space Shuttle cargo bay but occupy only 3 feet of its length is discussed. The new structure was named the Missions Peculiar Equipment Support Structure (MPESS). The basic design requirements were as follows: to serve as support structure for small number of experiments; to occupy the minimal length of cargo bay; to have a standard interface hole pattern; to provide support at an elevated position; to employ standard Spacelab pallet trunnion; and to ensure natural frequency between the STS liftoff and landing frequency. The bridge-like structure is a riveted and bolted truss with machind end fittings which interface with the Spacelab trunnions. The structure is fabricated from aluminum alloy and assembled with stainless steel fasteners.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center 2nd Symp. on Space Industrialization; p 260-271
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  • 33
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    Role of Space Station: The how of space industrialization (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The roles of the Space Station, as an R&D facility, as part of an industrial system which support space industralization, and as a transportation node for space operations are considered. Industrial opportunities relative to these roles are identified and space station concepts responsive to these roles are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 2nd Symp. on Space Industrialization; p 216-241
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  • 34
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    Concept for a commercial space station laboratory (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The concept of a privately owned and operated fee-for-service laboratory as an element of a civil manned space station, envisioned as the venture of a group of private investors and an experienced laboratory operator to be undertaken with the cooperation of NASA is discussed. This group would acquire, outfit, activate, and operate the labortory on a fee-for-service basis, providing laboratory services to commercial firms, universities, and government agencies, including NASA. This concept was developed to identify, stimulate, and assist potential commercial users of a manned space station. A number of the issues which would be related to the concept, including the terms under which NASA might consider permitting private ownership and operation of a major space station component, the policies with respect to international participation in the construction and use of the space station, the basis for charging users for services received from the space station, and the types of support that NASA might be willing to provide to assist private industry in carrying out such a venture are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center 2nd Symp. on Space Industrialization; p 204-215
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  • 35
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    Modular experimental platform for science and applications (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A modularized, standardized spacecraft bus, known as MESA, suitable for a variety of science and applications missions is discussed. The basic bus consists of a simple structural arrangement housing attitude control, telemetry/command, electrical power, propulsion and thermal control subsystems. The general arrangement allows extensive subsystem adaptation to mission needs. Kits provide for the addition of tape recorders, increased power levels and propulsion growth. Both 3-axis and spin stabilized flight proven attitude control subsystems are available. The MESA bus can be launched on Ariane, as a secondary payload for low cost, or on the STS with a PAM-D or other suitable upper stage. Multi-spacecraft launches are possible with either booster. Launch vehicle integration is simple and cost-effective. The low cost of the MESA bus is achieved by the extensive utilization of existing subsystem design concepts and equipment, and efficient program management and test integration techniques.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center 2nd Symp. on Space Industrialization; p 136-148
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  • 36
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    Space plasma investigations on the First Spacelab Mission (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A series of investigations was carried out during the First Spacelab Mission to study the space plasma environment from the Shuttle/Spacelab. The emphasis of the experiments was on the performance of particle injections from the Shuttle/Spacelab and studies of the ensuing effects on the orbiter, the near orbiter environment, and the earth's atmosphere. Results of these experiments, including electron beam injections, plasma injections, neutral injections, electron-plasma injections, electron-neutral injections, and ambient environmental measurements, are reviewed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 37
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    Spacecraft glow (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Spacecrft glow may be defined as optical emissions originating immediately above those surfaces of an orbiting spacecraft which face into the ram direction. In the case of the Space Shuttle at its lower orbital altitudes, the glow is bright enough to be seen by the unaided eye. The glow observed at the Dynamics Explorer was caused primarily by OH molecules which formed on the spacecraft surface from ionospheric atomic oxygen and hydrogen. The two theories which are currently considered to obtain an explanation for the glow phenomenon include the plasma interaction mechanism and the chemical mechanism. A number of difficulties appear to exclude the applicability of the plasma interaction mechanism. Thus, the chemical mechanism remains as the only viable theory. According to this mechanism, simple impact of incoming atmosphere atoms and molecules causes both formation and excitation of molecules at the surface of a spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 38
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    Landsat - An unmanned space platform (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Landsats 4 and 5, the latest in the series of unmanned earth observation satellites, are used as the space platform for two remote sensing, mechanical scanning instruments: the multispectral scanner (MSS) and the recently developed thematic mapper (TM). The primary objective of the experimental portion of the Landsat 4 and 5 missions is to assess the capability of the TM to provide improved information relative to the MSS.The higher spatial resolution of the TM over the MSS requires a higher degree of flight segment attitude stability than the earlier Landsats; therefore, a more stable, low-orbit space platform must be provided. This paper describes the orbital, electrical, mechanical, and thermal characteristics of Landsat 4 and 5 flight segment with special emphasis on the TM and MSS interfaces. Also described are flight segment disturbances caused by the TM and MSS scanning mirrors, motion from the Tracking and Data Relay Satellite (TDRS) antenna, solar array, and the attitude control system (ACS).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 39
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    Space Infrared Telescope Facility - Conceptual spacecraft definition (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The Space IR Telescope Facility (SIRTF) program, which envisions a 1-m aperture cryogenically cooled telescope for 1.8-700 micron observations having an operational lifetime of several years, is now conceived as a free-flying, dedicated platform rather than a Space Shuttle instrument. Attention is presently given to the design configuration requirements of this updated concept in the matters of (1) pointing and control, (2) communications, command, and data handling, and (3) electrical power supplies.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 40
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    Planetary spacecraft as optical instrument platforms (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The pointing system, telemetry rate, thermal control, power, command, and available mass of planetary spacecraft are described. A comparison of the pointing and stability capabilities of the three-axis stabilized spacecraft and the spin stabilized spacecraft is presented. The development of a hybrid spacecraft, which combines the spin and three-axis design, is examined. The attitude control and articulation system, and the instruments of the Galileo, a hybrid spacecraft, are analyzed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 41
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    Inertially referenced instrument pointing platform with momentum compensated articulation (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The characteristics of the Mariner Mark II Integrated Platform Pointing and Attitude Control System (IPPACS) microstep actuator with momentum compensation and the IPPACS optical reference tracker are examined, and the advantages of this new technology are identified. The momentum-compensated articulation acts to prevent platform articulation activity from disturbing the spacecaft. This guarantees dynamic stability, ensures a quiescent pointing environment, and decouples the design of the platform from the design of the spacecraft. A microstep actuator with harmonic drive provides platform angular step resolution to 0.5 arcsec for precision pointing of instruments. An optical reference tracker boresighted with scientific instruments guarantees accurate target-referenced closed-loop pointing. An IPPACS star and target tracker with 1 to 10 arcsec accuracy and wide 11 x 17 degrees field of view has been derived from Advanced Star and Target Reference Optical Sensor (ASTROS) CCD star tracker technology, greatly enhancing the optical referencing capabilities of future multimission interplanetary spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 42
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    Static shape determination and control for large space structures. I - The flexible beam. II - A large space antenna (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A method for determining and controlling the shape of large, continuous space structures by means of discrete or pointwise observations and control devices is presented. The general linear boundary value problem satisfied by a one-dimensional shape function is defined, and the existence of solutions is studied. The static shape control problems for one-dimensional systems with and without rigid body modes and the static shape estimation problem are presented and solved. Eigenfunction expansions are presented which provide approximations to the algorithm terms when the associated Green's function is not known. An integral operator approach is applied to the multidimensional static problem, and the results are illustrated with a finite element model of the disk of a large space antenna which assumes no rigid body modes. It is shown that the shape control algorithm must be modified for systems with rigid body modes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME, Transactions, Journal of Dynamic Systems, Measurement, and Control (ISSN 0022-0434); 106; 261-272
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  • 43
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    Dynamics and control of a large space antenna (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2997, Accession no. A82-38967
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 69-76
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  • 44
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    Science platform and attitude subsystem in-flight calibration for the Galileo spacecraft (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 21, p. 3640, Accession no. A81-44136
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 29-35
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  • 45
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    Effect of simulated mission loads on orbiter thermal protection system undensified tiles (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 441-447
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  • 46
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    Experimental demonstration of the control of flexible structures (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The Large Space Structure Technology Flexible Beam Experiment employs a pinned-free flexible beam to demonstrate such required methods as dynamic and adaptive control, as well as various control law design approaches and hardware requirements. An attempt is made to define the mechanization difficulties that may inhere in flexible structures. Attention is presently given to analytical work performed in support of the test facility's development, the final design's specifications, the control laws' synthesis, and experimental results obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 527-534
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  • 47
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    Experiments in control of flexible structures with noncolocated sensors and actuators (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: While the stable control of such flexible structures as limber spacecraft is easily achieved through the colocation of control actuators with sensors, noncolocation renders this extremely difficult. The most difficult case in point is that in which structural damping is low and spacecraft stiffness and inertia values are uncertain and changing. Attention is presently given to an apparatus in which each basic sensor/actuator noncolocation configuration is available, and inertias can be abruptly halved or doubled during control maneuvers. This feature can impose a sudden reversal in the plant's pole-zero sequence, which is a very difficult condition for the controller. Test results obtained to date demonstrate the inherent difficulty of achieving robustness in the case of noncolocation. It is noted that there may be very simple configurations in which there is no alternative to adaptive control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 546-553
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  • 48
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    Dynamics and control of large space structures (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An attempt is made to gather data useful to investigators in the fields of large space structure dynamics and control modeling, design and testing. Attention is given to structural dynamics and its relationship to such allied engineering fields as flutter analysis, as well as to problems in the prediction of atmospheric density at orbital altitude. The first challenge posed by large space structure control is the design of control systems with natural frequencies above several major structural frequencies. The establishment of a sufficiently accurate structural model, plant excitation, and shape maintenance, are noted to be additional problems.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 514-526
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  • 49
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    Designing Galileo to upper bound loads for shuttle/Centaur (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proceedings of the Shuttle Payload Dynamic Environments and Loads Prediction Workshop, Volume 2; p 617-664
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  • 50
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    Optimal design of a passive vibration absorber for a truss beam (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 733-739
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  • 51
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    Ground test experiment for large space structures, appendix I (1984)
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    Publication Date: 2011-08-19
    Description: Marshall Space Flight Center has developed a Large Space Structure (LSS) ground test verification experiment facility having adequate fidelity and flexibility to accommodate the demands of LSS control theory testing. The first experiment is in the subsystem verification and integration phase. This test employs the ASTROMAST, a lightweight S glass composite deployable beam structure, as the test article and is cited to prove out centralized and distributed sensor control strategies.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Control Dyn. Co. Definition of Ground Test for Verification of Large Space Struct. Control; 4 p
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  • 52
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    Review of technical papers, appendix H (1984)
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    Publication Date: 2011-08-19
    Description: Ten (10) papers reviewed deal directly with control systems of large space structures, such as observer designs or closed loop pole placement methods. Of the ten papers there are three principle concepts treated: observers, closed loop pole placement and a disturbance isolation technique. Three of the ten papers were selected for critical review as they embodied the three basic concepts. The objectives of the review were: (1) Check and verify the equations and derivations; (2) Relate these new techniques to standards in the literature; (3) Identify strengths and weaknesses of the methods; and (4) Determine suitable topics for further study using these methods.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; 10 p
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  • 53
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    Definition of ground test for Large Space Structure (LSS) control verification, appendix G (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A Large Space Structure (LSS) ground test facility was developed to help verify LSS passive and active control theories. The facility also perform: (1) subsystem and component testing; (2) remote sensing and control; (3) parameter estimation and model verification; and (4) evolutionary modeling and control. The program is examined as is and looks at the first experiment to be performed in the laboratory.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; 44 p
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  • 54
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    Section 1. Method of determining mode shapes and natural frequencies of the NASA unmodified test structure. Section 2. Continuous beam closed from solution to the NASA-LSS astromast torsional vibration, appendix E (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The methods used to determine the lower natural frequencies and their corresponding mode shapes of the NASA-LSS Astromast (Unmodified Test Structure), and the mass integrals associated with the mode shapes are illustrated. The test structure is modeled as a cantilever beam with 91 lumped masses and without the tip mass on the free end of the bram. This uncouples the torsion and bending modes and allows for them to be determined separately. The frequency range was limited to an upper bound of 100 rad/sec (15.92 Hz.). In this range from 0.-100. rad/sec, three bending frequencies and one torsion frequency was found.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; 26 p
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  • 55
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    Speed test results and hardware/software study of computational speed problem, appendix D (1984)
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    Publication Date: 2011-08-19
    Description: The HP9845C is a desktop computer which is tested and evaluated for processing speed. A study was made to determine the availability and approximate cost of computers and/or hardware accessories necessary to meet the 20 ms sample period speed requirements. Additional requirements were that the control algorithm could be programmed in a high language and that the machine have sufficient storage to store the data from a complete experiment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; 5 p
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  • 56
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    Elimination of uncontrollable rigid body mode, appendix C (1984)
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    Publication Date: 2011-08-19
    Description: The planar system model is examined which reveals two rigid body modes. One is due to the pure translation of the whole experiment assembly and is uncontrollable because the only control input is a torque at the gimbal. The other rigid body mode is due to the pointing of the gimbal and is the one for which control is sort. The problem arises from the Vector V2 which relates the control input to the modal coordinates. Since its fifth and sixth elements are both nonzero, neither body mode can be thrown away as is. The two rigid body modes must be transformed so that one is unaffected by the control input and one is left controllable. The uncontrollable mode can then be eliminated from the model for design purposes. A process is described to accomplish the elimination of the uncontrollable rigid body mode.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; 6 p
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  • 57
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    Oral presentation of first year final report, appendix A (1984)
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    Publication Date: 2011-08-19
    Description: Plans for self contained in-house capability to test Large Space Structures (LSS) and their control prior to flight are presented. A ground test facility which demonstrates and validates LSS control theory is defined. An experiment is designed which assures a high success rate for flight test. A strapdown algorithm is developed. Research on the astromast is reported, as is the development of an overall system model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of of Large Space Struct. Control; 28 p
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  • 58
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    Level of effort (1984)
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    Publication Date: 2011-08-19
    Description: The generation of a planar model of the ground test experiment structure is examined. This was done by adapting an in-house modal analysis code (Gimbalflex) to allow placement of sensors and actuators at certain locations on the structure. The next step in the development of this model was to adapt if for use with the control pole placement algorithm. The uncontrollable rigid body mode was removed from the model. This uncontrollable mode was due to the pointing of the gimbal. Control system design for the planar model was also initiated. A digital controller was planned utilizing the Control Pole Placement technique. The existence of rate of state feedback was assumed. Once this controller and other control algorithms were developed, it became necessary to conduct speed tests. A study was then made of additional hardware/software necessary to meet the speed requirement.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Definition of Ground Test for Verification of Large Space Struct. Control; p 2-13
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  • 59
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    Friction estimation technique for Galileo scan platform control (1984)
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    Publication Date: 2011-08-18
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 608-614
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  • 60
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    Design of the Galileo scan platform control (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Design of the scan platform control for the Galileo spacecraft is presented. Emphasis is placed on the inertial pointing of the scan platform when the spacecraft is in the dual-spin configuration. The various methods of operation used for Galileo scan pointing are outlined. Major design considerations, such as spacecraft flexibility and separation of actuator and sensor by a flexible structure, are discussed. The pointing requirements imposed on the scan platform control are explained. A high-level description of the relevant scan pointing algorithms is included. The performance of the design is demonstrated by a sample slew test case.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 422-429
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  • 61
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    Mechanical properties of the Shuttle Orbiter thermal protection system strain isolator pad (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2029, Accession no. A82-30079
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 253-260
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  • 62
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    Honeycomb sandwich structure for future space transportation systems with integral cryogenic tankage (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2029, Accession no. A82-30084
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 246-252
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  • 63
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    Comparison of Shuttle Orbiter surface pressures with wind tunnel and theoretical predictions (1984)
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 05, p. 606, Accession no. A83-16532
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 227-233
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  • 64
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    Gyro motion boundedness under uncertain vehicle spin and acceleration (1984)
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    Details
    Publication Date: 2011-08-18
    Description: Using a quadratic Liapunov function, a condition is obtained for the boundedness of the motion of the gyro mounted in a vehicle which has a time-varying uncertain angular acceleration and deceleration omega-x(t) about the output axis, and is spinning with uncertain angular velocity omega-z(t) about the spin axis of the gyro. A region of ultimate boundedness in the theta-theta plane is obtained which the motion of the gyro eventually enters and in which it remains after a finite interval of time for any uncertain omega-x(t) and omega-z(t). The gyro motion is shown to be bounded if the uncertainty in the spin velocity does not exceed a certain threshold value. This condition disappears if omega-z(t) = 0.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems (ISSN 0018-9251); AES-20; 119-127
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    Surface step induced gap heating in the Shuttle Thermal Protection System (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 5, p. 606, Accession no. A83-16533
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4560); 21; 156-161
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  • 66
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    Spacecraft contamination: Sources and prevention; Thermophysics Conference, 18th, Montreal, Canada, June 1-3, 1983, Selected Papers (1984)
    In:  Other Sources
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    Publication Date: 2016-03-09
    Description: Results of current research in the field of spacecraft contamination are presented. An overview of the various sources of contamination is given, showing the many and diverse mechanisms associated with the degradation of thermal and optical performance of spacecraft surfaces and optics. Some of the causes of contamination are discussed, including spallation of foam insulation on cryogenic fuel tanks, dispersion of particle contamination about a spacecraft, particle contamination of optical sensors, and the influence of the location of venting systems. Contamination prevention is addressed. Infrared transmittance and infrared optical properties of contaminants are considered along with the effects and properties of mixtures of exhaust species, of plume boundary layer flow, and of the contamination associated with bipropellant attitude control thrusters proposed for the Galileo spacecraft. Also discussed are: degradation of 'clean' thermal control surfaces over four years in orbit, in-orbit measurement of solar absorptance, and contamination from postfire efflux of a solid-propellant rocket motor.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 67
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    Search and rescue satellite (SARSAT) error analysis of the 406 MHz system (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: A computer simulation investigated conditions encountered by the SARSAT 406 MHz system. Three and four parameter emergency transmitter (ET) location solutions were determined. Latitude and longitude, a frequency bias, and in the four-parameters solutions, a linear frequency drift term were estimated. Earth gravity, frequency drift, and measurement noise are the major error contributors to the ET position. Time-tag ET height and velocity errors, although significant are not routinely present. In the four-parameter solutions the drift error is eliminated; however, the sensitivity to measurement noise increases. Using the four-parameter pass solutions, the 406 MHz oscillator specifications can be relaxed and still satisfy the 5 km positioning requirement. Since a linear oscillator drift is removed in the four-parameter solution, only the measurement noise over 10-15 min is important.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 345-359
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  • 68
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    A 406 MHz geostationary satellite SARSAT experiment (1984)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: A 406 MHz SARSAT experiment using the GOES system to demonstrate the utility of integrating a near-instantaneous distress alerting capability achievable by the geostationary satellites with the location capability of the low altitude, near-polar orbiting satellite system is described. Tests include the evaluation of technical performance of a variety of maritime, aviation, and land-based SARSAT beacons under operational environment conditions as well as a demonstration of system effectiveness in pseudo real distress incident situations. The technical performance tests parallel the CCIR coordinated trials program conducted at L-band frequencies using the INMARSAT satellites. Tests, including schedules, are outlined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 303-314
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  • 69
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    Canadian Astronautics Limited's SARSAT ground stations (1984)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: The SARSAT Local User Terminal (LUT) is described. The RF receiving subsystem is based on a conventional 3 m dish antenna mounted on an elevation-over-azimuth pedestal to permit tracking of the low altitude, near polar satellites. Only program tracking is used since orbit parameters and time must always be known precisely for use in position location. Operation of the LUT is split into real-time mode during which Doppler data are generated and stored, and post-pass during which data are sorted and position located. Location accuracy is to within 20 km.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 169-182
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  • 70
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    The COSPAS-SARSAT system (1984)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: The SARSAT/COSPAS satellite network uses 121.5 and 406 MHz buoys to locale ships and aircraft in distress. The 121.5 MHz system, obligatory on many aircraft, gives localization to within 10 km, and, despite being subject to considerable radio interference and a poor signal to noise ratio, is responsible for saving 200 lives. The 406 MHz location error is 2 km in 75% of cases, and 2 hr for 95% of cases in the worst conditions. It suffers however from interference from illegal broadcasts in the frequency band.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 95-110
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  • 71
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    Maneuvering of large flexible space antennas using optimal discrete-time controllers (1984)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: The problem of maneuvering large space structures is formulated as a discrete-time, finite-duration optimal regulator problem. Two methods are considered for minimizing the elastic motion during the maneuver. The methods are applied to retargetting maneuver of a large space antenna, and the results are compared with those obtained using bang-bang control. The optimal regulator designed using the model error sensitivity supression method gives the best performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 72
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    Space systems computer-aided design technology (1984)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: The interactive Design and Evaluation of Advanced Spacecraft (IDEAS) system is described, together with planned capability increases in the IDEAS system. The system's disciplines consist of interactive graphics and interactive computing. A single user at an interactive terminal can create, design, analyze, and conduct parametric studies of earth-orbiting satellites, which represents a timely and cost-effective method during the conceptual design phase where various missions and spacecraft options require evaluation. Spacecraft concepts evaluated include microwave radiometer satellites, communication satellite systems, solar-powered lasers, power platforms, and orbiting space stations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 73
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    Preliminary results of the dynamics and control of the SCOLE system (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Spacecraft Control Laboratory Experiment (SCOLE) system is assumed to be comprised of three main parts: the Space Shuttle Orbiter with its center of mass located at 0(sub 1); the mast, treated as a 130 ft long beam, connected to the Shuttle at 0(sub 2) and to the reflector at 0(sub 3); and the reflector, considered to be a flat plate with its center of mass at 0(sub 4). In the analysis given here, the angular momentum of the entire system is evaluated at point 0(sub 1) and the dynamics include the lateral displacements of the beam.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 158-215
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  • 74
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    High time resolution measurements of rocket potential changes induced by electron beam emission (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The transient charging and photon emission from the vacuum chamber testing of the Cooperative High Altitude Rocket Gun Experiment are studied. Graphs of the mother-daughter voltage versus time and high time resolution data related to the return current to the vehicle are examined. It is observed that for average sounding rocket densities of 10 to the -6th torr the slope of the voltage rise of the rocket begins to flatten 40 microsec after the onset of electron beam emission, and for higher gas pressure the rocket reaches a maximum voltage of 25 or 30 microsec after the onset of electron beam emission. The data reveal that the return current mechanism for the higher gas pressure is through the sheath.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 75
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    Space station automation study: Automation requriements derived from space manufacturing concepts,volume 2 (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Automation reuirements were developed for two manufacturing concepts: (1) Gallium Arsenide Electroepitaxial Crystal Production and Wafer Manufacturing Facility, and (2) Gallium Arsenide VLSI Microelectronics Chip Processing Facility. A functional overview of the ultimate design concept incoporating the two manufacturing facilities on the space station are provided. The concepts were selected to facilitate an in-depth analysis of manufacturing automation requirements in the form of process mechanization, teleoperation and robotics, sensors, and artificial intelligence. While the cost-effectiveness of these facilities was not analyzed, both appear entirely feasible for the year 2000 timeframe.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-177862-VOL-2 , NAS 1.26:177862-VOL-2
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  • 76
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    Instrument pointing technology for spaceborne science missions of the 1990's (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The technologies which will permit sub-0.1 arcsec pointing accuracies on spacecraft in the 1990s are examined, along with the accuracies required and the current state of the art. Of particular interest are multi-mission spacecraft. Pointing accuracy can only be obtained by integrating the instrument (telescope) as part of the spacecraft, minimizing disturbances and using reaction wheels for pointing. The pointer could be isolated from complex spacecraft disturbances by soft mechanical mounts, e.g., inflatible tethers, guy-wire suspension and fluidic pointing systems. All design options are being explored for the Space Station, Earth Observing System, Co-orbiting platform and GEO platform spacecraft, and for near-term planetary spacecraft which will employ nuclear electric propulsion.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-2021
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  • 77
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    Secular solution for delta-V during spin rate change maneuvers of rigid body spacecraft (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Analytic expressions have been found for Euler's Equations of Motion and for the Eulerian Angles for both symmetric and near symmetric rigid bodies under the influence of arbitrary constant body-fixed torques. These solutions have been used to solve for the secular terms in the translational delta-V equations in inertial space. This secular delta-V solution is of interest in application to spinning spacecraft in that it describes the average direction of the delta-V of the spacecraft during a spin-up maneuver. Numerical integration of the governing differential equations has verified that the secular delta-V solution is valid for large time and is accurate in many physical situations including spin-up maneuvers of the Galileo spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-2011
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  • 78
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    A comparison of aerobraking and aerocapture vehicles for interplanetary missions (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Several design features for employing aerobraking and aerocapture techniques on interplanetary spacecraft are described. Recent studies have identified silica fabrics mounted on carbon composite ribs as suitable aerobraking spacecraft shield materials. Aerocapture is best achieved with a biconic aeroshell design, with the aeroshell supported by Al honeycomb panels and allowing primitive aerodynamic maneuverability. The aeroshell would be covered with thermal protection materials capable of elevated temperatures of magnitudes that are a function of the expected atmospheric density, the surface area, the entry speed, spacecraft mass and maneuverability. Both technologies are concluded ready for implementation and development costs are estimated for various missions, showing that aerocapture will provide for greater payload masses, except for a Jupiter mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-2057
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  • 79
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    Experimental measurement of material damping for space structures (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A procedure for the measurement of material damping is described. The free decay of free-free beams, when lofted into free fall in vacuum, was recorded. Tests were performed on aluminum, graphite/epoxy, and graphite/magnesium metal matrix materials. Specimens with a fundamental free-free frequency below the elaxation frequency showed a higher level of damping and of stress dependence than predicted. For 0 sub 8 laminates, a material damping ratio of 0.00055 was found for fequencies varying from 45 Hz to 237 Hz. The damping was neither stress nor frequency dependent. For 90 sub 8 laminates, the damping ratio ranged from 0.0055 to 0.0066 as frequency ranged from 42 Hz to 143 Hz. Damping ratios for 90 sub 8 specimens were independent of stress. Experimentally measured damping ratios for metal matrix specimens with unidirectional graphite fibers, magnesium matrix, and either titanium or magnesium foil, ranged from .00039 to .00099, depending upon the matrix material, frequency, and possibly the stress range involved.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AFWAL Vibration Damping 1984 Workshop Proceedings; 18 p
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  • 80
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    Users guide: Steady-state aerodynamic-loads program for shuttle TPS tiles (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A user's guide for the computer program that calculates the steady-state aerodynamic loads on the Shuttle thermal-protection tiles is presented. The main element in the program is the MITAS-II, Martin Marietta Interactive Thermal Analysis System. The MITAS-II is used to calculate the mass flow in a nine-tile model designed to simulate conditions duing a Shuttle flight. The procedures used to execute the program using the MITAS-II software are described. A list of the necessry software and data files along with a brief description of their functions is given. The format of the data file containing the surface pressure data is specified. The interpolation techniques used to calculate the pressure profile over the tile matrix are briefly described. In addition, the output from a sample run is explained. The actual output and the procedure file used to execute the program at NASA Langley Research Center on a CDC CYBER-175 are provided in the appendices.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85724 , NAS 1.15:85724
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  • 81
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    Space station automation study: Automation requirements derived from space manufacturing concepts. Volume 1: Executive summary (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The electroepitaxial process and the Very Large Scale Integration (VLSI) circuits (chips) facilities were chosen because each requires a very high degree of automation, and therefore involved extensive use of teleoperators, robotics, process mechanization, and artificial intelligence. Both cover a raw materials process and a sophisticated multi-step process and are therfore highly representative of the kinds of difficult operation, maintenance, and repair challenges which can be expected for any type of space manufacturing facility. Generic areas were identified which will require significant further study. The initial design will be based on terrestrial state-of-the-art hard automation. One hundred candidate missions were evaluated on the basis of automation portential and availability of meaning ful knowldege. The design requirements and unconstrained design concepts developed for the two missions are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-177862-VOL-1 , NAS 1.26:177862-VOL-1
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  • 82
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    On-orbit cryogenic storage and resupply (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Methods of integrating pressure control, liquid acquisition, and liquid transfer concepts for the Cryogenic Fluid Management Facility, a reusable test bed in the Shuttle cargo bay studying the efficient management of cryogens in space, are investigated. Significant design data and criteria for future subcritical cryogenic storage and transfer systems are presented. Technology requirements for liquid storage/supply systems, thermal control systems, and fluid transfer/resupply are addressed, and fluid and thermal analysis pertaining to receiver tank chilldown and no-vent fill of the receiver tank are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 83
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    Space station automation study. Volume 1: Executive summary. Autonomous systems and assembly (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of the Space Station Automation Study (SSAS) was to develop informed technical guidance for NASA personnel in the use of autonomy and autonomous systems to implement space station functions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-176860 , NAS 1.26:176860 , DE85-902179 , MCR-84-1878-VOL-1
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  • 84
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    Improved materials characterization for spacecraft applications (1984)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: A material outgassing test consists of an effusion cell, mass spectrometer, and thermally controlled quartz crystal microbalance (TQCM). The material sample is placed in the effusion cell at a predetermined temperature, and the sample is outgassed in a vacuum of 0.000001 torr range. The total outgassing mass as a function of time is determined with the TQCM which is cooled to LN2 temperatures. Based on the view factor of the TQCM, the total outgassed mass can be determined. The technique can be verified by comparing the results to the actual mass loss of the sample which is determined by hanging the diffusion cell from the Cohn microbalance. The mass spectrometer can be used to determine if there are any low molecular weight components outgassing, such a nitrogen which does not condense on the TQCM. After the material outgasses to a point of saturation, the effusion cell is closed off, and the TQCM is slowly heated to allow the condensed film to be broken down into its components. As the temperature is increased, the components evaporate from the surface at a different rate and can be detected with the mass spectrometer. The relative amount of each component is found by the change in frequency of the TQCM as the component evaporates. Hence, from this test, not only is isothermal kinetic data obtained, but the primary components can also be identified in terms of their molecular weight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Goddard Space Flight Center 13th Space Simulation Conf.; p 341
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  • 85
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    The 406 MHz ELT/EPIRBs (1984)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: Specifications for the COSPAS/SARSAT beacons are presented and related design considerations are discussed. Critical design aspects having significant impact on cost and performance are highlighted. Among these is the oscillator, whose frequency drift specifications require stabilization by ovens or digital control. Design options are presented and their impact on cost and performance assessed. Beacon designs developed to meet COSPAS/SARSAT specifications are shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 195-208
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  • 86
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    Second-generation Space Shuttle (1984)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: This is a review of an in-house study at the Langley Research Center to identify the technology requirements that are necessary to develop a second-generation Space Shuttle in the post 2000 time period. The study, Future Space Transportation System Study, had two main objectives: (1) to define the launch-vehicle concepts which best meet the needs and opportunities for improved space transportation economics and capabilities for a Space Shuttle replacement and (2) to extend the level of technology assessments with respect to previous advanced system studies, especially in the areas of stuctures, propellant tankage, thermal protection systems, aerodynamics, and operations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 87
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    A controllability-stabilizability result for the NASA-IEEE Spacecraft Control Laboratory Experiment (SCOLE) configuration (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A nonlinear distributed parameter model for the NASA-Institute of Electrical and Electronics Engineers' Spacecraft Control Laboratory Experiment (SCOLE) configuration is considered. A linear feedback control law is proposed that points the line of sight of the antenna to any given target direction and at the same time stabilizes the oscillations of the entire flexible configuration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, Spacecraft Control Laboratory Experiment (SCOLE) Workshop, 1984; p 104-132
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  • 88
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    Error analysis of system mass properties (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An attempt is made to verify the margin of system mass properties over values that are sufficient for the support of such other critical system requirements as those of dynamic control. System nominal mass properties are designed on the basis of an imperfect understanding of the mass and location of constituent elements; the effect of such element errors is to introduce net errors into calculated system mass properties. The direct measurement of system mass properties is, however, impractical. Attention is given to these issues in the case of the Galileo spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1610
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  • 89
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    Computer-aided controllability assessment of generic manned Space Station concepts (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: NASA's Concept Development Group assessment methodology for the on-orbit rigid body controllability characteristics of each generic configuration proposed for the manned space station is presented; the preliminary results obtained represent the first step in the analysis of these eight configurations. Analytical computer models of each configuration were developed by means of the Interactive Design Evaluation of Advanced Spacecraft CAD system, which created three-dimensional geometry models of each configuration to establish dimensional requirements for module connectivity, payload accommodation, and Space Shuttle berthing; mass, center-of-gravity, inertia, and aerodynamic drag areas were then derived. Attention was also given to the preferred flight attitude of each station concept.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1624
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  • 90
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    TRASYS/SSPSTA thermal modeling comparison (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The Thermal Radiation Analysis System (TRASYS) and the Simplified Shuttle Payload Analyzer (SSPTA) are applied for the purpose of comparison to the Solar Maximum Repair Mission (SMRM) and Astro-1/UVT (Ultraviolet Telescope), making use also of the System Improved Numerical Differencing Analyzer (SINDA). The majority of radiation conductances obtained from the TRASYS and SSPTA computer codes are shown to be within + or - 20 percent of each other, though the interchange factors associated with some crucial components of the system are located beyond this region. A sample model is also considered, which consists of an outer and an inner boxes with emisivities of 0.32 and 0.80 respectively. It is concluded that a thorough, methodical comparison between the two codes is necessary.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 840926
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  • 91
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    Air Revitalization System integration (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper presents a status review of Spacecraft Air Revitalization System (ARS) integration using regenerable techniques. The paper addresses concepts of integration of individual subsystems into an Air Revitalization System, as well as integration of components within subsystems. An ARS design is presented based on the Electrochemical Depolarized Carbon Dioxide Concentrator Subsystem, the Sabatier Carbon Dioxide Reduction Subsystem, the Static Feed Water Electrolysis Subsystem, a condensing Humidity Control Subsystem, and a Water Handling Subsystem to perform the functions of CO2 removal, CO2 reduction, O2 generation, humidity control and by-product water distribution, respectively. The paper also highlights the numerous advantages of this integration. Trace contaminant control and the nitrogen supply are not included in the ARS described in this paper.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 840959
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  • 92
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    Space Station Environmental Control and Life Support System architecture - Centralized versus distributed (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Both Centralized and Distributed approaches are being evaluated for the installation of Environmental Control and Life Support (ECLS) equipment in the Space Station. In the Centralized facility concept, integrated processing equipment is located in two modules with plumbing used to circulate ECLS services throughout the Station. The Distributed approach locates the ECLS subsystems in every module of the Space Station with each subsystem designed to meet its own module needs. This paper defines the two approaches and how the advantages and disadvantages of each are tied to the choice of Space Station architecture. Other considerations and evaluations include: crew movement, Station evolution and the ducting impact needed to circulate ECLS services from centrally located processing equipment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 840961
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  • 93
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    Environmental control and life support system analysis tools for the Space Station era (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the concept of a developing emulation, simulation, sizing, and technology assessment program (ESSTAP) which can be used effectively for the various functional disciplines (structures, power, ECLSS, etc.) beginning with the initial system selection and conceptual design processes and continuing on through the mission operation and growth phases of the Space Station for the purpose of minimizing overall program costs. It will discuss the basic requirements for these tools, as currently envisioned for the Environmental Control and Life Support System (ECLSS), identifying their intended and potential uses and applications, and present examples and status of several representative tools. The development and applications of a Space Station Atmospheric Revitalization Subsystem (ARS) demonstration model to be used for concent verification will also be discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 840956
    Format: text
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    NASA TECHNICAL REPORTS
  • 94
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    Space Station reference configuration description (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The data generated by the Space Station Program Skunk Works over a period of 4 months which supports the definition of a Space Station reference configuration is documented. The data were generated to meet these objectives: (1) provide a focal point for the definition and assessment of program requirements; (2) establish a basis for estimating program cost; and (3) define a reference configuration in sufficient detail to allow its inclusion in the definition phase Request for Proposal (RFP).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-87493 , JSC-19989 , NAS 1.15:87493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 95
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    SARSAT 121.5/243 MHz technical evaluation (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NOAA 8 SARSAT system performance was tested at 121.5/243 MHz to measure detection probability, detection threshold, location accuracy, ambiguity resolution, and multiple access capacity. Detection probability exceeds 0.95 for a single satellite pass. Detection threshold margin varies from 2 dB (243 MHz, incoherent) to 20 dB (121.5, coherent). Position location error is 20 km 68% of the time. Ambiguity is resolved 75% of the time. The system can locate 10 separate test signals.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 451-460
    Format: text
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    NASA TECHNICAL REPORTS
  • 96
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    SARSAT 406 MHz system technical evaluation (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The location accuracy, access to spacecraft, uplink margin, and interference problems of the COSPAS-SARSAT system are reviewed. Over 90% of positions are accurate to within 5 km, in local mode, slightly worse in global mode. The random access parameters of SARSAT provide for the location of up to 90 beacons with a uniform distribution in the satellite visibility circle (2600 km radius). The ratio of messages correctly processed on board to messages transmitted to the satellite is 0.8, increasing as number of beacons decreases. Interference, particularly over western Europe and the United States degrades performance, but sources can be located.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: CNES Satellite Aided Search and Rescue. Exptl. Results and Operational Prospects; p 429-440
    Format: text
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    NASA TECHNICAL REPORTS
  • 97
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    Space station automation study. Volume 1: Executive summary. Autonomous systems and assembly (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The space station automation study (SSAS) was to develop informed technical guidance for NASA personnel in the use of autonomy and autonomous systems to implement space station functions. The initial step taken by NASA in organizing the SSAS was to form and convene a panel of recognized expert technologists in automation, space sciences and aerospace engineering to produce a space station automation plan.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-171514 , NAS 1.26:171514 , MCR84-1878-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 98
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    Space station automation study. Volume 2: Technical report. Autonomous systems and assembly (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application of automation to space station functions is discussed. A summary is given of the evolutionary functions associated with long range missions and objectives. Mission tasks and requirements are defined. Space station sub-systems, mission models, assembly, and construction are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-171515 , NAS 1.26:171515 , MCR84-1878
    Format: application/pdf
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  • 99
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    Definition of ground test for Large Space Structure (LSS) control verification (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An overview for the definition of a ground test for the verification of Large Space Structure (LSS) control is given. The definition contains information on the description of the LSS ground verification experiment, the project management scheme, the design, development, fabrication and checkout of the subsystems, the systems engineering and integration, the hardware subsystems, the software, and a summary which includes future LSS ground test plans. Upon completion of these items, NASA/Marshall Space Flight Center will have an LSS ground test facility which will provide sufficient data on dynamics and control verification of LSS so that LSS flight system operations can be reasonably ensured.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86495 , NAS 1.15:86495
    Format: application/pdf
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  • 100
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    NASA/MSFC ground experiment for large space structure control verification (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Marshall Space Flight Center has developed a facility in which closed loop control of Large Space Structures (LSS) can be demonstrated and verified. The main objective of the facility is to verify LSS control system techniques so that on orbit performance can be ensured. The facility consists of an LSS test article which is connected to a payload mounting system that provides control torque commands. It is attached to a base excitation system which will simulate disturbances most likely to occur for Orbiter and DOD payloads. A control computer will contain the calibration software, the reference system, the alignment procedures, the telemetry software, and the control algorithms. The total system will be suspended in such a fashion that LSS test article has the characteristics common to all LSS.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86496 , NAS 1.15:86496
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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