Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation

Yuto Kitazono; Koichi Yonemoto; Takahiro Fujikawa; Takahiro Matsukami

doi:10.1007/978-981-19-2635-8_27

Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation

Yuto Kitazono, Koichi Yonemoto, Takahiro Fujikawa, Takahiro Matsukami

Department of Mechanical and Aerospace Engineering

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

Abstract

The flight dynamics of a spaceplane strongly depends on the flight environment, including the dynamic pressure, angle of attack, and Mach number. In addition, spaceplanes fly at pitch angles around 90° during powered and coasting ascent, and Euler angles are known to be coupled with roll and yaw angles at such pitch angles. In this paper, the control system for a spaceplane based on dynamic inversion theory is proposed. To avoid the problem of the singularity of Euler angles, the equation of state is written in terms of quaternions. The control laws are designed and evaluated in the following three cases: (1) The case where only the attitude error calculation of the control law using the Euler angle is modified. (2) The case where the vector part of the quaternion is used as the control variable. (3) The case where the vector part of the error quaternion is used as the control variable. Finally, the results of the numerical simulation show that Case (3) has the best control performance.

Original language	English
Title of host publication	The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2
Editors	Sangchul Lee, Cheolheui Han, Jeong-Yeol Choi, Seungkeun Kim, Jeong Ho Kim
Publisher	Springer Science and Business Media Deutschland GmbH
Pages	369-381
Number of pages	13
ISBN (Print)	9789811926341
DOIs	https://doi.org/10.1007/978-981-19-2635-8_27
Publication status	Published - 2023
Event	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2021 - Virtual, Online Duration: 15 Nov 2021 → 17 Nov 2021

Publication series

Name	Lecture Notes in Electrical Engineering
Volume	913
ISSN (Print)	1876-1100
ISSN (Electronic)	1876-1119

Conference

Conference	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2021
City	Virtual, Online
Period	15/11/21 → 17/11/21

Keywords

Attitude control
Dynamic inversion
Nonlinear control
Quaternion
Spaceplane

Access to Document

10.1007/978-981-19-2635-8_27

Cite this

Kitazono, Y., Yonemoto, K., Fujikawa, T., & Matsukami, T. (2023). Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation. In S. Lee, C. Han, J.-Y. Choi, S. Kim, & J. H. Kim (Eds.), The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2 (pp. 369-381). (Lecture Notes in Electrical Engineering; Vol. 913). Springer Science and Business Media Deutschland GmbH. https://doi.org/10.1007/978-981-19-2635-8_27

Kitazono, Yuto ; Yonemoto, Koichi ; Fujikawa, Takahiro et al. / Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation. The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2. editor / Sangchul Lee ; Cheolheui Han ; Jeong-Yeol Choi ; Seungkeun Kim ; Jeong Ho Kim. Springer Science and Business Media Deutschland GmbH, 2023. pp. 369-381 (Lecture Notes in Electrical Engineering).

@inproceedings{c0a3eee85c5a46e9b62fdd12327e6b22,

title = "Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation",

abstract = "The flight dynamics of a spaceplane strongly depends on the flight environment, including the dynamic pressure, angle of attack, and Mach number. In addition, spaceplanes fly at pitch angles around 90° during powered and coasting ascent, and Euler angles are known to be coupled with roll and yaw angles at such pitch angles. In this paper, the control system for a spaceplane based on dynamic inversion theory is proposed. To avoid the problem of the singularity of Euler angles, the equation of state is written in terms of quaternions. The control laws are designed and evaluated in the following three cases: (1) The case where only the attitude error calculation of the control law using the Euler angle is modified. (2) The case where the vector part of the quaternion is used as the control variable. (3) The case where the vector part of the error quaternion is used as the control variable. Finally, the results of the numerical simulation show that Case (3) has the best control performance.",

keywords = "Attitude control, Dynamic inversion, Nonlinear control, Quaternion, Spaceplane",

author = "Yuto Kitazono and Koichi Yonemoto and Takahiro Fujikawa and Takahiro Matsukami",

note = "Publisher Copyright: {\textcopyright} 2023, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.; Asia-Pacific International Symposium on Aerospace Technology, APISAT 2021 ; Conference date: 15-11-2021 Through 17-11-2021",

year = "2023",

doi = "10.1007/978-981-19-2635-8_27",

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Kitazono, Y, Yonemoto, K, Fujikawa, T & Matsukami, T 2023, Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation. in S Lee, C Han, J-Y Choi, S Kim & JH Kim (eds), The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2. Lecture Notes in Electrical Engineering, vol. 913, Springer Science and Business Media Deutschland GmbH, pp. 369-381, Asia-Pacific International Symposium on Aerospace Technology, APISAT 2021, Virtual, Online, 15/11/21. https://doi.org/10.1007/978-981-19-2635-8_27

Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation. / Kitazono, Yuto; Yonemoto, Koichi; Fujikawa, Takahiro et al.
The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2. ed. / Sangchul Lee; Cheolheui Han; Jeong-Yeol Choi; Seungkeun Kim; Jeong Ho Kim. Springer Science and Business Media Deutschland GmbH, 2023. p. 369-381 (Lecture Notes in Electrical Engineering; Vol. 913).

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

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AU - Fujikawa, Takahiro

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PY - 2023

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N2 - The flight dynamics of a spaceplane strongly depends on the flight environment, including the dynamic pressure, angle of attack, and Mach number. In addition, spaceplanes fly at pitch angles around 90° during powered and coasting ascent, and Euler angles are known to be coupled with roll and yaw angles at such pitch angles. In this paper, the control system for a spaceplane based on dynamic inversion theory is proposed. To avoid the problem of the singularity of Euler angles, the equation of state is written in terms of quaternions. The control laws are designed and evaluated in the following three cases: (1) The case where only the attitude error calculation of the control law using the Euler angle is modified. (2) The case where the vector part of the quaternion is used as the control variable. (3) The case where the vector part of the error quaternion is used as the control variable. Finally, the results of the numerical simulation show that Case (3) has the best control performance.

AB - The flight dynamics of a spaceplane strongly depends on the flight environment, including the dynamic pressure, angle of attack, and Mach number. In addition, spaceplanes fly at pitch angles around 90° during powered and coasting ascent, and Euler angles are known to be coupled with roll and yaw angles at such pitch angles. In this paper, the control system for a spaceplane based on dynamic inversion theory is proposed. To avoid the problem of the singularity of Euler angles, the equation of state is written in terms of quaternions. The control laws are designed and evaluated in the following three cases: (1) The case where only the attitude error calculation of the control law using the Euler angle is modified. (2) The case where the vector part of the quaternion is used as the control variable. (3) The case where the vector part of the error quaternion is used as the control variable. Finally, the results of the numerical simulation show that Case (3) has the best control performance.

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Y2 - 15 November 2021 through 17 November 2021

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Kitazono Y, Yonemoto K, Fujikawa T, Matsukami T. Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation. In Lee S, Han C, Choi JY, Kim S, Kim JH, editors, The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology APISAT 2021, Volume 2. Springer Science and Business Media Deutschland GmbH. 2023. p. 369-381. (Lecture Notes in Electrical Engineering). doi: 10.1007/978-981-19-2635-8_27

Attitude Control of a Spaceplane Based on Dynamic Inversion Theory with Quaternion Error Calculation

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