Thrust Vector Control of an Upper-Stage Rocket with Multiple Propellant Slosh Modes. (26th August 2012)

• Record Type: Journal Article
• Authors: Rubio Hervas, Jaime; Reyhanoglu, Mahmut
• Other Names: Rodellar J. Academic Editor.
• Is Part Of: Mathematical problems in engineering. Volume 2012(2012)
• Publication Date: 2012-08-26
• Subjects: Engineering mathematics -- Periodicals; 510.2462
• DOI: 10.1155/2012/848741
• Languages: English
• ISSNs: 1024-123X

Abstract

Abstract : The thrust vector control problem for an upper-stage rocket with propellant slosh dynamics is considered. The control inputs are defined by the gimbal deflection angle of a main engine and a pitching moment about the center of mass of the spacecraft. The rocket acceleration due to the main engine thrust is assumed to be large enough so that surface tension forces do not significantly affect the propellant motion during main engine burns. A multi-mass-spring model of the sloshing fuel is introduced to represent the prominent sloshing modes. A nonlinear feedback controller is designed to control the translational velocity vector and the attitude of the spacecraft, while suppressing the sloshing modes. The effectiveness of the controller is illustrated through a simulation example.