Multibody Modeling of Sloshing in Spacecraft Ascent and Landing Maneuvers

Volume 6: 12th International Conference on Multibody Systems, Nonlinear Dynamics, and Control ◽

10.1115/detc2016-59541 ◽

2016 ◽

Author(s):

Paolo Lunghi ◽

Pierangelo Masarati ◽

Michéle Lavagna

Keyword(s):

Control System ◽

Attitude Control ◽

Significant Fraction ◽

Space Vehicles ◽

Attitude Control System ◽

Multibody Modeling ◽

Violent Sloshing ◽

Typical Method

Sloshing of liquids in tanks has been always a problem in the design of space vehicles. This is especially true in launch and powered landing systems, in which a significant fraction of the mass is made up of propellant. In such systems, uncontrolled or unexpected violent sloshing phenomena can even lead to the loss of the spacecraft. A typical method to cope with sloshing is to ensure that the attitude control system operates at frequencies much higher than those of the sloshing motion of the fuel. In this case, the project of the controller is realized assuming the liquid as static [1].

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Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4025998 ◽

2014 ◽

Vol 136 (2) ◽

Cited By ~ 9

Author(s):

Nicolas Guy ◽

Daniel Alazard ◽

Christelle Cumer ◽

Catherine Charbonnel

Keyword(s):

Control System ◽

Attitude Control ◽

Solar Panel ◽

Physical Parameters ◽

Attitude Control System ◽

Multibody Modeling ◽

Modeling And Analysis ◽

Complete Revolution ◽

The Stability ◽

Flexible Appendages

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.

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