Microstructure evolution of a hypereutectic Nb–Ti–Si–Cr–Al–Hf alloy processed by directional solidification

In this work, the Nb–14Si–24Ti–10Cr–2Al–2Hf–0.1Y alloy(at.%) was processed by the liquid–metal-cooled directional solidification(DS) at 1750 C with withdrawal rates of 1.2, 6,18 mm/min and post heat treatment(HT) at 1450 C for 10 h. The microstructures of the directionally solidified and heat treated samples were investigated. The results show that the microstructure of directionally solidified alloy mainly consists of petaloid Nbss+ Nb5Si3eutectics and Ti-rich Nbss+ Nb5Si3+ Cr2Nb eutectics. With the increase of withdrawal rate, the primary Nb5Si3is eliminated, Nbss+ Nb5Si3eutectic cells turn round and connected with the microstructure refinement and Nbss+ Nb5Si3+ Cr2Nb eutectics turn to a river-like morphology. After heat treatment,Nbss+ Nb5Si3+ Cr2Nb eutectics disappeared and petaloid Nbss+ Nb5Si3eutectics turn to a specific fiber-mesh structure gradually, which is promoted by higher withdrawal rates. Furthermore,both the volume fraction of Cr2Nb and the content of Cr in Nbssof Nbss+ Nb5Si3eutectics change regularly with the increase of withdrawal rate and heat treatment at 1450 C for 10 h.     

Ultrasound assisted solidification process of ternary Cu–Sn–Sb alloy

It is well-known that the application of ultrasound during liquid to solid transitions for alloys can refine the solidification microstructure and thus improves the mechanical properties. How-ever, most published work focuses on single phase dendritic growth, whereas little has been con-ducted on the multiphase alloys with complicated phase transformations during solidification. In this work, the solidification process of ternary Cu40Sn45Sb15 alloy was realized within intensive ultra-sonic field with a resonant frequency of 20 kHz and ultrasound power from 0 W to 1000 W. The ultrasound refines the size of the primary e(Cu3Sn) intermetallic compound by two orders of mag-nitudes. If the ultrasound power increases to 1000 W, g(Cu6Sn5) phase nucleates and grows directly from parent liquid phase without the occurrence of peri-eutectic reaction on the top of the alloy sam-ple where the ultrasound intensity is sufficiently high. These microstructural variations lead to the enhancement of compressive strength and elasticity modulus of ternary Cu40Sn45Sb15 alloy.     

GJB 9001A–2001、KJB 9001–2006和HB 9100–2003的比较分析

简要介绍航空工业现场使用的质量管理体系标准GJB 9001A-2001、KJB 9001-2006、HB 9100-2003的基本架构,并针对上述3个标准在适用范围、主要内容、适用性和可操作性上的区别以及各标准主要特点的比较分析,给出建立具有中国特色的、单一的航空工业质量管理体系的技术建议。     

Al–Mg–Si合金电弧熔丝增材构件组织与性能

以复合超高频脉冲方波变极性钨极氩弧(HPVP–GTAW)为热源,Al–5Mg(ER5087)和Al–5Si(ER4043两种焊丝为填丝材料进行铝合金电弧熔丝增材制造,通过控制两焊丝的送丝速度获得不同主要合金元素Mg和Si含量的Al–Mg–Si合金薄壁构件,试验研究不同Mg/Si比及热处理对薄壁构件组织及性能的影响。结果表明:合金组织主要由柱状晶及少量等轴晶组成,呈非均匀分布。调节主要合金元素含量可实现对铝合金增材构件性能的控制,随着Mg/Si比的增加,增材构件的力学性能呈上升趋势,各向同性;经过固溶及人工时效热处理后,增材构件的力学性能得到显著提升,但塑性降低。     

Selective laser melting of Al–8.5Fe–1.3V–1.7Si alloy: Investigation on the resultant microstructure and hardness

This article presents the microstructure and hardness variation of an Al–8.5Fe–1.3V–1.7Si(wt%, FVS0812) alloy after selective laser melting(SLM) modification. Three zones were distinguished across the melting pool of the SLM-processed FVS0812 alloy: the laser melted zone(LMZ), the melting pool border, and the heat affected zone(HAZ) in the previously deposited area around the melting pool. Inside the LMZ, either an extremely fine cellular-dendritic structure or a mixture zone of the a-Al matrix and nanoscale Al_(12)(Fe,V)_3Si particles appeared. With a decreased laser beam scanning speed, the cellular-dendritic structure zone within the LMZ shrank significantly while the mixture zone expanded. The a-Al and Al_(12)(Fe,V)_3Si mixture zone was also observed in the HAZ, but another phase, submicron h-Al_(13)Fe_4 particles with rectangular or hexagonal shapes,formed along the melting pool border. Microhardness tests indicated that the hardness of the SLM-processed FVS0812 samples far exceeded that of the as-cast FVS0812 alloy.     

An integrated graphic–taxonomic–associative approach to analyze human factors in aviation accidents

Human factors are critical causes of modern aviation accidents. However, existing accident analysis methods encounter limitations in addressing aviation human factors, especially in complex accident scenarios. The existing graphic approaches are effective for describing accident mechanisms within various categories of human factors, but cannot simultaneously describe inadequate human–aircraft–environment interactions and organizational deficiencies effectively, and highly depend on analysts' skills and experiences. Moreover, the existing methods do not emphasize latent unsafe factors outside accidents. This paper focuses on the above three limitations and proposes an integrated graphic–taxonomic–associative approach. A new graphic model named accident tree(AcciTree), with a two-mode structure and a reaction-based concept, is developed for accident modeling and safety defense identification. The AcciTree model is then integrated with the well-established human factors analysis and classification system(HFACS) to enhance both reliability of the graphic part and logicality of the taxonomic part for improving completeness of analysis. An associative hazard analysis technique is further put forward to extend analysis to factors outside accidents, to form extended safety requirements for proactive accident prevention. Two crash examples, a research flight demonstrator by our team and an industrial unmanned aircraft, illustrate that the integrated approach is effective for identifying more unsafe factors and safety requirements.     

Effects of cerium salts on corrosion behaviors of Si–Zr hybrid sol–gel coatings

The present work examines the effects of cerium salts on corrosion behaviors of Si–Zr hybrid sol–gel coatings. The Si–Zr hybrid sol–gel coatings on a 2A12 aluminum substrate were prepared through hydrolysis and condensation of glycidoxypropyl-trimethoxy-silane(GTMS) and zirconium(IV) n-propoxide(TPOZ). Used as inhibitors for corrosion, three types of cerium salts(Ce(NO_3)_3, CeCl_3, and Ce(CH_3COO)_3) were doped into the sol–gel coatings. Fourier transform infrared(FTIR) and scanning electron microscopy(SEM) were employed to investigate the structures and morphologies of various coatings, and the corrosion resistances of the coatings were evaluated by electrochemical methods and neutral salt spray tests. Experimental results indicate that the addition of cerium salts can hinder the process of corrosion due to their self-healing abilities. Furthermore, the sol–gel coating doped with Ce(CH_3COO)_3 has the best corrosion resistance because of the promotions of hydrolysis and condensation provided by CH_3COO.     

Effect of sodium tartrate concentrations on morphology and characteristics of anodic oxide film on titanium alloy Ti–10V–2Fe–3Al

The effect of sodium tartrate concentrations on morphology and characteristics of ano-dic oxide film on titanium alloy was investigated. The alloy substrates were anodized in different concentration solutions of sodium tartrate with the addition of PTFE emulsion and their morphol-ogy and characteristics were analyzed. The anodic oxide film presented a uniform petaloid drums and micro-cracks morphology. Additionally, micro-cracks dramatically swelled with the increase of the tartrate concentrations. The thickness of the anodic oxide film increased with the concentra-tions until the concentration reached 15 g/L. The results of Raman analysis illustrate that all sam-ples have similarity in the crystal structure, consisting of mainly amorphous TiO2, some anatase TiO2 and a small amount of rutile TiO2. And the ratios of anatase TiO2 and rutile TiO2 increase with the concentrations until it reaches 15 g/L. Furthermore, the intensity of the peaks increases with enhanced concentrations until the concentration reaches 15 g/L. The corrosion resistance of the anodic oxide film is increased by the sodium tartrate with higher concentrations before 15 g/L. The coefficient of friction of the anodic oxide film reduces with the concentrations until the concentration reaches 15 g/L, then the coefficient of friction of the anodic oxide film increases with the concentrations.     

Quasi-static tensile behavior of large-diameter thin-walled Ti–6Al–4V tubes at elevated temperature

As promising light-weight and high-performance structure components, large-diameter thin-walled(LDTW) Ti–6Al–4V titanium alloy(TC4) bent tubes are needed most urgently in many industries such as aviation and aerospace. Warm bending may be a feasible way for manufacturing these components. Understanding their temperature and strain rate dependent tensile behavior is the foundation for formability improvement and warm bending design. In this paper, uniaxial tensile tests were conducted at elevated temperatures ranging from 298 K to 873 K at tensile velocities of 2, 10, 15 mm/min. The main results show that the tensile behavior of LDTW TC4 tubes is different from that of TC4 sheets. The typical elongation of TC4 tubes at room temperature is 10%lower than that of TC4 sheets. The flow stress of TC4 tubes decreases greatly by about 50% with the temperature rising to 873 K. At temperatures of 573–673 K, the hardening exponent is at its highest value, which means the deformation mechanism changes from twining to more dislocation movement by slipping. The fracture elongation of TC4 tubes fluctuates with increasing temperature,which is associated with changes in the deformation mechanism and with the blue brittleness. The fractography of TC4 tubes at various temperatures, especially at 673 K, shows that second phases and impurities significantly influence fracture elongation. By considering the characteristics of the tensile behavior and by properly choosing the die material, the warm bending for TC4 tubes can be achieved at temperatures of 723–823 K.     

基于改进雅克比–旋量模型的航空发动机转子–叶片结构装配精度分析

转子–叶片是航空发动机的核心部件,具有装配结构复杂、装配难度大等特点,在高温高压条件下,转子–叶片装配误差被催化放大,容易导致疲劳裂纹等故障,严重影响整机安全性和可靠性。针对转子–叶片结构,传统的装配偏差分析方法常采用多特征并联结构中的一条支链作为单一主链来建立偏差传递模型,难以综合考虑转子–叶片复杂定位结构和局部并联关系。本文提出了基于改进的雅可比–旋量（Jacobian–Torsor,J–T）模型的转子–叶片装配偏差分析方法。首先分析了转子–叶片多级回转结构、止口定位结构和榫头榫槽结构,建立了考虑转子–叶片多特征局部并联关系的整机装配尺寸链;然后采用不完全定位策略将转子–叶片装配结合面表达为基于点接触形式的偏差旋量,建立了基于定位点系统的转子–叶片联合定位基准方案;最后提出转子–叶片装配精度指标及基于改进的雅克比–旋量模型的求解方法。以某航空发动机转子–叶片的径向、轴向和周向装配偏差分析为例,将传统雅克比–旋量模型、基于蒙特卡洛法的仿真模型、改进雅克比–旋量模型及实测结果进行了对比分析。结果表明,本文方法相较其他方法预测精度更高,与实测结果误差率不超过9%,提出了榫头榫槽更合理的装...     

增材制造Ti–6Al–4V组织的演化与拉伸性能的差异

Ti–6Al–4V适用于多种增材制造技术,但是不同增材技术制造的Ti–6Al–4V组织演变形式不同。以沉积效率最低的选区激光熔化和沉积效率最高的电弧填丝增材制造技术为研究对象,总结了这两种工艺条件下Ti–6Al–4V微观组织的演变形式和拉伸性能的差异。选区激光熔化制造的Ti–6Al–4V组织以α'马氏体为主,使其延展性降低。电弧填丝增材技术制造的Ti–6Al–4V晶粒粗大、存在晶界α相,导致其强度较低。针对这些问题,提出了有效改善性能的方法,同时对这两种增材技术的发展和未来的研究趋势进行了预测。     

Fast low-energy halo-to-halo transfers between Sun–planet systems

In this paper, the problem of fast low-energy halo-to-halo transfers between Sun–planet systems is discussed under ephemeris constraints. According to the structure of an invariant manifold, employing an invariant manifold and planetary gravity assist to save fuel consumption is analyzed from the view of orbital energy. Then, a pseudo-manifold is introduced to replace the invariant manifold in such a way that more transfer opportunities are allowed. Fast escape and capture can be achieved along the pseudo-manifold. Furthermore, a global searching method that is based on patched-models is proposed to find an appropriate transfer trajectory. In this searching method, the trajectory is divided into several segments that can be designed under simple dynamical models, and an analytical algorithm is developed for connecting the segments. Earth–Mars and Earth–Venus halo-to-halo transfers are designed to demonstrate the proposed approach. Numerical results show that the transfers that combine the pseudo-manifolds and planetary gravity assist can offer significant fuel consumption and flight time savings over traditional transfer schemes.     

改进CEEMD–MRSVD降噪方法及应用研究

针对总体经验模态分解(Ensemble empirical mode decomposition,EEMD)阈值降噪处理方法难以取得理想效果问题,提出了改进互补集合经验模态分解–多分辨率奇异值分解(Complementary ensemble empirical mode decomposition–multi-res...     

A step deformation method for superplasticity improvement of coarse-grained Ti–15V–3Cr-3Sn-3Al

Ti–15V–3Cr–3Sn–3Al(Ti–15–3), a kind of metastable beta titanium which has high specific strength and good cold-formability, is highlighted for applications in the aerospace manufacture industry. However, the technique for improving its formability at elevated temperatures is still a challenge at present. In this work, a step deformation method is proposed for superplasticity improvement of coarse grained Ti–15–3 plates at temperatures around its beta transus. The effects of the strain rate and the strain at the first stage on the superplasticity are investigated. The results show an increase of the strain rate sensitivity and a decrease of the flow stress under the step deformation mode compared to those obtained under constant strain rates at 780℃. The maximum strain to failure obtained in the step mode is 93% higher than that deformed in the constant strain rate mode. Strain rates, strains at the first stage, and temperatures have influences on the superplasticity improvement. The deformation mechanism is concluded as subgrain formation accommodated by grain boundary sliding rate-controlled by dislocation climb. The improved m value in the step deformation is accounted to the extra dislocation density produced during the strain rate reduction.     

Brazing diamond grits onto AA7075 aluminium alloy substrate with Ag–Cu–Ti filler alloy by laser heating

The brazing of diamond is a promising way to fabricate grinding wheels for efficient machining and precision grinding. This work investigated the feasibility of bonding diamond grits onto Aluminium Alloy 7075 (AA7075) substrate with a Ag–Cu–Ti filler alloy via laser fusion brazing. The interfacial microstructures and the strength of the brazed diamond joints were studied. The cross-section of the brazed diamond joint consists of a molten filler alloy layer, a molten pool, a heat effect zone, a columnar crystal zone and an equiaxed crystal zone. Within the interface of the filler alloy/substrate metal, microstructures observed possibly were Ag(s.s), Al(s.s), TixAl, Al2Cu and Mg intermetallic compounds. A layer of TiC with a thickness of about 30–50 nm was found at the bonding interface of the diamond/filler alloy. The averaged peak shear force of the brazed joints was found to be approximately 39.8 N. The abrasion grinding test indicated that the diamond/AA7075 brazed joint was adequate for grinding. However, the pulled-off of grit was found to be the primary failure of this type of brazed joint. This work broadened the brazing diamond technique and the range of applications of brazed diamond wheels for efficient grinding.