碩士生: 黃丙翰
畢業年分: 2023年1月
論文名稱: 並列電極陣列式真空陰極電弧推進器之研發、設計與測試(中文) / The development, design and demonstration of vacuum cathode arc thruster with parallel electrode array (英文)
中文摘要:
本研究則專注於發展適用於立方衛星的電力推進系統，由於立方衛星的體積較小、重量輕且所能提供的電力有限，因此本研究選擇真空電弧推進器進行研發與改良。本研究提出新概念「並列電極陣列式真空陰極電弧推進器」，該推進器具有多個推進單元組合而成，並且預期可以由誘發電極放電誘發主電極放電，研究結果顯示所設計之新穎推進系統可以成功點火。該概念改善傳統真空電弧推進器因系統內的石墨導電層重複附著而導致整體效率下降。本研究亦提出「多層絕緣層」取代傳統真空電弧推進器中的石墨層與絕緣體，該設計應用「三相點」的物理現象，促使推進器的擊穿電壓相較於真空可以降低，且運作更為穩定與持久。本研究也改善實驗室已發展的電感儲能裝置，包含改善電感元件的飽和問題等等。此外，本研究也完成一快速法拉第杯與示波器等量測儀器，量測推進器的各項參數。最終，本研究所製作的推進器的誘發電極每發的衝量可達50.867[μN∙s]；比衝值可達849.51 [s]；效率為22.8%；推力功率比為57.6 [μN/W]。
英文摘要:
This study focuses on the development of an electric propulsion system suitable for CubeSats. Due to the small volume, low mass, and limited power supply of CubeSats, a vacuum arc thruster was selected for further development and modification. A novel concept, the “Parallel Electrode Array Vacuum Cathode Arc Thruster,” is proposed, in which multiple propulsion units are combined, and the discharge of the induced electrode is expected to trigger the discharge of the main electrode. Experimental results confirm that the newly designed thruster system can be successfully ignited. This concept addresses the efficiency degradation commonly observed in conventional vacuum arc thrusters, where conductive graphite layers repeatedly redeposit within the system. Additionally, this study introduces a “multi-layer insulation” design to replace the graphite layer and insulator used in traditional vacuum arc thrusters. By utilizing the physical phenomenon of the “triple point,” the breakdown voltage of the thruster is reduced compared to vacuum conditions, while operational stability and durability are enhanced. Improvements were also made to the laboratory’s inductive energy storage device, including mitigation of inductor saturation issues. Furthermore, diagnostic instruments such as a fast Faraday cup and oscilloscope were implemented to measure key thruster parameters. The fabricated thruster demonstrated a per-pulse impulse bit of 50.867 μN∙s, a specific impulse of 849.51 s, an efficiency of 22.8%, and a thrust-to-power ratio of 57.6 μN/W.
