The ESA mission Solar Orbiter was successfully launched in February 2020. The Photospheric and Helioseismic Imager (PHI) provides measurements of the photospheric solar magnetic field and line of sight velocities at high solar latitudes with high polarimetric accuracy. The required pointing precision is achieved by an image stabilisation system (ISS) that compensates for spacecraft jitter. The ISS consists of a high-speed correlation tracker camera (CTC) and a fast steerable tip-tilt mirror operated in closed loop. We will present the results of the calibration measurements and performance tests from ground measurements, during commissioning and science phase. In addition, the correlation tracker was used to directly measure the pointing stability of the satellite.
A Carbon Fiber Reinforced Polymer (CFRP) optical bench has been developed for the Tunable Magnetograph instrument (TuMag) for the SUNRISE III mission. This mission is within the NASA Long Duration Balloon Program and it consists of 1-meter aperture telescope with three post-focal instruments to study the solar dynamics. One of them is TuMag: a diffraction-limited imager, a high sensitivity polarimeter and a high-resolution spectrometer. The composite material has been selected for the optical bench due to its lightweight, low sensitivity to thermal gradients and low coefficient of thermal expansion (CTE). Additionally, to the flight model optical bench, a breadboard model identical to the flight model has been manufactured including optical fiber Bragg temperature and strains sensors embedded in its upper skin. The goal is to demonstrate that the use of distributed fiber Bragg gratings (FBGs) can provide valuable information for strain and temperature mapping of an optical instrument onboard a payload, during its operation and its on-ground testing. Furthermore, surface mounted strain FBG sensors and thermocouples have been installed in the optical bench for intercomparison purposes. In this paper the results obtained for a thermal-vacuum test are presented. It consists of three thermal cycles with stabilization steps at 100ºC, 60ºC, 20ºC and -20ºC. The FBG embedded temperature sensors results have been compared with the surface mounted thermocouples; the FBG embedded strain sensor results have been compared to the surface mounted strain sensors.
The Tunable Magnetograph (TuMag) is one of the three post-focal instruments onboard SUNRISE III, a balloon-borne solar observatory aimed to the study of solar dynamics. TuMag is able to make Sun observations at three absorption solar lines: the Fe I lines at 525.02nm and 525.06nm, and the Mg I b2 line at 517.27nm. The spectral lines are scanned during the observation using a LiNbO3 etalon in double-pass configuration with a 65mÅ bandwidth. Additionally, to remove undesired orders of the Fabry-Perot interferometer, a narrow band filter with a ~1.5 Å FWHM is inserted in the optical path, and needs to be centered to the corresponding solar line. These filters feature high thermal sensitivity and incidence angle dependence. For this reason, they require a thermal stabilization of ±0.5°C and an angular position accuracy better than ±0.03 degrees. In order to switch between filters and hence the observation solar line, a Filter Wheel has been designed which comply with stringent thermal and mechanical requirements and it is presented in this work.
The ESA/NASA Solar Orbiter space mission has been successfully launched in February 2020. Onboard is the Polarimetric and Helioseismic Imager (SO/PHI), which has two telescopes, a High Resolution Telescope (HRT) and the Full Disc Telescope (FDT). The instrument is designed to infer the photospheric magnetic field and line-of-sight velocity through differential imaging of the polarised light emitted by the Sun. It calculates the full Stokes vector at 6 wavelength positions at the Fe I 617.3nm absorption line. Due to telemetry constraints, the instrument nominally processes these Stokes profiles onboard, however when telemetry is available, the raw images are downlinked and reduced on ground. Here the architecture of the on-ground pipeline for HRT is presented, which also offers additional corrections not currently available on board the instrument. The pipeline can reduce raw images to the full Stokes vector with a polarimetric sensitivity of 10−3 · Ic or better.
The Tunable Magnetograph (TuMag) is one of the three post-focus instruments onboard the SUNRISE III mission. It consists of a one-meter aperture telescope onboard a balloon within NASA Long Duration Balloon Program to study the solar dynamics. TuMag is a diffraction-limited imager, a high sensitivity polarimeter and a high resolution spectrometer. It will be able to study solar magnetic fields at high spatial resolution (~100km on the solar surface). It will make images of the solar surface magnetic field after measuring the state of polarization of light within three selected spectral lines: the Fe I lines at 525.02nm and 525.06nm, and the Mg I b2 line at 517.27nm. It will allow to be sensitive to physical quantities, and specifically to the magnetic fields, in the photospheric and chromospheric layers. TuMag will be the first solar magnetograph onboard an aerospace platform with the capability of tuning the solar line to be observed. TuMag consists of an Optical-Unit and an Electronic Unit to control it. The optical design is an optical relay of the telescope post-focal intermediate image where the light analysis is carried out in several stages. The polarization analysis is carried out with a polarization modulator based on Liquid Crystal Variable Retarders developed for the Solar Orbiter mission in operation currently. The spectral lines are scanned during the observation using a LiNbO3 etalon in double-pass configuration with a 65mÅ bandwidth. Additionally, to remove undesired orders of the Fabry-Perot interferometer, three narrow bandpass filters with a ~1.5 Å FWHM (Full Width at Half Maximum) are consecutively inserted in the optical path using a high precision and thermal controlled filter wheel. In this paper the optical, mechanical and thermal design of the TuMag optical unit is described as well as a brief summary of the results obtained during the manufacturing, assembling, integration and verification phases
The High Resolution Telescope (HRT) of the Polarimetric and Helioseismic Imager (SO/PHI) on-board the Solar Orbiter mission (SO) provides near diffraction limited observations of the solar surface. The HRT Refocus Mechanism (HRM) allows for acquiring calibration data in flight which are used in post processing on ground to estimate the image quality of SO/PHI-HRT data products and its dependence on the SO-Sun distance. Our aim is to characterise the wavefront aberrations in the optical path of SO/PHI-HRT and consequently the image quality in the focal plane of the telescope. We use calibration data taken during the Near Earth Commissionning Phase (NECP) and the second Remote Sensing Check-out Window (RSCW2) of Solar Orbiter’s Cruise Phase (CP). In particular, we apply a Phase Diversity (PD) analysis to estimate the low-order wavefront aberrations. The restoration with the retrieved Point Spread Function (PSF) from the PD analysis increases the RMS contrast of the solar granulation in the visible continuum from 4 % to 10−11%.
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.
The Polarimetric Helioseismic Imager for Solar Orbiter (SO/PHI) is an instrument on board in the Solar Orbiter mission. The Full Disk Telescope (FDT) will have the capability of providing images of the solar disk in all orbital faces with an image quality diffraction-limited. The Heat Rejection Entrance Window (HREW) is the first optical element of the instrument. Its function is to protect the instrument by filtering most of the Solar Spectrum radiation. The HREW consists of two parallel-plane plates made from Suprasil and each surface has a coating with a different function: an UV shield coating, a low pass band filter coating, a high pass band filter coating and an IR shield coating, respectively.
The temperature gradient on the HREW during the mission produces a distortion of the transmitted wave-front due to the dependence of the refractive index with the temperature (thermo-optic effect) mainly. The purpose of this work is to determine the capability of the PHI/FDT refocusing system to compensate this distortion.
A thermal gradient profile has been considered for each surface of the plates and a thermal-elastic analysis has been done by Finite Element Analysis to determine the deformation of the optical elements. The Optical Path Difference (OPD) between the incident and transmitted wavefronts has been calculated as a function of the ray tracing and the thermo-optic effect on the optical properties of Suprasil (at the work wavelength of PHI) by means of mathematical algorithms based on the 3D Snell Law. The resultant wavefronts have been introduced in the optical design of the FDT to evaluate the performance degradation of the image at the scientific focal plane and to estimate the capability of the PHI refocusing system for maintaining the image quality diffraction-limited. The analysis has been carried out considering two different situations: thermal gradients due to on axis attitude of the instrument and thermal gradients due to 1° off pointing attitude. The effect over the boresight at the instrument focal plane has also been analyzed.
The results show that the effect of the FDT HREW thermal gradients on the FDT performance can be optically corrected. The influence of the thermal gradients on the system is also presented.
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