隨著各國防空性能的不斷提升與超遠程精準打擊戰術的需求演進，為傳統空投用彈體配置滑翔擴展套件，使其由常規投放轉化為遠距受控滑翔，已成為不可或缺的選擇。然而，滑翔彈體於戰機分離過程中，面臨著複雜且強烈的戰機非對稱流場干擾。若初始彈射力與機翼展開時長配合不當，將導致彈體姿態發生不可逆之發散運動，對投放安全與彈體滑翔姿態造成嚴重影響。為了探討此動態分離特性，本研究使用CFD(Computational Fluid Dynamics)計算流體力學方法，針對F-16戰機在馬赫數0.6下投放似JDAM-ER滑翔彈體進行動態模擬，並藉由設定固定三種不同展開時長(0.6秒、0.8秒、1.0秒)，以及結合不同橫向偏移彈射器的方式進行投彈，以觀察受流場不對稱對於滑翔彈體分離過程的影響。
在數值模擬驗證方面，本研究首先參考經典風洞投彈實驗文獻，針對馬赫數1.2條件下之機翼掛載彈體投彈分離軌跡進行重現，模擬結果之彈體重心位移與姿態變化均與實驗數據呈現高度一致性，證實本研究數值模擬的可信度。
滑翔彈體動態分離之研究結果顯示，在改變彈體機翼展開時長的情況下，則隨著展開的時長越短(0.6秒)，中後期越快產生回復正俯仰力矩與更快下降的偏航角速度，但同時也會在初期產生更大的滾轉力矩峰值與滾轉角速度，並最終累積較大的滾轉角(18.32º)與更為明顯的Y方向回復位移量；反之，展開時長延長至1.0秒，雖在前中期能減緩滾轉角的累積，但在後期更晚產生回復的正俯仰力矩與更晚下降的偏航角速度，且滾轉力矩亦未能產生回復特徵。在彈射條件方面，橫向偏移彈射器能顯著抑制前期滾轉角速度，使-2 mm偏移案例(Case 4)之最終累積滾轉角下降至14.73º；然而，橫向偏移亦引發彈體-Y方向速度增加。此-Y方向速度一方面使彈體尾翼對彈體更快產生回復偏航力矩，使偏航角速度相較未偏移案例下降更明顯，累積之偏航角亦較未偏移案例小，但另一方面，其與初期較小的滾轉角共同作用，反而更擴大了中後期左右機翼的升力差，導致延緩回復滾轉力矩的出現，對彈體姿態自回復能力帶來負面影響。此外，對於更大的橫向偏移-4mm案例(Case 7)在相同機翼展開時長下，其前期滾轉角速度更進一步抑制，使最終累積之滾轉角顯著下降至10.95º，Y方向回復位移量亦為最小；同時更快產生回復偏航力矩，使偏航角(1.36º)顯著小於未偏移之Case 1與橫向偏移-2mm之Case 4。然而，前期更小之滾轉角速度與後期更快下降之偏航角速度共同作用，使Case 7於分離後期呈現較未偏移案例(Case 1)更明顯之低頭俯仰角速度，進而累積較大之低頭俯仰角(-1.19º)。綜上所述，機翼展開時長與橫向偏移彈射器的設計，在彈體的氣動與姿態變化上各有利弊，為未來的滑翔彈體設計，以及機翼展開時機的優化提供關鍵參考。

With advances in air defenses, equipping munitions with glide-extension kits has become essential. However, asymmetric aerodynamic interference during store separation can induce attitude divergence if ejector forces and wing deployment timing are improperly coordinated. This study uses CFD to simulate the separation of a JDAM-ER-like glide store from an F-16 at Mach 0.6, evaluating wing deployment durations (0.6 s, 0.8 s, 1.0 s) and lateral-offset ejectors. The numerical framework is validated against Mach 1.2 wind-tunnel trajectory and attitude data with good agreement.
Results show that a shorter deployment duration (0.6 s) promotes earlier pitch-yaw recovery despite a higher initial rolling moment peak and larger accumulated roll angle (18.32º), whereas extending deployment to 1.0 s fails to generate restoring rolling moment. Introducing a -2 mm lateral offset ejector reduces early roll accumulation (14.73º) and accelerates restoring yaw moment generation to yield a more pronounced yaw angular velocity reduction via induced negative Y velocity; however, this lateral velocity exacerbates mid-to-late wing lift differential, delaying roll recovery. Furthermore, a -4 mm offset further suppresses early roll velocity, minimizing the final roll angle (10.95º) and Y-displacement, while faster generation of the restoring yaw moment yields a smaller yaw angle (1.36º). However, joint action of lower early roll velocity and faster late yaw decay induces slightly higher late-stage nose-down pitch velocity, yielding a -1.19º pitch angle. In conclusion, deployment duration and lateral offset present critical aerodynamic trade-offs for glide store optimization.

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