Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure

Anuradha Sahu; Arun Kumar Mahodaya; Shreesha Chokkadi

doi:10.1007/978-981-15-1724-2_12

Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure

Anuradha Sahu
, Arun Kumar Mahodaya^*
, Shreesha Chokkadi

^*Corresponding author for this work

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

1 Citation (Scopus)

Abstract

Attitude maneuvers are required for reorienting the satellite for meeting various mission objectives. A higher satellite slew rate during maneuvers is a desirable characteristic for any mission design. At the same time, a higher slew rate demands a higher actuator torque capacity which is always constrained due to the physical limits of the actuator. This paper discusses the satellite attitude maneuver problem under slew rate and actuator capacity constraints. A quaternion feedback controller with quaternion and angular rate feedback is implemented to achieve a rest to rest reorientation maneuver. The control gains are computed based on the slew rate limits while the control commands incorporate the actuator limits. Three different configurations of four reaction wheels, (a) pyramid configuration, (b) skew configuration with three wheels along the body axes and the fourth wheel along body diagonal and (c) skew configuration with skew angle of 45°, are studied. The paper further discusses single reaction wheel failure conditions for all the three configurations and demonstrates satellite rest to rest maneuver within the slew rate and actuator limits.

Original language	English
Title of host publication	Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019
Editors	PSR Srinivasa Sastry, Jiji C.V., D.V.A. Raghavamurthy, Samba Siva Rao
Publisher	Springer Paris
Pages	119-131
Number of pages	13
ISBN (Print)	9789811517235
DOIs	https://doi.org/10.1007/978-981-15-1724-2_12
Publication status	Published - 01-01-2020
Event	1st International Conference on Small Satellites, ICSS 2019 - Hyderabad, India Duration: 07-02-2019 → 09-02-2019

Publication series

Name	Lecture Notes in Mechanical Engineering
ISSN (Print)	2195-4356
ISSN (Electronic)	2195-4364

Conference

Conference	1st International Conference on Small Satellites, ICSS 2019
Country/Territory	India
City	Hyderabad
Period	07-02-19 → 09-02-19

All Science Journal Classification (ASJC) codes

Automotive Engineering
Aerospace Engineering
Mechanical Engineering
Fluid Flow and Transfer Processes

Access to Document

10.1007/978-981-15-1724-2_12

Cite this

Sahu, A., Mahodaya, A. K., & Chokkadi, S. (2020). Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. In PSR. S. Sastry, J. C.V., D. V. A. Raghavamurthy, & S. S. Rao (Eds.), Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019 (pp. 119-131). (Lecture Notes in Mechanical Engineering). Springer Paris. https://doi.org/10.1007/978-981-15-1724-2_12

Sahu, Anuradha ; Mahodaya, Arun Kumar ; Chokkadi, Shreesha. / Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019. editor / PSR Srinivasa Sastry ; Jiji C.V. ; D.V.A. Raghavamurthy ; Samba Siva Rao. Springer Paris, 2020. pp. 119-131 (Lecture Notes in Mechanical Engineering).

@inproceedings{ef67bcc1084a4e97813dc125d9d9aa6c,

title = "Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure",

abstract = "Attitude maneuvers are required for reorienting the satellite for meeting various mission objectives. A higher satellite slew rate during maneuvers is a desirable characteristic for any mission design. At the same time, a higher slew rate demands a higher actuator torque capacity which is always constrained due to the physical limits of the actuator. This paper discusses the satellite attitude maneuver problem under slew rate and actuator capacity constraints. A quaternion feedback controller with quaternion and angular rate feedback is implemented to achieve a rest to rest reorientation maneuver. The control gains are computed based on the slew rate limits while the control commands incorporate the actuator limits. Three different configurations of four reaction wheels, (a) pyramid configuration, (b) skew configuration with three wheels along the body axes and the fourth wheel along body diagonal and (c) skew configuration with skew angle of 45°, are studied. The paper further discusses single reaction wheel failure conditions for all the three configurations and demonstrates satellite rest to rest maneuver within the slew rate and actuator limits.",

author = "Anuradha Sahu and Mahodaya, \{Arun Kumar\} and Shreesha Chokkadi",

note = "Publisher Copyright: {\textcopyright} 2020, Springer Nature Singapore Pte Ltd.; 1st International Conference on Small Satellites, ICSS 2019 ; Conference date: 07-02-2019 Through 09-02-2019",

year = "2020",

month = jan,

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doi = "10.1007/978-981-15-1724-2\_12",

language = "English",

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editor = "Sastry, \{PSR Srinivasa\} and Jiji C.V. and D.V.A. Raghavamurthy and Rao, \{Samba Siva\}",

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Sahu, A, Mahodaya, AK & Chokkadi, S 2020, Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. in PSRS Sastry, J C.V., DVA Raghavamurthy & SS Rao (eds), Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019. Lecture Notes in Mechanical Engineering, Springer Paris, pp. 119-131, 1st International Conference on Small Satellites, ICSS 2019, Hyderabad, India, 07-02-19. https://doi.org/10.1007/978-981-15-1724-2_12

Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. / Sahu, Anuradha; Mahodaya, Arun Kumar; Chokkadi, Shreesha.
Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019. ed. / PSR Srinivasa Sastry; Jiji C.V.; D.V.A. Raghavamurthy; Samba Siva Rao. Springer Paris, 2020. p. 119-131 (Lecture Notes in Mechanical Engineering).

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

TY - GEN

T1 - Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure

AU - Sahu, Anuradha

AU - Mahodaya, Arun Kumar

AU - Chokkadi, Shreesha

PY - 2020/1/1

Y1 - 2020/1/1

N2 - Attitude maneuvers are required for reorienting the satellite for meeting various mission objectives. A higher satellite slew rate during maneuvers is a desirable characteristic for any mission design. At the same time, a higher slew rate demands a higher actuator torque capacity which is always constrained due to the physical limits of the actuator. This paper discusses the satellite attitude maneuver problem under slew rate and actuator capacity constraints. A quaternion feedback controller with quaternion and angular rate feedback is implemented to achieve a rest to rest reorientation maneuver. The control gains are computed based on the slew rate limits while the control commands incorporate the actuator limits. Three different configurations of four reaction wheels, (a) pyramid configuration, (b) skew configuration with three wheels along the body axes and the fourth wheel along body diagonal and (c) skew configuration with skew angle of 45°, are studied. The paper further discusses single reaction wheel failure conditions for all the three configurations and demonstrates satellite rest to rest maneuver within the slew rate and actuator limits.

AB - Attitude maneuvers are required for reorienting the satellite for meeting various mission objectives. A higher satellite slew rate during maneuvers is a desirable characteristic for any mission design. At the same time, a higher slew rate demands a higher actuator torque capacity which is always constrained due to the physical limits of the actuator. This paper discusses the satellite attitude maneuver problem under slew rate and actuator capacity constraints. A quaternion feedback controller with quaternion and angular rate feedback is implemented to achieve a rest to rest reorientation maneuver. The control gains are computed based on the slew rate limits while the control commands incorporate the actuator limits. Three different configurations of four reaction wheels, (a) pyramid configuration, (b) skew configuration with three wheels along the body axes and the fourth wheel along body diagonal and (c) skew configuration with skew angle of 45°, are studied. The paper further discusses single reaction wheel failure conditions for all the three configurations and demonstrates satellite rest to rest maneuver within the slew rate and actuator limits.

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M3 - Conference contribution

AN - SCOPUS:85084666780

SN - 9789811517235

T3 - Lecture Notes in Mechanical Engineering

SP - 119

EP - 131

BT - Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019

A2 - Sastry, PSR Srinivasa

A2 - C.V., Jiji

A2 - Raghavamurthy, D.V.A.

A2 - Rao, Samba Siva

PB - Springer Paris

T2 - 1st International Conference on Small Satellites, ICSS 2019

Y2 - 7 February 2019 through 9 February 2019

ER -

Sahu A, Mahodaya AK, Chokkadi S. Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. In Sastry PSRS, C.V. J, Raghavamurthy DVA, Rao SS, editors, Advances in Small Satellite Technologies - Proceedings of 1st International Conference on Small Satellites, ICSS 2019. Springer Paris. 2020. p. 119-131. (Lecture Notes in Mechanical Engineering). doi: 10.1007/978-981-15-1724-2_12

Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure

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