共查询到16条相似文献,搜索用时 140 毫秒
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结构非线性颤振分析的KBM法及实验对比 总被引:3,自引:0,他引:3
本文讨论由初偏间隙型弹簧连接的三角翼带外挂系统的极限环颤振。分别用基于KBM法一次渐近解、二次渐近解的等效线化方法对初偏间隙型非线性作等效线化处理,并将颤振分析结果与模型风洞实验结果作对比。结果表明,无论是对于单稳定极限环颤振或是双稳定极限环颤振,基于KBM法二次渐近解的等效线化分析都比描述函数法具有更高的精度。对于初偏间隙型非线性,当极限环幅值不大时,高次谐波项对系统的响应影响较大。 相似文献
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具有操纵面立方非线性机翼的混沌响应 总被引:1,自引:0,他引:1
以二元机翼-操纵面立方非线性系统为研究对象,基于能量方法和活塞理论建立了三自由度二维翼段-操纵面的运动微分方程,采用当量线性化方法计算出系统极限环颤振频率,然后将操纵面孤立成单自由度系统,借用现有的单自由度杜芬振子的混沌运动的解析条件来分析操纵面在极限环颤振频率下的响应情况,从而预估原系统的混沌运动存在区域,并用数值积分方法研究了系统的复杂动力学响应。结果表明:在理论分析所获得的混沌运动区域内,系统确实存在混沌运动,但从数值模拟的结果上看,在上述的区域内,系统还存在一些狭窄的周期窗口。 相似文献
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以南京长江第四大桥流线型箱梁断面为研究对象,基于节段模型自由振动风洞试验,详细测试了断面在不同攻角下的颤振性能。探讨了断面运动形态非线性特征随风速和攻角的演化规律,及非线性特征演化的动力学机理。研究表明,负攻角下,动力系统多非稳态极限环随风速增大逐渐减小的特征使得系统响应依赖于初始振幅,并导致了颤振性能随初始激励增大急剧减弱的现象;正攻角下,多稳态极限环随风速增大而增大的特征使得系统颤振响应表征为典型的软颤振;高风速下,极限环的消失使得系统响应表征为硬颤振,且不依赖于初始振幅;最后,从模态阻尼随振幅的演化规律,解释了系统颤振形态在各攻角下异同的动力学机理。 相似文献
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偏航 侧摆联接刚度对带外挂三角机翼颤振特性的影响 总被引:2,自引:0,他引:2
本文对一带外挂三角翼模型进行了颤振理论计算和风洞实验。分析了机翼/外挂系统偏航及侧摆联接刚度对颤振特性的影响,并在低速风洞中进行了模型吹风实验。实验结果与理论计算相吻合,根据研究结果,得出了一些有参考价值的结论。 相似文献
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带外挂后掠机翼极限环颤振的分析与实验研究 总被引:2,自引:0,他引:2
从理论及实验两方面,研究了带外挂后掠机翼的极限环颤振分叉现象,得到了稳定、半稳定及不稳定极限环。理论分析采用谐波平衡法,并通过在时域拟合非定常空气动力后,用数值积分法对所得结果进行了比较。风洞实验结果验证了理论分析结果的正确性。 相似文献
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本文利用等效线化及数值计算方法,研究了带初偏间隙型非线性俯仰刚度的二元颤振系统的双稳态极限环颤振特性,给出了极限环稳定区间的稳定性判据.分别分析了初偏参数及速度参数对非线性颤振系统分叉曲线的影响及系统的分叉特性,并用数值计算方法得到精确的分叉参数值.本文为动力学系统的分叉研究提供了一个有实际意义的力学模型. 相似文献
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采用CFD/CSD耦合方法,建立了气动弹性仿真系统。基于系统辨识的方法,使用Volterra级数建立了降阶模型(ROM),实现了颤振边界的快速求解,分别使用CFD/CSD全耦合方法与ROM完成了AGARD 445.6标模的颤振分析,计算结果与实验相符较好。使用ROM完成了带边条平直翼的颤振分析。使用CFD/CSD耦合方法计算了此机翼在飞行动压下的气弹响应,结果表明即使在颤振边界内,仍然有可能出现极限环振荡(LCO)。对此,分析了其气弹响应中的动载情况。结果表明基于CFD/CSD耦合的方法可以真实地仿真气弹响应过程,准确地分析气弹响应中的动态载荷情况 相似文献
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飞行器大攻角飞行过程中的动态失速会导致结构自激扭转或俯仰运动,造成非线性失速颤振现象,直接影响飞行器飞行安全与结构安全。该文对标准Leishman-Beddoes (L-B)非线性非定常气动力模型进行马赫数修正,使其适用于低速不可压情形的动态失速气动力计算,然后基于二元翼段气动弹性模型,采用Newmark时域推进方法进行工程失速颤振计算。依据计算结果设计并完成了二元翼段失速颤振风洞试验。试验结果表明,多数试验状态,基于L-B模型的失速颤振计算结果与试验结果均吻合较好。结果验证了修正的L-B模型可以用来进行低速大展弦比平直翼段翼型的失速颤振工程分析与极限环振荡评估,同时,失速颤振速度与极限环幅值受初始攻角的影响很大。 相似文献
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The non-linear flutter and thermal buckling of an FGM panel under the combined effect of elevated temperature conditions and
aerodynamic loading is investigated using a finite element model based on the thin plate theory and von Karman strain-displacement
relations to account for moderately large deflection. The aerodynamic pressure is modeled using the quasi-steady first order
piston theory. The governing non-linear equations are obtained using the principal of virtual work adopting an approach based
on the thermal strain being a cumulative physical quantity to account for temperature dependent material properties. This
system of non-linear equations is solved by Newton–Raphson numerical technique. It is found that the temperature increase
has an adverse effect on the FGM panel flutter characteristics through decreasing the critical dynamic pressure. Decreasing
the volume fraction enhances flutter characteristics but this is limited by structural integrity aspect. The presence of aerodynamic
flow results in postponing the buckling temperature and in suppressing the post buckling deflection while the temperature
increase gives way for higher limit cycle amplitude. 相似文献
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The phenomenon of aerodynamic instability caused by wind is usually a major design criterion for long-span cable-supported bridges. If the wind speed exceeds the critical flutter speed of the bridge, this constitutes an Ultimate Limit State. The prediction of the flutter boundary therefore requires accurate and robust models. The state-of-the-art theory concerning determination of the flutter stability limit is presented. Usually bridge decks are bluff and therefore the aeroelastic forces under wind action have to be experimentally evaluated in wind tunnels or numerically computed through Computational Fluid Dynamics (CFD) simulations. The self-excited forces are modelled using aerodynamic derivatives obtained through CFD forced vibration simulations on a section model. The two-degree-of-freedom flutter limit is computed by solving the Eigenvalue problem.A probabilistic flutter analysis utilizing a meta-modelling technique is used to evaluate the effect of parameter uncertainty. A bridge section is numerically modelled in the CFD simulations. Here flutter derivatives are considered as random variables. A methodology for carrying out sensitivity analysis of the flutter phenomenon is developed. The sensitivity with respect to the uncertainty of flutter derivatives and structural parameters is considered by taking into account the probability distribution of the flutter limit. A significant influence on the flutter limit is found by including uncertainties of the flutter derivatives due to different interpretations of scatter in the CFD simulations. The results indicate that the proposed probabilistic flutter analysis provides extended information concerning the accuracy in the prediction of flutter limits.The final aim is to set up a method to estimate the flutter limit with probabilistic input parameters. Such a tool could be useful for bridge engineers at early design stages. This study shows the difficulties in this regard which have to be overcome but also highlights some interesting and promising results. 相似文献
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传统的气动弹性系统颤振分析模型大多是在确定性参数条件下建立的,当系统中存在不确定因素时,按确定性方法设计的气动弹性系统存在颤振失效风险.以概率和非概率区间模型为基础,建立了单源不确定性条件下颤振可靠性分析模型;在此基础上,针对含随机和区间多源不确定参数的气动弹性系统颤振可靠性分析问题,提出一种基于分步求解策略的新型混合... 相似文献
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K. WILLCOX J. PERAIRE 《International journal for numerical methods in engineering》1997,40(13):2413-2431
A strategy for computing aeroelastic solutions is proposed. An implicit LU factorization scheme for solving the time-dependent Euler equations on unstructured triangular meshes is presented and coupled with a typical section aeroelastic wing model. Efficiency is improved by coupling the LU factorization scheme with a GMRES algorithm. In this case the LU scheme plays the role of a preconditioner. The fluid and structural models are simultaneously integrated in time in a fully coupled manner. The response of a structural section in different flow regimes is determined and flutter boundaries are computed. In the transonic regime and beyond the region of linear stability, the section is found to exhibit limit cycle behaviour. © 1997 by John Wiley & Sons, Ltd. 相似文献