基于MDO理论的船舶总体设计方法

为提高船舶总体设计质效,本文基于船舶设计、多学科设计优化(Multi-disciplinary Design and Optimization,MDO)理论及其应用的相关资料,在梳理现阶段船舶设计理论及基本流程的基础上,分析MDO理论在指导船舶设计中应用的可行性。结果表明,在船舶设计过程中应重点关注船舶型线设计、推进系统设计及振动噪声性能控制等关键技术。通过分析上述技术方面的研究进展,并基于MDO理论提出若干关于提高船舶总体设计质效的建议,对改进船舶总体设计方法具有一定工程指导价值。

船舶推进轴系方案设计的关键技术研究进展

船舶推进轴系的设计质量是其安全、稳定运行的重要保证之一。鉴于船舶推进轴系的组成部件数量及工作环境,其设计是一个复杂的系统性问题。为提高轴系设计质量,国内外船舶领域的专家学者开展了大量的研究工作,相关设计单位和船级社也制定了一系列设计规范和流程。目前,船舶推进轴系常用设计方法的缺点已日趋凸显,故亟需对现有设计方法进行全面综合的分析研究。基于船舶推进轴系的方案设计流程,重点梳理推进轴系的校中及优化、轴系振动及减振控制和轴系设计质量评价等方面的技术进展,并提出未来需要进一步展开的研究工作,旨在为船舶推进轴系的优化设计提供参考。

舰艇电力推进轴系多学科优化设计研究

以电力推进轴系为对象,进行直线校中计算,得到各轴承负荷影响系数.基于CFD数值算法,计算考虑螺旋桨水动力的轴系校中特性,并对轴系校中特性进行优化.基于直线校中和合理校中两种状态,研究轴系不同校中状态对振动特性的影响.在此基础上,以后尾轴承垂向变位为变量,研究建立轴系校中特性及振动特性的多学科优化设计模型,为轴系设计质量的提高提供参考.

Experimental investigation on the wing-wake interaction at the mid stroke in hovering flight of dragonfly

This paper focuses on flow structures of the wing-wake interaction between the hind wing and the wake of the forewing in hovering flight of a dragonfly since there are arguments whether the wing-wake interaction is useful or not.A mechanical flapping model with two tandem wings is used to study the interaction.In the device,two identical simplified model wings are mounted to the flapping model and they are both scaled up to keep the Reynolds number similar to those of dragonfly in hovering flight since our experiment is conducted in a water tank.The kinetic pattern of dragonfly(Aeschna juncea) is chosen because of its special interesting asymmetry.A multi-slice phase-locked stereo particle image velocimetry(PIV) system is used to record flow structures around the hind wing at the mid downstroke(t/T=0.25) and the mid upstroke(t/T=0.75).To make comparison of the flow field between with and without the influence of the wake,flow structures around a single flapping wing(hind wing without the existence of the forewing) at these two stroke phases are also recorded.A local vortex identification scheme called swirling strength is applied to determine the vortices around the wing and they are visualized with the iso-surface of swirling strength.This paper also presents contour lines of z at each spanwise position of the hind wing,the vortex core position of the leading edge vortex(LEV) of hind wing with respect to the upper surface of hind wing,the circulation of the hind wing LEV at each spanwise position and so on.Experimental results show that dimension and strength of the hind wing LEV are impaired at the mid stroke in comparison with the single wing LEV because of the downwash from the forewing.Our results also reveal that a wake vortex from the forewing traverses the upper surface of the hind wing at the mid downstroke and its distance to the upper surface is about 40% of the wing chord length.At the instant,the distance of the hind wing LEV to the upper surface is about 20% of the wing chord length.Thus,there must be a wing-wake interaction mechanism that makes the wake vortex become an additional LEV of the hind wing and it can partly compensate the hind wing for its lift loss caused by the downwash from the forewing.