Open AccessApproximate optimal method for controlling the angular motion of a spacecraft as part of an orbital tether system
Author(s) -
Yu. M. Zabolotnov
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/984/1/012024
Subject(s) - spacecraft , physics , control theory (sociology) , orbital maneuver , center of mass (relativistic) , angular velocity , orbit (dynamics) , optimal control , relative motion , orbital mechanics , aerospace engineering , classical mechanics , computer science , satellite , mathematics , control (management) , engineering , mathematical optimization , artificial intelligence , energy–momentum relation , astronomy
An approximate optimal method for controlling the movement relative to the center of mass of a spacecraft as part of an orbital tether system is considered. The purpose of the control is to stabilize the spatial angular movement of the spacecraft relative to the direction of the tether connecting it to another spacecraft. If there is no control, the angular movement of the spacecraft relative to the direction of the tether may be unstable. This is primarily due to the disturbances that occur during the formation (deployment) of tether systems, as well as the internal small mass asymmetry of the spacecraft that inevitably occurs during its manufacture. An approximate optimal method for stabilizing the relative motion of a spacecraft on a tether is proposed, based on the Bellman dynamic programming principle and the averaging method. The averaging method is used for approximate solution of the Bellman partial differential equation, which allows in many cases to obtain the regulator’s equations in analytical form. An example of the application of this approach to stabilize the movement of a small spacecraft when deploying an orbital tether system is given.