Adaptive output feedback tracking control of spacecraft formation

Hong Wong, Vikram Kapila, Andrew G. Sparks

Research output: Contribution to journalArticle

Abstract

In this paper, an adaptive, output feedback control design methodology is presented for a spacecraft formation flying (SFF) system. A Lagrangian derivation of the SFF model is considered to produce position dynamics for follower spacecraft #n relative to follower spacecraft #(n - 1), where n is an arbitrary positive integer, assuming that the leader spacecraft in the formation follows a no-thrust, natural, elliptical orbit. Next, a control law is designed to provide a filtered velocity measurement and a desired adaptive compensation with semi-global, asymptotic, relative position tracking. To show the efficacy of the control algorithm, all desired trajectories are generated online by numerically solving the unperturbed nonlinear SFF dynamics with initial conditions satisfying a no-thrust, natural orbit constraint equation. The proposed control law is simulated for the case of two and three spacecraft and is shown to yield semi-global, asymptotic tracking of the relative position in addition to the convergence of disturbance parameter estimates.

Original languageEnglish (US)
Pages (from-to)117-139
Number of pages23
JournalInternational Journal of Robust and Nonlinear Control
Volume12
Issue number2-3
DOIs
StatePublished - Feb 2002

Fingerprint

Output Feedback
Tracking Control
Spacecraft
Feedback Control
Feedback
Formation Flying
Orbits
Orbit
Velocity Measurement
Output Feedback Control
Control Design
Velocity measurement
Control Algorithm
Feedback control
Design Methodology
Efficacy
Initial conditions
Disturbance
Trajectories
Trajectory

Keywords

  • Adaptive control
  • Output feedback
  • Spacecraft formation flying

ASJC Scopus subject areas

  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Applied Mathematics

Cite this

Adaptive output feedback tracking control of spacecraft formation. / Wong, Hong; Kapila, Vikram; Sparks, Andrew G.

In: International Journal of Robust and Nonlinear Control, Vol. 12, No. 2-3, 02.2002, p. 117-139.

Research output: Contribution to journalArticle

@article{95f4dfa9015048799302794471eca87a,
title = "Adaptive output feedback tracking control of spacecraft formation",
abstract = "In this paper, an adaptive, output feedback control design methodology is presented for a spacecraft formation flying (SFF) system. A Lagrangian derivation of the SFF model is considered to produce position dynamics for follower spacecraft #n relative to follower spacecraft #(n - 1), where n is an arbitrary positive integer, assuming that the leader spacecraft in the formation follows a no-thrust, natural, elliptical orbit. Next, a control law is designed to provide a filtered velocity measurement and a desired adaptive compensation with semi-global, asymptotic, relative position tracking. To show the efficacy of the control algorithm, all desired trajectories are generated online by numerically solving the unperturbed nonlinear SFF dynamics with initial conditions satisfying a no-thrust, natural orbit constraint equation. The proposed control law is simulated for the case of two and three spacecraft and is shown to yield semi-global, asymptotic tracking of the relative position in addition to the convergence of disturbance parameter estimates.",
keywords = "Adaptive control, Output feedback, Spacecraft formation flying",
author = "Hong Wong and Vikram Kapila and Sparks, {Andrew G.}",
year = "2002",
month = "2",
doi = "10.1002/rnc.679",
language = "English (US)",
volume = "12",
pages = "117--139",
journal = "International Journal of Robust and Nonlinear Control",
issn = "1049-8923",
publisher = "John Wiley and Sons Ltd",
number = "2-3",

}

TY - JOUR

T1 - Adaptive output feedback tracking control of spacecraft formation

AU - Wong, Hong

AU - Kapila, Vikram

AU - Sparks, Andrew G.

PY - 2002/2

Y1 - 2002/2

N2 - In this paper, an adaptive, output feedback control design methodology is presented for a spacecraft formation flying (SFF) system. A Lagrangian derivation of the SFF model is considered to produce position dynamics for follower spacecraft #n relative to follower spacecraft #(n - 1), where n is an arbitrary positive integer, assuming that the leader spacecraft in the formation follows a no-thrust, natural, elliptical orbit. Next, a control law is designed to provide a filtered velocity measurement and a desired adaptive compensation with semi-global, asymptotic, relative position tracking. To show the efficacy of the control algorithm, all desired trajectories are generated online by numerically solving the unperturbed nonlinear SFF dynamics with initial conditions satisfying a no-thrust, natural orbit constraint equation. The proposed control law is simulated for the case of two and three spacecraft and is shown to yield semi-global, asymptotic tracking of the relative position in addition to the convergence of disturbance parameter estimates.

AB - In this paper, an adaptive, output feedback control design methodology is presented for a spacecraft formation flying (SFF) system. A Lagrangian derivation of the SFF model is considered to produce position dynamics for follower spacecraft #n relative to follower spacecraft #(n - 1), where n is an arbitrary positive integer, assuming that the leader spacecraft in the formation follows a no-thrust, natural, elliptical orbit. Next, a control law is designed to provide a filtered velocity measurement and a desired adaptive compensation with semi-global, asymptotic, relative position tracking. To show the efficacy of the control algorithm, all desired trajectories are generated online by numerically solving the unperturbed nonlinear SFF dynamics with initial conditions satisfying a no-thrust, natural orbit constraint equation. The proposed control law is simulated for the case of two and three spacecraft and is shown to yield semi-global, asymptotic tracking of the relative position in addition to the convergence of disturbance parameter estimates.

KW - Adaptive control

KW - Output feedback

KW - Spacecraft formation flying

UR - http://www.scopus.com/inward/record.url?scp=0036465645&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0036465645&partnerID=8YFLogxK

U2 - 10.1002/rnc.679

DO - 10.1002/rnc.679

M3 - Article

AN - SCOPUS:0036465645

VL - 12

SP - 117

EP - 139

JO - International Journal of Robust and Nonlinear Control

JF - International Journal of Robust and Nonlinear Control

SN - 1049-8923

IS - 2-3

ER -