Algorithm of ISS Optimal Propellant Maneuver with Path Constraints in ISS Structure Loads

The Integrated Guidance, Navigation and Control (GN&C) system of ISS is composed of the Russian segment (RS) GN&C system (SUDN) and American segment (AS) GN&C. The ISS flight schedule prescribes regular ISS large-angle maneuvers, which might be executed with two different methods, both of which utilize RS thrusters and ensure allowed structural loads in ISS critical interfaces. In the first method maneuver is performed under RS control around Euler axis; specific constraints, developed by NASA and known as "Pulse-Train", are imposed on command signals to ensure ISS structural integrity. Maneuver of the second type is conducted under AS control, and RS thrusters are activated via the procedure of CMG momentum desaturation. The maneuver trajectory is computed on the Earth as the solution of Optimal Propellant Maneuver (OPM) problem of rigid body rotation under the influence of gravitation and atmospheric forces and with smooth control. In this paper we present new ISS OPM algorithm, developed for RS GN&C, which solves optimal control problem of flexible body rotation under the influence of external forces and with pulse-like control signals. Specific path constraints on allowed structural loads in ISS critical interfaces are also taken into account. Reduced flexible model of ISS and optimal control problem formulation are developed by Rocket and Space Corporation Energia (RSCE). Modeling of elastic body dynamics and optimization problem solution are conducted by DATADVANCE and then verified by RSCE specialists using their own algorithms. Findings of the research show that in all relevant cases the proposed algorithm is twice fuel-efficient compared to existing methods and makes it possible to lower the required number of thrusters firings by order of magnitude.

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