1,721,012 research outputs found
Structural performance of a multifunctional spacecraft structure based on plastic lithium-ion batteries
No full textA multifunctional structure reduces the mass and volume of a spacecraft through the removal of parasitic components of a functional structure, such as the purely structural “packaging” of the battery. Commercially available cells, of the plastic lithium-ion type, may be incorporated into structural sandwich panels, eliminating the need for a secondary structure in the battery subsystem. Locating the cells in the structure also removes them from the bus, which reduces the volume of the craft and, consequently, reduces the mass of the primary structure. Although the batteries studied in this work exhibited low mechanical properties, this paper will show that, by placing the cells carefully within the sandwich panel, structural performance is not compromised. Finite element models show a reduction in peak stress and deformation in multifunctional panels, compared to a conventional design, when a favourable layout is selected. Less conclusive results for peak acceleration, however, suggest that this type of multifunctional structure may not be appropriate for all applications. Comparison of the finite element modelling technique with a real panel's behaviour shows that the deformation and stress predicted by the model is consistent with reality, whilst the acceleration is reliable for low frequencies.<br/
Satelitte multifunctional power structure: feasibility and mass savings
No full textA multi-functional structure saves mass from a spacecraft by incorporating other functional subsystems into the structure. By using the structural properties of a non-structural element, inert structure may be eliminated, and the requirement to allot internal volume to the subsystem in question is removed.The current paper describes a multi-functional structure based on the secondary power system. By using commercially available plastic lithium-ion cells to form the core of a sandwich panel, inert mass is eliminated from both the structure and from the battery enclosure. The feasibility of the proposed multi-functional structure is demonstrated though vibration testing on a single cell, and the successful manufacture of a test panel.The work goes on to quantify the potential mass savings that may be achieved by using a multi-functional structure of this type. By varying a set of spacecraft attributes, the study identifies that small spacecraft with high power requirements have the potential to gain the most benefit from using a multi-functional structure of this type
Design of a multifunctional spacecraft structure using plastic lithium-ion batteries
No full textThe technology of multifunctional structures, when applied to spacecraft batteries, allows mass and volume to be saved through the removal of parasitic components of the battery. Electrochemical cells, in this case commercially available cells of the plastic lithium-ion type, may be incorporated directly into structural sandwich panels, removing the need for a secondary structure (i.e. the battery enclosure and its interface) to mount the cells. Placing the cells within the structure also removes them from the bus, reducing its volume and thus further reducing overall mass. Notwithstanding the relatively low mechanical properties exhibited by the batteries that have been investigated during our work, this paper shall demonstrate how, by optimizing the layout of the cells within a panel, adequate structural performance may be maintained. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc
Multifunctional power structures and related thermal issues
No full textMultifunctional spacecraft power structures are an incorporation of energy storage and generation into structures on a spacecraft. For the mass and volume saving benefits to be realised, the technology must be shown to be viable throughout the spacecraft's lifetime. Firstly, commercially available batteries where built into a structural panel and tested to determine the battery's capability to withstand the manufacturing cycle and the effect upon the mechanical characteristics of the panel. Secondly, a mathematical model was created to determine the temperatures a battery would experience in various earth orbits. It was found that spacecraft in most low earth orbits will require thermal control and that the addition of a phase change material is a feasible control solution. Copyright © 2008 by ASME
Multifunctional structure technologies for satellite applications
No full textConventional spacecraft subsystems are designed and manufactured separately, and are integrated only during the final stages of satellite development. This requires containers for the subsystems' hardware, mechanical interfaces, panels, frames, bulky wire harnesses, etc., which add considerable mass and volume. As all subsystems are generally secured to the structure, the multifunctional structure approach aims at merging these elements into the structure, so that the structure also carries out some of the typical functions of the subsystems (e.g. electrical energy storage). The main advantages are as follows: (i) removal of the bolted mechanical interfaces and most of the subsystems' containers; (ii) reduction of the satellite structure mass, as the strength of the parts of the subsystem imbedded into the structure are exploited, and substitute purely structural parts; (iii) reduction of the overall satellite volume, as elements such as battery packs or electronic harnesses can be built into the structure's volume. There are still issues that need to be addressed to allow a wider utilization of multifunctional structures. However, the development of concurrent engineering approaches, to carry out an integrated design of the spacecraft, together with advances in the subsystems' disciplines, will help to promote the further diffusion of multifunctional structures. © 2007 SAGE Pulications
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