비폭발식 분리장치가 포함된 De-orbiter 장치 개발 : Design and fabrication of the De-orbiter integrated with non-explosive separation device

다국어 초록 (Multilingual Abstract)

As satellites are actively developed nowadays, space debris has rapidly increased due to end-of-life satellites or collisions among satellites. Hence, developed countries such as Europe, USA, etc made a policy in which end-of-life satellites go out of its orbit to reduce the space debris. Especially, many researches on ’drag force sail’, one of mitigating methods among many different ways of deviation from orbit, have been conducted. Following this trend, De-orbiter device using Drag-sail is suggested and concept design has been shown in this paper. In the process of designing the device, we focused on following points : stowed sail with minimum volume and deployment of sail to have maximum area, design of separation mechanism and actuator considering mass and volume. To verify the quantitative/qualitative target specification of small satellite, we computed the de-orbit time with the below input conditions; below 150 kg, below 800 km altitude, above 10 m area of drag sail. As the result, we obtained de-orbit time of 16.68 years. The result satisfies European Space Agency recommended re-entry time of 25 years. In addition, deployment method based on tape spring is chosen to reduce mass and volume in this research. Moreover, we applied simple working principle to separation mechanism to shackle tape spring through SMA wire by considering benefits of actuator.
Analysis for stability and reliability is highly important because the above technology must operate well when satellite is end-of-life. To analyze reliability of one-shot device like Drag-sail deployment device, FMECA and FTA have been introduced and calculation for reliability using analysis for system diagram of malfunction has been done. As the analysis result based on system diagram of malfunction, the reliability of Drag-sail deployment device was 0.999868. Based on criticality analysis, the most influential mechanical parts on reliability are detected and improvement plan was suggested.

목차 (Table of Contents)

• TABLE OF CONTENTS
• SUMMARY ⅰ
• TABLE OF CONTENTS ⅱ
• LIST　OF FIGURES ⅳ
• LIST　OF TABLES ⅴ
• CHAPTER 1 INTRODUCTION 1
• 1.1 Research background 1
• 1.2 Research goal 4
• CHAPTER 2 STATE OF THE ART ON STUDY FOR DE-ORBIT SYSTEM USING MITIGATION AND CAPTURE METHOD 6
• 2.1 Capture method 7
• 2.2 Mitigation method 9
• CHAPTER 3 ESTABLISHMENT OF EACH COMPONENT REQUIREMENT FOR DE-ORBITER 11
• 3.1 Concept design of De-orbiter 11
• 3.2 Drag-sail area calculation through mission orbit simulation 13
• 3.3 Application of origami method for effective storage 16
• 3.4 Selection of Drag-sail materials considering operating environment of De-orbiter 17
• 3.5 Selection of actuator and separation mechanism 19
• 3.6 Deployment experiment of De-orbiter 26
• CHAPTER 4 RELIABILITY ANALYSIS OF DE-ORBITER 28
• 4.1 Introduction of FTA and FMECA 28
• 4.2 Reliability analysis for De-orbiter 28
• 4.2.1. Application to FTA method 28
• 4.2.2. Quantitative analysis 31
• 4.2.3. Probability of basic events 32
• CHAPTER 5 CONCLUSION 34
• REFERENCE 36
• 요 약 42