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Robust successive generalised dynamic inversion control of satellite launch vehicles

Published online by Cambridge University Press:  17 January 2025

A.H. Bajodah Open the ORCID record for A.H. Bajodah [Opens in a new window]  and
U. Ansari Open the ORCID record for U. Ansari [Opens in a new window]
A.H. Bajodah*
Affiliation:
Aerospace Engineering Department, King Abdulaziz University, Jeddah, Saudi Arabia
U. Ansari
Affiliation:
Aerospace Engineering Department, King Abdulaziz University, Jeddah, Saudi Arabia
*
Corresponding author: A.H. Bajodah; Email: abajodah@kau.edu.sa
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Abstract

In this paper, we designa robust Successive Generalised Dynamic Inversion (SGDI) flight control system for high-performance trajectory tracking of target sun-synchronous orbit Satellite Launch Vehicles (SLVs). The robust SGDI control system is designed to track an optimal reference trajectory such that the desired orbital terminal conditions of the ascent flight phase are achieved. The proposed SGDI is composed of two loops. The attitude control loop employs Dynamically Scaled Generalised Inversion (DSGI) of Servo Constraint Dynamics (SVD) in the deviations of Euler attitude angles from their desired optimal trajectories. The inner-dynamics control loop employs DSGI of an SVD in the SLV angular velocity components. Robustification control elements are augmented within the two loops of the baseline SGDI control system to overcome control performance degradation due to dynamic scaling of the Moore-Penrose generalised inverse, modeling and parametric uncertainties, and exogenous disturbances. The robust SGDI control system works to enforce global convergence of the SLV attitude trajectories to the reference trajectories. The high-performance attributes of the robust SGDI control system are verified via comparisons with a classical sliding mode control system, and by performing numerous runs of Monte Carlo simulations under various types of uncertainties and external wind disturbances.

Keywords

Generalized Dynamic Inversion ControlRobust ControlSatellite Launch VehicleTrajectory OptimizationLyapunov Stability

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 129 , Issue 1335 , May 2025 , pp. 1182 - 1214
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Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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