本研究主要針對氣態燃料脈衝爆震微推進器發展進行其概念驗證、設計以及最後使用低溫共燒陶瓷材料發展一微推進器原型。首先以實驗方式探討一矩形出口截面積僅為1 mm × 0.6 mm的無閥式脈衝爆震推進器在100 Hz以上連續操作情況。本研究使用高反應性的乙烯/氧氣反應物來縮短操作時反應波於微槽中形成爆震波距離。本研究使用高速顯影法拍攝證明反應波經由高重複性的火焰加與緩燃焰轉爆震焰過程(deflagration-to-detonation transition, DDT)達到爆震波狀態。接著針對脈衝爆震推進器操作時燃燒腔內壓力進行量測。由燃燒腔中壓力傳遞從點火前常壓開始增加至出口前超過 2 MPa以上。高速顯影及壓力量測驗證了使用乙烯/氧氣反應物，能使無閥式脈衝爆震機制於介尺度(sub-millimeter scale)微槽內成功操作並生成推力的可行性。
第二部份主要針對驗證的設計概念發展整合一脈衝爆震微推進器原型。微推進器發展主要使用低溫共燒陶瓷科技，而推進器原型燃燒腔尺寸約為58 mm3。點火電路以及離子感測器亦整合於陶瓷微推進器中。微推進器外觀，流道及燃氣與電路通孔(via holes)主要利用CO2雷射進行切割。於離子感測器實驗中也再次驗證，反應波於微推進器內傳遞至出口前能夠達到2000 m/s以上。最後也針對無閥式脈衝爆震微推進器於不同進氣壓力下穩定操作之操作區間與及極限進行量測。於氧氣進氣壓力大於等於乙烯時，微推進器能夠達到較高的穩定操作頻率，其最大操作頻率能達到450 Hz。且微推進器產生推力峰值約為20至30 mN。

The concept validation of a microthruster based on gaseous pulsed detonation and the prototype development using low temperature co-firing ceramic technologies are presented in this study. The feasibility of cyclic valveless pulsed detonation at frequencies over 100 Hz is investigated in a microchannel with 1 mm × 0.6 mm rectangular cross-section. Highly reactive ethylene/oxygen mixtures are utilized to reduce time and distance required for the reaction wave to run up to detonation state. High speed visualizations have shown that the reaction waves reach detonative state through highly repeatable flame acceleration and deflagration-to-detonation transition processes in the channel. Pressure measurements at four locations along the channel are performed to study the characteristics of detonation wave initiation and propagation in the sub-millimeter microchannel. The pressure in the channel is initially atmospheric, and abruptly rose over 2 MPa near the exit when the detonation wave passed by. In general, both the high-speed visualization and the pressure measurements prove the feasibility of utilizing valveless pulsed detonation as the mechanism for thrust generation at sub-millimeter scale using ethylene/oxygen mixtures.The validated concepts are implemented for the prototype development of an integrated pulsed detonation microthruster. The microthruster is fabricated using low temperature co-fired ceramic tape technology. The volume of the reaction channel in the microthruster was 58 mm3. Spark electrodes and ion probes are embedded in the ceramic microthruster. The channel and via holes are fabricated using laser cutting techniques. Ion probe measurements show that the reaction wave propagated at velocities larger than 2000 m/s before reaching the channel exit. The pulsed detonation microthruster has been successfully operated at frequencies as high as 450 Hz.

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