A Novel Structural Spacecraft Application of Metal-Polymer
6.1 Future Work
Chapter 5, has outlined the principles and concepts used in the mechanical design of an octahedral inflatable and rigidisable truss based structure that will be demonstrated on the RemoveDEBRIS mission. Robustness has been required from the presented structure as it must undergo an initial impact from a capturing net and then it must sustain pro-longed exposure to atmospheric drag while deorbiting is taking place. During the initial part of the mission, the structure will be pressurised. The critical axial load and bend-ing moments for rigidised pressurised and unpressurised cylinders has been calculated and the de-pressurisation rates have been observed experimentally for different fitting designs.
The development of a novel packaging method for triangular segments has been outlined from a practical point of view. The initial deployment test of the entire structure has been shown.
6.1 Future Work
The work presented in this document has accomplished the proposed objectives, however, the presented work may be further improved and expanded in the areas presented in this section.
As shown in the literature review and in the experiments, that were conducted in this work, the experimental value for Young’s modulus of thin aluminium foils deviates from the industry standard value for bulk aluminium of 68.9 GPa. The tensile testing method that was presented here is not suitable for the measuring the Young’s modulus in aluminium foils or laminates. Further studies are recommended to verify if the deviation in the measured modulus value is also affected by a possible change in the Poisson’s ratio of very thin foils and if rolling the typically ductile aluminium or laminates foils during stowage induces initial strains in the material. Other metal foils or laminates that are based on steels or lead may be tested.
A series of tensile and cantilever experiments may be conducted on thin aluminium samples, ranging from foils with a thickness of under 10 µm up to plates with a thickness of 1 mm.
By doing these tests it is possible to record whether the samples have been previously rolled and the cut-off thickness at which the modulus of elasticity starts to diverge. The
6.1. Future Work
numerical model for the foil may be applied to the thinnest sample that complies with the standard aluminium values. This will allow the experimenter to compare accurately the creasing behaviour of a material coupon form initially high curvatures to the final fold curvature.
The material models presented in this work are based on a simple bi-linear profile. The tensile tests have shown that the behaviour of the laminate is significantly more complex.
A tri-linear approach will capture this behaviour more accurately. For large curvatures, the addition of moment due to the self-weight of the coupon may be included.
The work presented in Chapter 4 considers the first step of the folding and rigidisation process, i.e. where folds are introduced in a laminate. In the future it is intended to use a similar approach to derive a set of governing equations for the deployment and rigidisation of a foil and three-ply metal-polymer-metal laminate fold. In this second model the shear effects must be considered.
Considering previous work and material backlash models (Greschik and Mikulas, 1996;
Takahashi and Shiono, 1991) and the application of metal-based laminate, the deployment and rigidisation steps may be derived in terms of the localised curvature κ(si). This addi-tional work will show the extent of residual creases post rigidisation creases in the form of geometrical imperfections. As the geometric imperfections are known, they may be mod-elled in an FEA program, thus simplifying the buckling analysis of a deployed and rigidised metal laminate cylinder.
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