The Line Emission Mapper (LEM) is a Probe mission concept developed in response to NASA’s Astrophysics Probe Explorer (APEX) Announcement of Opportunity. The LEM project is a collaboration between the Smithsonian Astrophysical Observatory (SAO), the NASA Goddard Space Flight Center (GSFC) and Lockheed Martin (LM). LEM is a large field of view (30′ equivalent diameter), soft X-ray mission (0.2-2.0 keV bandpass) with a large format microcalorimeter X-ray imaging spectrometer in the focal plane (1.3-2.5 eV spectral resolution) that provides unprecedented grasp (the product of effective area times field of view) in this bandpass. LEM’s sensitivity to diffuse X-ray emission will be orders of magnitude higher than existing or proposed missions. LEM’s primary science will characterize the diffuse gas in the X-ray haloes in galaxies, the outskirts of galaxy clusters and the filamentary structures between these clusters, and in the Milky Way star formation regions and Galactic halo, and Galactic and Local Group supernova remnants. To accomplish these objectives, the LEM spacecraft and mission have been designed to perform long observations of relatively faint objects and to perform an All-Sky Survey. The science payload consists of a single X-ray mirror assembly and a single focal plane instrument, the microcalorimeter operating at a temperature of 40 mK. The LEM spacecraft is a high-heritage, low-risk design that meets or exceeds all requirements, in particular the thermal requirements for the calorimeter, electronics, and mirror. The science mission profile supports high observing efficiency (> 90%), large sky coverage (45−150° field of regard), and flexible operations that maximize the science return. LEM mission and science operations follow the same successful approaches used by LM for 16 NASA missions and by SAO for 24 years of successful operation of a NASA Great Observatory, the Chandra X-ray Observatory. With multiple decades of experience developing and maintaining the Chandra X-Ray Center Data System, the LEM team will develop the software to produce and disseminate high-quality data to the entire astronomical community. In this paper, we discuss the design of the mission and spacecraft operations that supports the transformational science that LEM promises to deliver.
In the 2020 Astrophysics Decadal Survey, the National Academies identified cosmic feedback and structure formation as a key question that should drive research in the upcoming decade. In response to this recommendation, NASA released a call for X-ray and IR probe-class missions, with a $1B cost cap. The line emission mapper (LEM) is a mission concept designed in response to this call. LEM is a single-instrument X-ray telescope that consists of a Wolter–Schwarzschild type I X-ray optic with a 4 m focal length, coupled with an X-ray microcalorimeter with a 30′ field of view (FoV), 15″ angular resolution, and 2.5 eV energy resolution [full-width half maximum (FWHM)], with a 1.3 eV FWHM energy resolution central subarray. The high throughput X-ray mirror combined with the large FoV and excellent energy resolution allows for efficient mapping of extended emission-line dominated astrophysical objects from megaparsecs to sub-pc scales to study cosmic ecosystems and unveil the physical drivers of galaxy formation.
The line emission mapper x-ray microcalorimeter instrument requires a 4 K cryogenic system to precool a continuous adiabatic demagnetization refrigerator enabling high-resolution x-ray spectroscopy. The cryogenic system described in this work provides the required structural and thermal environments using mature cooling and structural technologies. The system is comprised of a dewar design based on heritage manufacturing processes and an efficient four-stage pulse tube cryocooler with supporting control electronics.
The line emission mapper (LEM) is a probe-class mission concept that is designed to detect x-ray emission lines from hot ionized gas (T > 106 K) that will enable us to test galaxy evolution theories. It will permit us to study the effects of stellar and black-hole feedback and flows of baryonic matter into and out of galaxies. The key to being able to study the hot gases that are otherwise invisible to current imaging x-ray spectrometers is that the energy resolution is sufficient to use cosmological redshift to separate extragalactic source lines from foreground Milky Way emission. LEM incorporates a large-format microcalorimeter array instrument called the LEM microcalorimeter spectrometer (LMS) with a light-weight x-ray optic with 10” half power diameter angular resolution. The LMS microcalorimeter array has pixels with 15″ pixel pitch over a 33′ field of view (FOV) optimized for the 0.3 to 2 keV energy band. The central 7′ region of the array has an energy resolution of 1.3 eV at 1 keV and the rest of the FOV has 2.5 eV energy resolution at 1 keV. The array will be read out with state-of-the-art time-division multiplexing. We present an overview of the LMS instrument, including details of the entire detection chain, the focal plane assembly, as well as the cooling system and overall mechanical and thermal design. For each of the key technologies, we discuss the current technology readiness level and the plan to advance them to be ready for flight. We also describe the current system design and our estimate for the mass, power, and data rate of the instrument. The design details presented concentrate primarily on the unique aspects of the LMS design compared with prior missions and confirm that the type of microcalorimeter instrument needed for LEM is not only feasible but also technically mature.
The Lynx x-ray microcalorimeter instrument on the Lynx X-ray Observatory requires a state-of-the-art cryogenic system to enable high-precision and high-resolution x-ray spectroscopy. The cryogenic system and components described provide the required environment using cooling technologies that are already at relatively high technology readiness levels and are progressing toward flight-compatible subsystems. These subsystems comprise a cryostat, a 4.5-K mechanical cryocooler, and an adiabatic demagnetization refrigerator that provides substantial cooling power at 50 mK.
NASA’s Wide Field Infrared Survey Telescope (WFIRST) is being designed to deliver unprecedented capability in dark energy and exoplanet science, and to host a technology demonstration coronagraph for exoplanet imaging and spectroscopy. The observatory design has matured since 2013 [“WFIRST 2.4m Mission Study”, D. Content, SPIE Proc Vol 8860, 2013] and we present a comprehensive description of the WFIRST observatory configuration as refined during formulation phase (AKA the phase-A study). The WFIRST observatory is based on an existing, repurposed 2.4m space telescope coupled with a 288 megapixel near-infrared (0.6 to 2 microns) HgCdTe focal plane array with multiple imaging and spectrographic modes. Together they deliver a 0.28 square degree field of view, which is approximately 100 times larger than the Hubble Space Telescope, and a sensitivity that enables rapid science surveys. In addition, the technology demonstration coronagraph will prove the feasibility of new techniques for exoplanet discovery, imaging, and spectral analysis. A composite truss structure meters both instruments to the telescope assembly, and the instruments and the spacecraft are on-orbit serviceable. We present the current design and summarize key Phase-A trade studies and configuration changes that improved interfaces, improved testability, and reduced technical risk. We provide an overview of our Integrated Modeling results, performed at an unprecedented level for a phase-A study, to illustrate performance margins with respect to static wavefront error, jitter, and thermal drift. Finally, we summarize the results of technology development and peer reviews, demonstrating our progress towards a low-risk flight development and a launch in the middle of the next decade.
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