Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Orbital perturbations caused by the space environment will induce deviations compared with prescribed motion trajectory or dynamic performance of tethered satellite system (TSS). To comprehensively investigate effects orbital on TSS, a precise variable-length element that can describe large deformation and flexibility tether is adopted in this paper to predict deployment dynamics considering perturbations, including atmospheric drag, solar pressure, lunisolar gravitation, J 2 perturbation. end, using arbitrary LagrangianEulerian (ALE) description frame work absolute nodal coordinate formulation (ANCF) developed firstly. Subsequently, governing equations for TSS are established context ANCF employment reference node (ANCF-RN). Effects gravity perturbation an optimal analyzed numerically. It shown except out-of-plane TSS. Additionally, tension less affected perturbations. By contrast, gravitation deviation path satellite, which should be considered design phase