Design of the ultra-low orbit Earth remote sensing spacecraft
Authors: Sobolev I.A.
Published in issue: #4(148)/2024
DOI: 10.18698/2308-6033-2024-4-2351
Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft
The paper considers possible design of the Earth remote sensing spacecraft intended for operation in the ultra-low orbits at an altitude of 200...300 km. It reviews the previously developed spacecraft operating in the ultra-low orbits and their main characteristics. Requirements to the spacecraft layout are formulated taking into consideration flight parameters in a zone with significant aerodynamic influence. Characteristics of the optoelectronic equipment to install on such spacecraft are assessed. Operation schemes of the propulsion system based on the SPD-100 electric rocket engines having sufficient flight experience are analyzed, working fluid reserves and mass of the propulsion system are estimated, and results of the correction maneuver computation are presented. The paper proposes main design solutions required in creation of a spacecraft of this class, in particular in design and development of optoelectronic equipment, power supply systems, orientation and stabilization systems.
EDN ZYCUKF
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