KEYWORDS: Monte Carlo methods, Polarimetry, Photons, X-rays, Solar radiation models, Solid modeling, Solar processes, Hard x-rays, Equipment, Compton scattering
The CUbesat Solar Polarimeter (CUSP) project is a CubeSat mission orbiting the Earth aimed to measure the linear polarization of solar flares in the hard X-ray band by means of a Compton scattering polarimeter. CUSP will allow to study the magnetic reconnection and particle acceleration in the flaring magnetic structures of our star. CUSP is a project in the framework of the Alcor Program of the Italian Space Agency aimed to develop new CubeSat missions. It is approved for a Phase B study. In this work, we report on the accurate simulation of the detector’s response to evaluate the scientific performance. A GEANT4 Monte Carlo simulation is used to assess the physical interactions of the source photons with the detector and the passive materials. Using this approach, we implemented a detailed CUSP Mass Model. In this work, we report on the evaluation of the detector’s effective area as a function of the beam energy.
The CUbesat Solar Polarimeter (CUSP) project aims to develop a constellation of two CubeSats orbiting the Earth to measure the linear polarization of solar flares in the hard X-ray band by means of a Compton scattering polarimeter on board of each satellite. CUSP will allow to study the magnetic reconnection and particle acceleration in the flaring magnetic structures. CUSP is a project approved for a Phase B study by the Italian Space Agency in the framework of the Alcor program aimed to develop CubeSat technologies and missions. In this paper we describe the a method for a multi-physical simulation analysis while analyzing some possible design optimization of the payload design solutions adopted. In particular, we report the mechanical design for each structural component, the results of static and dynamic finite element analysis, the preliminary thermo-mechanical analysis for two specific thermal cases (hot and cold orbit) and a topological optimization of the interface between the platform and the payload.
The CUbesat Solar Polarimeter (CUSP) project is a future CubeSat mission orbiting the Earth aimed to measure the linear polarization of solar flares in the hard X-ray band, by means of a Compton scattering polarimeter. CUSP will allow us to study the magnetic reconnection and particle acceleration in the flaring magnetic structures of our star. The project is in the framework of the Italian Space Agency Alcor Program, which aims to develop new CubeSat missions. CUSP is approved for a Phase B study that will last for 12 months, starting in mid-2024. We report on the current status of the CUSP mission project as the outcome of the Phase A.
The CUbesat Solar Polarimeter (CUSP) project is a CubeSat mission orbiting the Earth aimed to measure the linear polarization of solar flares in the hard X-ray band by means of a Compton scattering polarimeter. CUSP will allow the study of the magnetic reconnection and particle acceleration in the flaring magnetic structures of our star. CUSP is a project in the framework of the Alcor Program of the Italian Space Agency aimed at developing new CubeSat missions. It is approved for a Phase B study. In this work, we report on the characterization of the Avalanche Photodiodes (APDs) that will be used as readout sensors of the absorption stage of the Compton polarimeter. We assessed the APDs gain and energy resolution as a function of temperature by irradiating the sensor with a 55Fe radioactive source. Moreover, the APDs were also characterized as being coupled to a GAGG scintillator.
The CubeSat solar polarimeter (CUSP) project aims to develop a constellation of two CubeSats orbiting the Earth to measure the linear polarisation of solar flares in the hard x-ray band by means of a Compton scattering polarimeter on board of each satellite. CUSP will allow to study the magnetic reconnection and particle acceleration in the flaring magnetic structures. CUSP is a project approved for a Phase A study by the Italian Space Agency in the framework of the Alcor program aimed to develop CubeSat technologies and missions.
Photonic Integrated Circuits (PICs) are expected to have a primary role for space applications in the years to come. The growing interest for the PICs for space applications lays in the fact the integrated photonics brings notable advantages as, among others: 1) Size, Weight and Power (SWaP) reduction 2) Removal/reduction of electromagnetic interferences 3) More flexibility (e.g. Network-on-chip) 4) Convergence with integrated electronics with potential costs reduction and improved performance (e.g. Beamforming) 5) Possibility to avoid optical to electronic to optical conversions (O-E-O) by maintaining some functions at photonic level in the optical domain, like for example in optical beamforming and photonics-based up- and down-conversion However, photonic packaging is less mature than its microelectronic counterpart. In fact, considering the great advancements in designing and fabricating integrated photonic chips, photonic packaging still represents a limiting factor and requires dedicated effort especially in view of a full exploitation of integrated photonics for Space applications. There is necessity to develop the proper packaging technologies compatible with the Space requirements as well the proper packaging line processes controls and documentations. PIOTS project aims to answer such demand by creating an end-to-end packaging pilot line that is strategically oriented to the demands of ESA and European space industry. This goal will be demonstrated through the realization of two test vehicles and the validation of manufacturing processes, equipment and techniques by means of an adequate Quality System implementation, including documentation and in-line controls as required to manufacture a product complying with requirements of the space sector. The paper will update on the project status focusing on the two test vehicles: TV1 - a hermetically packaged laser integrated with a SOI device TV2- a hermetically packaged SOI device with 8 in/out pigtailed fibers.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.