Launched in March 2021, the 3U CubeSat nanosatellite was the first ever to use an ultra-lightweight harmonic diffractive lens for Earth remote sensing. We describe the CubeSat platform we used; our 10 mm diameter and 70 mm focal length lens synthesis, design, and manufacturing; a custom 3D-printed camera housing built from a zero-thermal-expansion metal alloy; and the on-Earth image post-processing with a convolutional neural network resulting in images comparable in quality to classical refractive optics used for remote sensing before.
Abstract. The paper presents a feasibility study for an optical system, based on a diffractive membrane. The authors have analyzed structural design of diffractive optical elements for space application and developed finite element models of diffractive lens's carrier and mount. The models were developed for two different schemes: MOIRE project and for the original scheme, developed by the authors. The schemes were analyzed for structural stiffness of the diffractive lens's carrier and mount. The shapes and frequencies of natural oscillations of the carriers of the lens were calculated. The problems of the membrane system's orbit injection and operation were analyzed. An algorithm for the terminal control of the orbital period, eccentricity and longitude of the point of standing of the orbital surveillance system was proposed.Keywords: diffractive optics, space membrane optical system, finite element modeling, space telescope, geostationary orbit Citation: Salmin VV, Karpeev SV, Peresypkin KV, Сhetverikov AS, Tkachenko IS. Feasibility study and modeling of components for an informational space system based on a large diffractive membrane.
The paper considers the problem of control over a large space structure (LSS) control at a given station on a geostationary orbit (GSO). An observation spacecraft with diffractive optical elements (DOE) is taken as an example of a large space structure. Various perturbing factors influence the motion of a LSS along GSO, most notably solar radiation pressure. Two problems are considered: control over the motion of the center of mass, and control of the motion in relation to the center of mass. The paper gives the results of modeling the process of LSS control, based on developed control algorithms.
This article surveys approaches to the selection of design parameters and modelling the functioning of the remote sensing satellite systems, taking into account the requirements and restrictions on customer resources. The objective of this research is to increase the efficiency of the use of space systems to solve urgent tasks of monitoring the earth’s surface. Firstly, an analysis of the requirements for space imagery materials and consumer information support was carried out, secondly, mathematical models of remote sensing equipment and onboard systems of small spacecraft were developed, and finally, a database with the technical characteristics of the onboard systems and remote sensing equipment of spacecraft, launch vehicles and ground-based reception and processing information facilities was created. As a result, software to determine main design parameters and modelling the functioning of cost-effective remote sensing satellite systems was developed.
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