Thrust-vector control of a three-axis stabilized spacecraft with fuel slosh dynamics

Jaime Rubio Hervas; Mahmut Reyhanoglu; Hui Tang

doi:10.1109/ICCAS.2013.6704015

Thrust-vector control of a three-axis stabilized spacecraft with fuel slosh dynamics

Jaime Rubio Hervas, Mahmut Reyhanoglu, Hui Tang

Research output: Chapter in book / Conference proceeding › Conference article published in proceeding or book › Academic research › peer-review

10 Citations (Scopus)

Abstract

The thrust vector control problem is studied for an upper-stage rocket with fuel slosh dynamics. The sloshing propellant is modeled as a multi-mass-spring system. The coupled equations of motion of the spacecraft and the fuel are expressed in terms of the three dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law.

Original language	English
Title of host publication	ICCAS 2013 - 2013 13th International Conference on Control, Automation and Systems
Pages	761-766
Number of pages	6
DOIs	https://doi.org/10.1109/ICCAS.2013.6704015
Publication status	Published - 1 Dec 2013
Externally published	Yes
Event	2013 13th International Conference on Control, Automation and Systems, ICCAS 2013 - Gwangju, Korea, Republic of Duration: 20 Oct 2013 → 23 Oct 2013

Conference

Conference	2013 13th International Conference on Control, Automation and Systems, ICCAS 2013
Country/Territory	Korea, Republic of
City	Gwangju
Period	20/10/13 → 23/10/13

Keywords

Lyapunov methods
Slosh dynamics

ASJC Scopus subject areas

Artificial Intelligence
Computer Science Applications
Control and Systems Engineering
Electrical and Electronic Engineering

More information

10.1109/ICCAS.2013.6704015

Cite this

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abstract = "The thrust vector control problem is studied for an upper-stage rocket with fuel slosh dynamics. The sloshing propellant is modeled as a multi-mass-spring system. The coupled equations of motion of the spacecraft and the fuel are expressed in terms of the three dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law.",

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Rubio Hervas, J, Reyhanoglu, M & Tang, H 2013, Thrust-vector control of a three-axis stabilized spacecraft with fuel slosh dynamics. in ICCAS 2013 - 2013 13th International Conference on Control, Automation and Systems., 6704015, pp. 761-766, 2013 13th International Conference on Control, Automation and Systems, ICCAS 2013, Gwangju, Korea, Republic of, 20/10/13. https://doi.org/10.1109/ICCAS.2013.6704015

Thrust-vector control of a three-axis stabilized spacecraft with fuel slosh dynamics. / Rubio Hervas, Jaime; Reyhanoglu, Mahmut; Tang, Hui.
ICCAS 2013 - 2013 13th International Conference on Control, Automation and Systems. 2013. p. 761-766 6704015.

Research output: Chapter in book / Conference proceeding › Conference article published in proceeding or book › Academic research › peer-review

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N2 - The thrust vector control problem is studied for an upper-stage rocket with fuel slosh dynamics. The sloshing propellant is modeled as a multi-mass-spring system. The coupled equations of motion of the spacecraft and the fuel are expressed in terms of the three dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law.

AB - The thrust vector control problem is studied for an upper-stage rocket with fuel slosh dynamics. The sloshing propellant is modeled as a multi-mass-spring system. The coupled equations of motion of the spacecraft and the fuel are expressed in terms of the three dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law.

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ER -

Thrust-vector control of a three-axis stabilized spacecraft with fuel slosh dynamics

Abstract

Conference

Keywords

ASJC Scopus subject areas

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