A. Besse
info
Please Note
<p>This page displays the records of the person named above and is not linked to a unique person identifier. This record may need to be merged to a profile.</p>
3 records found
1
Conference paper
(2026)
-
A. Mazzoli, A. Besse, J. Bouwmeester, I. Khan, Jérôme Loicq, P. Piron, R. Saathof, I. Sigusch, G. Terrasa, More Authors
The optical design layout of a single-spacecraft nulling interferometer is presented here as part of an ESA-initiated study to explore the design parameters and performance of an interferometric concept based on a single spacecraft with multiple
sub-apertures. Launch constraints drive the ray-traced model to cover the entire optical chain, from the telescope entrance to the null output after the recombination scheme. A trade-off among several telescope architectures led to the choice of a compact two-mirror solution consisting of four 2.5m diameter telescopes arranged in a linear configuration with an extended baseline. Optical performance at the null output is evaluated, confirming compatibility with starlight suppression
targets and establishing the key figures of merit for the interferometer. This work presents the first integrated optical design of the mission concept, laying the groundwork for future iterations that include mechanical, thermal, and control aspects. ...
sub-apertures. Launch constraints drive the ray-traced model to cover the entire optical chain, from the telescope entrance to the null output after the recombination scheme. A trade-off among several telescope architectures led to the choice of a compact two-mirror solution consisting of four 2.5m diameter telescopes arranged in a linear configuration with an extended baseline. Optical performance at the null output is evaluated, confirming compatibility with starlight suppression
targets and establishing the key figures of merit for the interferometer. This work presents the first integrated optical design of the mission concept, laying the groundwork for future iterations that include mechanical, thermal, and control aspects. ...
The optical design layout of a single-spacecraft nulling interferometer is presented here as part of an ESA-initiated study to explore the design parameters and performance of an interferometric concept based on a single spacecraft with multiple
sub-apertures. Launch constraints drive the ray-traced model to cover the entire optical chain, from the telescope entrance to the null output after the recombination scheme. A trade-off among several telescope architectures led to the choice of a compact two-mirror solution consisting of four 2.5m diameter telescopes arranged in a linear configuration with an extended baseline. Optical performance at the null output is evaluated, confirming compatibility with starlight suppression
targets and establishing the key figures of merit for the interferometer. This work presents the first integrated optical design of the mission concept, laying the groundwork for future iterations that include mechanical, thermal, and control aspects.
sub-apertures. Launch constraints drive the ray-traced model to cover the entire optical chain, from the telescope entrance to the null output after the recombination scheme. A trade-off among several telescope architectures led to the choice of a compact two-mirror solution consisting of four 2.5m diameter telescopes arranged in a linear configuration with an extended baseline. Optical performance at the null output is evaluated, confirming compatibility with starlight suppression
targets and establishing the key figures of merit for the interferometer. This work presents the first integrated optical design of the mission concept, laying the groundwork for future iterations that include mechanical, thermal, and control aspects.
Conference paper
(2026)
-
A. Besse, I. Khan, A. Mazzoli, J. Bouwmeester, P. Piron, R. Saathof, I. Sigusch, N. Bhattacharya, Jérôme Loicq, More Authors
One of the objectives of modern astronomy is the characterization of terrestrial exoplanets orbiting Sun-like stars in the mid-infrared, where instruments face requirements that can only be overcome by nulling interferometry. Particularly, optical effects such as polarization aberrations require careful attention for they deteriorate the null depth. Using the optical design of the Exoplanet Explorer concept study, we simulate the influence of polarization aberrations over the 3–20μm band, analyze their impact on the null depth and propose multiple compensation strategies for polarization aberrations. Furthermore, we present our nulling interferometry test bench, where we will experimentally investigate polarization aberrations in the beam combiner and phase shifter to provide more insights into the required polarization errors. These results will be used to implement polarization control subsystems in our 4-beams broadband nulling interferometry test bench CAPIBARA (Combining 4 APertures for mid-Infrared Broadband Analysis of Rocky-exoplanets Atmospheres).
...
One of the objectives of modern astronomy is the characterization of terrestrial exoplanets orbiting Sun-like stars in the mid-infrared, where instruments face requirements that can only be overcome by nulling interferometry. Particularly, optical effects such as polarization aberrations require careful attention for they deteriorate the null depth. Using the optical design of the Exoplanet Explorer concept study, we simulate the influence of polarization aberrations over the 3–20μm band, analyze their impact on the null depth and propose multiple compensation strategies for polarization aberrations. Furthermore, we present our nulling interferometry test bench, where we will experimentally investigate polarization aberrations in the beam combiner and phase shifter to provide more insights into the required polarization errors. These results will be used to implement polarization control subsystems in our 4-beams broadband nulling interferometry test bench CAPIBARA (Combining 4 APertures for mid-Infrared Broadband Analysis of Rocky-exoplanets Atmospheres).
Conference paper
(2026)
-
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.