Structural dynamic analysis of space launch vehicle using axisymmetric shell element including hydroelastic effect for pogo stability analysis

다국어 초록 (Multilingual Abstract)

Space launch vehicle exhibits many multidiscipline-related instabilities which are caused by coupling between the fuselage structural and other subsystem components. Pogo phenomenon is one of those coupled instabilities. This thesis focuses on the pogo phenomenon which is the longitudinal dynamic instability of space launch vehicles. For the prediction of the pogo phenomenon, it is essential to establish appropriate structural modeling, the characteristics of the feedlines and propulsion system. The purpose of this thesis is conducting the modal analysis of the launch vehicles. It was conducted by using the axisymmetric two-dimensional shell elements. The present analysis was validated using examples of the existing launch vehicles. The comparison in terms of modeling and results against the

목차 (Table of Contents)

• Chapter 1. Introduction 1
• 1.1 Background and Motivation 4
• 1.2 Previous Researches 4
• 1.2.1 Previous Research about Pogo Phenomenon 4
• 1.2.2 Previous Research about Structural Modeling 5
• 1.3 Objectives and Thesis Overview 8
• Chapter 2. Pogo Stability Analysis 9
• 2.1 Pogo Suppression on Saturn V 9
• 2.2 Pogo Suppression on Space Shuttle 14
• Chapter 3. Structural Modeling and Modal Analysis 18
• 3.1 Modal Analysis of the Launch Vehicles 18
• 3.2 Structural Modeling of the Complete Launch Vehicle 20
• 3.3 Formulation 23
• Chapter 4. Numerical Results and Discussion 30
• 4.1 Construction of the Present Analysis 30
• 4.2 Validation using an Example Launch Vehicle 31
• Chapter 5. Conclusion and Future Works 42
• 5.1 Conclusion 42
• 5.2 Future Works 44
• References 45
• 국문초록 52