The correction of quasi-static wavefront errors within a coronagraphic optical system will be a key challenge to overcome in order to directly image exoplanets in reflected light. These quasi-static errors are caused by mid to high-order surface errors on the optical elements as a result of manufacturing processes. Using high-order wavefront sensing and control (HOWFSC) techniques that do not introduce non-common path aberrations, the quasi-static errors can be corrected within the desired region of interest designated as the dark hole. For the future Habitable Worlds Observatory (HWO), HOWFSC algorithms will be key to attaining the desired contrasts. To simulate the performance of HOWFSC with space rated processors, optical models for a 6 m class space-borne observatory and a coronagraph have been developed. Phenomena such as the Talbot effect and beamwalk are included in the simulations using combinations of ray-based modeling and end-to-end propagation techniques. After integrating the optical models with the embedded processors, simulations with realistic computation times can be performed to understand the computational hardware performance that will be needed to maintain the desired contrasts. Here, the details of the optical models are presented along with the HOWFSC methods utilized. Initial results of the HOWFSC methods are also included as a demonstration of how system drifts will degrade the contrast and require dark hole maintenance.
Astronomical space interferometers have the potential to achieve milliarcsecond resolution via formation-flying collectors hundreds of meters apart. The collectors’ role is to transfer the starlight beams to a combiner that coherently interferes them. One challenge is controlling optical distances within a fraction of a wavelength while maneuvering the spacecraft to maintain their relative position. Since measuring relative position is much easier than controlling it, we propose long compact delay lines that significantly relax formation flying requirements. We present a proof-of-concept demonstrating an optical 4-m free-space delay in the lab. The delay line utilizes four high-reflectance mirrors in a configuration that fits within a 10cm x 20cm footprint suitable for a CubeSat. We also describe a visible-laser metrology approach that controls the optical path across the 4-m range. The delay line and metrology system would be part of the combiner spacecraft. Such an arrangement will not only relax the relative positioning requirements but also enable a two-spacecraft (total) interferometer that would make a technology demonstration mission more feasible in the near future.
Implementing high-order wavefront sensing and control (HOWFSC) algorithms on future space telescopes will require significant computing power. To enable the mission of Habitable Worlds Observatory to directly image exoplanets, we need to improve our understanding of the available performance of radiation-hardened processors. In this work, we describe the testing setup we use to evaluate HOWFSC algorithms, including Electric Field Conjugation and optical modeling on embedded processors. This testing setup enables accurate performance characterization of spaceflight-relevant CPUs and FPGAs in support of HOWFSC algorithms. We interface the embedded processors with a software model of a telescope and coronagraph to perform processor-in-the-loop testing. With this setup, we can test a range of telescope and HOWFSC algorithm configurations that are relevant to the design of future space missions, illuminating the feasibility of in-space HOWFSC algorithm execution.
Space interferometers could, in principle, exploit the relatively stable space environment and ease of baseline reconfiguration to collect measurements beyond the limitations of ground-based interferometers. In particular, a two-element interferometer could provide excellent uv-plane coverage over a few tens of low Earth orbits. One of the challenges for free-flying interferometers is controlling the optical path distance with subwavelength accuracies despite the collectors flying up to hundreds of meters apart. We consider two approaches: an artificial in-orbit laser guide star (LGS) that provides a phase reference for the space interferometer and fringe tracking on the science target itself. The two approaches (LGS versus no LGS) would require different image processing techniques. In this work, we explore image processing with LGS phase residuals due to global positioning system (GPS) uncertainties. We use GPS uncertainties from the Gravity Recovery and Climate Experiment Follow-On mission to simulate image retrieval with a 300-m baseline laser-guided space interferometer. This is done by fitting the slowly varying phase errors of complex visibility measurements. We also consider a 40-m baseline interferometer with visibility(-modulus)-only measurements. In this case, we simulate the bias in visibility due to fringe tracking in the presence of parasitic forces acting on the spacecraft. We then use a modified version of the hybrid input–output phase retrieval algorithm for image reconstruction. We conclude that under our optimistic assumptions, both approaches could enable general imaging of a few large stars even with CubeSats, although an LGS would significantly improve the best resolution obtainable.
Future space telescopes such as the Habitable Worlds Observatory (HWO) will use coronagraphs and wavefront control to achieve the approximate 1010 starlight suppression necessary to directly image Earth-like exoplanets. Wavefront control algorithms such as Electric Field Conjugation (EFC) will control thousands of actuators at cadences of seconds or minutes. EFC uses a Jacobian matrix which maps Deformable Mirror (DM) voltages to the change in electric field at the image plane. The Jacobian matrix grows in size with the number of pixels, DM actuators, and spectral channels. EFC on proposed future telescopes like HabEx and LUVOIR will require as much as 25 GFLOPS (floating point operations per second). This level of compute density has never been achieved on radiation-hardened processors that are used on NASA Class-A missions such as the Roman Space Telescope. Previous work has focused on estimating the Compute Density (CD) of processors using assumptions about memory access characteristics and the parallelizability of algorithm implementation. Such analysis produces large uncertainty due to the assumptions necessary to compute CD. To refine the estimates of EFC compute capability of current generation processors, we determine the FLOPS performance of processors using benchmark tests which represent the operations mix and memory access patterns of EFC. The expected EFC iteration computation period on future space telescopes based on application benchmarks is reported. We have created a ray tracing optical model for the telescope assembly as well as a physical optics model for the telescope and coronagraph for the purposes of testing HOWFC algorithms. This testing can be applied to CPUs and FPGAs, representing a range of potential compute architectures.
Space interferometers could, in principle, exploit the relatively stable space environment and ease of baseline reconfiguration to collect measurements beyond the limitations of ground-based interferometers. In particular, a two-element interferometer could provide excellent uv-plane coverage over a few tens of low-Earth orbits. One of the challenges for free-flying interferometers is controlling the optical path distance with sub-wavelength accuracies despite the collectors flying up to hundreds of meters apart. This work considers two approaches: an artificial in-orbit laser guide star (LGS) that provides a phase reference for the space interferometer and fringe tracking on the science target itself. The two approaches (LGS vs. no LGS) would require different image processing techniques. In this work, we explore image processing with LGS phase residuals due to GPS uncertainties. We use GPS uncertainties from the GRACE-FO mission to simulate image retrieval with a 300 m baseline laser-guided space interferometer. This is done by fitting the slowly varying phase errors of complex visibility measurements. We also consider a 40 m baseline interferometer with visibility(-modulus)-only measurements. In this case, we simulate the bias in visibility due to fringe tracking in the presence of parasitic forces acting on the spacecraft. We then use a modified version of the Hybrid Input-Output phase retrieval algorithm for image reconstruction. We conclude that under our optimistic assumptions, both approaches could enable general imaging of a few large stars even with CubeSats, although an LGS would significantly improve the best resolution obtainable.
This work presents a novel calibration method for time transfer and ranging systems. The CLICK-B/C design uses a shared aperture for transmit and receive, and optical isolation is achieved using free-space dichroics and band-pass filters. During calibration, the transmitter is tuned close to the receiver assigned wavelength, bypassing filtering during calibration. The receiver is able to measure the outgoing signal due to internal reflections on the telescope lenses. The transmitter and receiver delays can then be subtracted from time of flight, eliminating delay uncertainties arising from all components of the transmitter and receiver, with minimal change in their operating conditions. Thanks to the high repetition rates of communication links, more than 10 MHz, this method could lead to millimeter-level absolute ranging, as well as time transfer accuracy in the low picoseconds, enabling new applications and advances in space radio interferometry, GPS-denied navigation, and time synchronization for synthetic aperture telescopes.
The CubeSat Laser Infrared Crosslink (CLICK) B/C mission seeks to demonstrate laser crosslinks for full-duplex communications and two-way ranging and time-transfer between two 3U CubeSats: CLICK-B and CLICK-C. Laser crosslinks between satellites can provide enhanced performance, with high data transfer rates and high precision range and timing information, using low size, weight, and power (SWaP) optical transceiver terminals. CLICK-B and CLICK-C will demonstrate laser crosslinks with data rates of at least 20 Mbps over separation distances ranging from 25 km to 580 km. CLICK-B/C will also demonstrate a ranging precision of better than 50 cm and a time transfer precision of better than 200 ps single shot over these distances. We present the design and development status and recent testing results of the laser transmitter and fine pointing, acquisition, and tracking (PAT) system, which are key to achieving these capabilities. The 1550 nm laser transmitter follows a master oscillator power amplifier (MOPA) design using an erbium-doped fiber amplifier (EDFA) for an average output power of 200 mW. A semiconductor optical amplifier (SOA) is used to achieve the pulse position modulation (PPM), ranging in order from 4 PPM - 128 PPM. The PAT system uses a microelectromechanical systems (MEMS)-based fast steering mirror (FSM) for fine pointing. A quadrant photodiode (quadcell) provides feedback for the actuation and steering of the FSM.
Future planned space telescopes, such as the IR/O/UV Large Telescope, recommended by Astro2020 will be used to directly image exo-Earths. They will employ high-order wavefront sensing and control (HOWFSC) to correct static and slow wavefront errors in the image plane to achieve contrasts better than 109. Our work evaluates the computational requirements for HOWFSC algorithms and compares these to the capabilities of processors that are expected to be available during mission development. We find that HOWFSC creates unprecedented requirements for space-based computational power, such as the ∼1013 floating-point operations necessary to generate the dark hole, based on the Large UV/Optical/IR (LUVOIR) study. In our worst-case estimates, maintaining an LUVOIR-size dark hole at 1010 contrast might require up to several orders of magnitude more computational throughput than available on the most advanced radiation-hardened processor.
The mirrors of astronomical interferometers need to be aligned within a fraction of a wavelength relative to one another. This would be especially challenging for optical instruments with mirrors separated by hundreds of meters flying in Earth’s orbit. However, in this work, we show that this alignment can be achieved by means of: (i) flying the mirror cluster in a particular orbital configuration; (ii) closing a coarse positioning loop using GNSS (Global Navigation Satellite System); and (iii) closing a fine wavefront-control loop using light from a laser guide star. The orbital configuration is designed to keep the mirrors passively pointing at the target star (up to a small orbital perturbation) while the interferometer cluster is orbiting and changing its baseline. The laser guide star would be flying in the same orbit but in the opposite direction. In medium- or high-Earth orbit, the interferometer would be able to observe a star for several hours per orbit. In this work, we analyzed the performance of an optical space interferometer consisting of nine 20 cm mirrors mounted on CubeSats and flying 3 km apart (together with a combiner and a laser guide star small satellite). This configuration supports a resolution of 0.04 milliarcseconds - an order of magnitude better than current ground-based interferometers. We estimate the performance of this system imaging stellar surfaces assuming perfect wavefront estimation and control.
KEYWORDS: Space operations, Telescopes, Space telescopes, Computer architecture, Commercial off the shelf technology, Algorithm development, Radiation effects, Wavefront sensors, Satellites, Detection and tracking algorithms
Future planned space telescopes such as HabEx and LUVOIR will be used to directly image exo-Earths. These telescopes use coronagraph instruments to suppress starlight and resolve dim exoplanets. They will employ high order wavefront sensing and control (HOWFSC) to correct static and slow wavefront errors in the image plane to achieve contrasts above 109. This work evaluates architectures to meet the computational requirements for HOWFSC algorithms with available processors. We find that the computational requirements of HOWFSC will impose unprecedented requirements on space-based components and that typical combinations of computational resource and control architecture will consume significant observation time. Science yield from the space telescope can be improved, and mission risk and cost reduced, by using co-flying or ground-in-the loop computational offload architectures. In particular, a high-capability co-flying processor could use commercial components 104 times more powerful than typical radiation hardened options. This would enable key HOWFSC algorithms to run in seconds rather than hours or days, removing operational constraints on the science mission. While commercial processors may be more susceptible to total ionizing dose radiation effects over the expected mission lifetime of 5-10 years, the relatively low cost of development and replacement launches make these co-flying processors an attractive option. We evaluate three major co-flying architecture trades: (i) inter-spacecraft distance, (ii) risk classification, and (iii) processor selection. We find that one or more low-cost replaceable co-flying processors with COTS components and flying several kilometers from the telescope spacecraft can provide all needed computation.
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