Adaptive tracking control using synthesized velocity from attitude measurements

H. Wong; M. S. De Queiroz; V. Kapila

doi:10.1016/S0005-1098(01)00038-3

Adaptive tracking control using synthesized velocity from attitude measurements

H. Wong, M. S. De Queiroz, V. Kapila

Mechanical and Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results.

Original language	English (US)
Pages (from-to)	947-953
Number of pages	7
Journal	Automatica
Volume	37
Issue number	6
DOIs	https://doi.org/10.1016/S0005-1098(01)00038-3
State	Published - Jun 2001

Keywords

Adaptive control
Attitude tracking
Output feedback
Spacecraft

ASJC Scopus subject areas

Control and Systems Engineering
Electrical and Electronic Engineering

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10.1016/S0005-1098(01)00038-3

Cite this

@article{7762a12256e34e59a0029c04f5b9386e,

title = "Adaptive tracking control using synthesized velocity from attitude measurements",

abstract = "The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results.",

keywords = "Adaptive control, Attitude tracking, Output feedback, Spacecraft",

author = "H. Wong and {De Queiroz}, {M. S.} and V. Kapila",

note = "Funding Information: This paper was not presented at any IFAC meeting. This paper was recommended for publication in revised form by Associate Editor B. Brogliato under the direction of Editor Frank Lewis. This work was supported in part by the Air Force Office of Scientific Research under grant F49620-93-C-0063, the Air Force Research Lab/VAAD, WPAFB, OH, under IPA: Visiting Faculty Grant, and the NASA/New York Space Grant Consortium under grant 32310-5891. ",

year = "2001",

month = jun,

doi = "10.1016/S0005-1098(01)00038-3",

language = "English (US)",

volume = "37",

pages = "947--953",

journal = "Automatica",

issn = "0005-1098",

publisher = "Elsevier Limited",

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TY - JOUR

T1 - Adaptive tracking control using synthesized velocity from attitude measurements

AU - Wong, H.

AU - De Queiroz, M. S.

AU - Kapila, V.

N1 - Funding Information: This paper was not presented at any IFAC meeting. This paper was recommended for publication in revised form by Associate Editor B. Brogliato under the direction of Editor Frank Lewis. This work was supported in part by the Air Force Office of Scientific Research under grant F49620-93-C-0063, the Air Force Research Lab/VAAD, WPAFB, OH, under IPA: Visiting Faculty Grant, and the NASA/New York Space Grant Consortium under grant 32310-5891.

PY - 2001/6

Y1 - 2001/6

N2 - The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results.

AB - The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results.

KW - Adaptive control

KW - Attitude tracking

KW - Output feedback

KW - Spacecraft

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DO - 10.1016/S0005-1098(01)00038-3

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SN - 0005-1098

VL - 37

SP - 947

EP - 953

JO - Automatica

JF - Automatica

IS - 6

ER -

Adaptive tracking control using synthesized velocity from attitude measurements

Abstract

Keywords

ASJC Scopus subject areas

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