Thrust vectoring is a promising technology that offers the potential for improved maneuverability, control efficiency, and stealth characteristics of aircraft. Optimized nozzle design over a range of operating conditions is one of the most crucial factors for maximum thrust vectoring operation. Our goal was to investigate the optimal design of bypass dual throat nozzle to maximize thrust vectoring. We performed a multi-objective optimization study by varying the nozzle bypass angle, convergence angle, and bypass width to see what impact these parameters had on the performance of the bypass dual throat nozzle. A steady numerical simulation has been performed on 55 different nozzle configurations to compare their thrust vectoring performance and losses. In all simulations, the k-ϵ turbulence model is used to determine the vectoring states of the nozzle. The computational fluid dynamics analysis was followed by a multi-objective optimization process using the Response Surface Methodology within the ModeFrontier software. The testing of the optimized nozzle shapes using ANSYS FLUENT verified the accuracy and reliability of the multi-objective optimization algorithm. These findings suggest that nozzle convergence does not significantly affect thrust vectoring. In contrast, bypass width and bypass angle significantly affected thrust vectoring.

推力矢量是一种很有前途的技术，它可以提高飞机的机动性、控制效率和隐身特性。在一系列操作条件下优化的喷嘴设计是最大推力矢量操作的最关键因素之一。我们的目标是研究旁路双喉喷嘴的优化设计，以最大化推力矢量。我们通过改变喷嘴旁通角、收敛角和旁通宽度进行了多目标优化研究，以了解这些参数对旁通双喉喷嘴性能的影响。已经对 55 种不同的喷嘴配置进行了稳定的数值模拟，以比较它们的推力矢量性能和损失。在所有模拟中，k- ε湍流模型用于确定喷嘴的矢量化状态。计算流体动力学分析之后是使用 ModeFrontier 软件中的响应面方法的多目标优化过程。使用ANSYS FLUENT对优化后的喷嘴形状进行测试，验证了多目标优化算法的准确性和可靠性。这些发现表明喷嘴收敛不会显着影响推力矢量。相比之下，旁路宽度和旁路角度显着影响推力矢量。