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Proceedings Paper • Open Access

Solar orbiter/PHI full disk telescope entrance window mechanical mount
Author(s): J. Barandiaran; P. Zuluaga; A. B. Fernandez; I. Vera; D. Garranzo; A. Nuñez; L. Bastide; M. T. Royo; A. Alvarez

Paper Abstract

PHI is a diffraction limited, wavelength tunable, quasi-monochromatic, and polarization sensitive imager. These capabilities are needed to infer the magnetic field and line-of-sight (LOS) velocity of the region targeted by the spacecraft (spacecraft (S/C)).

PHI will consist of two telescopes: The High Resolution Telescope (HRT)[1] and the Full Disk Telescope (FDT). The HRT and the FDT will view the Sun through entrance windows located in the S/C heat shield. These windows act as heat rejecting filters with a transmission band of about 30 nm width centered on the science wavelength, such that the total transmittance (integral over the filter curve weighted with solar spectrum, including white leakage plus transmission profile of the pass band) does not exceed 4% of the total energy falling onto the window [2][3].

The HREW filter has been designed by SELEX in the framework of an ESA led technology development activity under original ESTEC contract No. 20018/06/NL/CP[4], and extensions thereof. For FDT HREW SLEX will provide the windows and it coatings.

The HREW consists of two parallel-plane substrate plates (window 1 & window 2)[5] made of SUPRASIL 300 with a central thickness of 9 mm and a wedge of 30 arcsec each. These two substrates are each coated on both sides with four different coatings. These coatings and the choice of SUPRASIL help to minimize the optical absorptivity in the substrate and to radiatively decouple the HREW, which is expected to run at high temperatures during perihelion passages, from the PHI instrument cavity.

The temperature distribution of the HREW is driven by two main factors: the mechanical mounting of the substrates to the feedthrough, and the radiative environment within the heat-shield/feedthrough assembly.

The mechanical mount must ensure the correct integration of both suprasil substrates in its correct position and minimize the loads in windows due to thermal induced deformations and launching vibration environment.

All the subsystem must survive to a launching vibration environment and fulfill optical requirements in an environmental conditions according o its position in the external part of the spacecraft with a pressure of 0.0013Pa and a temperature -163°C<T<230°C.

Paper Details

Date Published: 17 November 2017
PDF: 8 pages
Proc. SPIE 10563, International Conference on Space Optics — ICSO 2014, 1056319 (17 November 2017); doi: 10.1117/12.2304261
Show Author Affiliations
J. Barandiaran, Instituto Nacional de Técnica Aeroespacial (Spain)
P. Zuluaga, Instituto Nacional de Técnica Aeroespacial (Spain)
A. B. Fernandez, Instituto Nacional de Técnica Aeroespacial (Spain)
I. Vera, Instituto Nacional de Técnica Aeroespacial (Spain)
D. Garranzo, Instituto Nacional de Técnica Aeroespacial (Spain)
A. Nuñez, Instituto Nacional de Técnica Aeroespacial (Spain)
L. Bastide, ISDEFE (Spain)
M. T. Royo, Instituto Nacional de Técnica Aeroespacial (Spain)
A. Alvarez, Instituto Nacional de Técnica Aeroespacial (Spain)

Published in SPIE Proceedings Vol. 10563:
International Conference on Space Optics — ICSO 2014
Zoran Sodnik; Bruno Cugny; Nikos Karafolas, Editor(s)

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