本論文以開發一組冷流噴射推進器目的，利用市售元件完成本論文冷流噴射推進器設計與製作，本冷流噴射推進器包含1)由氣瓶、刺穿機構、絕對氣壓計、調壓閥、電磁閥與各式空壓元件與機構設計組成的冷流噴射推進氣動平台，及2)透過本實驗室所開發的LUTOS微作業系統操控實驗與量測及遙傳數據的微處理器控制系統。本冷流噴射推進器將搭載於探空八號回收艙中，並利用回收艙中的酬載三軸加速度與旋轉速度感測次系統(Accelerometer & Gyro, GG)進行減滾效果量測。實測證實本系統可依照任務的規劃在回收艙系統的遙控下正確執行與遙傳10秒的開迴路噴射推進減滾效能測試與10秒之閉迴路減滾控制測試量測數據。在ㄧ大氣壓的環境下，減滾之角減速度可達44度每秒平方。A cold gas thruster propulsion test bed is developed for the de-spin experiment of a sounding rocket recovery system RS of the Sounding Rocket 8 Project. The cold gas thruster propulsion system consists of the pneumatic test bed and the electronic control system to execute and measure the dynamic effects of the thruster. Pneumatic components are the cold gas supplying CO2 canister, its piercing valve, pressure regulation valve, absolute pressure guage, a solenoid thrust control valve and the nozzles. The experiment execution and dynamic variable measurement is controlled by a micro processor running an in-house developed LUTOS micro-operating system. In sounding rocket 8 project, this system is to execute 10 seconds of open loop thruster performance test and 10 seconds of closed loop de-spin control test. Physical test verified the correct execution and real time telemetry of test measurements. The data shows that a de-spin of angular deceleration of 44 deg/sec^2 can be achieved in one atmosphere pressure environment.
