Table of contents

These proceedings contain the scholarly papers presented in the 6^th International Conference on Aeronautical, Aerospace and Mechanical Engineering (AAME 2023). AAME has been held in different parts of the world for some years, as indicated by the number sequence. This year (2023), the conference was held in hybrid mode during February 24-26, 2023 to cater for the needs of participation from different countries. The face-to-face conference was held in Nanjing, China simultaneously with the virtual conference.

This conference has invited keynote speakers who are professors from renowned universities in China and Singapore. Delegates from around the world including China, Japan, Brazil and Peru took the opportunity to share their research results and discussed potential scientific and engineering development from their work. All papers in these proceedings have passed the vigorous review process involving reviewers of the International Technical Committee. Authors benefited from valuable comments and improved their submissions to the satisfaction of reviewers.

The papers in the proceedings have been categorized into four chapters. Four papers are collected in Chapter one which entitles "Functional material design and performance experiments". Five papers are collected in Chapter two which entitles "Line simulation and mechanical analysis". Chapter three, which entitles "Mechanical design and system simulation" and Chapter four, which entitles "Aerospace power and promotion system design and control" have three and four papers included respectively.

The variety of research topics presented in AAME2023 and novelty exhibited in the papers published in these proceedings once again demonstrated the value of the 2023 6th International Conference on Aeronautical, Aerospace and Mechanical Engineering enabling researchers of different nationalities and different engineering fields to participate in a live research conversation. The conference organizers would like to thank the conference committee, the conference secretariat, keynote speakers and all participants for their hard work making AAME2023 a success as well as publishing valuable knowledge contributing to state-of-the-art research in aeronautical, aerospace and mechanical engineering. We sincerely hope that these proceedings will provide readers with an extensive overview and serve as a valuable reference for your further research. The conference organising committee looks forward to seeing all of you at the next conference.

List of Conference Committees, Statement of Peer Review are available in this Pdf.

All papers published in this volume have been reviewed through processes administered by the Editors. Reviews were conducted by expert referees to the professional and scientific standards expected of a proceedings journal published by IOP Publishing.

• Type of peer review: Double Anonymous

• Conference submission management system: Morressier

• Number of submissions received: 30

• Number of submissions sent for review: 21

• Number of submissions accepted: 16

• Acceptance Rate (Submissions Accepted / Submissions Received × 100): 53.3

• Average number of reviews per paper: 2

• Total number of reviewers involved: 10

• Contact person for queries:

Name: FAN WU

Email: fan@zhconf.ac.cn

Affiliation: SAISE

Aluminum alloy is widely used in aircraft structural components. The high cutting force in the conventional machining often causes the burr formation in the machined parts. To overcome the problems, machining method with low cutting force are recommended. In this study, we attempted to mechanize the manual drilling (soft-machining) to establish a new drilling method with a small probability of burr generation. The thrust force in manual drilling is less than one-tenth of that in CNC machining. A total of more than 200 holes were drilled with the same drill at 35 to 110N of applied load. In the drilling of single plate, burr formation is related to the inclination of the drill exit surfaces. Even in the drilling of stacked plates, the soft-machining can drill the through holes at the specified points in all conditions. In the soft-machining, the level of load P[N] becomes an important parameter to minimize the damage generation and it may be a mandatory to adjust the load to the minimum level required for cutting and tool feed. Applying soft machining to robotic drilling may solve vibration problem.

Aluminum alloy 7050 has been widely used in the structure of aerospace vehicles because of its excellent comprehensive performance. In this paper, based on the extended finite element method and classical theory, the material parameters in the finite element simulation are calculated, next the metal plate with a central pre-crack is analyzed for static load breaking and fatigue damage under cyclic loading, the observation of different loading levels and the damage characteristics under different preset crack lengths are summarized, the rules are summarized to provide support for follow-up work.

In tension stringing construction, the conductor defects of loose strand often occur, which affects the construction quality and conductor life. There is no suitable method to express the physical state of such loose strand at present. Through the study of the loose strands section of the conductor, the physical model of the loose strands of the conductor is established, and the physical calculation formula of scattered strands and lantern included in loose strands defect is proposed, as well as the discrimination coefficient of the scattered strands k₁ and the lantern k₂ . 3D scanning technology of industrial CT was used to scan and model the loose strand samples of JL/G1A-630/45-45/7 and JL1/G2A-1250/100-84/19 ACSR obtained from the loose strand reproduction test of conductor. The CT scanning model is evenly intercepted to measure multiple sections, and the scattered strands coefficient and the lantern coefficient are calculated. The results show that: When k₁ and k₂ ≥ 1.2, the scattered strands and lantern defects of the conductor are more obvious, which can be used as a criterion.

An algebraic (zero-equation) transition model is developed to capture multiple transition mechanisms. The newly devised algebraic transition model is parameterized using "flow-structure-adaptive" variables and coupled with the truncated Spalart-Allmaras (SA) turbulence model. The intermittency factor γ relies on "local flow information" and is directly linked to the "vorticity-based production" term of the SA model. Splitting γ into lower and higher regimes of the "free-stream turbulence intensity" enhances the model coefficient calibration and predictions of various phenomena ("natural, bypass, separation-induced, wake-induced", etc.) encountered in transitional flows. Simulations approve that the new formulation provides good correspondence with other transition models, available in the literature.

Turbulence models are considered one of the most important sources of numerical errors in the CFD studies on different aeronautical problems. The mesh type can also affect the numerical accuracy and computational efficiency. In this paper, various simulations on the store separation from an aircraft model in the transonic flow have been carried out by coupling the CFD and the rigid body dynamics on the overset mesh. The influence of S-A model, Standard k-epsilon model, SST k-omega model and inviscid model on the simulation results is examined. Different mesh types of both unstructured mesh and structured mesh as component part in overset are also considered. Grid-independence study are first carried out. The effects of different turbulence models and mesh types are then examined by comparing the trajectories, velocities and Eulerian angles. Recommendations are given to get better results for the simulation of multi-body separation problem.

Vertical wind tunnels play very important role in parachute training, helicopter rotor test, flight experience and other aspects, among which the double returns vertical wind tunnel has spread widely due to its low lose and low running cost. By using innovative structure design and finite element method, the general layout, research on design of supports and important sections are completed. The design part mainly describes glass flight section, integrated fan section, wind speed adjust device, ventilation door and the whole raft foundation structure. The dynamic debugging results show that the double return vertical wind tunnel has rational design, little vibration and high efficiency.

This paper details two static aeroelastic analysis methods applied to a passenger aircraft model with high aspect ratio wing. The influence of nonlinear aerodynamic force on static aeroelastic derivatives in the transonic regime is analysed. The traditional aerodynamic influence coefficient (AIC) matrix method can produce fast and reliable aerodynamic force and is widely used in aeroelastic analysis. However, the AIC matrix computed by linear aerodynamics will lead to some errors in transonic regime because of the nonlinear effect of aerodynamics. By generating the correction matrices, the AIC matrix is modified, and the accuracy of transonic static aeroelastic correction of aerodynamic data can be improved. The static derivatives are compared to the results of the computational fluid dynamics (CFD) / computational structural (CSD) interaction method.

In this paper, a Moving-Least-Squares (MLS)-based immersed boundary method (IBM) for simulating viscous compressible flows is proposed. For this method, the compressible lattice Boltzmann flux solver (LBFS) is used to solve the flow field on the Eulerian mesh and the MLS-based IBM introduced in present paper is used to implement boundary condition. The discrete Lagrangian points are used to represent the Solid boundaries. A second-order MLS interpolation is used for numerical exchange between two grids of IBM. The forced implicit boundary condition is adopted to ensure that the physical boundary condition can be accurately satisfied. The present method is able to achieve a higher numerical accuracy than traditional IBM, which use the Delta function for interpolation. Some numerical validation tests are used for the validation of proposed method. The order and accuracy of the MLS approximation are tested by using a classical example of flow past a cylinder. Test of flow past the NACA0012 airfoil at different Mach numbers, angles of attack and Reynolds numbers is applied to verified the accuracy.

S-gear is a new type of gear with the advantages of small sliding coefficient, high meshing efficiency and large load-bearing capacity due to the concave-convex contact in a vicinity of the meshing start and end. In view of the excellent characteristics and potential value of S-gears, this paper deeply studies the designation and meshing characteristics of the S-gears. First, based on the relationship of S-shaped rack-cutter and machining motion, the tooth surface of the S-gears is generated. Second, by superimposing the surface of modified volume with the standard tooth surface, the modified tooth surface of S-gears is constructed. On this basis, using MATLAB programming, the coordinates of 3D grid node of modified S-gears are calculated. Third, loaded tooth contact analysis (LTCA) is used to study the meshing characteristics of the S-gears with longitudinal modifications and misalignment angle errors. Ultimately, one example is presented and the result shows that after tooth surface modification, the load distribution of S-gears is effectively improved and error sensitivity is greatly reduced. S-gear is a new type of gear which is different from involute gears and has great potential application prospect in large load-bearing field, which will be further studied in the future.

The objective of this study was the design of a hydraulic bicycle and the assembly of a floating structure, steering and propulsion to be able to navigate. To this end, a variety of studies have been conducted. A study on the selection of the most suitable materials for the marine environment was also conducted, where a detailed analysis of each component of the power transmission was carried out, where the Shigley-McGrawhill mechanical engineering design book of machine elements was also used. The study of the structural part was carried out to ensure the integrity of the user, also a study of the transmission of pedaling power to the propeller and the pontoons to be able to withstand a maximum load of 120 kg and stability to ensure buoyancy.

This work aims to design a mechanical transfer system that allows us to integrate the need for power and speed ratio existing in the industry to obtain a safe mechanism ensuring the transmission system, which is optimal for maintenance. The methodology consists of two-stage gearbox design features a gear mechanism with a gear ratio of 10 to 1 to decrease the output speed and increase the motor torque. The gearbox design parameters were calculated using the Excel program; for the simulations the SolidWorks program was used. To check the gear analysis, the calculation of the safety factor of the pinion, the gears and the material validation are evidenced.

This article presents the data acquisition, exploratory data analysis, model training, evaluation, and use of hyperparameters in a machine learning model that will be used to predict telemetry data from the Amazonia-1 satellite. The Amazonia-1 satellite was launched in 2021, it uses the Multi-Mission Platform as a service module and has a Wide Field Imager imaging camera. Its power subsystem has 715 telemetries with distinct data types that will be used as dependent and independent variables. The amount of telemetry data generated daily is large, making manual analysis of this data unfeasible. The ensemble XGBoost machine learning algorithm is used to predict the values of the dependent variable D008 "Battery Module 1 Voltage" that belongs to the electric power subsystem. For the evaluation and performance Mean Absolute Error (MAE), Root Mean Square Error (RMSE), and R2 are used. The final learning model resulted in the coefficient of determination (R²) with 99.99%, MAE of 0.005749, and RMSE of 0.007727. After the cross-validation step, RMSE reached 0.006888. The execution time was 57 minutes and 32 seconds. Based on these numbers, we can consider that the machine learning model built reached a good result, especially when used with cross-validation.

The attitude stability requirements of spacecraft are closely related to their application scenarios. Spacecraft's motion will always be affected by internal and external disturbances during its orbital movement, which makes the attitude no longer meet the stability requirements of the mission design convention. This paper focuses on the study of the effect of random disturbance torques on the spacecraft attitude. The basic covariance method is proposed to study the influence of random disturbance torques on the spacecraft attitude. The simulation results show that the method of covariance analysis can be applied to study the attitude deviation of spacecraft due to random disturbances.

Due to the severe flight environment, hypersonic vehicles are susceptible to external disturbances and aerodynamic parameter uncertainties, dramatically challenging the precise control and stable tracking. This paper presented a fixed-time disturbance observer (FTDO) to obtain better tracking performance for hypersonic vehicles. The FTDO can improve the tracking performance under external disturbances and aerodynamic parameter perturbations, whose observation time is bounded and does not depend on the initial errors. The backstepping control can guarantee finite-time convergence with the finite-time control technique. A second-order filter is designed to process the complexity explosion problem in the traditional backstepping control and ensure the tracking system's finite-time stability. Then with Lyapunov theory, it is proved that the control system is stable and convergent in finite time. Finally, three numerical simulation results based on typical conditions are given to show the effectiveness and advantage of the developed control scheme, and external disturbances can be estimated accurately within two seconds. These results have reference value for flight controller design of hypersonic and other aircraft in complex disturbance environments.

The following paper presents a novel approach that can be applied to Operational Load Monitoring and Structural Health Monitoring processes. The approach is based on artificial intelligence (AI) and digital image correlation (DIC) techniques. DIC is an optical method that allows measuring full-field structural displacements and strains. In the presented approach only a relatively small fragment of the material's surface is monitored by DIC. The obtained partial image of strains or displacements is then processed by a carefully trained AI model, an image classification network, able to predict the state of whole structure (e.g. materials stresses, potential loss of material continuity). The assumption is that all possible load cases and states of the monitored structure can be identified and simulated, so the data obtained from simulations can then be used to train the image classification network. A numerical example is presented as proof of the presented concept. A modern lightweight aerostructure in the form of a hat-stiffened composite panel was used as monitored structure in the presented example and its Operational Load Monitoring was performed based on a relatively small fragment of normal strains map. The reference maps to train the network were simulated numerically. The prediction model estimates the Tsai-Wu failure criterion value for the whole composite material. The obtained accuracy of predictions proved the effectiveness and efficiency of the proposed approach.