Temperature effect on buckling properties of ultra-thin-walled lenticular collapsible composite tube subjected to axial compression

This paper seeks to outline the temperature effect on the buckling properties of ultra-thin-walled lenticular collapsible composite tube(LCCT) subjected to axial compression.The buckling tests of the LCCT specimens subjected to axial compression were carried out on INSTRON-500 N servo-hydraulic machine in dry state and at the temperatures of 25 C, 100 C and 80 C. The load–displacement curves and buckling initiation loads were measured and the buckling initiation mechanism was discussed from experimental observations. Experiments show that the buckling initiation load, on average, is only about 2.2% greater at the low temperature of 80 C than at the room temperature of 25 C due to the material hardening, demonstrating an insignificant increase in the buckling initiation load, whereas it is about 19.5% lower at the high temperature of 100 C than at the room temperature owing to the material softening, implying a significant decrease in the buckling initiation load. The failure mode of the LCCT in axial compression tests at three different temperatures can be reckoned to be characteristic of the buckling initiation and propagation around the central region until rupture. The finite element(FE) model is presented to simulate the buckling initiation mechanism based on the eigenvalue-based methodology. Good correlation between experimental and numerical results is achieved.     

STRAIN REGULARITY IN REINFORCERS OF SHORT-FIBER/ WHISKER REINFORCED COMPOSITE AND ITS APPLICATION

Based on the study of strain distribution in short-fiber/whisker reinforced metal matrix composites, a deformation characteristic parameter λ is defined as the ratio of the root-mean-square strain of reinforcers to the macro-linear strain along the same direction. Quantitative relation between λ and microstructure parameters of the composite is obtained. As an example of applying and verifying λ, the stress-strain curve of [AlBO]w/Al composite under tensile loading is predicted and favorably compared with experiments. By using λ, the stiffness modulus of the composite with arbitrary reinforcer orientation under any loading condition is predicted from the microstructure parameters of material.     

A novel in-plane mode rotary ultrasonic motor

Ultrasonic motors have the merits of high ratio of torque to volume, high positioning precision, intrinsic holding torque, etc., compared to the conventional electromagnetic motors. There have been several potential applications for this type of motor in aerospace exploration, but bearings and bonding mechanism of the piezoelectric ring in the motors limit the performance of them in the space operation conditions. It is known that the Langevin type transducer has excel- lent energy efficiency and reliability. Hence using the Langevin type transducer in ultrasonic motors may improve the reliability of piezoelectric motors for space applications. In this study, a novel in-plane mode rotary ultrasonic motor is designed, fabricated, and characterized. The proposed motor operates in in-plane vibration mode which is excited by four Langevin-type bending vibra- tors separately placed around a ring-shaped stator. Two tapered rotors are assembled to the inner ring of the stator and clamped together by a screw nut. In order to make the motor more stable and convenient to fix, a thin cylindrical support is placed under the stator ring. Due to its no-bearing structure and Langevin transducer excitation, the prototype ultrasonic motor may operate well in aeronautic and astronautic environments.     

Damage characteristics and constitutive modeling of the 2D C/Si C composite: Part I – Experiment and analysis

This paper reports an experimental investigation on the macroscopic mechanical behaviors and damage mechanisms of the plain-woven(2D) C/Si C composite under in-plane on- and offaxis loading conditions. Specimens with 15, 30, and 45 off-axis angles were prepared and tested under monotonic and incremental cyclic tension and compression loads. The obtained results were compared with those of uniaxial tension, compression, and shear specimens. The relationships between the damage modes and the stress state were analyzed based on scanning electronic microscopy(SEM) observations and acoustic emission(AE) data. The test results reveal the remarkable axial anisotropy and unilateral behavior of the material. The off-axis tension test results show that the material is fiber-dominant and the evolution rate of damage and inelastic strain is accelerated under the corresponding combined biaxial tension and shear loads. Due to the damage impediment effect of compression stress, compression specimens show higher mechanical properties and lower damage evolution rates than tension specimens with the same off-axis angle. Under cyclic tension–compression loadings, both on-axis and off-axis specimens exhibit progressive damage deactivation behaviors in the compression range, but with different deactivation rates.     

涡量场测量

 <正> The space .distributions of vorticity were measured by using a vorticimctcr (vorti-city probe) in the field induced by a vortex shedding from the wing-tip of a rectangular wing under different angles of attack. The results show that the vorticimetcr having the advantages of high sensitivity, simpler calibration process and easiness to use, is capable of measuring the vorticity directly, and finding out the center trace of the vortex core exactly. Through the measurements, a counter rotating vortex with a center strength of 1/17 to that of the main wing-tip vortex existing nearby is discovered. The center vorticity would decay substantially as the main wing-tip vertex moves down-stream. For instance, the peak vorticity at x = 2.5c (c, the chord length) will decay to about 25% of that at x = 0.1c, while its scale remains almost unchanged. At the cross-section x = 0.1c, the scale of the wing-tip vortex was about 0.2c spanwisc and-0.18c along the longtudinal direction. Finally, the strengths of a pair of in     

Design and Coupled Thermo-Mechanical Analysis of Silicon Carbide Primary Mirror Assembly

Based on the principle that the thermal expansion coefficient of the support structure should match that of the mirror, three schemes of primary mirror assembly were designed. Of them, the first is fused silica mirror plus 4J32 flexible support plus ZTC4 sup-port back plate, the second K9 mirror plus 4J45 flexible support plus ZTC4 support back plate, and the third SiC mirror plus SiC rigid support back plate. A coupled thermo-mechanical analysis of the three primary mirror assemblies was made with finite element method. The results show that the SiC assembly is the best of all schemes in terms of their combination properties due to its elimination of the thermal expansion mismatch between the materials. The analytical results on the cryogenic property of the SiC primary mirror assembly show a higher surface finish of the SiC mirror even under the cryogenic condition.     

An iterative approach for modal analysis of solid rocket motor incorporating frequency dependent modulus

The modulus of viscoelastic materials varies with excitation frequency.However,during modal analysis of frequency dependent materials,a material evaluation frequency is necessary because stiffness cannot be modified during eigenfrequency procedure.As a result,only those vibration modes are accurate,of which eigenfrequency is close to the material evaluation frequency.In order to obtain vibration modes of solid rocket motor (SRM) using material modulus based on frequency which is the same as the eigenfrequency,an iterative approach was proposed.Results of the iterative technique show that frequency modes obtained from the method are in complete agreement with the eigenfrequency and material evaluation frequency.      

Investigation on Thermal Contact Conductance Based on Data Analysis Method of Reliability

The method of reliability is proposed for the investigation of thermal contact conductance (TCC) in this study. A new definition is introduced, namely reliability thermal contact conductance (RTCC), which is defined as the TCC value that meets the reliability design requirement of the structural materials under consideration. An experimental apparatus with the compensation heater to test the TCC is introduced here. A practical engineering example is utilized to demonstrate the applicability of the proposed approach. By using a statistical regression model along with experimental data obtained from the interfaces of the structural materials GH4169 and K417 used in aero-engine, the estimate values and the confidence level of TCC and RTCC values are studied and compared. The results show that the testing values of TCC increase with interface pressure and the proposed RTCC model matches the test results better at high interface pressure.     

Atomization mechanism of a charged viscoelastic liquid sheet

In order to study atomization mechanism of a viscoelastic liquid sheet in an electric field,the spatial–temporal stability analysis of a viscoelastic liquid sheet injected into a dielectric stationary ambient gas in the presence of a vertical electric field is conducted. The dispersion relations of both sinuous and varicose disturbance modes are solved to explore the spatial–temporal instability of a charged viscoelastic sheet, by setting both the wave number and frequency complex. A parametric study is performed to test the influence of the dimensionless parameters on the absolute instability of the sheet. The results show that the increase of liquid Weber number and time constant ratio, or decrease of gas to liquid density ratio and Reynolds number, can damp the absolute instability. The effect of the liquid elasticity depends on the value of time constant ratio: when time constant ratio is small, the increase of liquid elasticity could amplify absolute growth rate, but the effect is weak when the elasticity number is relatively large; when time constant ratio is large, the increase of liquid elasticity cannot affect the absolute growth rate. Moreover, the variation of electrical Euler number can hardly influence the absolute instability of a charged viscoelastic sheet.     

Investigation of the steam-cooled blade in a steam turbine cascade

With the increasing demand for electricity,an efficiency improvement and thereby reduced CO2 emissions of the coal-fired plants are expected in order to reach the goals set in the Kyoto protocol.It can be achieved by a rise of the process parameters.Currently,live steam pressures and temperatures up to 300 bars and 923 K are planned as the next step.Closed circuit steam cooling of blades and vanes in modern steam turbines is a promising technology in order to establish elevated live steam temperatures in future steam turbine cycles.In this paper,a steam-cooled test vane in a cascade with external hot steam flow is analyzed numerically with the in-house code CHTflow.A parametric analysis aiming to improve the cooling effectiveness is carried out by varying the cooling mass flow ratio.The results from two investigated cases show that the steam cooling technique has a good application potential in the steam turbine.The internal part of the vane is cooled homogeneously in both cases.With the increased cooling mass flow rate,there is a significant improvement of cooling efficiency at the leading edge.The results show that the increased cooling mass flow ratio can enhance the cooling effectiveness at the leading edge.With respect to trailing edge,there is no observable improvement of cooling effectiveness with the increased cooling mass flow.This implies that due to the limited dimension at the trailing edge,the thermal stress cannot be decreased by increasing the cooling mass flow rate.Therefore,impingement-cooling configuration at the trailing edge might be a solution to overcome the critical thermal stress there.It is also observed that the performance of the cooling effective differs on pressure side and suction side.It implicates that the equilibrium of the cooling effectiveness on two sides are influenced by a coupled relationship between cooling mass flow ratio and hole geometry.In future work,optimizing the hole geometry and cooling steam supply conditions might be the solutions for an equivalent cooling effectiveness along whole profile.      

受面内非均匀分布载荷的矩形板屈曲分析

薄板线性稳定性分析进行了很多年,发展得较为完善并且有手册可方便查阅。受非均匀面内分布载荷的板因为解析解不易求出,在分析中一般假设应力与边缘处的作用力分布规律相同。实际上此时板内的应力分布却与边缘处的不一样,而且还会产生另外两个应力分量,其影响取决于边界条件。采用有限元法分析非均匀载荷作用时薄板的稳定性问题,给出多种边界条件下的板的屈曲载荷,还给出了相应的基于受均匀载荷薄板屈曲载荷的当量因子。同时发现《飞机设计手册》中薄板受某线性载荷作用时的临界载荷因子不够精确。研究结果为承受非均匀面内分布载荷的板结构设计提供参考依据。     

受压正交异性矩形分层的屈曲和后屈曲

 一、引言 为了给飞行器的设计提供理论依据,采用力法分析了不同材料的受压固支、简支正交异性矩形分层模型的屈曲和后屈曲,把一组非线性偏微分方程构成的边值问题化为求解一组非线性代数方程,进而用梯度法解之,最后给出有关的计算结果,并说明了支承条件的影响。     

单/双轴预拉载荷对碳纤维复合材料高速冲击性能的影响研究

针对发动机工作时受预载荷的叶片受到外物冲击的情况,设计一种面内单轴及双轴预加载装置,开展单轴与双轴不同大小预拉载荷下碳纤维/环氧树脂复合材料（T700/TDE-86）的高速冲击试验,探究预拉载荷对复合材料抗冲击性能的影响,并结合超声C扫描分析预拉载荷对损伤面积的影响。结果表明：面内初始载荷对复合材料层合板抗冲击性能和分层损伤面积有显著影响;预拉载荷会提高靶板的抗弯刚度,减少靶板吸收的能量,减小弹道极限,且在双轴预拉情况下更明显;弹体击穿靶板后分层损伤面积几乎不变,而预拉载荷会减小分层损伤面积,且在双轴预拉情况下更明显。     

复合材料板拉/压-剪复合载荷屈曲相关方程

利用轴向拉伸/压缩和面内剪切载荷构建了一个相互作用函数,并将其通过幂级数展开成二次多项式,利用单轴试验测试的复合材料板屈曲载荷,基于数学原理和合理的假设,推导确定了多项式的各项待定系数,构建了轴向拉伸/压缩和剪切复合载荷下的复合材料板屈曲相关方程,从数学上理性地解决了传统屈曲相关方程不适用于复合材料板（尤其是非均衡铺层板）的问题。利用提出的相关方程预测了4种不同的非均衡铺层复合材料板在轴向拉伸/压缩和剪切载荷作用下的屈曲相关曲线,并与有限元特征值法的模拟结果进行了对比,两者具有很好的一致性,而对于传统相关方程,其铺层的非均衡性越大则预测误差越大。最后通过均衡铺层的复合材料加筋壁板的压剪复合试验进一步证明了提出的相关方程的有效性。     

三维矩形板1/4椭圆角裂纹的通用权函数

对三维矩形板1/4椭圆角裂纹的通用权函数进行了研究.基于有限元方法计算了裂纹面承受沿宽度方向的均布、线性分布和2次分布应力时的参考应力强度因子解,建立了形式较为统一、较高精度以及适用范围相对更宽的参考应力强度因子近似表达式.在此基础上获得了三维矩形板1/4椭圆角裂纹的通用权函数,最后采用裂纹面分别承受3次、5次和7次幂函数分布应力下的应力强度因子有限元解对通用权函数的计算精度进行了检验和验证.结果表明:建立的通用权函数相比已有的通用权函数精度由4%(A点)和6%(B点)提高到1.06%(A点)和1.6%(B点),补充验证的7次幂函数分布载荷下的应力强度因子通用权函数解的精度达到3.67%(A点)7.45%(B点).      

航空发动机复合材料机匣屈曲特性的有限元分析

复合材料是60年代出现的一种性能优异的新型材料,目前复合材料在航空航天结构领域里已得到了一些的应用。本文利用线性板壳理论和线性屈曲模型,针对某航空发动机树脂基复合材料外涵道机匣构件及此材料层合板进行结构有限元建模与屈曲特性的有限元分析,以期为航空发动机的结构设计提供参考依据。      

Nomex蜂窝夹层结构面内剪切性能试验研究

采用改进设计的像框试验对Nomex蜂窝夹层结构的面内剪切性能进行了表征测试与研究。试验结果表明,在像框的持续性剪切载荷作用下,夹层结构首先发生了板-芯界面脱粘,继而蒙皮在竖直方向上形成了巨大的鼓包和皱褶。随着剪切载荷的增加,夹层结构最终发生了横向的断裂。多次试验结果所得的低于3%的离散率也预示出面内剪切像框试验的有效性和准确性。此外,试样和夹具之间的固定程度是影响面内剪切像框试验的关键因素。仅采用螺钉进行固定的试样测试时,螺钉受拉力的移动直接导致了夹层结构边缘破坏,然而样件本身所受像框的面内剪切载荷有限,试验无效。     

碳/碳多孔防热复合材料压缩性能研究

常见高性能热防护材料的力学性能较为薄弱,这成为了飞行器热防护系统发展的瓶颈。因此,如何设计热防护材料,使其具有良好隔热效果同时兼具足够的承载能力,成为当前的研究热点。本文针对碳/碳多孔防热复合材料进行了单轴压缩实验,获得了其压缩应力—应变曲线,研究了其压缩变形特征及相应的失效模式,并通过SEM观测变形前后的材料细观结构,分析了材料内部的细观变形机制,也为进一步建立表征材料内部细观结构特征的有限元模型和进行数值模拟研究奠定了实验基础。实验结果表明:材料内部纤维主要沿面内随机分布,呈现出明显的分层现象。受其结构的影响,该材料面内方向力学性能比厚度方向优越。     

含分层损伤复合材料层合板前后屈曲行为研究

采用基于Mindlin一阶剪切理论的四节点板单元,分析了简支和固支两种边界条件下含圆形分层复合材料层合板前后屈曲行为。结果表明,尽管浅部分层的存在使层合板的前屈曲临界载荷大幅度下降,但层合板仍能继续承受很大的后屈曲载荷,这种情况下的前屈曲是由于分层部分的局部行为造成的。同时,在相同的铺设和分层厚度及边界条件下,分层半径越大,后屈曲临界载荷越低,固支下的后屈曲临界载荷比简支下的临界载荷高。     

固体推进剂药柱泊松比随机粘弹性有限元分析

为了研究泊松比的分布对固体推进剂药柱结构分析的影响，发展了一种地不可压缩材料的粘弹增量有限元方法，进行了泊松比随机粘弹性有限元的研究，要用局部平均方法对随机场进行离散，给出了二阶摄动有限 元变异方程。算例表明，对药桩进行随机模拟，计算效率和精度较高。