Orbital Demonstration of Gossamer Structure Shape Estimation using Time-of-Flight Camera System

Kuwahara, Toshinori; Pala, Alperen; Potier, Adrien; Shibuya, Yoshihiko; Sato, Yuji; Fujita, Shin; Suzuki, Daisuke; Kaneko, Tetsuya

doi:10.1109/sii52469.2022.9708770

Cited by 1 publication

(1 citation statement)

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“…This camera system collects distance information to the sail surface and downlinks the data to the ground to allow analyses to obtain better insight into the three-dimensional dynamic behavior of the boom and drag sail in space [20]. In fact, we reported the results of our estimation of the shape of the SDOM when deployed in space in 2022 [21]. Now, the SDOM film with the two missing connections exhibited a characteristic behavior that was observed by the onboard cameras.…”

Section: Trouble Of Sdommentioning

confidence: 83%

De-Orbit Maneuver Demonstration Results of Micro-Satellite ALE-1 with a Separable Drag Sail

et al. 2023

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ALE-1, a micro-satellite created for the demonstration of artificial shooting stars, required orbital descent before mission execution due to safety aspects in orbit. ALE-1 utilized a drag sail called SDOM (Separable De-Orbit Mechanism) for a passive de-orbit maneuver, which was successfully completed, lowering the orbit from about 500 km down to about 400 km. This paper summarizes the detailed history of satellite operation and the results of the de-orbit maneuver demonstration during the past three years. Although the SDOM sail faced difficulty in keeping the desired deployed shape of the drag sail due to mechanical troubles, by letting the sail be a drag flag instead, it could still deliver a meaningful de-orbit performance to allow the satellite to successfully lower the orbit as planned. The de-orbit effect of the drag flag was evaluated using comparisons between orbit propagation simulations and the actual orbit transition flight data provided in the form of TLE (Two-Line Element) sets. Through this study, it is demonstrated that the SDOM can provide orbit transfer capabilities for satellites. Furthermore, the de-orbit performance of the drag flag can be evaluated, which could be an important reference for the future implementation of de-orbit devices to solve space debris problems.

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Section: Trouble Of Sdommentioning

confidence: 83%