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  • 1
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    Systems design and comparative analysis of large antenna concepts (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Conceptual designs are evaluated and comparative analyses conducted for several large antenna spacecraft for Land Mobile Satellite System (LMSS) communications missions. Structural configurations include trusses, hoop and column and radial rib. The study was conducted using the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) system. The current capabilities, development status, and near-term plans for the IDEAS system are reviewed. Overall capabilities are highlighted. IDEAS is an integrated system of computer-aided design and analysis software used to rapidly evaluate system concepts and technology needs for future advanced spacecraft such as large antennas, platforms, and space stations. The system was developed at Langley to meet a need for rapid, cost-effective, labor-saving approaches to the design and analysis of numerous missions and total spacecraft system options under consideration. IDEAS consists of about 40 technical modules efficient executive, data-base and file management software, and interactive graphics display capabilities.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Antenna Systems Technol., Pt. 1; p 157-174
    Format: text
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  • 2
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    Systems design and analysis of the microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Systems design and analysis data were generated for microwave radiometer spacecraft concept using the Large Advanced Space Systems (LASS) computer aided design and analysis program. Parametric analyses were conducted for perturbations off the nominal-orbital-altitude/antenna-reflector-size and for control/propulsion system options. Optimized spacecraft mass, structural element design, and on-orbit loading data are presented. Propulsion and rigid-body control systems sensitivities to current and advanced technology are established. Spacecraft-induced and environmental effects on antenna performance (surface accuracy, defocus, and boresight off-set) are quantified and structured material frequencies and modal shapes are defined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: The Microwave Radiometer Spacecraft; p 69-94
    Format: text
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  • 3
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    Future large space systems opportunities: A case for space-to-space power? (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Applications and options for beaming power to near-earth space users from a central space power platform are examined. The cost effectiveness of on-board versus remote power transfer is examined for orbital transfer propulsion systems. Performance characteristics are projected for advanced power generation, transmission, and receiver systems for the 1990's. Major technological development needs are identified with particular emphasis on large space systems technology.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: Large Space Systems Technol., Vol. 1; p 507-531
    Format: text
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  • 4
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    Mathematical synthesization of complex structures (1984)
    In:  CASI
    Details
    Publication Date: 2006-04-09
    Description: A mathematical synthesization approach for rapidly modeling and analyzing complex structures comprised of hundreds or thousands of repeating individual structural members, interconnecting hardware, and other components was described. The techniques are applicable to any structure with repeating structural members. The capabilities are embodied within the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) computer-aided design system. IDEAS has a full range of integrated spacecraft modeling, design, analysis, performance, and cost estimating capabilities which include about 40 technical program and executive, data base, and file management systems. With IDEAS, a single user at an interactive terminal can create, design, analyze, and conduct parametric studies of Earth orbiting spacecraft in a timely, cost-efficient manner. The system is particularly useful in the conceptual design phases of advanced space missions when a multiplicity of concepts must be evaluated. The IDEAS interactive finite-element modeling capabilities are discussed. The mathematical synthesization programs were structured not only to provide a detailed finite-element model of the structure but also to automatically perform the many auxiliary computations needed to analyze the spacecraft in its orbital operational environment.
    Keywords: NUMERICAL ANALYSIS
    Type: Computer-Aided Geometry Modeling; p 389-398
    Format: text
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  • 5
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    Dynamic performance of several large antenna concepts (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Four antenna concepts the box truss, tetrahedral truss, wrap-radial rib, and hoop and column antenna were examined for the dynamic performance when subjected to an operational environment. Space applications for the concepts are numerous; however, the land mobile satellite system (LMSS) was chosen as a baseline study and its operational constraints are applied to each concept. The dynamic response of each concept is examined for structural displacement and structural damping effects. The necessity of a control system for vibrational displacement reduction is examined along with a comparison of the relative merits of each antenna concept.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 141-163
    Format: text
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  • 6
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    Maneuvering of large flexible space antennas using optimal discrete-time controllers (1984)
    In:  Other Sources
    Details
    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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  • 7
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    Space systems computer-aided design technology (1984)
    In:  Other Sources
    Details
    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
    Format: text
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  • 8
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    Interactive modeling, design and analysis of large spacecraft (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An efficient computer aided design and analysis capability applicable to large space structures was developed to relieve the engineer of much of the effort required in the past. The automated capabilities can be used to rapidly synthesize, evaluate, and determine performance characteristics and costs for future large spacecraft concepts. The interactive design and evaluation of advanced spacecraft program (IDEAS) is used to illustrate the power, efficiency, and versatility of the approach. The coupling of space environment modeling algorithms with simplified analysis and design modules in the IDEAS program permits rapid evaluation of completing spacecraft and mission designs. The approach is particularly useful in the conceptual design phase of advanced space missions when a multiplicity of concepts must be considered before a limited set can be selected or more detailed analysis. Integrated spacecraft systems level data and data files are generated or subsystems and mission reexamination and/or refinement and for more rigorous analyses.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Computational Aspects of Heat Transfer in Struct.; p 199-219
    Format: application/pdf
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  • 9
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    Thermal modeling and analysis of structurally complex spacecraft using the IDEAS system (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Large antenna satellites of unprecedented sizes are needed for a number of applications. Antenna diameters on the order of 50 meters and upward are required. Such antennas involve the use of large expanses of lattice structures with hundreds or thousands of individual connecting members. In connection with the design of such structures, the consideration of thermal effects represents a crucial factor. Software capabilities have emerged which are coded to include major first order thermal effects and to purposely ignore, in the interest of computational efficiency, the secondary effects. The Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) is one such system. It has been developed for an employment in connection with thermal-structural interaction analyses related to the design of large structurally complex classes of future spacecraft. An IDEAS overview is presented. Attention is given to a typical antenna analysis using IDEAS, the thermal and loading analyses of a tetrahedral truss spacecraft, and ecliptic and polar orbit analyses.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1459
    Format: text
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  • 10
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    A computer program to calculate radiating viscous stagnation streamline flow with strong blowing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program (program LEE) has been developed to calculate the fully coupled solution of the radiating viscous stagnation streamline flow with strong blowing. The report describes the digital computer program, including FORTRAN IV listing, flow charts, instructions for the user, and a test case with input and output. Program LEE is available through COSMIC.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-2805 , L-8918
    Format: application/pdf
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