TY - GEN
T1 - Model Predictive Control-Based Guidance and Control System for Simultaneous Multi-Satellite Assembly in Proximity Operation
AU - Atallah, Mohammed
AU - Okasha, Mohamed
AU - Dief, Tarek N.
AU - Omar, Farag
N1 - Funding Information:
This work is supported by the startup grant funded by the College of Engineering at The United Arab Emirates University (UAEU). The grant code is G00003527.
Publisher Copyright:
© 2022 IEEE.
PY - 2022
Y1 - 2022
N2 - This paper proposes a Model Predictive Control (MPC) framework for designing a guidance and control (G&C) system for multi-satellite assembly in proximity operation. The control system is designed by using a linear time-invariant dynamic model for circular orbit (Hill-Clohessy-Wiltshire model). Output and input constraints are studied and implemented in linear form to reduce the computational power. A collision-free maneuver is ensured by setting a hyper-plane-rotation constraint. In addition, a new form of line-of-sight constraint is developed based on the first-order approximation of the circular cone equation to guarantee smooth docking. Moreover, control input constraints are considered by setting upper and lower bounds for each input. The robustness of the system is studied by simulating the response for elliptical orbit with different values of eccentricity. The proposed GNC is verified in three stages; first, numerical simulation has been performed, second, optimized C++ code is generated and its results are compared to simulation results, and third, the C++ code is tested on the target board to verify the ability to compute the control action within the sampling time.
AB - This paper proposes a Model Predictive Control (MPC) framework for designing a guidance and control (G&C) system for multi-satellite assembly in proximity operation. The control system is designed by using a linear time-invariant dynamic model for circular orbit (Hill-Clohessy-Wiltshire model). Output and input constraints are studied and implemented in linear form to reduce the computational power. A collision-free maneuver is ensured by setting a hyper-plane-rotation constraint. In addition, a new form of line-of-sight constraint is developed based on the first-order approximation of the circular cone equation to guarantee smooth docking. Moreover, control input constraints are considered by setting upper and lower bounds for each input. The robustness of the system is studied by simulating the response for elliptical orbit with different values of eccentricity. The proposed GNC is verified in three stages; first, numerical simulation has been performed, second, optimized C++ code is generated and its results are compared to simulation results, and third, the C++ code is tested on the target board to verify the ability to compute the control action within the sampling time.
KW - in-orbit assembly
KW - Line-of-Sight
KW - model predictive control
KW - proximity operation
UR - http://www.scopus.com/inward/record.url?scp=85137265000&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85137265000&partnerID=8YFLogxK
U2 - 10.1109/ICMAE56000.2022.9852870
DO - 10.1109/ICMAE56000.2022.9852870
M3 - Conference contribution
AN - SCOPUS:85137265000
T3 - 2022 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
SP - 114
EP - 124
BT - 2022 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 13th International Conference on Mechanical and Aerospace Engineering, ICMAE 2022
Y2 - 20 July 2022 through 22 July 2022
ER -