Determine of program control system structure for orbital tether system deployment with limitation to tether deployment velocity

The problem of programmatic orbital tether system deployment is studied. The problem of program control system structure for programmatic orbital tether system deployment, the problem of gain value in feedback path optimization is considered. The classical automatic control theory is used. Optimal (relay) and control program of orbital tether system deployment with limitations to tether velocity are considered as nominal programs. Nominal control program was formatted in assumption, that tether is weightless. Nominal control program is carried out by tether tension regulation. For program control system formation, the linearization of orbital tether systems deployment differential equations is carried out. Principe of control above nominal trajectory is deviation control between real parameter and it’s nominal value. Controlled parameters are tether length and it’s velocity. Control by parameters angle between descent spacecraft and local vertical line and angular velocity are not implement, since this parameters is not available for measurement. A reduction of perturbed trajectory to nominal is carried out by reduction of nominal tether tension. Correction of tether tension is carried out in accordance with proportional control law. Values of gains in feedback path are optimized by integral quadratic criteria. The influence of tether mass is considered as perturbing factor, that deflecting orbital tether trajectory from nominal. Numerical simulation orbital tether system deployment with feedback path show that formed program control system allow to readjust tether length and velocity to its nominal values. Value of control error of angle between descent spacecraft and local vertical line is hold at zero and at some point it increase monotonically. Resulted angular velocity is oscillating quantity. Introduction of limitation to tether velocity improves control process. Control error of angle between descent spacecraft and local vertical line and amplitude of oscillations of angular velocity decrease.