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Thrust Vector Control of an Upper-Stage Rocket with Multiple Propellant Slosh Modes
Mathematical Problems in Engineering
  • Mahmut Reyhanoglu, Embry-Riddle Aeronautical University - Daytona Beach
  • Jaime Rubio Hervas, Embry-Riddle Aeronautical University - Daytona Beach
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“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.”—Publisher’s website (Hindawi Publishing Corp.)
Required Publisher’s Statement
“This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.”--Publisher’s website
Citation Information
Mahmut Reyhanoglu and Jaime Rubio Hervas. "Thrust Vector Control of an Upper-Stage Rocket with Multiple Propellant Slosh Modes" Mathematical Problems in Engineering Vol. 2012 Iss. Article ID 848741 (2012) p. 1 - 18
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