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Stellar in-flight calibrations have a relevant impact on the capability of space optical instruments, such as telescopes or cameras, to provide reliable scientific products, i.e., accurately calibrated data. Indeed, by using the in-flight star images, instrument optical performance can be checked and compared with the on-ground measurements. The analysis of star images carried out throughout the entire lifetime of the instrument in space will enable tracking changes in instrument performance and sensitivity due to degradation or misalignment of the optical components. In this paper, we present the concept, the necessary input and the available outputs of the simulations performed to predict the stars visible in the field of view (FoV) of a specific space instrument. As an example of the method, its application to two specific cases, the Metis coronagraph onboard Solar Orbiter and the stereo camera STereo Channel (STC) onboard BepiColombo, are given. Due to their proximity to the Sun, and to Mercury for STC, both instruments operate under harsh environmental conditions in terms of radiation exposure ((e.g., cosmic rays and SEP), high temperatures and significant temperature variations. Therefore, it is crucial to monitor their optical performances.

Landslides have been identified on several solar system bodies, and different mechanisms have been proposed to explain their runout length. We analyze images from the Rosetta mission and report the global characterization of such features on comet 67P/Churyumov‐Gerasimenko's surface. By assuming the height to runout length as an approximation for the friction coefficient of landslide material, we find that on comet 67P, this ratio falls between 0.50 and 0.97. Such unexpected high values reveal a rocky‐type mechanical behavior that is much more akin to Earth dry landslides than to icy satellites' mass movements. This behavior indicates that 67P and likely comets in general are characterized by consolidated materials possibly rejecting the idea that they are fluffy aggregates. The variability of the runout length among 67P landslides can be attributed to the different volatile content located in the top few meters of the cometary crust, which can drive the mass movement. Comet 67P Churyumov‐Gerasimenko has been imaged with unprecedented spatial detail thanks to the high‐resolution OSIRIS camera (Optical, Spectroscopic and Infrared Remote Imaging System) on board the Rosetta spacecraft. 67P is characterized by an extremely diverse morphology comprising different surface features such as rough consolidated terrains, smooth plains, unconsolidated mantles, pits, fractures, cliffs, cuestas, ubiquitous boulders, and layers. The peculiarity of 67P is also reflected by the widespread presence of landslides. By using high‐resolution images, we analyze the shape and aspect ratio of the landslides located on comet 67P finding a mechanical behavior of the cometary material that is more akin to Earth dry landslides than to icy satellites' mass movements. These results make 67P a very peculiar object, mainly composed by ices and refractory materials but characterized by rocky‐type properties rather than icy‐type characteristics. In addition, the considerable variability among the different landslides of 67P suggests that different volatile contents located in the top few meters of the cometary crust play a fundamental role on mass movement, hence being a general indicator for the subsurface cometary heterogeneities. The height to runout length (H/L) of comet 67P/Churyumov‐Gerasimenko landslides ranges between 0.50 and 0.9767P landslide reveal a rocky‐type mechanical behavior indicating that comets are made by consolidated materialsThe H/L variability is an indicator of the different volatile content located in the top few meters of the cometary crust

A wide-field, large-aperture, and lightweight Schmidt configuration has been studied for a space mission proposal named Extreme Universe Space Observatory free flyer (EUSO-FF). EUSO-FF will be devoted to the study of ultrahigh energy cosmic rays, i.e., with energy >5×10^19  eV, through the detection of UV fluorescence light emitted by air showers in the Earth’s atmosphere. The proposed telescope has a field of view of about 50° and an entrance pupil diameter of 4.2 m. The mirror is deployable and segmented to fit the diameter of the launcher fairing; the corrector is a lightweight annular corona.

BepiColombo is the fifth cornerstone mission of the European Space Agency (ESA) foreseen to be launched in August 2014 with the aim of studying in great detail the Mercury planet. One of the BepiColombo instruments is the STereoscopic imaging Channel (STC), which is part of the Spectrometers and Imagers for MPO BepiColombo Integrated Observatory SYStem (SIMBIOSYS) suite: an integrated system for imaging and spectroscopic investigation of the Mercury surface. STC is a stereo camera consisting of two sub-channels, which are looking at +/-20° from nadir direction, that share the detector and some of the optical components. The main scientific camera objective is the 3D global mapping of the entire surface of Mercury with a scale factor of 50 m per pixel at periherm. Five different spectral bands are foreseen, a panchromatic and four intermediate bands, in the range between 410 and 930 nm. To avoid mechanisms, the technical solution chosen for wavelength selection is the single substrate stripe-butted filter in which different glass pieces, with different transmission properties, are glued together. This peculiar choice for the filter architecture, coupled with the fact that the filter is mounted very close to the detector, creates multiple ghosts which can affect seriously the quality of the images. The intensity and the position of the ghost images generated by each filter strip are discussed. An analysis of the ghosts impact on the imaging performance and the solution adopted to limit the degradation are presented.

In this paper, the results of the thermo-elastic analysis performed on the stereo channel of the imaging system Integrated Observatory System for the BepiColombo European Space Agency mission to Mercury are presented. The aim of the work is to determine the effects of ambient parameter variations on the equipment performance; the optical performance is changing during the mission lifetime primarily because of the optics misalignments and deformations induced by temperature variations. The camera optics and their mountings are modeled and processed by a thermo-mechanical finite element model (FEM) program, which reproduces the expected optics and structure thermo-elastic deformations in the instrument foreseen operative temperature range, i.e., between −20?°C and 30?°C. The FEM outputs are elaborated using a MATLAB optimization routine: an algorithm based on nonlinear least square data fitting is adopted to determine the surface equation (plane, spherical, nth polynomial) which best fits the deformed optical surfaces. The obtained surfaces are then directly imported into a ZEMAX code for sequential ray-tracing analysis. Variations of the optical spot diagrams, modulation transfer function curves, and ensquared energy are then computed. The overall analysis shows that the preferred solution for mounting the optical elements is adopting the kinematic constraints instead of using the classical glue solution.

We present the catadioptric optical design solution for the stereo channel of the imaging system SIMBIOSYS for the BepiColombo European Space Agency mission to Mercury. The main scientific objectives of the instrument are the three-dimensional global mapping of the entire surface of Mercury in the panchromatic band and imaging of selected areas in four broad colored bands; both tasks have to be accomplished with a scale factor of 50?m per pixel at periherm. The system consists of an original compact layout in which the two stereo subchannels share a common detector; also, the optical components are common to the two subchannels, with the exception of the first element, which is a rhomboid prism. The field of view of each subchannel is about 5°×5° with a scale factor of 23 arcsec/pixel. The ray-tracing simulation of the system shows that the design guarantees optimal aberration balancing over the entire field of view and the entire wavelength range covered by the instrument, with ensquared energy of the order of 80% in one pixel.

Adaptive optics (AO) has been recently used for the development of ophthalmic devices. Its main objective has been to obtain high-resolution images for diagnostic purposes or to estimate high-order eye aberrations. The core of every AO system is an optical device that is able to modify the wavefront shape of the light entering the system; if you know the shape of the incoming wavefront, it is possible to correct the aberrations introduced in the optical path from the source to the image. The aim of this paper is to demonstrate the feasibility, although in a simulated system, of estimating and correcting an aberrated wavefront shape by means of an iterative gradient-descent-like software procedure, acting on a point source image, without expensive wavefront sensors or the burdensome computation of the point-spread-function (PSF) of the optical system. In such a way, it is possible to obtain a speed and repeatability advantage over classical stochastic algorithms. A hierarchy in the aberrations is introduced, in order to reduce the dimensionality of the state space to be searched. The proposed algorithm is tested on a simple optical system that has been simulated with ray-tracing software, with randomly generated aberrations, and compared with a recently proposed algorithm for wavefront sensorless adaptive optics.

The description of an adaptive optics (AO) system with no wavefront sensor to correct primary aberrations is presented. This system is based on closed loop software that iteratively analyzes a point source target image on the instrument focal plane and suitably modifies the AO device. The performed tests with a pull-only deformable mirror (DM) have shown that the system works very well, reaching an optimal focusing condition in a few seconds using standard components. Such a system can be conveniently applied in all the fields in which a not very fast optical adaptation is acceptable.

The design of a quasi-null lens system for the fabrication of an aspheric oblate convex ellipsoidal mirror is presented. The Performance and tolerance of the system have been analyzed. The system has been applied successfully for the fabrication of the primary mirror of the Wide Angle Camera (WAC), the imaging system onboard the Rosetta, the European Space Agency cornerstone mission dedicated to the exploration of a comet. The WAC is based on an off-axis two-mirror configuration, in which the primary mirror is an oblate convex ellipsoid with a significant conic constant.

A spectroheliograph dedicated to the observation of the solar disk in the extreme-ultraviolet OV spectral line at 62.97 nm is described. As demonstrated in the Skylab SO-82A spectroheliograph [ Appl. Opt.16, 870 ( 1977)], this line is uniquely suited to characterize solar plasma in the important 250, 000 K temperature regime. No multilayer coating or suitable filter is yet available to select this wavelength, so an optical design based on a double spectrograph with a spatial filter to remove the unwanted radiation has been developed. Analysis of the optical design shows that this instrument can obtain a 1 arcsec spatial resolution (two pixels) with a relatively high image-acquisition cadence. A preliminary tolerance analysis has been performed. A simple method of instrument alignment in visible light is also described.

The final optical design of the Wide Angle Camera for the Rosetta mission to the P/Wirtanen comet is described. This camera is an F/5.6 telescope with a rather large 12° × 12° field of view. To satisfy the scientific requirements for spatial resolution, contrast capability, and spectral coverage, a two-mirror, off-axis, and unobstructed optical design, believed to be novel, has been adopted. This configuration has been simulated with a ray-tracing code, showing that theoretically more than 80% of the collimated beam energy falls within a single pixel (20″ × 20″) over the whole camera field of view and that the possible contrast ratio is smaller than 1/1000. Moreover, this novel optical design is rather simple from a mechanical point of view and is compact and relatively easy to align. All these characteristics make this type of camera rather flexible and also suitable for other space missions with similar performance requirements.