Technology for large space systems: A special bibliography with indexes

This bibliography lists 460 reports, articles, and other documents introduced into the NASA scientific and technical information system between January 1, 1968 and December 31, 1978. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design in the area of the Large Space Systems Technology (LSST) Program. Subject matter is grouped according to systems, interactive analysis and design, structural concepts, control systems, electronics, advanced materials, assembly concepts, propulsion, and flight experiments

Type synthesis and static balancing of a class of deployable mechanisms

This thesis addresses the type synthesis and static balancing of a class of deployable mechanisms, which can be applied in applications in many areas including aerospace and daily life. Novel construction methods are proposed to obtain the deployable mechanisms. First, the type synthesis of the foldable 8-revolute joint (R) linkages with multiple modes is presented. Two types of linkages are constructed by connecting planar 4R linkages and spherical 4R linkages. The obtained linkages can be folded into two layers or four layers, and have multiple motion modes. A spatial triad is also adopted to build single-loop linkages, then the single-loop linkages are connected using spherical (S) joints or RRR chains to obtain deployable polyhedral mechanisms (DPMs). The DPMs have only 1- degree-of-freedom (DOF) when deployed, and several mechanisms with 8R linkages and 10R linkages have multiple motion modes and can switch modes through transition positions. In addition, when connecting single-loop linkages using half the number of the RRR chains, the prism mechanisms obtain an additional 1-DOF rotation mode. Furthermore, the DPMs are developed into statically balanced mechanisms. The geometric static balancing approaches for the planar 4R parallelogram linkages, planar manipulators, spherical manipulators and spatial manipulators are developed so that the mechanisms can counter gravity while maintaining the positions of the mechanisms. Only springs are used to design the statically balanced system readily, with almost no calculation. A novel numerical optimization approach is also introduced which adopts the sum of squared differences of the potential energies as the objective function. Using the proposed static balancing approaches, the 8R linkages and the DPMs presented in this thesis can be statically balanced

Optimization of the wing-fuselage interface of the UAS30-P2

This thesis presents the optimization of the spar connector of the aircraft UAS30-P2. The spar connector is the primary airframe structure of the aircraft. It connects the all flight surfaces of the aircraft with the fuselage. The structure is made up of extruded aluminium bars. The spar connector supports all aerodynamic loads and inertial loads of the aircraft. These loads are transmitted through the carbon fibre reinforced polymer (CFRP) spar of the aircraft. Since the spar connector supports all the aerodynamic and inertial loads of the aircraft, it is the most crucial component in the entire Unmanned aerial vehicle (UAV). Thus, it needs to be strong and stiff enough to withstand the exceptional circumstances in which the aircraft must operate. The thesis reviews both, the choice of materials and shape optimization of the spar connector, achieving a more efficient structure. The choice of material is reviewed by studies conducted on the available materials for this purpose. The optimization is carried out using the studies and the results of the Finite element analysis (FEA) of the component. Later the optimized Finite element (FE) model of wing interface structure is analyzed based on the Finite element method results. The results were then compared with the analysis results of the original FE model of wing interface structure of UAS30-P2. As a result, it was observed an appreciable reduction accompanied by the improvement in the performance characteristics is of the metallic spar connector of UAS30-P2.Esta tese apresenta a otimização do conector da longarina principal da aeronave UAS30-P2. O conector da longarina principal é a estrutura primária da aeronave. Conecta todas as superfícies de voo da aeronave com a fuselagem. A estrutura é composta por barras de alumínio extrudido. O conector da longarina principal suporta todas as cargas aerodinâmicas e cargas inerciais da aeronave. Essas cargas são transmitidas através da longarina principal de polímero reforçado com fibra de carbono (CFRP) da aeronave. Como o conector da longarina principal suporta todas as cargas aerodinâmicas e inerciais da aeronave, é o componente mais crucial em todo o veículo aéreo não tripulado (UAV). Sendo assim, ele precisa ser forte e rígido o suficiente para suportar as circunstâncias excecionais em que a aeronave deve operar. A tese analisa tanto a escolha dos materiais quanto a otimização da forma do conector longarina principal, conseguindo uma estrutura mais eficiente. A escolha do material é revisada por estudos realizados sobre os materiais disponíveis para esse fim. A otimização é realizada utilizando os estudos e os resultados da análise FE do componente. Posteriormente, a estrutura otimizada é analisada com base nos resultados do método dos elementos finitos. Os resultados foram então comparados com os resultados da análise da estrutura original. Como resultado, foi observado uma redução apreciável, acompanhada pela melhoria nas características de performance do conector metálico da longarina principal do UAS30-P2

Technology for large space systems: A bibliography with indexes (supplement 14)

This bibliography lists 645 reports, articles and other documents introduced into the NASA scientific and technical information system between July 1, 1985 and December 31, 1985. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design according to system, interactive analysis and design, structural and thermal analysis and design, structural concepts and control systems, electronics, advanced materials, assembly concepts, propulsion, and solar power satellite systems

Space station systems: A bibliography with indexes (supplement 2)

This bibliography lists 904 reports, articles and other documents introduced into the NASA scientific and technical information system between July 1, 1985 and December 31, 1985. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design according to system, interactive analysis and design, structural and thermal analysis and design, structural concepts and control systems, electronics, advanced materials, assembly concepts, propulsion, and solar power satellite systems. The coverage includes documents that define major systems and subsystems, servicing and support requirements, procedures and operations, and missions for the current and future space station

The 29th Aerospace Mechanisms Symposium

The proceedings of the 29th Aerospace Mechanisms Symposium, which was hosted by NASA Johnson Space Center and held at the South Shore Harbour Conference Facility on May 17-19, 1995, are reported. Technological areas covered include actuators, aerospace mechanism applications for ground support equipment, lubricants, pointing mechanisms joints, bearings, release devices, booms, robotic mechanisms, and other mechanisms for spacecraft

33rd Aerospace Mechanisms Symposium

The proceedings of the 33rd Aerospace Mechanisms Symposium are reported. JPL hosted the conference, which was held at the Pasadena Conference and Exhibition Center, Pasadena, California, on May 19-21, 1999. Lockheed Martin Missiles and Space cosponsored the symposium. Technology areas covered include bearings and tribology; pointing, solar array and deployment mechanisms; orbiter/space station; and other mechanisms for spacecraft

Space station systems: A bibliography with indexes (supplement 6)

This bibliography lists 1,133 reports, articles, and other documents introduced into the NASA scientific and technical information system between July 1, 1987 and December 31, 1987. Its purpose is to provide helpful information to the researcher, manager, and designer in technology development and mission design according to system, interactive analysis and design, structural and thermal analysis and design, structural concepts and control systems, electronics, advanced materials, assembly concepts, propulsion, and solar power satellite systems. The coverage includes documents that define major systems and subsystems, servicing and support requirements, procedures and operations, and missions for the current and future Space Station

Study of the different alternatives for the commercial construction process of FOWT concept Windcrete

The aim of this thesis is to gain some insight on the constructability of a monolithic concrete spar buoy concept for floating offshore wind turbines: Windcrete