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 language | English (US) |
|---|---|
| Pages (from-to) | 117-139 |
| Number of pages | 23 |
| Journal | International Journal of Robust and Nonlinear Control |
| Volume | 12 |
| Issue number | 2-3 |
| DOIs | |
| State | Published - Feb 2002 |
Fingerprint
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 journal › Article
}
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 -