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A passive high altitude deorbiting strategy

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Figure

Figure 1: Artist's impression of a CubeSat with deployed reflective deorbiting balloon (image credits: ESA, Aalborg University)
Figure 2.
Figure 3: σ as a function of balloon diameter for a total spacecraft mass of 1.3 kg.
Figure 4: Phase plane diagram for a spacecraft with 15,000 km semi-major axis and a coefficient of reflectivity of cR = 1.9 for three different values of σ
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