Model Identification and Attitude Control Methodology for the Flexible Body of a Satellite

A novel gray-box neural network model (GBNNM), including multi-layer perception (MLP) neural network (NN) and integrators, is proposed for a model identification and fault estimation (MIFE) scheme. With the GBNNM, both the nonlinearity and dynamics of a class of nonlinear dynamic systems can be approximated. Unlike previous NN-based model identification methods, the GBNNM directly inherits system dynamics and separately models system nonlinearities. This model corresponds well with the object system and is easy to build. The GBNNM is embedded online as a normal model reference to obtain the quantitative residual between the object system output and the GBNNM output. This residual can accurately indicate the fault offset value, so it is suitable for differing fault severities. To further estimate the fault parameters (FPs), an improved extended state observer (ESO) using the same NNs (IESONN) from the GBNNM is proposed to avoid requiring the knowledge of ESO nonlinearity. Then, the proposed MIFE scheme is applied for reaction wheels (RW) in a satellite attitude control system (SACS). The scheme using the GBNNM is compared with other NNs in the same fault scenario, and several partial loss of effect (LOE) faults with different severities are considered to validate the effectiveness of the FP estimation and its superiority.

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Motion of a Tethered System Under Attitude Control With Large Deformation, Rotation and Translation

Volume 5: 19th Biennial Conference on Mechanical Vibration and Noise, Parts A, B, and C ◽

10.1115/detc2003/vib-48320 ◽

2003 ◽

Cited By ~ 1

Author(s):

Shoichiro Takehara ◽

Yoshiaki Terumichi ◽

Masahiro Nohmi ◽

Kiyoshi Sogabe

Keyword(s):

Large Deformation ◽

Attitude Control ◽

Rigid Bodies ◽

Torque Control ◽

Body Motion ◽

Joint Torque ◽

Control Technique ◽

Flexible Body ◽

First Eigenvalue ◽

Reaction Wheel

In this paper, we discuss about the motion of a system consisting of a very flexible body and rigid bodies at its end under attitude control to the end body. A tethered subsatellite in space is known as an example of this system. We consider two mathematical models for flexible body. First, the flexible body motion in a plane is described by using Finite Element Method formulation. Second, the flexible body in planer motion is described by using Absolute Nodal Coordinate formulation. In this method, it is easy to describe the motion of the flexible body with large deformation, rotation and translation displacement. We can consider interaction between the deflection of the flexible body and the motion of the rigid bodies in these methods. Furthermore we attempt to control the attitude of the end body using a reaction wheel. The flexible body motion is influenced on the motion of the rigid bodies under attitude control of end body. The control technique consists of an attitude control by the reaction wheel and a control by the reaction wheel with the joint torque control to cancel accumulation of angular momentum. First, eigenvalue analysis is carried out where control gain changes. Second, the motion under controlled system is discussed under free vibration. We compared these results. Furthermore we treat large deformation problem. The end of flexible body moves horizontally. As a result, we confirm the interaction between flexible body and rigid body under the attitude control.

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Attitude Control Methodology for Large Solar Sails

Journal of Guidance Control and Dynamics ◽

10.2514/1.g000048 ◽

2015 ◽

Vol 38 (4) ◽

pp. 662-670 ◽

Cited By ~ 19

Author(s):

Bo Fu ◽

Fidelis O. Eke

Keyword(s):

Attitude Control ◽

Solar Sails ◽

Control Methodology

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Control Structure Interaction of Multi-Flexible-Body Space Station and RCS Attitude Control

10.4271/922016 ◽

1992 ◽

Cited By ~ 1

Author(s):

David S. Chang ◽

James B. Caldwell

Keyword(s):

Attitude Control ◽

Control Structure ◽

Space Station ◽

Flexible Body ◽

Structure Interaction

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An overview of prescribed performance control and its application to spacecraft attitude system

Proceedings of the Institution of Mechanical Engineers Part I Journal of Systems and Control Engineering ◽

10.1177/0959651820952552 ◽

2020 ◽

pp. 095965182095255

Author(s):

Caisheng Wei ◽

Qifeng Chen ◽

Jun Liu ◽

Zeyang Yin ◽

Jianjun Luo

Keyword(s):

Attitude Control ◽

Attitude Determination ◽

Control Method ◽

Quantitative Description ◽

Basic Structure ◽

Performance Control ◽

Prescribed Performance ◽

Aerospace Applications ◽

Prescribed Performance Control ◽

Control Methodology

High-quality control method is of great importance for the attitude determination and maneuvering of spacecraft in the on-orbit servicing technology. Prescribed performance control methodology, as a potential way, has gained considerable attention due to its quantitative description for the transient and steady-state control performance in recent years. Thus, this article constructs a survey for the prescribed performance control methodology along with the detailed analysis of the attitude control methods in the existing reported works. Then, the basic structure of prescribed performance control methodology is discussed in theory, and application to the attitude control of postcapture spacecraft works as an example to further explain the procedure of prescribed performance control methodology. Finally, with consideration of some vital aerospace applications, potential open issues of the prescribed performance control methodology are analyzed.

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