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| 1 | 几何大变形太阳能无人机非线性气动弹性稳定性研究显示文摘大柔性太阳能无人机在气动载荷的作用下产生较大的弯曲变形,机翼结构的刚度、质量分布等特性亦发生较大改变,线性理论无法满足这类飞机气动弹性稳定性分析的精度要求。基于Co-rotational(CR)理论,推导了结构变形后的切线刚度矩阵和质量矩阵,建立了大柔性机翼结构动力学模型;采用建立在局部气流坐标系下的片条非定常气动力模型,建立了考虑几何非线性效应的大柔性无人机气动弹性运动方程。引入准模态假设,采用P-k法研究了几何大变形对类'太阳神'布局太阳能无人机的气动弹性稳定性的影响。研究结果表明:随着弯曲变形的增加,非线性颤振速度可降低10%以上,非线性颤振频率可下降8%;合理的增加扭转刚度、前移弹性轴、前移剖面质心等,均可以有效改善几何大变形引起的不利影响。研究工作对大柔性飞机的气动弹性设计具有一定的参考意义。 | 王伟 周洲 祝小平 王睿 | 2015 | 西北工业大学学报2015，33，1： | 13 |
| 2 | Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method显示文摘A rapid and efficient method for static aeroelastic analysis of a flexible slender wing when considering the structural geometric nonlinearity has been developed in this paper. A non-planar vortex lattice method herein is used to compute the non-planar aerodynamics of flexible wings with large deformation. The finite element method is introduced for structural nonlinear statics analysis. The surface spline method is used for structure/aerodynamics coupling. The static aeroelastic characteristics of the wind tunnel model of a flexible wing are studied by the nonlinear method presented, and the nonlinear method is also evaluated by comparing the results with those obtained from two other methods and the wind tunnel test. The results indicate that the traditional linear method of static aeroelastic analysis is not applicable for cases with large deformation because it produces results that are not realistic. However, the nonlinear methodology, which involves combining the structure finite element method with the non-planar vortex lattice method, could be used to solve the aeroelastic deformation with considerable accuracy, which is in fair agreement with the test results. Moreover, the nonlinear finite element method could consider complex structures. The non-planar vortex lattice method has advantages in both the computational accuracy and efficiency. Consequently, the nonlinear method presented is suitable for the rapid and efficient analysis requirements of engineering practice. It could be used in the preliminary stage and also in the detailed stage of aircraft design. | Xie Changchuan Wang Libo Yang Chao Liu Yi | 2013 | Chinese Journal of Aeronautics2013，26，3： | 13 |
| 3 | Theoretic analysis and experiment on aeroelasticity of very flexible wing显示文摘A high-altitude long-endurance aircraft with high-aspect-ratio wing usually generates large deformation,which brings the geometric nonlinear aeroelastic problems.In recent decades,it has become a key focus of the international researchers of aeroelasticity.But some critical technologies are not developed systematically,such as aerodynamic calculation methods of the curved wing with deformation,moreover,there are few experimental validations of these technologies.In this paper,we established the steady aerodynamic calculating method of the curved wing with quite large deformation based on the extended lifting line method,and calculated the unsteady aerodynamics using the strip theory considering curved surface effects.Combining the structure geometrical nonlinear finite element method,we constructed a systematic analytic approach for the static aeroelasticity and flutter of very flexible wing,and further designed the ground vibration and wind tunnel test to verify this approach.Through the test and the theoretic results comparison,we concluded that the extended lifting line method has adaptable precision for the static aeroealsticity and the strip theory considering curved surface effects for flutter analysis can give exact critical speed and flutter mode when the dynamic stall does not happen.The work in this paper shows that the geometric nonlinear aeroelastic analytic approach for very flexible wing has very high efficiency and adaptable precision.It can be used in the engineering applications,especially the iterated design in preliminary stage. | XIE ChangChuan LIU Yi YANG Chao | 2012 | Science China(Technological Sciences)2012，55，9： | 10 |
| 4 | 大变形飞机配平与飞行载荷分析方法显示文摘提出了一种可同时考虑结构几何非线性效应曲面气动力效应的大变形飞机静气动弹性配平和载荷分析方法.该方法利用三维曲面涡格法计算大变形飞机的曲面气动力,引入非线性结构有元计算方法考虑结构几何非线性效应,采用曲面样条插值方法解决气动/结构耦合问题,然后结合全机在变形构型下的刚体运动平衡方程进行柔性飞机大变形状态气动/结构耦合情况下的静气动弹性配平迭代求解.以某常规局大展弦比柔性飞机半展长缩比模型为例,应用该方法对其纵向静气动弹性配平特性及飞行荷进行详细的分析与研究,并与MSC Flightloads线性方法的计算结果进行了对比.分析结果表明结构变形较小时,本文非线性方法和线性方法的计算结果吻合较好.而当结构具有较大变形时,由于线性方法无法考虑气动力曲面效应和结构几何非线性效应故不再适用,而本文出的非线性方法可对大柔性飞机在大变形构型下的配平特性作出较为准确合理的预测,并可满足飞机设计各个阶段的工程应用需求,完成考虑结构几何非线性静气动弹性配平特性的多轮次快速分析. | 杨超 王立波 谢长川 刘燚 | 2012 | 中国科学:技术科学2012，42，10： | 10 |
| 5 | 大展弦比机翼气动弹性的几何非线性效应显示文摘随着飞行器性能和需求的提高,大展弦比机翼逐渐成为新型飞行器的主要结构形式。这类机翼具有高升阻比、大变形、重量轻等特性,几何非线性效应明显。该文采用本征梁结构模型和有限状态入流气动模型,对典型大展弦比机翼的几何非线性效应开展结构的静、动态特性和气动弹性研究。分析结果发现:考虑几何非线性效应后,机翼的变形减小;颤振临界速度降低,并且与攻角相关;机翼的时域响应则表现为衰减振动、单频极限环和多频极限环振荡,不出现振动发散状态;与传统的线性气动弹性现象显著不同。该文的方法能够有效预示大展弦比机翼的气动弹性现象。 | 付志超 陈占军 刘子强 | 2017 | 工程力学2017，34，4： | 10 |
| 6 | Gust response analysis and wind tunnel test for a high-aspect ratio wing显示文摘A theoretical nonlinear aeroelastic response analysis for a flexible high-aspect ratio wing excited by harmonic gust load is presented along with a companion wind tunnel test. A multidisciplinary coupled numerical calculation is developed to simulate the flexible model wing undergoing gust load in the time domain via discrete nonlinear finite element structural dynamic analysis and nonplanar unsteady vortex lattice aerodynamic computation. A dynamic perturbation analysis about a nonlinear static equilibrium is also used to determine the small perturbation flutter boundary. A novel noncontact 3-D camera measurement analysis system is firstly used in the wind tunnel test to obtain the spatial large deformation and responses. The responses of the flexible wing under different static equilibrium states and frequency gust loads are discussed. The fair to good quantitative agreements between the theoretical and experimental results demonstrate that the presented analysis method is an acceptable way to predict the geometrically nonlinear gust response for flexible wings. | Liu Yi Xie Changchuan Yang Chao Cheng Jialin | 2016 | Chinese Journal of Aeronautics2016，29，1： | 10 |
| 7 | Aeroelastic trim and flight loads analysis of flexible aircraft with large deformations显示文摘A method for static aeroelastic trim analysis and flight loads computation of a flexible aircraft with large deformations has been presented in this paper,which considers the geometric nonlinearity of the structure and the nonplanar effects of aerodynamics.A nonplanar vortex lattice method is used to compute the nonplanar aerodynamics.The nonlinear finite element method is introduced to consider the structural geometric nonlinearity.Moreover,the surface spline method is used for structure/aerodynamics coupling.Finally,by combining the equilibrium equations of rigid motions of the deformed aircraft,the nonlinear trim problem of the flexible aircraft is solved by iterative method.For instance,the longitudinal trim analysis of a flexible aircraft with large-aspect-ratio wings is carried out by both the nonlinear method presented and the linear method of MSC Flightloads.Results obtained by these two methods are compared,and it is indicated that the results agree with each other when the deformation is small.However,because the linear method of static aeroelastic analysis does not consider the nonplanar aerodynamic effects or structural geometric nonlinearity,it is not applicable as the deformations increase.Whereas the nonlinear method presented could solve the trim problem accurately,even the deformations are large,which makes the nonlinear method suitable for rapid and efficient analysis in engineering practice.It could be used not only in the preliminary stage but also in the detail stage of aircraft design. | YANG Chao WANG LiBo XIE ChangChuan LIU Yi | 2012 | Science China(Technological Sciences)2012，55，10： | 10 |
| 8 | 柔性飞机大变形曲面气动力计算及配平分析显示文摘柔性飞机在载荷作用下产生较大的弹性变形并呈现出几何非线性特性,机翼升力面呈现出大变形空间曲面的特征,传统平面气动力的工程分析方法无法给出空间变形下的真实载荷状态进而影响柔性飞机气动弹性分析的准确性。该文基于柔性飞机几何非线性气动弹性分析的需求,建立了曲面三维升力线和曲面涡格两种不同的曲面定常气动力方法,并结合曲面样条插值完成了大变形下结构运动信息与气动载荷信息之间的相互作用和交换,实现气动面随结构变形的自适应更新。进行了柔性飞机的全机非线性配平分析,并对两种不同的气动力方法的分析结果进行对比,归纳出柔性飞机几何非线性气动弹性配平分析的特点。升力线方法分析快速简单,涡格法可以考虑机翼弯度影响,便于复杂模型的多轮次反复计算。两种方法的分析结果具有较好的一致性,当飞机变形较小时都与传统的线性分析方法吻合较好;当结构变形较大时,非线性配平结果随风速和结构质量呈非线性变化,与传统线性分析结果产生明显差别需在设计初期引起重视。 | 刘燚 谢长川 王立波 胡锐 杨超 | 2015 | 工程力学2015，32，10： | 9 |
| 9 | 大展弦比大柔性机翼载荷分布求解的一种方法显示文摘大展弦比大柔性机翼在气动力作用下产生较大的弯曲和扭转变形,会引起明显的气动载荷重新分布。基于一种只具有2个广义转角自由度的梁单元模型,提出了一种大展弦比大柔性机翼载荷重新分布的新方法。该方法将大柔性机翼弯曲变形的几何非线性问题转化为线性问题,同时,基于弯曲变形结果,可在局部坐标系下进行机翼扭转变形求解,避免了整体坐标系下扭转变形的几何非线性问题。综合来看,该方法可将具有明显几何非线性效应的大展弦比大柔性机翼的载荷重新分布问题转化为线性问题,且计算量小,效率高,非常适合工程实用。通过与大柔性悬臂梁解析解的对比,验证了本文方法的正确性和有效性。 | 段静波 周洲 王伟 江涛 王睿 | 2016 | 航空学报2016，37，3： | 8 |
| 10 | 基于曲面涡格法的柔性飞机静气动弹性分析显示文摘该文采用曲面涡格法对柔性飞机进行曲面气动力建模,并进一步考察了可压缩情况下曲面涡格法载荷的计算精度,满足了柔性飞机曲面气动载荷计算的需求。在气动载荷计算的基础上结合结构几何非线性分析与插值计算,完成了柔性飞机几何非线性静气动弹性分析。分析结果表明,曲面涡格法在可压缩情况下载荷计算精度较好且气动力曲面建模优势明显,可用于工程复杂模型的曲面气动力计算。与传统线性静气动弹性计算相比,考虑结构几何非线性及气动力曲面效应的非线性静气动弹性分析更符合真实物理情景,载荷计算更为准确,结构变形结果更为可靠。 | 刘燚 杨澜 谢长川 | 2018 | 工程力学2018，35，2： | 8 |
| 11 | 大展弦比柔性机翼气动弹性风洞模型设计与试验验证显示文摘大展弦比柔性机翼飞机的气动弹性是当前理论研究的热点,而风洞试验研究则是揭示大变形气动弹性运动机理和验证理论方法的必要手段。该文建立了能够考虑几何非线性特点的大展弦比柔性机翼风洞试验模型结构设计方案。该方案设计结合几何非线性气动弹性理论分析与模型地面试验,在确保分析模型与理论模型一致的基础上,进行了实物模型的气动弹性风洞试验。风洞试验结果表明大展弦比柔性机翼的结构大变形效应对其气动弹性特性产生了一定影响,大变形导致结构水平弯曲模态发生失稳进而降低了模型的颤振速度,与几何非线性气动弹性分析结果一致。试验颤振速度、颤振模态均与理论分析结果吻合,验证了该文几何非线性气动弹性分析方法的准确性。 | 谢长川 胡锐 王斐 刘燚 常楠 | 2016 | 工程力学2016，33，11： | 8 |
| 12 | 一种基于光固化快速成型的飞机静弹性风洞试验模型设计方法显示文摘高速风洞静弹性模型设计和制造是静弹性风洞试验的一个关键。为解决模型设计周期长、制造费用高等问题,提出了一种基于立体光固化快速成型面向高速风洞大展弦比机翼静弹性模型研制方法。基于机翼刚度分布相似参数,采用机翼钢梁骨架和树脂蒙皮组合结构,通过优化结构尺寸完成静弹性模型结构设计;使用机械加工和快速成型技术完成模型制造,并通过地面刚度试验对加工模型进行了刚度分布验证。风洞试验结果表明:基于立体光固化成型技术设计和制造的静弹性风洞试验模型工程实用、可行,与传统静弹性模型研制过程相比,具有研制周期短、成本低而且不存在因填充物带来附加刚度的显著优势。 | 王超 张征宇 殷国富 孙岩 朱伟军 | 2014 | 航空学报2014，35，5： | 6 |
| 13 | 飞翼式柔性飞机纵向动力学建模与稳定性分析显示文摘柔性飞行器在飞行过程中容易发生大变形,这种变形将导致机翼甚至整个飞行器的气动弹性和飞行动力学特性发生变化,特别是对稳定性的影响.本文采用三段式刚体假设,以变上反角的方式来描述机翼的展向弯曲变形,对一类飞翼式柔性飞行器进行了纵向动力学建模,并进一步分析了操纵面、推力和迎角与上反角的关系,以及变上反角对飞行稳定性的影响.结果表明,在保持速度和高度不变的情况下,稳定性受上反角的影响比较明显,如果变形过大,飞行器将变为动不稳定,且短周期模态不能保持.因此,为了保持飞机的纵向稳定性,必须要控制飞机的变形. | 沈华勋 徐亮 陆宇平 何真 | 2016 | 动力学与控制学报2016，14，3： | 6 |
| 14 | 大型水平轴风力机叶片气动弹性计算显示文摘给出了一种考虑几何非线性的大型风力机静、动气动弹性一体化计算方法.采用涡尾迹方法进行风力机气动载荷计算.建立风力机风轮的三维壳模型.沿周向平均风力机叶片载荷并加载到结构模型进行非线性静气动弹性分析.基于动力学小扰动假设,在静平衡构型下进行动力学线性化,计算风轮固有振动特性.继而结合非定常涡尾迹方法计算风力机动气动弹性响应.计算了NH1500叶片考虑几何非线性的静气动弹性位移和动气动弹性响应.结果表明,大型风力机叶片几何非线性较为明显地减小静气动弹性位移,同时降低动气动弹性的响应幅值.大型风力机气动弹性响应计算需要考虑几何非线性. | 唐迪 陆志良 郭同庆 | 2013 | 应用数学和力学2013，34，10： | 5 |
| 15 | 考虑大变形的大展弦比机翼气动弹性优化设计显示文摘针对大展弦比机翼飞机自身特点,在结构大变形情况下,将弹性力学几何非线性理论引入到大柔性飞行器的气动弹性力学分析中,建立完整的几何非线性气动弹性分析方法框架。该方法主要包含两方面:结构非线性刚度和曲面气动力的计算。结合优化设计,为了提高优化设计效率,针对迭代过程进行有效简化。基于ISIGHT优化平台,发展一种适用于初步设计阶段大展弦比机翼在大变形情况下的气动弹性优化设计方法,有效地避免了结构大变形情况下线性气动弹性分析造成的设计偏差。为了摆脱对初始设计点的依赖,结合局部算法,采用组合优化策略,开展了大展弦比机翼的几何非线性气动弹性优化设计,首先应用蚁群算法定位目标极值在设计空间中所处的区域,再应用直接搜索算法对该区域精确寻优,获得更加准确的设计结果。 | 王斐 李秋彦 谢长川 孟杨 | 2017 | 四川理工学院学报(自然科学版)2017，30，2： | 4 |
| 16 | 一种基于CR理论的大柔性机翼非线性气动弹性求解方法显示文摘大展弦比大柔性机翼在气动载荷的作用下,产生较大的弹性变形,其惯性特性、刚度特性、动气动弹性特性等亦发生较大改变,常规的线性气动弹性分析方法不再适用。基于Co-rotational(CR)理论,推导了机翼变形后的切线刚度矩阵和质量矩阵,建立了考虑几何非线性效应的大柔性机翼结构动力学模型;耦合改进的ONERA非线性非定常气动力模型,提出了一种适用于大柔性机翼的非线性气动弹性求解方法。采用Newmark直接数值积分法及松耦合技术在时域内对气动弹性运动方程进行求解,对所提出的非线性气动弹性求解方法的正确性和精度进行了验证,并研究了大柔性机翼的极限环颤振特性。研究表明:适用于大柔性机翼完整的非线性气动弹性建模需要考虑机翼结构大变形和非定常气动力动态失速等非线性因素;弯曲变形可降低临界极限环颤振速度的15%以上,而前移弹性轴能够有效的提高临界极限环颤振速度;所提出的非线性气动弹性求解方法具有较好的精度和效率,满足大柔性机翼非线性气动弹性的求解需求。 | 王伟 周洲 祝小平 王睿 | 2015 | 振动与冲击2015，34，19： | 3 |
| 17 | Experimental investigation on the wing-wake interaction at the mid stroke in hovering flight of dragonfly显示文摘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. | LAI GuoJun SHEN GongXin | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，11： | 2 |
| 18 | 大展弦比气弹机翼柔性非线性变形的气动力效应分析与风洞试验显示文摘从飞行器刚弹耦合动力学模型出发,引入柔性机翼准定常假设,建立大柔性飞行器非线性静气动弹性气动力方程,利用非线性迭代求解思路模拟了柔性飞行器的静气动弹性响应行为,开展了大展弦比飞机静气动弹性风洞试验验证,采用气动力有限基本解与机翼的耦合计算,发现了大柔性飞机大变形状态下载荷及结构变形形式随风速的变化规律.传统基于小变形假设的线性分析方法和刚体分析由于无法考虑气动面随结构变形的曲面气动力因素和结构变形后的非线性刚度特性,均与风洞试验存在一定的误差.对于大展弦比柔性飞机的非线性静气动弹性分析十分必要. | 刘燚 许云涛 吕计男 | 2020 | 气体物理2020，5，6： | 1 |
| 19 | 低音速气动弹性机翼的主动控制显示文摘基于模糊滑模控制(FSMC)方法研究了低音速机翼颤振的主动控制。提出一种模糊滑模控制方法,主要解决非线性气动弹性的浮沉和俯仰二维机翼的颤振问题。根据气动弹性机翼,设计了滑模面,建立了模糊滑模控制器,控制器能有效抑制颤振。与自适应控制技术相比较,结果显示模糊滑模控制收敛性更好。 | 仇磊 | 2015 | 电子设计工程2015，23，16： | 1 |
| 20 | 弹性载荷设计中插值方法的研究显示文摘通过对考虑静气动弹性影响的载荷设计中多种插值方法的研究与比较,对适用于三维情况下的气动和结构模型之间耦合计算时的载荷传递和位移插值方法进行原理分析和优劣比较,最终确定了曲面样条函数和形函数面积坐标加权两种数据传递方法,分别对其进行了公式推导与编程实现,并利用已有的算例模型计算得出的各项气动力数据调用程序进行插值计算,最后将插值前后的结果进行对比来验证程序的合理性。 | 刘晓晨 | 2020 | 民用飞机设计与研究2020，，4： | 1 |
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