摘要：The paper studies the deployment dynamics of along tethered spacecraft system (TSS) with an atmosphericsounder. The tether (several ten kilometers) is deployed from thespacecraft by means of a mechanism that works only for braking.A dynamic nominal deployment control law is designed in anorbital moving coordinate system taking into account theaerodynamic forces acting on the end-bodies (the spacecraft andatmospheric sounder) and inextensible tether. The motionstability of the TSS is analyzed. The deployment process isstudied in a geocentric coordinate system with consideration ofthe dynamics of control mechanism operation, tether elasticity,and other perturbations. The numerical simulations show thatdesigning the nominal deployment control law taking intoaccount the aerodynamic force reduces the system’s controlerror several times for the deployment process.
关键词：Tethered spacecraft system; atmospheric;sounder; modeling; nominal deployment control law; motion;stability; control error
