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| Numerical Simulation of Rocket Fairing Spin Separation in Low-Altitude High-Dynamic-Pressure Environment |
| LI Yi1， OU Shuyan1， LIANG Weidong2， DONG Jiabao2， ZHUANG Zhidong2 |
| 1. Shaanxi Aerospace Flight Vehicle Design Key Laboratory， Northwestern Polytechnical University， Xi'an 710072， Shaanxi， China； 2. Shanghai Electro-Mechanical Engineering Institute， Shanghai 201109， China |
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Abstract To investigate the motion characteristics of the fairing separation of aircraft in a low-altitude high-dynamic-pressure environment, a numerical simulation was applied using the CFD-rigid body dynamics coupling method. This study has revealed the flow structure and dynamic behavior of the fairing during the process. Specifically, focused on the asymmetric inflow conditions, the disparate opening speeds of the two fairing halves, and the variations in the detachment angle of the fairing. Results show that under asymmetric inflow conditions, the separation of one half of the fairing is suppressed, being detrimental to a safe separation. Increasing the detachment angle is beneficial in terms of enlarging the windward area of the fairing while accelerating its separation from the aircraft.
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Received: 25 March 2023
Published: 22 March 2025
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2025, Vol. 8 
