着舰路径对舰载直升机起降安全影响研究

机舰耦合流场中存在着涡–涡干扰,是一个复杂紊乱的非定常流场,舰载直升机在不同着舰路径上必然会受到不同程度的影响,进而限制舰载直升机的起降能力。现基于简化护卫舰和UH-60直升机的耦合模型,结合计算流体力学和直升机飞行动力学,对不同着舰路径(正后方进场、斜向进场、横向进场)下的直升机起降风限图特征进行分析研究。结果显示,三种进场方式中,正后方进场风限图包络最大、横向进场风限图包络最小;斜向进场方式下,当进场方向、机头朝向和甲板风方向一致时,风速边界最大。建议直升机优先选择正后方进场,若采用斜向进场时,直升机进场方向、机头朝向尽量和甲板风方向保持一致。There is vortex interference in the coupled flow field between helicopter and ship, which is a complex and turbulent unsteady flow field. Shipborne helicopter will inevitably be affected on different landing paths, thereby limiting their takeoff and landing capabilities. Based on a simplified coupling model of frigate and UH-60 helicopter, combined with computational fluid dynamics and helicopter flight dynamics, the characteristics of helicopter’s candidate flight envelope under different landing paths (stern approach, oblique approach, lateral approach) are analyzed and studied. The results showed that among the three approach methods, the candidate flight envelope for stern approach was the largest, and that for lateral approach was the smallest. For the oblique approach, the maximum wind speed boundary occurs when the directions of approach, heading and wind-over-deck are consistent. It is recommended that helicopters prioritize stern approach. If using oblique approach, the direction of approach and heading should be as consistent as possible with the direction of wind-over-deck.

机库构型对舰船艉流场的影响

为改善机库导致的舰船艉流场的不稳定性,设计了3种机库构型。设计包含上层建筑与附近空气流场的整体计算域,建立CFD数值模拟计算模型,采用Fluent软件,计算新机库构型下舰船艉流场各部分下洗和侧洗速度。对计算结果进行分析,结果显示,机库边缘圆滑过渡的方案可以有效改善下洗或侧洗速度,加装导流板对流场改善效果不明显。

舰载直升机通用矩阵式系留座优化设计方法研究

为提高舰载直升机系留保障的通用性,舰船采用矩阵式系留座。针对矩阵式系留座的设计,建立了矩阵式系留座优化模型,与传统优化算法相比,该模型兼顾考虑两型舰载直升机的系留强度,采用了双目标模糊策略,使用罚函数处理索具长度约束和系留许用载荷约束,并基于粒子群算法进行寻优。通过某保障两型舰载直升机的舰船矩阵式系留座仿真算例分析,验证了模型和算法的可行性和优化效果。