### Abstract

The attitude of a spacecraft is its orientation in space. The orientation is with respect to a particular reference like the Earth and Sun [1]. The spacecraft is considered to be a rigid body whose attitude can be described by two sets of equations, namely, the kinematics equation, which relates the time derivatives of the orientation angles to the an- gular velocity vector and the dynamics equation, which describes the time evolution of the angular velocity vector [2, 3]. Various parameterizations of the attitude exist to represent the orientation angles. A comprehensive survey of attitude representations is given in [4]. The attitude control problem was first presented in the literature in [5]. A general procedure for the design and analysis of a three-axis, large-angle attitude control system was developed based on properties common to all attitude control systems. In [6], a general framework is prepared for the analysis of attitude tracking control of a rigid body using the non- singular unit quaternion representation. An adaptive tracking control scheme wherein the unknown spacecraft inertia matrix is compensated using linear parameterization is discussed in [7]. Reference [8] proposes an adaptive attitude tracking controller that identifies the inertia matrix via periodic command signals. Reference [9] discusses the adaptive attitude tracking control using synthesized velocity from attitude measurements by incorporating a velocity filter formulation.

Original language | English |
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Title of host publication | Lecture Notes in Control and Information Sciences |

Pages | 39-48 |

Number of pages | 10 |

Volume | 360 |

DOIs | |

Publication status | Published - 2007 |

### Publication series

Name | Lecture Notes in Control and Information Sciences |
---|---|

Volume | 360 |

ISSN (Print) | 01708643 |

### Fingerprint

### ASJC Scopus subject areas

- Library and Information Sciences

### Cite this

*Lecture Notes in Control and Information Sciences*(Vol. 360, pp. 39-48). (Lecture Notes in Control and Information Sciences; Vol. 360). https://doi.org/10.1007/978-1-84628-974-3_3

**Internal model control-based adaptive attitude tracking.** / Al-Garni, Ahmed; Kassem, Ayman; Shafiq, Muhammad; Ahmed, Rihan.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

*Lecture Notes in Control and Information Sciences.*vol. 360, Lecture Notes in Control and Information Sciences, vol. 360, pp. 39-48. https://doi.org/10.1007/978-1-84628-974-3_3

}

TY - GEN

T1 - Internal model control-based adaptive attitude tracking

AU - Al-Garni, Ahmed

AU - Kassem, Ayman

AU - Shafiq, Muhammad

AU - Ahmed, Rihan

PY - 2007

Y1 - 2007

N2 - The attitude of a spacecraft is its orientation in space. The orientation is with respect to a particular reference like the Earth and Sun [1]. The spacecraft is considered to be a rigid body whose attitude can be described by two sets of equations, namely, the kinematics equation, which relates the time derivatives of the orientation angles to the an- gular velocity vector and the dynamics equation, which describes the time evolution of the angular velocity vector [2, 3]. Various parameterizations of the attitude exist to represent the orientation angles. A comprehensive survey of attitude representations is given in [4]. The attitude control problem was first presented in the literature in [5]. A general procedure for the design and analysis of a three-axis, large-angle attitude control system was developed based on properties common to all attitude control systems. In [6], a general framework is prepared for the analysis of attitude tracking control of a rigid body using the non- singular unit quaternion representation. An adaptive tracking control scheme wherein the unknown spacecraft inertia matrix is compensated using linear parameterization is discussed in [7]. Reference [8] proposes an adaptive attitude tracking controller that identifies the inertia matrix via periodic command signals. Reference [9] discusses the adaptive attitude tracking control using synthesized velocity from attitude measurements by incorporating a velocity filter formulation.

AB - The attitude of a spacecraft is its orientation in space. The orientation is with respect to a particular reference like the Earth and Sun [1]. The spacecraft is considered to be a rigid body whose attitude can be described by two sets of equations, namely, the kinematics equation, which relates the time derivatives of the orientation angles to the an- gular velocity vector and the dynamics equation, which describes the time evolution of the angular velocity vector [2, 3]. Various parameterizations of the attitude exist to represent the orientation angles. A comprehensive survey of attitude representations is given in [4]. The attitude control problem was first presented in the literature in [5]. A general procedure for the design and analysis of a three-axis, large-angle attitude control system was developed based on properties common to all attitude control systems. In [6], a general framework is prepared for the analysis of attitude tracking control of a rigid body using the non- singular unit quaternion representation. An adaptive tracking control scheme wherein the unknown spacecraft inertia matrix is compensated using linear parameterization is discussed in [7]. Reference [8] proposes an adaptive attitude tracking controller that identifies the inertia matrix via periodic command signals. Reference [9] discusses the adaptive attitude tracking control using synthesized velocity from attitude measurements by incorporating a velocity filter formulation.

UR - http://www.scopus.com/inward/record.url?scp=77949397787&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=77949397787&partnerID=8YFLogxK

U2 - 10.1007/978-1-84628-974-3_3

DO - 10.1007/978-1-84628-974-3_3

M3 - Conference contribution

AN - SCOPUS:77949397787

SN - 9781846289736

VL - 360

T3 - Lecture Notes in Control and Information Sciences

SP - 39

EP - 48

BT - Lecture Notes in Control and Information Sciences

ER -