Patent ID: 9511882
Filing Date: 2016-12-06
CPC Classification: B64G,G05D

Claim Text:
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.