학위논문 (박사)-- 서울대학교 대학원 : 기계항공공학부, 2017. 2. 신상준. ; This thesis presents an estimation methodology on the vibratory response of the supersonic flight vehicle caused by various dynamic loads during operation. High-speed flight vehicle (HSFV) is an imaginary supersonic flight vehicle with an air breathing engine (i.e., ramjet engine). It undergo severe dynamic loads which are generated during the launch and in-flight environments. And a typical vehicle is composed of thin plate skin structures with high-performance electronic units sensitive to such vibratory loads. Such lightweight structures are then exposed to external dynamic loads which consist of random excitation, shock, and acoustic loads created under the operating environments. Three types of dynamic loads (acoustic loads, rocket motor self-induced excitation loads and aerodynamic fluctuating pressure loads) are considered as major components in this thesis. Generally, for large structural components such as an entire launch vehicle considering high frequency range, proper structural response analysis method should be chosen because it is known that deterministic method (such as finite element analysis) is not capable of precisely and efficiently predicting the response for high frequency ranges. To overcome such limitations of the deterministic method for high frequency range, statistical energy analysis is used in this thesis. The estimation results are compared with respect to the design specification (MIL-STD-810) to examine the appropriateness. The objective of this thesis is to study an estimation methodology which helps to establish design specification for the dynamic loads acting on the vehicle which cannot be followed general design procedure because there exit a little data can be applied to establish design dynamic loads. ; Chapter 1. Introduction 1 1.1. Background and Motivation 1 1.2. Dynamic Loads on a High Speed Flight Vehicle 6 1.2.1. Rocket Motor Vibratory Loads 7 1.2.2. Acoustic Vibratory Loads 8 1.2.3. Aerodynamic Fluctuating Pressure Excitation Loads 8 1.3. Analytical Method for the Higher Frequency Response 10 1.4. Objectives and Layout of Thesis 14 Chapter 2. Statistical Energy Analysis 17 2.1. Brief Historical Background 17 2.2. Theoretical Background 20 2.3. Advantages and Limitations 37 Chapter 3. Dynamic Loads on the High Speed Flight Vehicle during Launch Events 39 3.1. Acoustic Loads on the Launch Pad 39 3.2. Rocket Motor Vibratory Load 46 3.2.1. Rocket Motor Self-Excited Vibration 46 3.2.2. Overview of Input Force Estimation 49 3.3. Aerodynamic Fluctuating Surface Pressure Excitation Loads 50 Chapter 4. Input Force Estimation Method to Predict the Rocket Motor Self-Excited Loads 52 4.1. Introduction 52 4.2. Theoretical Background 53 4.3. Verification by a Simple Structure 67 Chapter 5. Prediction on Fluctuating Surface Pressure of the High Speed Flight Vehicle 83 5.1. Introduction 83 5.2. Present Prediction Procedure 87 5.3. Existing Semi-Empirical Model for the Attached Flows 90 5.3.1. Cockburn and Robertsons model 90 5.3.2. Emfimtsovs model 92 5.3.3. Goodys model 93 5.4. Verification of the present prediction procedure 95 5.4.1. Rocket Motor Self-Excited Vibration 95 5.4.2. Predicting fluctuating pressure using the present procedure on the ATLAS-Agena shroud 96 5.4.3. Examination of the surface pressure fluctuation spectrum 108 5.5. Fuselage excitation on a high speed flight vehicle 114 5.5.1. Devlopment of the present prediction analysis 114 5.5.2. Prediction on the fluctuating surface pressure of the vehicle 119 Chapter 6. Vibratory Response Analysis Using SEA 129 6.1. Development of the Present Response Aanlysis Model 129 6.2. Discussion of the predicted structural Response 135 Chapter 7. Conclusions and Future Works 147 7.1. Summary 147 7.2. Future Works 151 Bibliography 152 Appendix 162 Abstract in Korean 180 ; Doctor


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    Titel :

    Prediction on the Excitation Loads and Vibratory Response of the Supersonic Flight Vehicle with Air Breathing Inlet ; 공기 흡입구를 가진 초음속 비행체의 가진하중 및 진동응답 예측에 관한 연구



    Erscheinungsdatum :

    2017-01-01


    Medientyp :

    Hochschulschrift


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Klassifikation :

    DDC:    621 / 629



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