Abstract
This study presents a dynamic quadratic-optimal (DQO) output feedback controller for satellite formation reconfiguration based on a linear matrix inequality (LMI) approach. A relative motion model involving communication topology of formation flying on a circular reference orbit is established through graph theory. As the design of a static quadratic-optimal (SQO) output feedback controller was determined to be infeasible, emphasis is placed on designing a DQO output feedback controller. Introducing an impulse function enables us to transform the original DQO output feedback control (DQO-OFC) problem into an optimal L2-norm problem, which can be solved in the standard frame of an LMI approach. It is infeasible to employ a conventional substitution method to treat a nonlinear term with a quadratic form. Thus, an elimination method is adopted in order to address nonlinear terms in the matrix inequalities to obtain a set of equivalent LMIs. Additional control quantities are developed in order to retain the formation configuration in a non-zero state. Simulation results demonstrate validity and functionality of the proposed DQO output feedback controller.
| Original language | English |
|---|---|
| Pages (from-to) | 214-231 |
| Number of pages | 18 |
| Journal | Aerospace Science and Technology |
| Volume | 63 |
| DOIs | |
| Publication status | Published - 2017 Apr 1 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
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Dynamic optimal output feedback control of satellite formation reconfiguration based on an LMI approach. / Wei, Changzhu; Park, Sang-Young.
In: Aerospace Science and Technology, Vol. 63, 01.04.2017, p. 214-231.Research output: Contribution to journal › Article
TY - JOUR
T1 - Dynamic optimal output feedback control of satellite formation reconfiguration based on an LMI approach
AU - Wei, Changzhu
AU - Park, Sang-Young
PY - 2017/4/1
Y1 - 2017/4/1
N2 - This study presents a dynamic quadratic-optimal (DQO) output feedback controller for satellite formation reconfiguration based on a linear matrix inequality (LMI) approach. A relative motion model involving communication topology of formation flying on a circular reference orbit is established through graph theory. As the design of a static quadratic-optimal (SQO) output feedback controller was determined to be infeasible, emphasis is placed on designing a DQO output feedback controller. Introducing an impulse function enables us to transform the original DQO output feedback control (DQO-OFC) problem into an optimal L2-norm problem, which can be solved in the standard frame of an LMI approach. It is infeasible to employ a conventional substitution method to treat a nonlinear term with a quadratic form. Thus, an elimination method is adopted in order to address nonlinear terms in the matrix inequalities to obtain a set of equivalent LMIs. Additional control quantities are developed in order to retain the formation configuration in a non-zero state. Simulation results demonstrate validity and functionality of the proposed DQO output feedback controller.
AB - This study presents a dynamic quadratic-optimal (DQO) output feedback controller for satellite formation reconfiguration based on a linear matrix inequality (LMI) approach. A relative motion model involving communication topology of formation flying on a circular reference orbit is established through graph theory. As the design of a static quadratic-optimal (SQO) output feedback controller was determined to be infeasible, emphasis is placed on designing a DQO output feedback controller. Introducing an impulse function enables us to transform the original DQO output feedback control (DQO-OFC) problem into an optimal L2-norm problem, which can be solved in the standard frame of an LMI approach. It is infeasible to employ a conventional substitution method to treat a nonlinear term with a quadratic form. Thus, an elimination method is adopted in order to address nonlinear terms in the matrix inequalities to obtain a set of equivalent LMIs. Additional control quantities are developed in order to retain the formation configuration in a non-zero state. Simulation results demonstrate validity and functionality of the proposed DQO output feedback controller.
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U2 - 10.1016/j.ast.2016.12.031
DO - 10.1016/j.ast.2016.12.031
M3 - Article
AN - SCOPUS:85009964780
VL - 63
SP - 214
EP - 231
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
SN - 1270-9638
ER -