Output regulation control for satellite formation flying using differential drag

Mohamed Shouman, Mai Bando, Shinji Hokamoto

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper proposes a new hybrid control action of differentials aerodynamic drag and thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation algorithm for formation flying missions is developed based on the Schweighart-Sedwick relative dynamics equations. It is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. Parametric Lyapunov algebraic equation is derived to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation flying missions. Numerical simulations using a high fidelity relative dynamics model are implemented to analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm for actual satellite parameters. The paper exploits a high-precision orbit propagator model to verify the robustness of the control algorithm.

Original languageEnglish
Title of host publicationSpaceflight Mechanics 2019
EditorsFrancesco Topputo, Andrew J. Sinclair, Matthew P. Wilkins, Renato Zanetti
PublisherUnivelt Inc.
Pages3433-3452
Number of pages20
ISBN (Print)9780877036593
Publication statusPublished - Jan 1 2019
Event29th AAS/AIAA Space Flight Mechanics Meeting, 2019 - Maui, United States
Duration: Jan 13 2019Jan 17 2019

Publication series

NameAdvances in the Astronautical Sciences
Volume168
ISSN (Print)0065-3438

Conference

Conference29th AAS/AIAA Space Flight Mechanics Meeting, 2019
CountryUnited States
CityMaui
Period1/13/191/17/19

Fingerprint

formation flying
drag
Drag
Satellites
Aerodynamic drag
aerodynamic drag
output
aerodynamics
Orbits
satellite control
linear quadratic regulator
low Earth orbits
Dynamic models
viability
dynamic models
Earth (planet)
trajectory
Trajectories
perturbation
regulation

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Shouman, M., Bando, M., & Hokamoto, S. (2019). Output regulation control for satellite formation flying using differential drag. In F. Topputo, A. J. Sinclair, M. P. Wilkins, & R. Zanetti (Eds.), Spaceflight Mechanics 2019 (pp. 3433-3452). [AAS 19-307] (Advances in the Astronautical Sciences; Vol. 168). Univelt Inc..

Output regulation control for satellite formation flying using differential drag. / Shouman, Mohamed; Bando, Mai; Hokamoto, Shinji.

Spaceflight Mechanics 2019. ed. / Francesco Topputo; Andrew J. Sinclair; Matthew P. Wilkins; Renato Zanetti. Univelt Inc., 2019. p. 3433-3452 AAS 19-307 (Advances in the Astronautical Sciences; Vol. 168).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Shouman, M, Bando, M & Hokamoto, S 2019, Output regulation control for satellite formation flying using differential drag. in F Topputo, AJ Sinclair, MP Wilkins & R Zanetti (eds), Spaceflight Mechanics 2019., AAS 19-307, Advances in the Astronautical Sciences, vol. 168, Univelt Inc., pp. 3433-3452, 29th AAS/AIAA Space Flight Mechanics Meeting, 2019, Maui, United States, 1/13/19.
Shouman M, Bando M, Hokamoto S. Output regulation control for satellite formation flying using differential drag. In Topputo F, Sinclair AJ, Wilkins MP, Zanetti R, editors, Spaceflight Mechanics 2019. Univelt Inc. 2019. p. 3433-3452. AAS 19-307. (Advances in the Astronautical Sciences).
Shouman, Mohamed ; Bando, Mai ; Hokamoto, Shinji. / Output regulation control for satellite formation flying using differential drag. Spaceflight Mechanics 2019. editor / Francesco Topputo ; Andrew J. Sinclair ; Matthew P. Wilkins ; Renato Zanetti. Univelt Inc., 2019. pp. 3433-3452 (Advances in the Astronautical Sciences).
@inproceedings{fa764e2db36f4282a98bac9effaee13f,
title = "Output regulation control for satellite formation flying using differential drag",
abstract = "This paper proposes a new hybrid control action of differentials aerodynamic drag and thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation algorithm for formation flying missions is developed based on the Schweighart-Sedwick relative dynamics equations. It is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. Parametric Lyapunov algebraic equation is derived to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation flying missions. Numerical simulations using a high fidelity relative dynamics model are implemented to analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm for actual satellite parameters. The paper exploits a high-precision orbit propagator model to verify the robustness of the control algorithm.",
author = "Mohamed Shouman and Mai Bando and Shinji Hokamoto",
year = "2019",
month = "1",
day = "1",
language = "English",
isbn = "9780877036593",
series = "Advances in the Astronautical Sciences",
publisher = "Univelt Inc.",
pages = "3433--3452",
editor = "Francesco Topputo and Sinclair, {Andrew J.} and Wilkins, {Matthew P.} and Renato Zanetti",
booktitle = "Spaceflight Mechanics 2019",
address = "United States",

}

TY - GEN

T1 - Output regulation control for satellite formation flying using differential drag

AU - Shouman, Mohamed

AU - Bando, Mai

AU - Hokamoto, Shinji

PY - 2019/1/1

Y1 - 2019/1/1

N2 - This paper proposes a new hybrid control action of differentials aerodynamic drag and thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation algorithm for formation flying missions is developed based on the Schweighart-Sedwick relative dynamics equations. It is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. Parametric Lyapunov algebraic equation is derived to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation flying missions. Numerical simulations using a high fidelity relative dynamics model are implemented to analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm for actual satellite parameters. The paper exploits a high-precision orbit propagator model to verify the robustness of the control algorithm.

AB - This paper proposes a new hybrid control action of differentials aerodynamic drag and thrusters to control satellite formation flying in low Earth orbits. Parameterized output regulation algorithm for formation flying missions is developed based on the Schweighart-Sedwick relative dynamics equations. It is implemented to precisely track the different trajectories of reference relative motion and eliminates the effects of the J2 perturbations. Parametric Lyapunov algebraic equation is derived to ensure the stability of the linear relative model subject to saturated inputs. The main goal of this study is to approve the viability of using the differentials in aerodynamic drag to precisely control different formation flying missions. Numerical simulations using a high fidelity relative dynamics model are implemented to analyze the performance of the proposed control algorithm in comparison with the linear quadratic regulator algorithm for actual satellite parameters. The paper exploits a high-precision orbit propagator model to verify the robustness of the control algorithm.

UR - http://www.scopus.com/inward/record.url?scp=85072950180&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85072950180&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:85072950180

SN - 9780877036593

T3 - Advances in the Astronautical Sciences

SP - 3433

EP - 3452

BT - Spaceflight Mechanics 2019

A2 - Topputo, Francesco

A2 - Sinclair, Andrew J.

A2 - Wilkins, Matthew P.

A2 - Zanetti, Renato

PB - Univelt Inc.

ER -