Unsteady Adjoint-Based Optimization of Flame Deflectors to Mitigate Ignition Overpressure

Date

2026-4-16

Author

Danışan, Ercan Umut

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The solid rocket boosters (SRBs) of space launch vehicles generate strong, transient Ignition Overpressure (IOP) waves in the first seconds of ignition. These waves travel through the launch environment and reflect off the Flame Deflector (FD) back toward the vehicle. The reflected, high-amplitude waves may damage the vehicle and sensitive payloads. Computational Fluid Dynamics (CFD) simulations are essential for accurately capturing the pressure environment during launches of both new and existing space vehicles. One method to reduce IOP effects on the rocket is to optimize the flame deflector geometry. This study investigates a flat-plate FD inclined at 45° for shape optimization. Due to the problem's unsteady nature, the unsteady discrete-adjoint method is used to reduce pressure values. Shape optimization simulations are performed with the open-source SU2 CFD solver for its support of the unsteady adjoint method.

Subject Keywords

Cfd, Unsteady Adjoint, Shape Optimization, SU2

URI

https://hdl.handle.net/11511/119126

Collections

Graduate School of Natural and Applied Sciences, Thesis