軽量LVサーボ直駆動機構を用いたラッチバルブの飛行試験
Flight Testing of Latch Valve with Lightweight LV-Servo Direct Drive Mechanism
ロケットのラッチバルブ制御において従来のステップモータを小型軽量なサーボモータに置き換え、厳しい温度・圧力環境下での性能と信頼性を飛行試験で検証した。
著者: Hao-Che Huang, Chih-Shin Chang, Jui-Cheng Hsu, Shih-Sin Wei
分類: eess.SY, cs.RO, cs.SY
原文アブストラクト
In the field of rocket technology, the latch valve assumes a pivotal role in regulating the flow of fuel gases and liquids to ensure the requisite energy supply. This project endeavors to innovate by replacing the conventional step motor mechanism with a servo motor for latch valve control. The selected servo motor, boasting a more compact form factor and reduced mass, aligns seamlessly with the project's overarching objectives. While servo motors offer myriad advantages, it is imperative to acknowledge and address the constraints of their maximum output torque to guarantee the latch valve's reliable operation. Furthermore, as a rocket ascends, it encounters significant fluctuations in internal temperature and pressure. Consequently, rigorous environmental testing becomes paramount to validate the servo motor's performance under these dynamic conditions, thus ensuring the latch valve's unwavering functionality. The primary focus of this project is the design and testing of the mechanism's performance in simulated rocket environments, achieved through the implementation of the servo motor for latch valve control. The results reveal that the servo motor demonstrated its effectiveness and reliability in controlling the latch valve under the rigorous environmental conditions of rocket flight.