Optimization of the tether-assisted return mission of a guided re-entry capsule

The oscillations of a body with an orbital tethered system

“…In dynamic deployment the tether is released more rapidly than in static deployment, 2,3 and, under the action of the Coriolis force, the capsule is deflected from the vertical, and then, after the tether unfolds to its complete length, return motion of the capsule to the vertical begins. The tensile force of the tether, variable in value and direction, produces an additional moment, under the action of which the satellite performs non-stationary oscillations about the centre of mass, which, in turn, leads, for example, to the occurrence of undesirable additional microaccelerations.…”

“…[1][2][3][4] In this paper we assume that the law of variation of the tensile force of the tether and the trajectory of the load, attached to the tether, are known, and we investigate the oscillations of the satellite as a rigid body under the action of the tensile force of the tether and the gravitational moment.…”

The Oscillations of a Spacecraft under the Action of the Tether Tension Moment and the Gravitational Moment

“…Consider the motion of a spacecraft about of a mass center during the dynamic deployment of a tethered system with a re-entry capsule. In dynamic deployment the tether is released more rapidly than in static deployment [2,4] and, under the action of the Coriolis force, the capsule is deflected from the vertical, and then, after the tether unfolds to its complete length, return motion of the capsule to the vertical begins. The tether tension, variable in value and direction, produces an additional moment, under the action of which the satellite performs non-stationary oscillations about of the mass center, which, in turn, leads, for example, to the occurrence of an undesirable additional microaccelerations.…”

“…Assuming that the change in the value and direction of the tensile force is slow and the gravitational moment is equal to zero, approximate and exact solutions of the non-linear differential equations of the perturbed and the unperturbed motions are obtained in terms of elementary functions and elliptic Jacobi functions. Similar solutions in linear statement of problem for the case when the gravitational moment takes place are found.In the majority of publications devoted to an analysis of space tethered systems, the object of the investigation is the tether and the load, in which the satellite is regarded as a point mass [1][2][3][4][5][6][7][8]. And only in the papers [9, 10] motion of a spacecraft relative of the mass center was considered.…”

“…In the majority of publications devoted to an analysis of space tethered systems, the object of the investigation is the tether and the load, in which the satellite is regarded as a point mass [1][2][3][4][5][6][7][8]. And only in the papers [9, 10] motion of a spacecraft relative of the mass center was considered.…”