FW
F.D. Wilting
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1
Conference paper
(2026)
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G. Terrasa, J. Bouwmeester, F.D. Wilting, A. Besse, Jérôme Loicq, I. Khan, R. Saathof, I. Sigusch, P. Piron, More Authors
The mechanical and thermal design of a single spacecraft nulling interferometer is presented as part of a new study initiated by the European Space Agency to explore the design parameters and performance of an interferometric concept
based on a single spacecraft with multiple sub-apertures. Launch constraints impose strict mass and volume limitations and necessitate secondary mirror deployment. Deployment concepts were evaluated through comparison and modal
analysis. Due to thermal considerations, a preliminary thermal model was also developed. Results emphasize the necessity for a multi-layer sunshield and highly reflective materials to achieve the required temperature range.
Temperature gradients across the payload and their effects on deformations have been identified as key factors for future investigation. This study provides the first integrated thermo-mechanical concept for the interferometer, laying the
groundwork for further analysis and trade-off studies in later phases. ...
based on a single spacecraft with multiple sub-apertures. Launch constraints impose strict mass and volume limitations and necessitate secondary mirror deployment. Deployment concepts were evaluated through comparison and modal
analysis. Due to thermal considerations, a preliminary thermal model was also developed. Results emphasize the necessity for a multi-layer sunshield and highly reflective materials to achieve the required temperature range.
Temperature gradients across the payload and their effects on deformations have been identified as key factors for future investigation. This study provides the first integrated thermo-mechanical concept for the interferometer, laying the
groundwork for further analysis and trade-off studies in later phases. ...
The mechanical and thermal design of a single spacecraft nulling interferometer is presented as part of a new study initiated by the European Space Agency to explore the design parameters and performance of an interferometric concept
based on a single spacecraft with multiple sub-apertures. Launch constraints impose strict mass and volume limitations and necessitate secondary mirror deployment. Deployment concepts were evaluated through comparison and modal
analysis. Due to thermal considerations, a preliminary thermal model was also developed. Results emphasize the necessity for a multi-layer sunshield and highly reflective materials to achieve the required temperature range.
Temperature gradients across the payload and their effects on deformations have been identified as key factors for future investigation. This study provides the first integrated thermo-mechanical concept for the interferometer, laying the
groundwork for further analysis and trade-off studies in later phases.
based on a single spacecraft with multiple sub-apertures. Launch constraints impose strict mass and volume limitations and necessitate secondary mirror deployment. Deployment concepts were evaluated through comparison and modal
analysis. Due to thermal considerations, a preliminary thermal model was also developed. Results emphasize the necessity for a multi-layer sunshield and highly reflective materials to achieve the required temperature range.
Temperature gradients across the payload and their effects on deformations have been identified as key factors for future investigation. This study provides the first integrated thermo-mechanical concept for the interferometer, laying the
groundwork for further analysis and trade-off studies in later phases.