SUNRISE III mission is a one-meter aperture telescope onboard a balloon within NASA Long Duration Balloon Program. Three post-focus instruments are used for studying the Sun’s dynamics and magnetism, among which the Tunable Magnetograph (TuMag) is a tunable imaging spectropolarimeter. TuMag is a diffraction-limited imager, a high sensitivity polarimeter (< 10-3 ), and a high-resolution spectrometer ( ~ 65 mÅ). It will be able to study solar magnetic fields at high spatial resolution (~100 km 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 525.02 nm and 525.06 nm, and the Mg I b2 line at 517.27 nm. It will be sensitive to the solar vector magnetic fields and line-of-sight velocities, 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. In this paper the TuMag end-to-end tests carried out during the verification phase are described. These tests are performed to characterize and calibrate the instrument. Specifically, they determine the polarimetric and spectroscopic performances of the instrument as well as the image quality. The availability of a singular facility, an ISO6 clean room with a coelostat on the building roof, allowed the use of solar light during the verification campaign. This was key to a complete instrument verification due to the unique spectroscopic and polarimetric characteristics of solar light.
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
Liquid crystals on silicon spatial light modulator (LCOS-SLM) combine the potential of reflection type spatial light modulators with the compactness and robustness of a single chip. They are used today for beam steering applications, optical beam shaping and laser processing. These devices have a high potential for space applications due to the fact that they allow to introduce any tailored wavefront distortion in an imaging instrument. Then, image reconstruction methods as phase diversity can be used to determine the Point Spread Function (PSF) inflight and, later, to introduce a corrective wavefront distortion to correct possible deviations of the expected optical quality.
Among other aberrations, the beam phase control can act on the level of focus. In space optical applications image refocusing is usually performed by means of mechanisms, either by using linear displacement of lenses or rotating wheels with plates with different thicknesses. The compactness and absence of mechanical parts of LCOS-SLM can be of great advantage for these applications. LCOS-SLM can save complexity and weight. It also reduces the risk associated to the wear of moving parts.
However, this technology has not been qualified for space applications. Liquid crystal leaks as well as outgassing issues may result as a consequence of a low pressure environment. Thermal issues can also result in loss of device homogeneity and the radiation tolerance should be analyzed. In any case, an exhaustive space simulation test is mandatory to increase the Technological Readiness Level of these devices for their use in space systems.
In our work we are showing preliminary test of a commercial LCOS-SLM under thermo-vacuum conditions. These tests are basic calibrations used to evaluate performance and degradation in a simulated space environment. Different calibration procedures are also discussed. This technology, with potential to greatly simplify an instrument design, was included in a proposal for the instrument IMaX+ spectro-polarimeter, to be onboard the mission Sunrise III, within the NASA Long Duration Balloon program.
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