Propulsion System Effects on the Controllability of a Second-Stage Spaceplane

Master thesis (2019)

Authors

J. Anckaert Aerospace Engineering

Contributors

E. Mooij Astrodynamics & Space Missions - Aerospace Engineering (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2019 Jorg Anckaert
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Published Date

2019

Language

English

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Faculty

Aerospace Engineering

Abstract

Spaceplanes are the future of space travel and launching objects into space. They are fully reusable, and provide a lot of flexibility to a mission. This thesis focuses on the propulsion system and its impact on the stability and control of a spaceplane. The main research question is: "Which parameters and deficiencies in the propulsion system of a winged second-stage spaceplane effect its controllability at single points during the hypersonic ascent phase?" To analyse propulsion effects, a dedicated propulsion model is developed to simulate the rocket engines of the vehicle. These engines are used for thrust vector control (TVC) of the vehicle. An incremental nonlinear dynamic inversion (INDI) controller is designed to study the controllability of the system. It is demonstrated that this INDI controller can effectively control the vehicle, even when subjected to thrust deficiencies, such as engine-out failures, engines getting stuck, thrust fluctuations and inertia shifts.