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为解决舰面非定常流场数据量过大的问题,采用本征正交分解(POD)方法对舰面流场进行重构,发展了一种耦合POD重构流场的直升机舰面起降数值模拟方法。首先采用计算流体力学(CFD)方法计算舰面非定常流场,获得离散数据样本;然后提取流场的POD模态,并截取能够捕捉到原流场主要特征的少量模态对原流场进行重构;最后建立耦合重构舰面流场的直升机高阶飞行动力学模型。以直升机返航进场为例进行数值模拟,并将计算得到的操纵量和飞行状态与飞行试验结果进行对比。结果表明:使用POD方法重构后的舰面流场数据约为原始样本数据的8.5%,且重构流场与原始流场吻合良好,POD方法能够解决舰面非定常流场数据量过大的问题。与飞行试验数据的对比表明,本文方法捕捉到了舰面非定常流场对直升机的影响,可用于直升机舰面起降研究。
In order to solve the problem that the data amount of the unsteady flow field in the ship is too large, the Orthogonal Decomposition (POD) method is used to reconstruct the flow field of the ship surface. A helicopter landing surface coupled with POD reconstruction flow field is developed Numerical simulation method. Firstly, the computational fluid dynamics (CFD) method is used to calculate the unsteady flow field of the ship surface to obtain discrete data samples. Then, the POD mode of the flow field is extracted and a small number of modalities that capture the main features of the original flow field are extracted from the original flow field Reconstruction; Finally, the establishment of coupling and reconstruction of the surface flow field helicopter high-order flight dynamics model. Taking the helicopter return approach as an example, numerical simulation is carried out, and the calculated manipulated variable and flight status are compared with the flight test results. The results show that the reconstructed POD data is about 8.5% of the original sample data, and the reconstructed flow field is in good agreement with the original flow field. The POD method can solve the problem that the data amount of unsteady flow field is too large The problem. The comparison with the flight test data shows that this method captures the impact of the unsteady flow on the helicopter and can be used for helicopter landing.