Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'

Raunaq Rakesh; Smit Kamal; Carina Pereira; Naman Saxena; Revathi Ravula; Faraz Haider; Siddhath Mayya; Karun Potty

doi:10.1109/ICACCI.2015.7275676

Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'

Raunaq Rakesh, Smit Kamal, Carina Pereira, Naman Saxena, Revathi Ravula, Faraz Haider, Siddhath Mayya, Karun Potty

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

2 Citations (Scopus)

Abstract

This paper describes the control systems employed by a nano-satellite 'Parikshit' to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled in terms of quaternions and its advantages over euler angles have also been mentioned. A concise description of the numerical integration techniques and step size determination have also been mentioned. In order to simulate the environment conditions, influential disturbance torques along with their effects have been evaluated and estimated. The results from these simulations used to test the controller in space environment for attitude control have been analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.

Original language	English
Title of host publication	2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	607-613
Number of pages	7
ISBN (Electronic)	9781479987917
DOIs	https://doi.org/10.1109/ICACCI.2015.7275676
Publication status	Published - 01-01-2015
Externally published	Yes
Event	International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015 - Kerala, India Duration: 10-08-2015 → 13-08-2015

Conference

Conference	International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015
Country/Territory	India
City	Kerala
Period	10-08-15 → 13-08-15

All Science Journal Classification (ASJC) codes

Signal Processing
Hardware and Architecture
Information Systems
Computer Networks and Communications

Access to Document

10.1109/ICACCI.2015.7275676

Cite this

Rakesh, R., Kamal, S., Pereira, C., Saxena, N., Ravula, R., Haider, F., Mayya, S., & Potty, K. (2015). Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'. In 2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015 (pp. 607-613). [7275676] Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ICACCI.2015.7275676

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abstract = "This paper describes the control systems employed by a nano-satellite 'Parikshit' to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled in terms of quaternions and its advantages over euler angles have also been mentioned. A concise description of the numerical integration techniques and step size determination have also been mentioned. In order to simulate the environment conditions, influential disturbance torques along with their effects have been evaluated and estimated. The results from these simulations used to test the controller in space environment for attitude control have been analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.",

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Rakesh, R, Kamal, S, Pereira, C, Saxena, N, Ravula, R, Haider, F, Mayya, S & Potty, K 2015, Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'. in 2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015., 7275676, Institute of Electrical and Electronics Engineers Inc., pp. 607-613, International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015, Kerala, India, 10-08-15. https://doi.org/10.1109/ICACCI.2015.7275676

Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'. / Rakesh, Raunaq; Kamal, Smit; Pereira, Carina et al.
2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015. Institute of Electrical and Electronics Engineers Inc., 2015. p. 607-613 7275676.

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

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AU - Rakesh, Raunaq

AU - Kamal, Smit

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AU - Saxena, Naman

AU - Ravula, Revathi

AU - Haider, Faraz

AU - Mayya, Siddhath

AU - Potty, Karun

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N2 - This paper describes the control systems employed by a nano-satellite 'Parikshit' to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled in terms of quaternions and its advantages over euler angles have also been mentioned. A concise description of the numerical integration techniques and step size determination have also been mentioned. In order to simulate the environment conditions, influential disturbance torques along with their effects have been evaluated and estimated. The results from these simulations used to test the controller in space environment for attitude control have been analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.

AB - This paper describes the control systems employed by a nano-satellite 'Parikshit' to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled in terms of quaternions and its advantages over euler angles have also been mentioned. A concise description of the numerical integration techniques and step size determination have also been mentioned. In order to simulate the environment conditions, influential disturbance torques along with their effects have been evaluated and estimated. The results from these simulations used to test the controller in space environment for attitude control have been analysed and used to evaluate the performance of the controller. All graphs pertaining to the simulations have been analysed and discussed.

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Rakesh R, Kamal S, Pereira C, Saxena N, Ravula R, Haider F et al. Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'. In 2015 International Conference on Advances in Computing, Communications and Informatics, ICACCI 2015. Institute of Electrical and Electronics Engineers Inc. 2015. p. 607-613. 7275676 doi: 10.1109/ICACCI.2015.7275676

Dynamics and control system design of a polar low-earth orbit nano-satellite 'Parikshit'

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