HaloSat is a CubeSat-class microsatellite sensitive in the 0.4 to 7.0 keV energy band and designed to survey the entire sky in search of soft x-ray emissions from highly ionized oxygen residing in the halo of the Milky Way galaxy. Those observations will help constrain the mass and spatial distribution of the Milky Way halo and help us understand if hot galactic halos constitute a significant contribution to the overall cosmological baryon budget. We describe the science instrument calibration products, including channel-to-energy transformation, instrument energy resolution and instrument response, and the on-ground efforts that led to their creation. We also describe the alignment process used to obtain the field of view information for the HaloSat science instrument.
We have fabricated a blazed x-ray reflection grating with a period of 160 nm using thermally activated selective topography equilibration (TASTE) and electron-beam (ebeam) physical vapor evaporation. TASTE makes use of grayscale ebeam lithography to create three-dimensional (3-D) structures in resist, which can then be thermally reflown into a desired profile. A blazed grating profile can be fabricated by selectively reflowing a periodic staircase structure into a wedge. This was done for the first time at a grating period of 160 nm, 2.5 times smaller than previous x-ray gratings fabricated using TASTE. The grating was patterned over a 10 mm by 60 mm area in a 147-nm-thick layer of poly(methyl methacrylate) resist and coated with 5 nm of chromium and 15 nm of gold using ebeam evaporation. The diffraction efficiency of the grating was measured using beamline 6.3.2 at Lawrence Berkeley National Laboratory’s Advanced Light Source. The results show a total absolute diffraction efficiency ≳40 % at lower energies, with maximum single-order diffraction efficiency ranging from 20% to 40%. The total diffraction efficiency was ≳30 % across the measured bandpass of 180 to 1300 eV.
HaloSat is the first mission funded by NASA’s Astrophysics Division to use the CubeSat platform. Using three co-aligned silicon drift detectors, the HaloSat observatory measures soft (0.4 to 7 keV) x-ray emission from sources of diffuse emission such as the hot, gaseous halo of the Milky Way. We describe the design and construction of the science payload on HaloSat and the reasoning behind many of the choices. As a direct result of the design choices and adherence to best practices during construction, the HaloSat science payload continues to perform well after more than one year on-orbit.
We have fabricated a blazed X-ray reflection grating with a period of 160 nm using thermally activated selective topography equilibration (TASTE). The grating was tested for diffraction efficiency using the soft X-ray reflectometer at Lawrence Berkeley National Laboratory's Advanced Light Source. Preliminary results show total absolute diffraction efficiency ≥ 40% at lower energies, with maximum single order diffraction efficiency ranging from 20-40%. Total diffraction efficiency was ≥ 30% across the entire measured band pass of 180 eV to 1300 eV.
The Rockets for Extended-source X-ray Spectroscopy (tREXS) are a series of suborbital rocket payloads being developed at The Pennsylvania State University. The tREXS science instrument is a soft X-ray grating spectrometer that will provide a large field-of-view and unmatched spectral resolving power for extended sources. Each instrument channel consists of a passive, mechanical focusing optic and an array of reflection gratings. The focal plane consists of an array of CIS113 CMOS sensors. tREXS I is currently in the design phase and is being developed for a launch in 2021 to observe diffuse soft X-ray emission from the Cygnus Loop supernova remnant. An analysis of instrument optics, gratings, and focal plane camera is discussed.
Astronomical X-ray diffraction gratings are a key technology under development for current and future NASA missions. X-ray reflection gratings, developed at Penn State University, have recently demonstrated both leading diffraction efficiency and high spectral resolving power. However, recent results are the result of different fabrication techniques and a single technique has not yet been developed to yield a grating that satisfies both the diffraction efficiency and resolving power required by future missions. Here we seek to leverage exiting electron-beam lithographic techniques to produce a grating with groove groove pattern capable of high resolving power. We then introduce new ion-milling techniques to create custom groove profiles capable of high diffraction efficiency. The goal is to produce a radial groove pattern with precisely blazed facets that are customizable based on ion mill input parameters. The process should be insensitive to groove density (ranging from ~150 nm to 400+ nm), facet size, and desired facet angle. Initial efforts in this study have concentrated on constraining various parameters in ion milling to fully characterize the effect of each parameter on the grating groove profile. We present here initial results and discuss experimental verification and future work.
The Polarimeter for Relativistic Astrophysical X-ray Sources (PRAXyS) is one of three Small Explorer (SMEX)
missions selected by NASA for Phase A study. The PRAXyS observatory carries an X-ray Polarimeter Instrument (XPI)
capable of measuring the linear polarization from a variety of high energy sources, including black holes, neutron stars,
and supernova remnants. The XPI is comprised of two identical mirror-Time Projection Chamber (TPC) polarimeter
telescopes with a system effective area of 124 cm2 at 3 keV, capable of photon limited observations for sources as faint
as 1 mCrab. The XPI is built with well-established technologies. This paper will describe the performance of the XPI
flight mirror with the engineering test unit polarimeter.
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