Configurable space station momentum

摘要

A method of deploying a modular space station comprises placing an initial space station module in space in a first deployment, the initial space station module including a first control law and momentum component that provides an initial solution for guidance, navigation, and control (GNC) during the first deployment. A first space station modular segment is joined with the initial space station module in a second deployment to produce a first joint configuration of the space station. A second control law and momentum component provides a second solution for GNC of the first joint configuration during the second deployment. A second space station modular segment is joined to the first joint configuration in a third deployment to produce a second joint configuration of the space station. A third control law and momentum component provides a third solution for GNC of the second joint configuration during the third deployment.

主权项

1. An attitude control system for a modular space station, comprising:
a first momentum exchange section comprising an array of control moment gyroscopes or reaction wheels; an attitude control electronics section in operative communication with the first momentum exchange section, the attitude control electronics section comprising at least one flight computer processor configured with a partitioned operating system that adheres to a protocol that provides a real time operating system interface for partitioning of avionics computer resources in time and space domains, wherein the at least one flight computer processor is configured to execute instructions for operation of a control law in providing an operative connection to the first momentum exchange section; and one or more attitude sensors in operative communication with the attitude control electronics section; wherein the control law is implemented by a plurality of software applications comprising: a first application that provides an initial solution for guidance, navigation, and control of a first deployment of the space station, in which the first space station module is placed in space; a second application that provides a second solution for guidance, navigation, and control of a second deployment of the space station in which a second space station module is joined to the first space station module to produce a first configuration of the space station; and a third application that provides a third solution for guidance, navigation, and control of a third deployment of the space station in which a third space station module is joined to the first configuration of the space station to produce a second configuration of the space station; wherein the first momentum exchange section includes momentum for a portion of the first configuration of the space station.