Feasibility Study and Modeling of Components for an Informational Space System Based on a Large Diffractive Membrane

Abstract

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.

Modeling control over large space structure on geostationary orbit

“…This observation spacecraft can be defined as a large space structure: DOE assembly diameter is 10 meters, and the distance from the optical elements to the body of the spacecraft is 60 meters. The design of the frame that connects DOE to the body is discussed in detail in [2].…”

Development of method for selecting motion control laws of space optical system on based diffractive membranes during transfer into geostationary orbit

“…The spacecraft with a membrane diffractive optical system will have a much smaller mass compared to a spacecraft with a refractive optical system. However, such a spacecraft would have large dimensions -the diameter of the lens is of the order of 10-20 m, the distance from the lens to the spacecraft body is of the order of 50 to 70 m. The paper [4] presents a design of the load-bearing structure for an Earth remote sensing satellite with diffractive optics (Figure 1). When such a structure is being propelled by a chemical booster block, significant overloads can occur, which can lead to undesirable structural changes of the diffractive observation system.…”