Attitude Control of a Flexible, Spinning, Toroidal Manned Space Station |
Contents
Physical Interpretation | 23 |
FLEXIBLE VEHICLES WITH COUPLED TWOAXIS LINEARFEEDBACK | 29 |
EQUATIONS OF MOTION FOR THE CONTROLLED SPINNING SPACE | 39 |
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Appendix balanced control forces BALANCED FORCES body-fixed center of mass centroidal line Chapter characteristic equation characteristic roots computer results computer solutions consider control axes control moments control system coordinates Coriolis forces damping ratio defined by Eq deflection derived determined equations of motion excited flexible mode flexible vehicles employing force and sensor forces or moments formulas higher modes IMAGINARY S/OMEGA in-plane indicated inertia linear loci marginal stability modal poles mode number mode shapes moment of inertia natural frequency number represents observed from Eqs obtain orthogonal parameters points of control rate network REAL S/OMEGA rigid-mode root locus rotating sensor locations shown in Fig sin ny small gains spin axis spinning space station structural damping Substituting Eqs symmetric cross section third mode toroid UNCOUPLED SYSTEM values yields ατ ΕΙ ух ху