Effect of thin condensate films of a metal working fluid of an electric propulsion engine on the integral optical coefficients of a spacecraft’s thermal control coating

Design and verification of elongated load installation for a spacecraft

“…Therefore, it is particularly important to design a reasonable installation mode for the payload to minimize the impact of platform response on its performance [6] . At present, most of the loads installed on spacecraft are traditional large space loads, whose installation method is usually directly or through the fixed connection between the support and the structure of the platform, and the installation accuracy depends on the software calibration of the spacecraft devices [7][8] . For the slender load, its height and span are large, so arranging it on the structural plate of the platform directly will cause the overall envelope of the satellite to be too large, which is not only difficult to meet the envelope requirements of the carrier, but also cause the fundamental frequency of the integrator to be too large [9] .…”