Development of a design methodology for heat-loaded dimensionally stable elements of carbon plastic construction for a remote sensing of the Earth space equipment

Abstract

One of the most important tasks of the Federal Space Program of Russia for the period until 2025 is the creation of spacecraft for remote sensing of the Earth. An integral part of the design of this class spacecraft is the determination of the parameters of the orbits that are most effective from the standpoint of information content, energy supply and the duration of active existence. In orbital flight, the temperature state of spacecraft in a complex way varies in time and space. The inhomogeneous temperature field of the structural elements of spacecraft can cause shape distortion, which adversely affects the performance of targets. A technique for a comprehensive analysis and determination of the platform composite design parameters, which is part of the spacecraft for remote sensing of the Earth is proposed. The conditions of thermal loading for flight in a sun-synchronous orbit are considered and mathematical modeling of the operating conditions that ensure the effective operation of such spacecraft is performed. The results of modeling the thermal regime of options for composite platform designs are presented. The technique will be useful in determining the complex of orbital characteristics of the Earth remote sensing satellite at the stage of technical proposals.

Keywords

• earth remote sensing spacecraft
• solar-synchronous orbit
• polymer composite materials
• stress-strain state