The corrosion of materials is a worldwide issue. Even though many corrosion protection methods had been presented, it still hard to satisfy the demand of the development of materials. In recent years, bio-inspired superhydrophobic surface has attract many attentions because of its special wettability, numerous researchers had utilized this novel surface in corrosion protection field and obtained some excellent achievements. Based on this background, the basic concepts and theories of the wetting on solid surface were expounded briefly in this paper, and then focused on introducing the application of superhydrophobic technology on corrosion protection of aeronautical materials field. After that, the theoretical basis of superhydrophobic technology for corrosion protection was summarized. At last, the current existing problems and the future development directions of this technology for corrosion protection were pointed out.

    With the continuous development of science and technology, the demand for high-purity materials becomes more and more urgent. The high purity material industry has penetrated into various fields of national economy, national defense construction and social life, which plays an important role in economic and social development. The preparation technology for high-purity materials is an important symbol to measure the development level of metallurgical technology in a country. Compared with other melting technologies, electron beam melting technology has the characteristics of high vacuum, high temperature, good controllability, and it is not limited by the shape of the raw material. Therefore, this technology is possible to solve the problems in preparation of high-purity materials. This paper reviews the research status of electron beam melting technology in preparation of high-purity simple substance and multicomponent alloy. Meanwhile, the current major problems and development directions are discussed, which provide ideas for the development of electron beam melting technology with high efficiency, low cost and large-scale application.

   To promote the fatigue property of the disk’s stress-concentration structure made by powder metallurgy uperalloy, cast-iron shots, ceramic beads and the compound of the two kinds of shots are employed to peen the PM notched atigue sample. Strengthening layer is characterized by surface profile analysis using white light interfere, residual stress measurement ith X-ray diffraction and electrochemical corrosion, and micro-hardness profile research. Fatigue strengthening effect s compared with high-temperature notched (structure stress-concentration coefficient Kt=1.7) fatigue life of rotating-bending ode. The results show that strengthening layer is introduced by shot peening on the surface of FGH95 alloy. After shot eening, the surface average roughness and Kurtosis value are 0.9–1.5μm and close to 3 respectively. Surface residual stress s about –800 – –1150MPa, and the depth is 120~250μm. Moreover, compared with the as-received hardness 480–510HV0.2, he peening surface hardness increased to 575–625HV0.2, and the hardness layer depth is 175–250μm. The double shot peening ethod, firstly using the cast-iron shot in big intensity and secondly using the ceramic shot in small intensity, brings the aximum residual compressive stress, the highest hardness and biggest depth on the surface, and the smaller roughness with mooth bottom of crater, which obtains the best fatigue strengthening effect. The median fatigue life estimations of the double hot peening at 550MPa/650℃ is 20 times higher than original one.

    To improve the high temperature oxidation resistance of titanium and titanium alloys, a Ti5Si3/Ti3Al composite coating with oxidation resistance at 1000℃ was prepared by laser alloying on TA2 titanium alloy with inner layer of silicon powder and outer layer of aluminum powder. XRD, SEM and isothermal oxidation technology were used to study the microstructure and the air isothermal oxidation performance of the coating at 1000℃ for 50h. The results show that the composite coating is mainly composed of primary Ti5Si3 phase and Ti5Si3/Ti3Al eutectic structure; the oxidative weight gain rate of the composite coating is about one twelfth of that of the substrate; the oxidation products of the composite coating are mainly TiO2, Al2O3 and SiO2; the existence of two phases Ti5Si3 and Ti3Al in the composite coating is the main reason for the improvement of its oxidation resistance at 1000℃ .

    TiN coatings with no crack and uniform compact structure were fabricated on the TC4 titanium alloy by laser micro-fusion in-situ synthesized technology. The micro-structure, chemical composition and phase of the coating were analyzed, in addition, the micro hardness of the coating, bond strength between coating and titanium alloy matrix, and the wear resistance of coating were tested. The resistance of erosion of SiO2 particles with high-speed was also tested. It was found that the bonding strength of TiN coating and TC4 titanium alloy was 240–270MPa due to good metallurgical combination between them. The micro hardness of the coatings was found to reach 1550HV0.1, around 4.5 times of the matrix which is ascribed to the formation of TiN with high hardness. Moreover, the loss weight of coating wear was 14.7% of TC4 titanium alloy and the mass loss of the substrate was twice that of the coating at an erosion angle of 60°.

    To investigate the geometry effect on laser peen forming (LPF) for panel shaping, finite element simulation is performed with single-curved cylindrical specimens based on the eigenstrain model, and LPF experiments are conducted to verify the simulation results. The normalized deviation between the deformations of non-planar specimen and planar plate is proposed as the indicator to evaluate the geometry effect, based on which the effect of typical geometric parameters on LPF is analyzed including axial length, plate thickness, sectional arc length and sectional radius. The results show that the normalized deviation is irrelevant to the axial length when axial length is more than twice as the arc length. Moreover, the normalized deviation is observed to decrease with the increasing sectional radius, the decreasing arc length or the increasing plate thickness, respectively, when other parameters are specified.

    For fatigue failure occurring in a stiffener of an aircraft web plate earlier, the structure of the web plate is improved by means of simulation analysis and experimental validation. Firstly, the web plate dynamic model is set up, the causes of fatigue failure are analyzed by calculating the stress distribution and fatigue life of the web plate. Secondly, an improvement design is conducted on the original structure of the web plate based on principle of stiffness distribution. The finite element calculation result shows that improved design decreases the maximum stress of the stiffener and improves the fatigue life of the web plate. Finally, by comparing the fatigue tests of original structure and improved structure, the results verify the accuracy of finite element model and the effectiveness of the improvement.

    This paper presents a simulation prediction method of cutting force based on MATLAB in boring process, and a simulation software of cutting force is developed. By establishing the basic parameters of boring process, the relationship of cutting area and line length, cutting tool geometry parameters and machining process parameters is studied. According to the participation of the main and secondary cutting edges, the boring process is divided into four working conditions, and the cutting area and the line length are calculated respectively under the four working conditions, and the corresponding function curves are obtained by MATLAB simulation. The mathematical model of cutting force about cutting area and line length is established, and the relationship between cutting force and basic parameters of boring is obtained. At the same time, the vibration of cutting tools in boring process is studied. Through experimental comparison, the accuracy of simulation prediction method based on MATLAB is verified, which provids the basis for intelligent control of cutting force and vibration in boring process.

    With the increasing demand for aircraft performance, structural weight reduction has become an important task in aerospace manufacturing industries. The Al-Li alloy exhibits many excellent performance including light weight, high strength, etc. These noteworthy advantages make it an ideal aerospace lightweight structural material with great development potential. At the same time, laser welding technology is considered as the most effective joining method for aluminum alloys. Nevertheless, the reliability of the welded structure is recognized as a challenge owing to the unique characteristics of the welded Al-Li alloy and the requirements of the civil aircraft industries. In this paper, the special micro-structure and defects in Al-Li alloy laser welded joint are introduced. The formation mechanism and inhibition measures of equiaxed grain along the fusion boundary (EQZ), welding pores, welding cracks and joint softening defects are analyzed.

    The 3D model was simplified by Abaqus software, and the finite element model of the frame molding die was established by using solid element and shell element respectively, and the stress level and deformation of the mould under the typical working conditions such as bracing, paving and lifting were analyzed. It is found that the difference between the two model analysis results is small, so the shell element can be used instead of the solid element in the lightweight design. Based on the shell elements, the lightweight design of the mould was carried out by using the sizing optimization module of Abaqus, and the suitable thickness of the clapboard is determined.

    Aeronautical TC4 Titanium alloy parts is fabricated by selective laser melting 3D printing. Some key application problems of selective laser melting are investigated about optimization design of CAD model, building parameters and post-processing. We analysize the factors that affect the quality of 3D printing. Some suggestions and advices are made about the industrialization of titanium alloy selective laser melting 3D printing.

    The influence of the excitation condition on the aeroengine rotor blade response in fatigue test is studied. Numerical analysis and experiments test results show that in the rigid clamping condition, the relative relationship between the rotor blade clamping and the test device excitation load vector has no significant effect on the first-order natural frequency, mode shape and stress distribution. In the first mode shape vibration condition, the span stress component dominates the surface stress of the blade, the clamping influences the transfer function between excitation and response. There exists a clamping position, in which, minimum excitation energy is required when the vibration amplitude of blade tip reaches certain amount. The conclusion is of great significance to improve the rotor blade fatigue performance evaluation technology.

    Carbon fiber reinforced polymer (CFRP) is a kind of material with epoxy resin as matrix material and carbon fiber as reinforced material, which has the characteristics of high strength, high specific strength and corrosion resistance. CFRPs and titanium alloys are two kinds of lightweight materials widely used in aerospace fields. CFRPs and titanium alloys often appear as laminated structures in the key areas of large passenger aircraft, which leads to a large number of hole-making of CFRP/Ti stacks in the manufacturing and assembly processes of large passenger aircraft. The variation of heat and force as well as chip shape in the CFRP/Ti stacks drilling process will directly affect the cutting state of the tool.Therefore, the study of force-thermal behavior and chip forming in the CFRP/Ti stacks drilling process was carried out in this paper, which has important guiding significance for the actual drilling process of CFRP-Ti stack.