The COronal Diagnostic EXperiment (CODEX) is the solar coronagraph developed by NASA-Goddard Space Flight Center in collaboration with the Korea Astronomy and Space Science Institute (KASI), and the Italian National Institute for Astrophysics (INAF). CODEX will be launched in September 2024 and will be hosted by the International Space Station (ISS) as an external payload. CODEX is designed to observe the linearly polarized K-corona within the wavelength range 385-440 nm to obtain simultaneous measurements of density, temperature, and radial velocity of the coronal electrons. CODEX is a two-stage externally occulted coronagraph, with a field of view of 2.67 degrees, featuring two fold mirrors, and a series of occulting elements that minimize the amount of diffracted light reaching the detector. The polarization of the solar corona is measured by means of a commercial polarization image sensor manufactured by Sony, the IMX253MZR, that spatially modulates the incoming light beam. The polarimetric characterization of the instrument is one of the fundamental steps to derive the desired physical quantities of the solar corona from observations. It is hence crucial to understand how the instrument modifies the incident polarized light, especially due to the presence of the two fold mirror system within the light path, which is notoriously a source of polarization aberrations. This work describes the polarimetric characterization of the CODEX coronagraph, to determine an estimation of the instrumental polarization, and the results are presented.
The COronal Diagnostic EXperiment (CODEX) is a Heliophysics mission to measure the density, temperature, and velocity of the electrons in the solar corona with the primary goal of improving our understanding of the physical conditions of the solar wind in the acceleration region. The temperature and velocity measurement requires much higher signal-to-noise ratio than the density measurements. In solar coronagraphs, the diffraction of the solar disk light due to the occulting element is the dominant source of noise. Therefore, to further suppress the diffracted sun light with respect to the existing coronagraphs is a critical element of the CODEX design. To minimize the stray light due to diffraction, the selected optical design is a two-stage standard coronagraph with an external occulter, an internal occulter, and a Lyot stop. What is unique for this design is that a focal mask was inserted at the telescope focal plane. It works together with the field lens suppressing the stray light down by ~ another order of magnitude as compared to a traditional three-stage approach. During the optical design, a Fourier Transform based beam propagation software, i.e., GLAD, was used to model the beam path through the full coronagraph, from the external occulter to the detector array. All diffraction sensitive elements: external occulter, internal occulter, focal mask, and Lyot stop were carefully modeled and optimized. As a result, the requirement of achieving a stray light level which is one order of magnitude lower than F-corona was satisfied. On the other hand, to achieve the final suppression, a precision optical alignment is another must. This paper also presents our creative alignment procedure: using the combination of metrology, precision alignment equipment, and real time diffraction ring monitoring to minimize the diffraction. The final test results show that the suppression ratio (B/B0) reaches 10-11 level, which is equivalent to one order of magnitude lower than F-corona.
Helianthus is a technological development project funded by the Italian Space Agency for a Phase A study of a space weather station with solar photonic propulsion. Helianthus will have a synchronous orbit with the Earth-Moon barycenter, positioned at about 7 millions km from Earth towards the Sun, thus much closer to the Sun with respect to historical Space Weather instrumentation, which are typically orbiting the Earth or L1. This sub-L1 halo orbit is maintained by radiation pressure on a solar sail as the propulsion mechanism: once in flight, the spacecraft will have a huge square sail, about 40 m long. The scientific payload will be hosted at the center of the sail and will comprise remote-sensing and in situ instruments. Remote sensing: an X-ray detector to detect Solar Flares and SailCor, a coronagraph with a wide field of view. In situ: a plasma analyzer and a magnetometer. For this ”Sailcraft”, a scientific payload with reduced mass and envelope is under study. The maximum allowed mass for the entire scientific payload shall not exceed 5 kg. Both the X-Ray detector and the in situ instruments have a flight heritage. This study aims at developing a laboratory prototype of a coronagraph matching the constraints of mass and envelope of the Helianthus payload. SailCor is a 20 cm long coronagraph with a field of view ranging heliocentric heights 3-30 solar radii. The external occulter is mounted on an extendable boom that will be deployed once in flight. SailCor presents an innovative solution that combines the diffraction apodization by the external occulter and the internal occulter positioning so that no Lyot stop is required. The classical design of externally occulted coronagraphs foresees the positioning of an internal occulter as a conjugated element to the external occulter with respect to the primary objective. The function of the internal occulter is to block the image of of the diffraction from the external occulter edge. Then, a secondary objective generates the coronal image on the detection system. The SailCor solution takes advantage of the focusing effect that the entrance aperture of the instrument induces on the light diffracted by the external occulter. This effect is used to calculate the position of the internal occulter with respect to the primary focal plane. With this approach, there is no need for a Lyot stop and the detection system can be placed at the first focal plane, with a significant reduction of envelope and mass. This contribution describes the design of the prototype of SailCor, used in laboratory to experimentally define the geometry of the occultation system. The activity has been carried out in the INAF OPSys facility clean environment (ISO5/6) hosted at ALTEC S.p.A. (Torino). The source is a solar divergence simulator.
The PROBA-3 double-spacecraft formation flying mission of the European Space Agency (ESA) has been presented in recent papers with details about the mission profile, the operation objectives, and the implemented technologies. PROBA-3 will fly the externally occulted coronagraph ASPIICS (Association of Spacecraft for Polarimetric and Imaging Investigation of the Corona of the Sun), with the telescope on one satellite and the occulter on the other one, at 144m. The scientific objective is to realize an artificial total solar eclipse to observe the lower Sun corona. The high accuracy metrology control is the core of the mission and several sub-systems will be verified and validated to realize the coronagraphic formation. Between these, the Shadow Position Sensors (SPS), composed of eight photo-multipliers mounted around the ASPIICS entrance pupil monitoring the solar penumbra symmetry, will return the 3D positioning of the formation with the highest accuracy. The SPS on-ground calibration was completed in 2021 and one of the main aspects of the test has been the implementation of an illumination scheme to simulate the same conditions the SPS will experience in flight. This was realized using a suite of LED sources properly assembled in a testbed used to reproduce the expected observation configurations. This testbed is supported by a dedicated software able to simulate the different illumination conditions and to drive the control of the LEDs in order to feed each SPS sensor with the proper light flux. In this paper, we review the SPS metrology system, the calibration testbed setup, and we discuss the interface control software, the simulation tool, and the data acquisition procedure adopted to calibrate the LED sources. Additional presentation content can be accessed on the supplemental content page.
Helianthus is a phase A study of a space weather station with solar photonic propulsion. The scientific payload will be made of: an x-ray spectrometer to detect solar flares; SailCor, a coronagraph with a wide field of view; a plasma analyzer; a magnetometer. The maximum allowed mass for the entire scientific payload shall not exceed 5 kg. The two imaging devices (coronagraph and X-ray spectrometer) are of fundamental importance for the sake of remotely and timely mapping the status of the Sun and provide Earth stations with early warning of potentially disruptive events. An extensive research on available x-Ray detectors was performed and the Amptek FAST-SDD spectrometer was selected. It is a very light, compact and vacuum compatible instrument. In order to prove the device readiness for flight, a measurement campaign was organized to investigate its performance in terms of spectral range, spectral resolution, dynamic range and response speed. The campaign was run at the INAF XACT facility in Palermo (Italy). This paper describes the facility, the measurement campaign and the results.
The Coronal Magnetograph - CorMag - experiment aims at studying the magnetic field topology of the solar corona. The direction of the coronal magnetic field vector would be derived from narrow-wavelength bandpass observations of the linearly polarized FeXIV line-emission (530.3 nm), interpreted through the "saturated" Hanle effect. CorMag will be a medium-duration, high-altitude balloon payload of the European Union-funded HEMERA Program. CorMag is an internally-occulted coronagraph whose design was derived from the externally-occulted, formation-flying ASPIICS coronagraph of the PROBA-3 ESA solar mission. The configuration for this mission will be illustrated, together with the expected polarization sensitivity. This mission is a demonstrator for future space-based coronagraphs with the capability of visible-light and infrared polarization measurements for coronal magnetic field diagnostics.
The PROBA3 mission of the European Space Agency is the first formation flying (FF) mission that will be flown in high elliptic geocentric orbit aiming at verifying and validating different metrology control systems and algorithms in order to realize and maintain the formation of two independent spacecraft, in total autonomy. The final target accuracy for the relative and absolute alignment of the two satellites is of about 2mm over an inter satellite distance of 144.3m. During the FF, the two spacecraft will realize a giant coronagraph with the external occulter on one payload and the telescope on the other one. The Sun Corona observation will be the scientific tool for the FF validation. Between the different metrology systems that will be tested, the Shadow Position Sensor (SPS) is the most challenging one, aiming at returning the relative and absolute position of the formation with the finest accuracy: 0.5mm out of the guidance and navigation and control loop and 2mm within the loop. The mission program is now in the Phase D with the realization and the testing of the flight model. Due to the high expected performance, a fine calibration of the SPS subsystem is mandatory. In this paper, we discuss the radiometric and spectral calibration plan, the algorithm validation procedure, and the laboratory test-bed realized to reproduce the in-flight observation conditions of the SPS by using a set of calibrated LED and a mechanical set-up equivalent to the SPS system. Preliminary results are also reviewed.
In 1999 the European solar scientific community proposed to ESA the Solar Orbiter (SO), a mission to explore the circumsolar region, to perform quasi helio-synchronous observations, and to obtain the first out-of-ecliptic imaging and spectroscopy of the solar poles and of the equatorial corona. Presently, SO is one of the three missions under study within the ESA Cosmic Vision 2015-2025 program, and a key ESA-NASA missions within the International Living with a Star Program. SO, to be launched on January 2017, is expected to provide major advances steps forward in understanding the Sun-heliosphere connection.
PROBA3 is the first high precision formation flying (FF) mission under responsibility of the European Space Agency (ESA). It is a technology mission devoted to in-orbit demonstration of the FF techniques, with two satellites kept at an average inter-satellite distance of 144m. The guiding scientific rationale is to realize a diluted coronagraph with the telescope (ASPIICS) on one satellite and the external occulter on the other satellite to observe the inner Solar corona at high spatial and temporal resolution, down to 1.08R⊙. The two spacecraft will be orbiting in a high eccentricity geocentric trajectory with perigee at 600km and the apogee at 60000Km and with an orbital period of 19hrs. The FF acquisition and operations will last about 6 hrs around the apogee and different metrology systems will be used for realizing and controlling the FF. The alignment active most critical sub-system is the Shadow Positioning Sensors (SPS), a series of Si-PM (Silicon Photomultiplier) disposed around the ASPIICS telescope's entrance aperture and measuring the proper positioning of the penumbra generated by the occulter at the center of the coronagraph’s optical reference frame. The FF alignment measurement accuracies required to the SPS are: 500μm for lateral movements and 50mm for longitudinal movements. This paper gives an overview of the opto-mechanical and electronic design and of the software algorithm for the FF intersatellite positioning. The expected performance of the SPS metrology system are reported.
The SPECtro-heliograph for the Transition REgion (SPECTRE) experiment is one of the instruments of the Solar Heliospheric Activity Research and Prediction Program (SHARPP) suite initially foreseen aboard the NASA mission Solar Dynamics Observatory (SDO) of the International Living With a Star (ILWS) program. The scientific objective of the SPECTRE experiment was to characterize the rapid evolution of plasma in the transition region of the solar atmosphere, producing full-disk 1.2 arcsec-resolution images of the solar atmosphere at the very critical 63 nm OV spectral line, characterizing a solar plasma temperature of about 250,000 K. Unfortunately, NASA very recently and unexpectedly, during the instrument Phase A study, decided not to proceed with the realization of SHARPP. The authors of this paper think that all the work done so far in the definition of SPECTRE should not be lost. So, they have decided to summarize in this paper the main characteristics of this instrument and the results of the analysis so far performed: the hope is that in a next future this work can be used again for realizing an instrument having similar characteristics.
METIS, the Multi Element Telescope for Imaging and Spectroscopy, is an instrument proposed to the European Space Agency to be part of the payload of the Solar Orbiter mission. The instrument design has been conceived for performing extreme ultraviolet (EUV) spectroscopy both on the solar disk and off-limb, and near-Sun coronagraphy and spectroscopy. The proposed instrument suite consists of three different interconnected elements, COR, EUS and SOCS, sharing the same optical bench, electronics, and S/C heat shield aperture. COR is a visible-EUV multiband coronagraph based on a classical externally occulted design. EUS is the component of the METIS EUV disk spectrometer which includes the telescope and all the related mechanisms. Finally, SOCS is the METIS spectroscopic component including the dispersive system and the detectors. The capability of inserting a small telescope collecting coronal light has been added to perform also EUV coronal spectroscopy. METIS can simultaneously image the visible and ultraviolet emission of the solar corona and diagnose, with unprecedented temporal coverage and space resolution the structure and dynamics of the full corona in the range from 1.2 to 3.0 (1.6 to 4.1) solar radii (R, measured from Sun centre) at minimum (maximum) perihelion during the nominal mission. It can also perform spectroscopic observations of the solar disk and out to 1.4 R within the 50-150 nm spectral region, and of the geo-effective coronal region 1.7-2.7 R within the 30-125 nm spectral band.
Present telescopes and future extremely large telescopes make use of fiber-fed spectrographs to observe at optical and
infrared wavelengths. The use of fibers largely simplifies the interfacing of the spectrograph to the telescope. At a high
spectral resolution (R>50,000) the fibers can be used to achieve very high spectral accuracy.
GIANO is an infrared (0.95-2.5μm) high resolution (R=50,000) spectrometer[1] [2] [3] that was recently commissioned
at the TNG telescope (La Palma). This instrument was designed and built for direct feeding from the telescope [4].
However, due to constraints imposed on the telescope interfacing during the pre-commissioning phase, it had to be
positioned on the rotating building, far from the telescope focus. Therefore, a new interface to the telescope, based on
IR-transmitting ZBLAN fibers with 85μm core, was developed.
In this article we report the first, preliminary results of the effects of these fibers on the quality of the recorded spectra
with GIANO and with a similar spectrograph that we set-up in the laboratory. The effects can be primarily associated to
modal-noise (MN) that, in GIANO, is much more evident than in optical spectrometers, because of the much longer
wavelengths.
Polarimeters based on electro-optically tunable liquid crystals (LC) represent a new technology in the field of
observational astrophysics. LC-based polarimeters are good candidates for replacing mechanically rotating polarimeters
in most ground-based and space-based applications. During the 2006 total solar eclipse, we measured the visible-light
polarized brightness (pB) of the solar K-corona with a LC-based polarimeter and imager (E-KPol). In this presentation,
we describe the results obtained with the E-KPol, and we evaluate its performances in view of using a similar device for
the pB imaging of the K-corona from space-based coronagraphs. Specifically, a broad-band LC polarimeter is planned
for the METIS (Multi Element Telescope for Imaging and Spectroscopy) coronagraph for the Solar Orbiter mission to
be launched in 2017. The METIS science driver of deriving the coronal electron density from pB images requires an
accuracy of better than 1% in the measurement of linear polarization. We present the implications of this requirement on
the METIS design to minimize the instrumental polarization of the broad-band visible-light (590-650 nm) polarimeter
and of the other optics in the METIS visible-light path. Finally, we report preliminary ellipsometric measurements of the
optical components of the METIS visible-light path.
The "Association de Satellites Pour l'Imagerie et l'Interférométrie de la Couronne Solaire", ASPIICS, is a solar
coronagraph to be flown on the PROBA 3 Technology mission of the European Space Agency. ASPIICS heralds the
next generation of coronagraphs for solar research, exploiting formation flying to gain access to the inner corona under
eclipse-like conditions in space. The science goal is high spatial resolution imaging and two-dimensional
spectrophotometry of the Fe XIV, 530.3 nm, emission line. This work describes a liquid crystal Lyot tunable-filter and
polarimeter (LCTP) that can implement this goal. The LCTP is a bandpass filter with a full width at half maximum of
0.15 nm at a wavelength of 530.3 nm. The center wavelength of the bandpass is tunable in 0.01 nm steps from 528.64
nm to 533.38 nm. It is a four stage Lyot filter with all four stages wide-fielded. The free spectral range between
neighboring transmission bands of the filter is 2.7 nm. The wavelength tuning is non-mechanical using nematic liquid
crystal variable retarders (LCVR's). A separate LCVR of the Senarmont design, in tandem with the filter, is used for the
polarimetric measurements. A prototype of the LCTP has been built and its measured performances are presented here.
The Turin Astronomical Observatory, Italy, has implemented in ALTEC, Turin, a new Optical Payload Systems
(OPSys) facility for testing of contamination sensitive optical space flight instrumentation. The facility is specially
tailored for tests on solar instruments like coronagraphs. OPSys comprises an ISO 7 clean room for instrument assembly
and a relatively large (4.4 m3) optical test and calibration vacuum chamber: the Space Optics Calibration Chamber
(SPOCC). SPOCC consists of a test section with a vacuum-compatible motorized optical bench, and of a pipeline section
with a sun simulator at the opposite end of the optical bench hosting the instrumentation under tests. The solar simulator
is an off-axis parabolic mirror collimating the light from the source with the solar angular divergence. After vacuum
conditioning, the chamber will operate at an ultimate pressure of 10-6 mbar.
This work describes the SPOCC's vacuum system and optical design, and the post-flight stray-light tests to be carried
out on the Sounding-rocket Experiment (SCORE). This sub-orbital solar coronagraph is the prototype of the METIS
coronagraph for the ESA Solar Orbital mission whose closest perihelion is one-third of the Sun-Earth distance. The plans
are outlined for testing METIS in the SPOCC simulating the observing conditions from the Solar Orbiter perihelion.
The Dual Rotating Retarder Polarimeter technique has been used for the calibration of the EKPol polarimeter, which is a
K-corona imaging instrument based on a Liquid Crystal Variable Retarder (LCVR), and designed to measure the linear
polarized radiation coming from the solar corona during total solar eclipses. We put a major emphasis on the EKPol
properties at different wavelengths and temperature. In particular, the chromatic dependence of the LCVR rotation
prevents from using large band observations, owing to the loss of contrast in the measured modulation curves. This study
is also intended as a basis for the design of achromatic LCVRs.
We describe the design and first calibration tests of an imaging polarimeter based on Liquid Crystal Variable Retarders (LCVRs), for the study of the solar K-corona. This K-polarimeter (KPol) is part of the visible light path of the UltraViolet and Visible-light Coronal Imager (UVCI) of the Sounding-rocket Coronagraphic Experiment (SCORE). SCORE/UVCI is an externally occulted, off-axis Gregorian telescope, optimized for the narrow-band (i.e., λ/▵λ ~10) imaging of the HeII, λ 30.4 nm and HI λ 121.6 nm coronal emission. We present some preliminary results of the application of LCVR plates to measurements of linear polarized radiation. LCVR plates replace mechanically rotating retarders with electro-optical devices, without no moving parts. LCVR are variable waveplates, in which the change of the retardance is induced by a variable applied voltage. The retardance of a LCVR is a function of the wavelength. KPol observations of the visible coronal continuum of the Sun (K-corona) will be made over the 450-600 nm wavelength band. We have studied the LCVR's properties in this bandpass. We tested a LCVR plate assembled in a linear polarization rotator configuration to measure the polarization plane rotation of input radiation as a function of wavelength. We estimated the LCVR's chromatic response in the KPol wavelength bandpass. The preliminary results show reasonable achromatic behaviour at high regimes of the driving voltage, Vd (i.e., Vd>3 volt).
A new concept CCD camera is currently under development at the XUVLab of the Department of Astronomy and Space Science of the University of Florence. This CCD camera is the proposed detector for the space- and ground-based solar corona observations. This camera will be the detector for the polarimetric channels of the UVC coronagraph of the HERSCHEL rocket mission to observe the solar corona in an optical broadband. The ground-based application consists in a UVC prototype for coronagraphic measurements from Earth in the visible range. Within this project, a CCD camera with innovative features has been produced: the camera controller allows the fine tuning of all the parameters related to charge transfer and CCD readout, i.e., the use of virtually any CCD sensor, and it implements the new concept of high level of versatility, easy management, TCP/IP remote control and display.
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