混合式火箭具備固、液態火箭易運送及保存、控制性佳等優點，但藥柱燃燒退縮率低，無法大規模應用。過去改善結構以提升退縮率研究著重於使用複數孔、螺紋設計，但受限材料只可使用傳統加工，可製作結構受限。積層製造技術突破了製程限制，為製作複雜結構藥柱的新方法，但仍面臨精度、材料性質等問題。相較其他技術，DLP型光固化3D列印技術提高製造速度和精度，且材料不受熱變形。然而光固化材料在混合式燃料火箭藥柱的應用較少被探討。本研究旨在調配具有一定機械及燃燒性質光固化材料，並製造不同結構藥柱，進行燃燒測試並評估其效果。
本研究調配了兩種以脂肪族聚氨酯丙烯酸酯及甲基丙烯酸月桂酯(LMA)作為主體的光固化材料系統。為確保材料具有所需的機械強度和燃燒性質，製作試片進行機械、燃燒性質的測試。透過評估機械及燃燒性質後，在以脂肪族PUA系列中選擇了PIH-532，LMA系列中選擇LIT-424製作小型藥柱，使用自行搭建的燃燒試驗系統進行測試。與文獻材料(PP、ABS)進行比較發現，PIH-532比PP高約8%，LIT-424比PP、ABS則各高出約40%、25%，並觀察到尾焰長度與燃燒退縮率具有正相關。此外製作的兩種特殊內部結構藥柱，星型螺旋藥柱的燃燒退縮率相較直孔實心藥柱提高60%及81%。透過觀察各種結構藥柱的燃燒過程，並驗證了緻密多孔結構能增加燃燒表面積，從而具有其燃燒效果。最後透過熱重分析(TGA)試驗測試得出交聯密度低的光固化高分子材料會燃燒時最先產生裂解，交聯密度高的多官能數單體、寡聚物會須較高溫度才會產生裂解。

The hybrid rocket boasts advantages in easy transport and storage, akin to solid and liquid rockets, offering good controllability. However, its propellant's low combustion regression rate limits its widespread use. Prior studies focused on enhancing this rate through porous or helical designs, constrained by materials compatible only with traditional manufacturing, thereby restricting structural possibilities. Additive manufacturing has broken these constraints, allowing for complex propellant structures. Yet, challenges persist concerning precision and material properties. In comparison, DLP-type photo-curing 3D printing technology enhances production speed and accuracy while maintaining material integrity. However, the application of photo-curing materials in hybrid rocket propellants remains underexplored. This study aims to develop light-curing materials with specific mechanical and combustion properties, fabricate various structural propellants, conduct combustion tests, and evaluate their efficacy.
This study developed two photopolymer material systems using aliphatic polyurethane acrylate and lauryl methacrylate (LMA) as the main components. To ensure the materials possessed the required mechanical strength and combustion properties, specimens underwent mechanical and combustion property tests. Following the evaluation of these properties, PIH-532 from the aliphatic PUA series and LIT-424 from the LMA series were selected to manufacture small-scale rocket motors. Tests were conducted using a self-constructed combustion testing system. Comparative analysis with reference materials (PP, ABS) revealed that PIH-532 outperformed PP by approximately 8%, while LIT-424 surpassed PP and ABS by around 40% and 25%, respectively. Positive correlations between flame length and burnback rate were observed. Moreover, the burnback rates of two specially designed internally structured rocket motors, particularly the star-shaped spiral design, increased by 60% and 81%, respectively, compared to the solid straight-hole motor. Through the observation of the combustion processes of various motor structures, it was confirmed that dense porous structures increased the combustion surface area, thereby enhancing their burning efficiency. Finally, thermal gravimetric analysis (TGA) tests indicated that low cross-linking density photopolymer materials exhibited early decomposition during combustion, while those with high cross-linking density, including multi-functional monomers and oligomers, required higher temperatures to initiate decomposition.

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