Re-entry attitude two-loop SMC of the spacecraft and its logic selection

Jie Jia; Fengqi Zhou; Jun Zhou

Re-entry attitude two-loop SMC of the spacecraft and its logic selection

Jie Jia
, Fengqi Zhou
, Jun Zhou

School of Astronautics

Northwestern Polytechnical University Xian

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

3 Scopus citations

Abstract

This paper develops a re-entry attitude control method of a Spacecraft by sliding mode control (SMC) theory. The controller utilizes two-loop SMC scheme and provides robust, de-coupled tracking of both the angular velocity and orientation angles of the Spacecraft. And pointing to the blending controlling characteristic of the aerodynamic surfaces and reaction control system of the Spacecraft, allocating the control torque commands into the actuators such as the aerodynamic surfaces and reaction control system by the optimal control logic selection allocation algorithm. Simulation of the Spacecraft re-entry attitude controlling demonstrates robust, de-coupled tracking performance of this method and its validity.

Original language	English
Title of host publication	1st International Symposium on Systems and Control in Aerospace and Astronautics
Pages	623-626
Number of pages	4
State	Published - 2006
Event	1st International Symposium on Systems and Control in Aerospace and Astronautics - Harbin, China Duration: 19 Jan 2006 → 21 Jan 2006

Publication series

Name	1st International Symposium on Systems and Control in Aerospace and Astronautics
Volume	2006

Conference

Conference	1st International Symposium on Systems and Control in Aerospace and Astronautics
Country/Territory	China
City	Harbin
Period	19/01/06 → 21/01/06

Cite this

@inproceedings{54a1eddde9c84d3da77c5c5e3a8f4e61,

title = "Re-entry attitude two-loop SMC of the spacecraft and its logic selection",

abstract = "This paper develops a re-entry attitude control method of a Spacecraft by sliding mode control (SMC) theory. The controller utilizes two-loop SMC scheme and provides robust, de-coupled tracking of both the angular velocity and orientation angles of the Spacecraft. And pointing to the blending controlling characteristic of the aerodynamic surfaces and reaction control system of the Spacecraft, allocating the control torque commands into the actuators such as the aerodynamic surfaces and reaction control system by the optimal control logic selection allocation algorithm. Simulation of the Spacecraft re-entry attitude controlling demonstrates robust, de-coupled tracking performance of this method and its validity.",

author = "Jie Jia and Fengqi Zhou and Jun Zhou",

year = "2006",

language = "英语",

isbn = "0780393953",

series = "1st International Symposium on Systems and Control in Aerospace and Astronautics",

pages = "623--626",

booktitle = "1st International Symposium on Systems and Control in Aerospace and Astronautics",

note = "1st International Symposium on Systems and Control in Aerospace and Astronautics ; Conference date: 19-01-2006 Through 21-01-2006",

}

Jia, J, Zhou, F & Zhou, J 2006, Re-entry attitude two-loop SMC of the spacecraft and its logic selection. in 1st International Symposium on Systems and Control in Aerospace and Astronautics., 1627414, 1st International Symposium on Systems and Control in Aerospace and Astronautics, vol. 2006, pp. 623-626, 1st International Symposium on Systems and Control in Aerospace and Astronautics, Harbin, China, 19/01/06.

Re-entry attitude two-loop SMC of the spacecraft and its logic selection. / Jia, Jie; Zhou, Fengqi; Zhou, Jun.
1st International Symposium on Systems and Control in Aerospace and Astronautics. 2006. p. 623-626 1627414 (1st International Symposium on Systems and Control in Aerospace and Astronautics; Vol. 2006).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Re-entry attitude two-loop SMC of the spacecraft and its logic selection

AU - Jia, Jie

AU - Zhou, Fengqi

AU - Zhou, Jun

PY - 2006

Y1 - 2006

N2 - This paper develops a re-entry attitude control method of a Spacecraft by sliding mode control (SMC) theory. The controller utilizes two-loop SMC scheme and provides robust, de-coupled tracking of both the angular velocity and orientation angles of the Spacecraft. And pointing to the blending controlling characteristic of the aerodynamic surfaces and reaction control system of the Spacecraft, allocating the control torque commands into the actuators such as the aerodynamic surfaces and reaction control system by the optimal control logic selection allocation algorithm. Simulation of the Spacecraft re-entry attitude controlling demonstrates robust, de-coupled tracking performance of this method and its validity.

AB - This paper develops a re-entry attitude control method of a Spacecraft by sliding mode control (SMC) theory. The controller utilizes two-loop SMC scheme and provides robust, de-coupled tracking of both the angular velocity and orientation angles of the Spacecraft. And pointing to the blending controlling characteristic of the aerodynamic surfaces and reaction control system of the Spacecraft, allocating the control torque commands into the actuators such as the aerodynamic surfaces and reaction control system by the optimal control logic selection allocation algorithm. Simulation of the Spacecraft re-entry attitude controlling demonstrates robust, de-coupled tracking performance of this method and its validity.

UR - https://www.scopus.com/pages/publications/33750934791

M3 - 会议稿件

AN - SCOPUS:33750934791

SN - 0780393953

SN - 9780780393950

T3 - 1st International Symposium on Systems and Control in Aerospace and Astronautics

SP - 623

EP - 626

BT - 1st International Symposium on Systems and Control in Aerospace and Astronautics

T2 - 1st International Symposium on Systems and Control in Aerospace and Astronautics

Y2 - 19 January 2006 through 21 January 2006

ER -

Re-entry attitude two-loop SMC of the spacecraft and its logic selection

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