摘要
本論文主要探討可用於空射小型火箭的無人機載台設定。目前淡江大學太空實驗室正在發展小型太探火箭，受限於台灣北部地區試射場地的不足，因此採用無人機載台進行空射火箭，將是選擇之一。本論文所探討的無人機載台，將用於搭載一公尺長、一公斤重、10 公分粗的火箭，因此，飛機的規格主要根據此項任務開立。再參考了世界上各式空射火箭的載具，本論文採用了雙體機的設計。 具體來說，本論文首先依據需要執行的任務定義飛機各項規格，接著依照所開立的規格，推算出所需的各項空氣動力參數。接著，依照所需要的空氣動力係數去挑選合適的翼型，並據此用計算流力求得全機的各項導係數。在結構方面，本論文採用CATIA 進行建模，並將各項資訊整合之後，粗布估算飛機的動態方程式。論文最後也簡單陳列若干可用的硬體設備。本論文的研究成果，日後將有助於空射火箭的無人機載台發展。
並列摘要
This paper focuses on the setting of UAV stations that can be used for air-launched small rockets. At present, the Space Laboratory of Tamkang University is developing small-scale rockets, which is limited by the lack of test sites in northern Taiwan. Therefore, it is one of the choices to use airborne rockets for drone carriers. The UAV platform discussed in this paper will be used to carry a rocket measuring one meter long, one kilogram and 10 cm thick. Therefore, the specifications of the aircraft are mainly based on this task. Referring to the vehicles of various air-launched rockets in the world, this paper adopts the design of the double-body machine. Specifically, this paper first defines the aircraft specifications according to the tasks that need to be performed, and then derives the required aerodynamic parameters according to the specifications that are opened. Then, according to the required aerodynamic coefficient, the appropriate airfoil is selected, and the calculation coefficients of the whole machine are obtained according to the calculated flow force. In terms of structure, this paper uses CATIA to model and integrate various information to estimate the dynamic equation of the aircraft. At the end of the paper, some of the available hardware devices are simply displayed. The research results of this paper will contribute to the development of airborne rocket drone carriers in the future.