Model-free image-based wavefront correction techniques, such as the stochastic parallel gradient descent (SPGD) algorithm, will be useful in achieving diffraction-limited optical performance in near-future optical remote sensing systems. One difficulty facing the image-based method is that the correction performance depends on the evaluation metric and the evaluated scene. We propose several evaluation functions and investigate the relationship between the optimization speed and the scene textures for each metric in the SPGD algorithm. Based on the simulation results, the study experimentally compared wavefront correction performance using four cost functions and two extended aerial images. Consequently, we found that the deviation-based cost function allowed efficient wavefront correction for versatile extended scenes. In addition, observing extended scenes with distinct structures can facilitate correction speed. Furthermore, we numerically validated this approach in a segmented-aperture imaging system for large telescopes. We believe that the presented approach allows us to realize spaceborne remote sensing with unprecedented high angular resolution.

Deviation-based wavefront correction using the SPGD algorithm for high-resolution optical remote sensing.

Consider a constellation of over a hundred low Earth orbit satellites that aim to capture every point on Earth at least once a day. Clearly, there is a need to download from each satellite a large set of high-quality images on a daily basis. In this paper, we present a laser communication (lasercom) framework that stands as an alternative solution to existing radio-frequency means of satellite communication. By using lasercom, the suggested solution requires no frequency licensing and therefore allows such satellites to communicate with any optical ground station on Earth. Naturally, in order to allow laser communication from a low Earth orbit satellite to a ground station, accurate aiming and tracking are required. This paper presents a free-space optical communication system designed for a set of ground stations and nano-satellites. A related scheduling model is presented, for optimizing the communication between a ground station and a set of lasercom satellites. Finally, we report on SATLLA-2B, the first 300 g pico-satellite with basic free-space optics capabilities, that was launched on January 2022. We conjecture that the true potential of the presented network can be obtained by using a swarm of few hundreds of such lasercom pico-satellites, which can serve as a global communication infrastructure using existing telescope-based observatories as ground stations.

/pdf/pico-sat-to-ground-control-optimizing-download-link-via-1ktxy06h.pdf

Pico-Sat to Ground Control: Optimizing Download Link via Laser Communication

The phase diversity (PD) method is effective for scene-based wavefront sensing and control (WFSC) in spaceborne high-resolution imagers for Earth observation. The simplest way of performing the PD WFSC is offering a diversity wavefront by directly actuating a corrective device, such as a deformable mirror. However, this strategy faces a challenge in constructing a numerical model of the provided diversity wavefront because some corrective actuators' properties prevent us from precisely determining their deflection behaviors. To avoid this modeling issue, we propose the sequential PD (SPD) method to compensate for static aberration using a corrective device with modeling errors. The SPD WFSC repeats the PD WFSC to gradually correct the aberration, where the estimated corrective wavefront is regarded as the known diversity in the subsequent PD WFSC. The numerical simulation validated that the proposed idea improved the correction performance when a corrective device had a linear modeling error. Additionally, a demonstration experiment succeeded in aberration removal using a face-sheet deformable mirror with inter-actuator coupling and non-linear responses. An additional simulation demonstrated that the proposed method effectively corrected the discontinuous wavefront aberration in multi-aperture imaging systems. The SPD WFSC can potentially bring us optical remote sensing systems with unprecedentedly high resolution. 

Sequential phase diversity for wavefront correction using a deformable mirror with modeling errors.

Earth observation (EO) missions remain a challenging task for small satellite platforms due to their demanding requirements and space environment effects. In this study, the camera payload development and mission requirements are presented together with the ground-based testing results for a 6U CubeSat called KITSUNE, operating at low Earth orbit. The major challenge of the payload development is maintaining the focus of the optical system despite the thermal vacuum environment in orbit since the low thermal capacity and rapid temperature variation of CubeSats hinder the camera focus. First, the payload is developed with an objective of a 5-m-class imaging mission, which has a 31.4 MP CMOS sensor and a lens with a 300-mm focal length. Second, polyimide heaters and multilayer insulators are utilized in order to maintain focus during imaging operations. Third, a collimator lens is used to aid in image capture during thermal vacuum tests. These images are analyzed thoroughly using various focus measure operators. The Diagonal Laplacian was found to be the most suitable operator due to the consistency in test results. The results also showed that the heat generated by the camera sensor significantly affects the lens temperature and, ultimately, the target temperature of the lens was defined at −1.8°C. Finally, the test results are discussed, including thermal vacuum, vibration, total ionization dose, and the effect of exposure to direct sunlight on the CMOS sensor.

Design and environmental testing of imaging payload for a 6 U CubeSat at low Earth orbit: KITSUNE mission

Microelectromechanical Systems (MEMS) Deformable Mirrors (DMs) are a key technology option for adaptive optics instruments for space applications because they provide high-precision wavefront control with small form-factor, low-power devices. The Deformable Mirror Demonstration Mission (DeMi) CubeSat demonstrated a MEMS DM in space for the first time in order to raise the Technology Readiness Level (TRL) of the technology for future space applications such as high-contrast imaging of exoplanets and optical communications. The DeMi payload demonstrated a 140-actuator MEMS DM from Boston Micromachines Corporation. DM performance was measured with a Shack Hartmann wavefront sensor (SHWFS). The DeMi CubeSat began on-orbit operations in July 2020 and has since met the mission goals of measuring individual actuator displacements to a precision of 12 nm and correcting wavefront errors in space to <100 nm RMS error. The DeMi mission has raised the TRL of MEMS DM technology from a 5 to a 9. This paper summarizes the DeMi payload design and the results from over a year of on-orbit operations. Individual actuator measurements from ground and space operations show the MEMS DM actuating in space with similar performance and measurement uncertainty to ground data with no dead or under-actuating actuators detected. Wavefront control experiments show the DeMi payload correcting thermal- and vibration-induced wavefront errors in space.

On-orbit operations summary for the Deformable Mirror Demonstration Mission (DeMi) CubeSat

Microelectromechanical systems (MEMS) deformable mirrors (DMs) can provide high-precision wavefront control with a small form-factor, low power device. This makes them a key technology option for future space telescopes requiring adaptive optics for high-contrast imaging of exoplanets with a coronagraph instrument. The Deformable Mirror Demonstration Mission (DeMi) CubeSat payload is a miniature space telescope designed to demonstrate MEMS DM technology in space for the first time. The DeMi payload contains a 50-mm primary mirror, an internal calibration laser source, a 140-actuator MEMS DM from Boston Micromachines Corporation, an image plane wavefront sensor, and a Shack–Hartmann wavefront sensor (SHWFS). The key DeMi payload requirements are to measure individual actuator wavefront displacement contributions to a precision of 12 nm and correct both static and dynamic wavefront errors in space to less than 100-nm RMS error. The DeMi mission will raise the technology readiness level of MEMS DM technology from a five to at least a seven for future space telescope applications. We summarize the DeMi optical payload design, calibration, optical diffraction model, alignment, integration, environmental testing, and preliminary data from in-space operations. Ground testing data show that the DeMi SHWFS can measure individual actuator deflections on the MEMS DM to within 10 nm of interferometric calibration measurements and can meet the 12-nm precision mission requirement for actuator deflection voltages between 0 and 120 V. Payload data from throughout environmental testing show that the MEMS DM and DeMi payload survived environmental testing and provides a valuable baseline to compare with space data. Initial data from space operations show the MEMS DM actuating in space with a median agreement between individual actuator measurements from space and equivalent ground testing data of 12 nm.

/pdf/optical-calibration-and-first-light-for-the-deformable-53u34ngtxf.pdf

Optical calibration and first light for the deformable mirror demonstration mission CubeSat (DeMi)

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Optical calibration and first light for the deformable mirror demonstration mission CubeSat (DeMi)