摘要
本研究利用Cambridge Rocketry Toolbox 來模擬探空火箭的飛行軌跡與飛行數據分析，將火箭外型、推力數據、飛行穩定設計、速度和加速度的變化、飛行姿態以及飛行軌跡，透過實驗與數值計算模擬建立，有助於探空火箭設計初期進行快速設計分析，在火箭完成設計後並可搭配當天的飛行環境去設定，進行軌跡模擬分析。 模擬中使用成功大學火箭第三型的外型及推力，風場設定為量測到的大氣數據進行模擬計算，結果分析其火箭的飛行數據以及模擬的飛行軌跡，再與飛行測試的結果相互比較。再以原先預估能到達20公里以上的火箭加以模擬，分別以發射角82度和72度的方向分別去模擬出其飛行軌跡和分析飛行數據。
並列摘要
This research is used Cambridge Rocketry Toolbox to simulate the flight trajectory and flight analysis data of sounding rockets. The rocket shape, thrust data, flight stability design, velocity and acceleration, flight attitude, and flight trajectory are established through experiments and numerical calculations. It is helpful for rapid design analysis in the early stage of sounding rocket design. After the rocket is designed, it can be set with the flight environment of the day to perform trajectory simulation analysis. In the simulation are used NCCU type three rocket shape and thrust data. The wind field is set to the measured atmospheric data for simulation calculation. The results are analyzed for the rocket's flight data and then compared with the flight test results. Then use the rocket originally estimated to reach more than 20 kilometers to simulate, and use the launch angle of 82 degrees and 72 degrees respectively to simulate its flight trajectory and analysis flight data.