Current manufacturing-oriented product model is less adaptable to subsequent numerical simulation. Toimprove transition efficiency between product geometry model and analysis model, product model representation in numericalsimulation phase has been analyzed. Then problems and requirements of analysis-oriented modeling have beensummarized before an analysis-oriented product modeling technique was proposed through improving parametric modelingtechnology. Finally, structure framework of the technique is constructed. To verify its validity, turbine blade models for differentnumerical simulations are generated, which reduce the difficulty of blade design and analysis integration. Other highqualitydigital models can take advantages from it.

With the deep application of new generation information technology in industry, traditional product research and development mode has changed. This paper introduces the modeling and simulation, dynamically predicts and estimates complex product lifecycle business process by using digital clues and digital twin, to achieve the business closedloop mapping of digital space and physical space of the product planning and definition, simulation and analysis, verification and confirmation. At last, combined with the smart manufacturing framework of aviation industry, the application idea in the production lifecycle is given to enhance the digital and intelligent level of the production process.

The virtual manufacturing technology (VMT) can be used to model, simulate and optimize the whole life cycle of a product in the stage of the product design, so that more efficient, more economic and more flexible production can be organized. Thus the goal for shortening the product development cycle, reducing the development costs, optimizing the product quality and improving the production efficiency can be achieved. This paper briefly introduces the implication and characteristics of VMT and the situation of its applications. Then it reviews the applications of VMT in the aircraft  manufacturing industry, which includes the successful cases of the virtual design of the aircraft theoretical surfaces and aerodynamics, the virtual manufacturing of the parts, the virtual assembly of the components and the virtual design of the production line, so that the significance of the VMT applications is demonstrated. Finally, it gives the production for the future  development and applications of VMT.

Aiming at the problems of small volume, multi-model, complex assembly process and high precision requirements of aircraft parts assembly products, the research on virtual assembly technology based on VR is carried out. So that workers can plan assembly process and path of the products, select the fixture and operation method to verify the rationality of the assembly process design, timely detect various design flaws in the process, structural interference and other issues, intuitively scientifically analyze assembly operability, visibility, reachability before producing. According to the simulation of virtual simulation, modification and optimization of technological methods, tooling structure and production line layout, a scientific and rational product assembly process program to shorten the assembly cycle, reduce assembly costs and improve the quality of parts assembly is ultimately generated.

To resolve the problem viewing and looking for itemized manufacturing information manually in MBD (Model Based Definition) models is a heavy workload and time-consuming work in the process of production preparation, therefore the techniques of retrieval, extraction, analysis and reconstruction of non-geometric information were studied based on the storage specification in MBD models. A system of organizing and reconstructing process information for MBD models was developed, which satisfied different levels of needs for different stages, different roles and different professions in the manufacturing process.

This paper presents an automatic detection system for aeronautic rivets based on image recognition. The working process and principle of the system are introduced and the hardware components of the system are given. Then, based on the analysis of evaluation function of image definition captured by CCD camera, an autofocusing method which can be applied in different rivets detection is proposed. Finally, through the analysis of image filter processing and the verification of edge-detection algorithm, the scheme from edgedetection of rivets images to feature extraction is established and the main function interfaces of the system are designed.

It is difficult to be placed in the position of the laser tracker to meet the requirement of measuring accuracy for the special environment such as the external disassembly and reassembly of a certain type of fork type wing-fuselage docking aircraft. Firstly, this paper presents a direct measurement method based on vision. Secondly, builds the measurement system model, analyzes the key technology of vision measurement system involved, and presents a method of ellipse detection based on arc combination. Finally, through the simulation test of fork type wing-fuselagedocking, verifies the actual feasibility of these method. The experimental results show that the cross axis gap distance measurement precision can reach 0.03mm, and the axis angle measurement accuracy reaches 0.025°, which meets the requirements of actual docking measurement.

Owing to such features as lightweight, integrity, the aeroengine casing evolves into complex structure, large dimension, thin walls. Associated with increasing requirement for accuracy, casing is prone to severe distortion after machining. This research investigated the mechanism of casing distortion and proposed a strategy of deformation control based on the allowance division. The surface residual stress of TC4 forging casing blank was measured by the ESPI (Electronic Speckle Pattern Interferometry) technologies. Then, the inner residual stress distribution of TC4 casing was deduced from the finite element simulation. Machining process of TC4 casing was modelled and simulated. Two simulation strategies were proposed and optimized by comparing the deformation. Finally, the simulation result was verified by experiment for machining a casing under optimized plan in the workshop.

With the wide application of composite materials in aviation structures, the study on the aeronautical composite materials repairing has become a research focus. Under the background of single-sided adhesive bonding repaired composite laminates, this paper analyzed the residual strength of adhesive bonding composite structures and applied the failure theories and damage to the evolution of adhesive bonding composites. Based on FEM software platform, this paper proposed a united method for integrating multiple UMAT subroutines, and the numerical model had been establishment to analyze the compression strength variation with different diameters of single-sided adhesive bonding repaired composite laminates. An experimental test had been processed on single-sided adhesive bonding repaired composite laminates. By comparing the compression strength of different groups with different thickness, different shapes and different stacking sequences of repairing patch, this paper investigated and generated design references that how to increase their compression residual strength to these composite structures. And the relative errors between predicted values and experimental results were less than 5 percent.

The surface quality and profile accuracy of blade directly affect the aero-dynamic and working performance of aeroengine. The scientific inspection for aeroengine blade is the crucial technologies to ensure the manufacturing accuracy of blades. Aiming at the current situation of existing gap between China’s aero blade measurement technology with equipment and foreign advanced level, by summarizing the research status and development trend of coordinate measuring machine measurement technology for blade, it can provide a reference for the development of blade detection technology and related instrument. Firstly, the importance and necessity of blade inspection are expounded, and a series of technical difficulties in detecting process are introduced. Secondly, the technical status and equipment are analyzed, and the key technology and its research progress in the detection process are emphatically introduced. Finally, the development trend is pointed out based on the current research status.

The curvature of airplane shape was more heteromorphosis, and complex and convex curvature skin was largely applied with the improvement of the airplane aerodynamic and stealth performance requirement, then the traditional forming method has not completely met the configuration requirements of new generation fighter. The basic principle and key technology of sheet hydroforming was introduced and the key parameters, such as chamber pressure, thickness reduction ratio, sheet instability and curation tolerance were analyzed and optimized by using finite element simulation method during sheet forming process based on the background of complex hyperbolic skin production of a certain type airplane. The industrial production was guided by the results of numerical simulation. The hydroforming technology provided a new method of industrial manufacture for large complex concave and convex curvature skin parts and met the requirements of the concave and convex curvature shape skin for the new generation of airplane, which had proved through theoretical analysis and industrial procetice.

Static tensile experiments were occupied on a composite fan blade according to the standardized experimental process to verify the mechanical properties required for the normal running of the blades. The test conditions covered the rated condition and the double overloaded condition of the blades. Experimental results have reflected that the composite blades meet the strength and fatigue lifetime requirements of normal operation. The formulation of the experimental procedure can provide references on the mechanical performance testing of the similar products. A setting method of composite property used on the CAE modeling of the complicated curving structures was proposed and a finite element model of the composite blade was established based on this method. The load-displacement response of the composite blade under the condition of the rated centrifugal force was calculated. Numerical results are in good agreement with experimental results, which indicates that the model is applicable in the analysis of the composite blades.

For meeting the need of new type aircraft assembly detection, proposed an assembly detection new method based on laser radar, which uses laser radar to measure the positioning reference of assembly components, analyze the measurement data and extract the key size information. The method solved the assembly problem fundamentally. This paper combined with the assembly testing instance of certain component on an aircraft, solved the out of tolerance of size coordination in the process of aircraft assembly. The results prove that the digital assembly detection technology based on laser radar can detect the assembly problem effectively. The new method is of great significance to realize the digital automatic aircraft assembly.

The compound helicopter can vertically take-off, hover and conduct low speed flights. At the same time, it has high speed, long range and endurance. These features make it significant in both military and civilian fields. This paper concludes the advantages of compound helicopter compared with the traditional configuration, and gives an overview on the developing compound products nowadays. The overall configuration and aerodynamics interference are analyzed in detail, along with the control strategy and control/stability characteristic concluded. What’s more this work analyzes the multiple choices of rotor blade configuration and the assistant trust/lift system, and summarizes the technology features of the compound helicopter.

The material of Inconel617 alloy has the properties of corrosion resistance, high temperature oxidation resistance and wear resistance in the practical application. But, its wear resistance is poor. In order to improve the wear resistance of Inconel617 alloy, HVOF (high velocity oxygen fuel) and electron beam surface modification technology were used to prepare WC-CoCr ceramic coating on Inconel617 alloy. The microstructure and element distribution of the alloy layer were analyzed. Hardness and wear resistance of the alloy layer were tested. The results show that in the process of electron beam processing, the forming metallurgical bond of coating remelting and matrix could increase wear resistance significantly. Compared with the substrate, hardness of the cladding layer improves significantly.

The design proposal of aircraft engine digital installation system based on vision is proposed. The offline trajectory of engine installation in Cartesian space is planned by transformation of coordinates. The measure arithmetic of engine pose based on image low-rank matrix recovery is elaborated. The engine online trajectory planning based on vision is proposed. Engine installation experiments are accomplished, and practice results show that the new proposed digital installation technology has advantages of stability, efficiency and accuracy.