Analysis of Performance Characteristics of a Low-Orbit Space Remote Sensing System Based on a Two-Mirror Ritchey–Chrétien Optical Design

The article presents an analysis of size and mass characteristics of an optical space-based remote Earth sensing system. An approach for modification of the two-mirror Ritchey–Chrétien optical design is proposed in order to be able to implement it on board of a low-orbit streamlined satellite fitted with an electric propulsion system for orbit correction. A procedure for joint optimization of the satellite platform and payload characteristics is described. An analysis of the propulsion system is carried out. A method for designing low-orbit small surveillance spacecraft with optical payload fitted with a swivel mirror, capable to produce high-resolution imagery, is proposed. A preliminary design of a low-orbit streamlined satellite, obtained using the developed method, is presented.