Launcher Attitude Control based on Incremental Nonlinear Dynamic Inversion: A Feasibility Study Towards Fast and Robust Design Approaches

TL;DR

This paper explores the application of Incremental Nonlinear Dynamic Inversion (INDI) for launch vehicle attitude control, demonstrating its potential for improved robustness and performance over traditional linear controllers in a representative ascent scenario.

Contribution

It introduces INDI to the launcher GNC community, presents a stability analysis approach, and compares INDI with traditional PD controllers, highlighting its advantages and challenges.

Findings

INDI offers increased robustness and performance in attitude control.

INDI is more sensitive to sensor noise and actuator delay than linear controllers.

The proposed stability analysis method effectively evaluates INDI's applicability.

Abstract

The so-called ``New Space era'' has seen a disruptive change in the business models and manufacturing technologies of launch vehicle companies. However, limited consideration has been given to the benefits that innovation in control theory can bring; not only in terms of increasing the limits of performance but also reducing mission preparation or ``missionisation'' efforts. Moreover, there is a gap between the current state-of-practice that still relies on linear controls and other modern control techniques that could bring relevant improvements in launcher attitude control. Nonlinear Dynamic Inversion (NDI) is a technique that basically `cancels' the nonlinearities of a class of nonlinear systems, allowing for a single linear control law to be applied without the need for gain-scheduling across different operational points. Incremental NDI (INDI) is a variation of NDI that generates incremental commands and employs acceleration feedback to reduce model dependency, making it easier to design, and results in being more robust in closed-loop. While INDI has been applied successfully to several aerospace applications, its applicability to launch vehicles has not yet been adequately investigated. The objective of this paper is therefore to introduce and raise awareness of the INDI method among the launcher guidance, navigation, and control (GNC) community, showcasing its implementation on a representative launch ascent application scenario which highlights INDI's strengths and challenges. We present a new, practical approach for stability analysis of INDI for attitude control, and compare INDI with scheduled PD controllers with- and without angular acceleration estimates. Results show that, while INDI controllers are generally more sensitive to sensor noise and actuator delay than linear controllers, their potential benefits outweigh these limitations in terms of robustness and performance.