On dynamical formulation of a tethered satellite system with mass transport
Abstract
Two satellites connected by a long flexible tether along the earth radial direction comprise a stable equilibrium state. This research investigates the manner in which a third mass transporting from one satellite to the other disturbs the equilibrium state. A system of four equations of inplane motion has been derived based on the assumptions that the tether remains straight between the masses and of constant length. A combination of computer subroutines DGEAR and ZANAYT is suggested for the approximate solution of the system of nonlinear differential equations with one constraint condition on the variables. Alternatively, a system of four independent differential equations are derived by eliminating the Lagrange multiplier.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 May 1984
 Bibcode:
 1984STIN...8428888L
 Keywords:

 Analysis (Mathematics);
 Computer Programming;
 Differential Equations;
 Mass Transfer;
 Nonequilibrium Conditions;
 Subroutines;
 Tethered Satellites;
 Approximation;
 Circular Orbits;
 Equilibrium;
 Formulations;
 Functions (Mathematics);
 Kinetic Energy;
 Scientific Satellites;
 Tethering;
 Transport Properties;
 Vector Analysis;
 Launch Vehicles and Space Vehicles