Aerospace Research Research Articles

An application of aircraft noise metrics to the Artemis-I launch

In aerospace and acoustical research, there has been significant focus on understanding the negative effects of noise from jet aircraft and flyover vehicles. However, there has been relatively little investigation into the specific noise impacts of launch vehicles. Despite a considerable rise in the number of launches from various spaceports globally in the past decade, there appears to be poor understanding of the potential harm these increasing launches could pose to nearby communities, including both humans and wildlife. This paper aims to apply established noise metrics such as overall sound pressure level, sound exposure level, and effective perceived noise level, commonly used in aircraft policy, to quantify the potential noise impact of launch vehicles, using measurements from the Artemis-I mission as a case study.

Flight test for the noise source modeling of the optionally piloted personal air vehicle

An acoustic flight test is carried out in order to obtain the noise hemisphere of the optionally piloted personal air vehicle (OPPAV). The OPPAV is one-seater, research urban air mobility (UAM) being developed by Korea Aerospace Research Institute. Noise radiated from the aircraft is measured using a microphone array consisting of a total of 78 microphones. Flight logs such as the aircraft position, velocity, and attitude are recorded synchronously with the acoustic signals. Measured acoustic signals are dedopplerized and divided into a number of segments. Noise source model for the OPPAV flight is constructed using these segments. The noise source model will be used for the assessment of noise annoyance during urban flight of the UAMs.

Unsteady separation mechanism of ground horizontal-sliding takeoff system

Complex aerodynamic interference has long posed challenges to the safe separation of multi-body systems. Based on a new conceptual ground horizontal-sliding takeoff approach, the rocket sled system, computational fluid dynamics (CFD) simulations are conducted to study the separation between the payload and the rocket booster, with the Advisory Group for Aerospace Research and Development Model B representing the payload. The motion trajectory of the payload and the unsteady interaction flow mechanisms during separation are analyzed by altering the payload's layout, center of gravity (CoG), and sliding Mach number. The results show that positioning the payload closer to the front along the axis increases the likelihood of collisions after separation. At a sliding velocity of Ma=3, the payload tends to exhibit a nose-down attitude when lc/lp<0.64. Conversely, when lc/lp>0.64, the pitching angle becomes excessively large, which increases the risk of stalling or somersaulting. Furthermore, the CoG needs to move forward to reduce the growth rate of the pitching angle when the separation Mach number is increased. These studies can provide valuable references for the development of separation technology for the rocket sled system.

Gamma rays impact on 2D-MoS2 in water solution.

Two-dimensional transition metal dichalcogenides, particularly MoS2, are interesting materials for many applications in aerospace research, radiation therapy and bioscience more in general. Since in many of these applications MoS2-based nanomaterials can be placed in an aqueous environment while exposed to ionizing radiation, both experimental and theoretical studies of their behaviour under these conditions is particularly interesting. Here, we study the effects of tiny imparted doses of 511keV photons to MoS2 nanoflakes in water solution. To the best of our knowledge, this is the first study in which ionizing radiation on 2D-MoS2 occurs in water. Interestingly, we find that, in addition to the direct interaction between high-energy photons and nanoflakes, reactive chemical species, generated by γ-photons induced radiolysis of water, come into play a relevant role. A radiation transport Monte Carlo simulation allowed determining the elements driving the morphological and spectroscopical changes of 2D-MoS2, experimentally monitored by SEM microscopy, DLS, Raman and UV-vis spectroscopy, AFM, and X-ray photoelectron techniques. Our study demonstrates that radiolysis products affect the Molybdenum oxidation state, which is massively changed from the stable + 4 and + 6 states into the rarer and more unstable + 5. These findings will be relevant for radiation-based therapies and diagnostics in patients that are assuming drugs or contrast agents containing 2D-MoS2 and for aerospace biomedical applications of 2DMs investigating their actions into living organisms on space station or satellites.

Self-healing and thermal transport behavior in catalytic vitrimer-graphene composite

Vitrimers are a distinct category of polymers that could conduct dynamic cross-linking in response to temperature stimuli. In this work, using a molecular dynamics simulation model, we explore self-healing and the thermal transport behavior of vitrimer-graphene composites to overcome its inherent slow self-healing process. The temperature-dependent reversible cross-link mechanisms, which possess the capacity to dynamically modify the mechanical properties of these substances, are studied by explicitly integrating the temperature-dependent reaction probabilities. This modeling approach efficiently predict the changes in the mechanical properties of vitrimers when undergoing temperature cycling both above and below the topological freezing point, as well as the damage healing and subsequent recuperation of mechanical behaviors. The heat transport behavior of the graphene-vitrimer composite is investigated using non-equilibrium molecular dynamics in conjunction with self-healing models. The thermal conductivity of vitrimer-graphene composites, calculated by including a bilayer graphene sheet with varied flake size and interlayer spacings, exhibits a considerable enhancement as compared to standalone vitrimers. Notably, the thermal conductivity is subject to change when the separation distance changes. These results shed light on the self-healing and heat transmission in vitrimer and open the door to possible applications in several fields, including electronics, energy efficiency, aerospace, and materials research.

A case study into the safety management systems for the effects of potential space weather risks, for operators of very high altitude ‘near space’ flights from Mojave Air & Space Port, California, and the associated regulatory challenges

Mojave Air & Space Port is located in Mojave, California, United States. It is at an elevation of 2,801 feet (854 m), is nearly 3000 acres in size and has three runways. It is licensed by the FAA for horizontal launches of reusable spacecraft and is already a major hub for aerospace research and space enterprises, which includes potential space flights and very high altitude subsonic, supersonic, and hypersonic flights.During potential very high-altitude ‘near space’ space flights, the effects of cosmic radiation exposure, especially during sudden changes in space weather, such as ground level enhancement (GLE) or solar particle events (SPEs), could have significant health implications for crew and passengers. This case study examines the intricate landscape of radiation risks, regulatory challenges, licensing complexities, and approaches to risk management for very high-altitude ‘near space’ space flights from Mojave Air and Space Port carrying one or more paying "space flight participant" (being an individual, who is not crew, carried aboard a launch vehicle or re-entry vehicle).The study explores the specific challenges of risk assessment of very high-altitude flights, looking in detail at the risk posed by the space weather radiation environment in flight planning and execution, for both Space Port and flight operator. The study covers the ‘end to end’ licensing process and the regulatory considerations of space weather required for both Space Port and flight operator. Further, we look at the integration of Safety Management Systems (SMS), namely, we explore how SMS frameworks proactively identify, assess, and mitigate risks throughout the ‘near space’ space flight process. Further, the study presents a template for addressing the regulatory framework for flights, risk assessment, pre-flight briefings, and the flight licensing procedure.This case study offers valuable insights for Space Port and flight operators, regulators, and policymakers, contributing to the development of comprehensive safety strategies, which are crucial for safe very high-altitude ‘near space’ space exploration.Plain Language Summary: A case study of how the potential space weather risks can be successfully managed for very high altitude ‘near space’ subsonic, supersonic, and hypersonic flights from Mojave Air and Space Port, California, USA carrying one or more space flight participant(s).

Koopman neural operator approach to fast flow prediction of airfoil transonic buffet

Transonic buffet on airfoil is of great importance in the aerodynamic characteristics of aircraft. In the present work, a modified Koopman neural operator (KNO) is applied to predict flow fields during the transonic buffet process of the OAT15A [ONERA (National Office for Aerospace Studies and Research) Aerospatiale Transport aircraft 15 Airfoil] airfoil. Transonic buffet flow with different angles of attack is simulated by Reynolds averaged numerical simulation with the Menter's k−ω shear stress transport (SST) model at Reynolds number Re=3×106. A prediction model is directly constructed between the flow fields at several previous time nodes and that at the future time node by KNO. The predictions of flow fields with single sample and multi samples are performed to demonstrate the prediction accuracy and efficiency of KNO. The prediction of sequence flow fields based on the iterative prediction strategy is achieved for the transonic buffet process. The results indicate that KNO can achieve a fast and accurate prediction of flow physical quantities for the transonic buffet. Compared with other deep learning models including Unet and Fourier neural operator, KNO has a more advanced capability of predicting airfoil transonic buffet flow fields with higher accuracy and efficiency and less hardware requirements.

Взрывная дегазация Земли на полуострове Ямал и прилегающей акватории Карского моря

Remote sensing data from space and using UAVs make it possible to solve a wide range of tasks related to the study of Earth degassing processes in the Arctic. For the first time, via comprehensive aerospace research on the Yamal Peninsula, we have discovered 4992 zones of gas blowouts (explosions) in the form of craters (pockmarks) at the bottom of 3551 thermokarst lakes and 16 rivers. In addition, we have identified another 669 zones of explosive degassing in the coastal zones of the Kara Sea, mainly in gulfs, estuaries and bays. Taking into account the Yugorsky Peninsula and Bely Island, we have detected 6022 explosive degassing zones in the studying region, including 905 ones offshore. We have proved previously made conclusions that the Neytinsko-Seyakhinsky and Sabetta districts are the most gas-explosive. It is substantiated that possible intense natural degassing of the Earth, especially occurring in the process of degradation of subaquatic permafrost and dissociation of gas hydrates, can radically change the elastic-strength properties of bottom soil, while its saturation with gas can disrupt conditions for the construction of various objects, including underwater gas pipelines. Widespread gas blowouts in the north of Western Siberia with the formation of craters on land and offshore can lead to emergencies and even disasters at oil and gas industrial facilities and to fires in the tundra.

Active Vibration Avoidance Method for Variable Speed Welding in Robotic Friction Stir Welding Based on Constant Heat Input.

Robotic Friction Stir Welding (RFSW) technology integrates the advantages of friction stir welding and industrial robots, finding extensive applications and research in aerospace, shipbuilding, and new energy vehicles. However, the high-speed rotational process of friction stir welding combined with the low stiffness characteristics of serial industrial robots inevitably introduces vibrations during the welding process. This paper investigates the vibration patterns and impacts during the RFSW process and proposes an active vibration avoidance control method for variable speed welding based on constant heat input. This method utilizes a vibration feedback strategy that adjusts the spindle speed actively if the end-effector's vibration exceeds a threshold, thereby avoiding the modal frequencies of the robot at its current pose. Concurrently, it calculates and adjusts the welding speed of the robot according to the thermal equilibrium equation to maintain constant heat input. A simplified dynamic model of the RFSW robot was established, and the feasibility of this method was validated through simulation experiments. This study fills the gap in vibration analysis of RFSW and provides new insights into control strategies and process optimization for robotic friction stir welding.

New smart twisting active rotor (STAR): pretest predictions

A Mach-scaled model rotor with an active twist capability is in preparation for a wind tunnel test in the large low-speed facility of the German-Dutch wind tunnel (DNW) with international participation by the German Aerospace Center (DLR), US Army Combat Capabilities Development Command (DEVCOM) Aviation & Missile Center, National Aeronautics and Space Administration, French Aerospace Lab (ONERA), Korea Aerospace Research Institute, Konkuk University, Japan Aerospace Exploration Agency, Glasgow University, and DNW. To get the maximum benefit from the test and the most valuable data within the available test time, the tentative test matrix was covered by predictions of the partners, active twist benefits were evaluated, and support was provided to the test team to focus on the key operational conditions.

About Project EWALD (The first results of 2023)

The review provides an overview about the project in frame Horizon TMA MSCA Staff Exchange. The name of our project EWALD – Earth Observation for Early Warning of Land Degradation at Europe Frontier. The results of two visits on the exchange of project tasks are described. The first Staff Exchange between the Scientific Center for Aerospace Research of Earth, Kyiv, Ukraine (CASRE) and the University of Zhilina, Slovakia (Uniza). The second is between the Scientific Center for Aerospace Studies, Kyiv, Ukraine (CASRE) and the University of Kadi Ayad, Marrakesh, Morocco (UCAM). Annotation of the Scientific Report for 12 months of the EWALD project, which was positively adopted by the commission, was provided.

Korea Pathfinder Lunar Orbiter (KPLO) Operation: From Design to Initial Results

Korea Pathfinder Lunar Orbiter (KPLO) is South Korea’s first space exploration mission, developed by the Korea Aerospace Research Institute. It aims to develop technologies for lunar exploration, explore lunar science, and test new technologies. KPLO was launched on August 5, 2022, by a Falcon-9 launch vehicle from cape canaveral space force station (CCSFS) in the United States and placed on a ballistic lunar transfer (BLT) trajectory. A total of four trajectory correction maneuvers were performed during the approximately 4.5-month trans-lunar cruise phase to reach the Moon. Starting with the first lunar orbit insertion (LOI) maneuver on December 16, the spacecraft performed a total of three maneuvers before arriving at the lunar mission orbit, at an altitude of 100 kilometers, on December 27, 2022. After entering lunar orbit, the commissioning phase validated the operation of the mission mode, in which the payload is oriented toward the center of the Moon. After completing about one month of commissioning, normal mission operations began, and each payload successfully performed its planned mission. All of the spacecraft operations that KPLO performs from launch to normal operations were designed through the system operations design process. This includes operations that are automatically initiated post-separation from the launch vehicle, as well as those in lunar transfer orbit and lunar mission orbit. Key operational procedures such as the spacecraft’s initial checkout, trajectory correction maneuvers, LOI, and commissioning were developed during the early operation preparation phase. These procedures were executed effectively during both the early and normal operation phases. The successful execution of these operations confirms the robust verification of the system operation.

Powertrain Design For Small Scale Parallel Hybrid-Electric Test Bench

Parallel hybrid-electric propulsion systems for small scale unmanned aerial systems (UAS) when tested with an internal combustion engine are susceptible to damage due to increased torque compared to all-electric configurations. The University of Victoria Centre for Aerospace Research has conducted testing and identified several locations in the system for potential upgrades. One of the largest issues identified was the electromagnetic clutch’s inability to handle the torque of the Corvid-50 engine. Thus, a new clutch and powertrain system was specified which is better rated for combustion operation. Similar findings are reported based on testing performed at Ł-Institute of Aviation, where a hybrid-electric powertrain stand experienced torque spikes. The spike amplitude was several times higher than the nominal momentum of the ICE, given in the specification sheets. In result, at some working modes, a strong slippage of the clutch has been observed. It is also of highest importance to propose and test potential methods to minimize momentum influence to the powertrain. The goal is to increase robustness of such hybrid systems, and decrease the overall mass of the system.

Rapid, iterative design approach for preliminary configuration of a High Altitude, Long Endurance aircraft

This paper presents a rapid iterative design approach, used to develop a preliminary configuration of an Unmanned Aerial Vehicle (UAV), which is to perform a High-Altitude, Long Endurance (HALE) mission. First, based on a set of requirements, an initial aircraft concept is developed.The rapid iterative design approach revolves around an energy-based flight profile simulation, which is updated with an improved aerodynamic model of the aircraft during every iteration. An aircraft configuration is defined by a set of constant parameters. A corresponding flight profile consists of an altitude and velocity profile, as a function of time. The behaviour of the aircraft is simulated based on the specified flight profile.For sizing the aircraft components exposed to the airstream, the aerodynamic design phase aims to create an airframe which achieves the performance outlined in the flight performance simulation, utilizing the obtained aircraft parameters. Using the geometric data, a 3D-model of the aircraft is created, which is essential for the aircraft’s weight and balance calculations and for determining the airframe shape exposed to the airflow. A Computational Fluid Dynamics (CFD) simulation is conducted to obtain the actual aerodynamic characteristics of the airframe. If the performance requirement of the flight performance simulation is not met, another iteration of the aerodynamic design phase is required.The design framework stands out due to its rapid iteration capability, accessibility, and straightforward application, making it particularly advantageous for educational settings in which students engage with aircraft design. The approach aims to offer satisfactory results for an initial aircraft conceptualization.This design framework emerged from the DLR Design Challenge 2023, an annual competition hosted by the German Center for Aerospace Research, where student teams develop preliminary aircraft designs. This years challenge tasked the teams with designing an aircraft system to restore internet coverage over a disaster-affected region. The described approach was used to develop the Sentinel System of the DHBW Ravensburg team. However, the simulation and development process is not limited to applications within this challenge.

Chemical Kinetic Analysis of High-Pressure Hydrogen Ignition and Combustion toward Green Aviation

In the framework of the “Multidisciplinary Optimization and Regulations for Low-boom and Environmentally Sustainable Supersonic aviation” project, pursued by a consortium of European government and academic institutions, coordinated by Politecnico di Torino under the European Commission Horizon 2020 financial support, the Italian Aerospace Research Centre is computationally investigating the high-pressure hydrogen/air kinetic combustion in the operative conditions typically encountered in supersonic aeronautic ramjet engines. This task is being carried out starting from the zero-dimensional and one-dimensional chemical kinetic assessment of the complex and strongly pressure-sensitive ignition behavior and flame propagation characteristics of hydrogen combustion through the validation against experimental shock tube and laminar flame speed measurements. The 0D results indicate that the kinetic mechanism by Politecnico di Milano and the scheme formulated by Kéromnès et al. provide the best matching with the experimental ignition delay time measurements carried out in high-pressure shock tube strongly argon-diluted reaction conditions. Otherwise, the best behavior in terms of laminar flame propagation is achieved by the Mueller scheme, while the other investigated kinetic mechanisms fail to predict the flame speeds at elevated pressures. This confirms the non-linear and intensive pressure-sensitive behavior of hydrogen combustion especially in the critical high-pressure and low-temperature region which is hard to be described by a single all-encompassing chemical model.

A Structural Health Monitoring System for Bond Line Flaws Detection on a Full-Scale Wingbox Section Demonstrator

In recent years, there has been a significant increase in the use of structural health monitoring (SHM) technologies as systems for monitoring the integrity of aircraft’s structures. The use of compact and embeddable sensor networks, like the ones based on fibre optics (FO), is particularly attractive from the perspective of releasing an integrated structural system with intrinsic sensing capacity. Usually, an SHM system architecture is completed by a dedicated algorithm that processes the data gathered from the sensors to elaborate on the level of damage currently suffered by the structure, with the further possibility of providing information to the relevant specialists involved with its supervision. One of the main SHM applications that is attracting major interest is related to the inspection and detection of anomalies in bonded joints, which is extremely relevant in many composite realizations. Aeronautical regulations allow the use of bonded joints on an aircraft’s primary structure but require the implementation of a means to ensure their absolute safety, such as the introduction of further mechanical links aimed at stopping the propagation of a possible flaw or the availability of Non-Destructive Inspection (NDI) systems to prove the absence of relevant damaged areas. Generally, the main typical defects occurring during the manufacturing of bonded joints include adhesive curing, kissing bonds, poor porosity, and poor surface preparation. The current NDI systems more widely used and available to detect defects are still inaccurate due to the lack of standard procedures for the creation of representative defects in a controlled manner, which would allow for the development of reliable methodologies and tools able to ensure the safety of a bonded joint, as required by safety regulations. This paper shows the results relative to the implementation of an SHM system developed by the Italian Aerospace Research Centre (CIRA) aimed at monitoring the bonding lines between spar caps and panels of a typical composite wingbox section and detecting faults in location and length. The work was performed during typical ground static tests by using a fibre optical sensing network embedded within relevant adhesive paste layers during the manufacturing process of the structure. In the reported investigation, the SHM system assumed the function of an NDI system tool. The results show that the developed SHM system has good reliability for the detection of both the position and size of damage areas that were artificially inserted within the test article during the bonding phase, showing its potential as a candidate to be used as a tool to verify the conditions of a bonded joint, as required by aviation authorities’ regulations.

Hidden Markov Models and Flight Phase Identification

The use of Hidden Markov Models (HMMs) in segmenting flight phases is a compelling approach with significant implications for aviation and aerospace research. It leverages the temporal sequences of flight data to delineate various phases of an aircraft’s journey, making it a valuable tool for enhancing the anal- ysis of flight performance and safety. In this work, we implement a multivariate HMM to identify 6 flight phases: taxi, takeoff, climb, cruise, approach and rollout. We reach a median global accuracy of about 97% over a sample of several thousand flights with a very low number of decoded unlikely transitions. Regarding several performance metrics, our method is competitive with existing methods in the litera- ture, such as fuzzy logic. Additionally, it provides, for each point of the flight, a probability of belonging to each phase. Even in situations where there are missing values in the data, HMMs remain effective, ensuring that no critical information is lost during the segmentation process. We show that HMMs work seamlessly with the fine granularity of Flight Data Recorder (FDR) data. HMMs offer remarkable flex- ibility and adaptability, proving particularly effective when the number or order of phases is unknown or not predetermined, as is often the case with complex flight scenarios such as helicopter flights. This adaptability is crucial for handling the diverse range of flight operations that differ from one aircraft to another. An example is given with the segmentation of an Automatic Dependent Surveillance–Broadcast (ADS-B) helicopter flight operated by the Swedish National Police.

Remote methods of research assessment of the impact of agricultural economic processes on the environmental destruction of the territory

The research is about solving the problem of assessing the impact of agricultural processes on the environmental safety of territories. The research was carried out on the selection, uploading and processing of data from the aerial survey of the area. High-quality multispectral images of the study areas were selected in accordance with the time-related thematic tasks of aerospace research of agricultural plots. With the help of Google Earth Engine platform, JavaScript programming language, ENVI and ArcMap software complexes, segmentation of the image of space images was carried out on these images. Each of them has its own normalized color scale, and highlights certain objects with different colors. To improve the visualization of differences in images, the classification of index images using the Isodata method was studied.An Agrocontrol module for automated deciphering of agricultural was developed. The module allows to select agricultural land with further vectorization and the possibility of creating a geodatabase automatically. Based on results, preliminary cartographic models of the studied territories were created with the indication of land plots that are dangerous for the ecological state of the region and require more careful consideration.At the stage of practical research, an analysis of the received data, based on the agricultural holding "Mriya", was carried out on the scheme of crop rotation, hybrids of grain crops grown on the territory of the plots, the types and amount of fertilizers used, as well as the volume of the harvest for the last 5 years. This made it possible to prove the correlation between the chemical composition of the used fertilizers and the corresponding exceedances of the MPC norms of the soil samples chemical composition.

Computational Investigation of a Flexible Airframe Taxiing Over an Uneven Runway for Aircraft Vibration Testing

<div>Ground vibration testing (GVT) is an important phase of the development, or the structural modification of an aircraft program. The modes of vibration and their associated parameters extracted from the GVT are used to modify the structural model of the aircraft to make more reliable dynamics predictions to satisfy certification authorities. Due to the high cost and the extensive preparations for such tests, a new method of vibration testing called taxi vibration testing (TVT) rooted in operational modal analysis (OMA) was recently proposed and investigated by the German Institute for Aerospace Research (DLR) as alternative to conventional GVT. In this investigation, a computational framework based on fully coupled flexible multibody dynamics for TVT is presented to further investigate the applicability of the TVT to flexible airframes. The time domain decomposition (TDD) method for OMA was used to postprocess the response of the airframe during a TVT. The framework was then used to examine the impact of the taxiing speed, shock absorber damping coefficient, and bump geometry on the outcome of the computational TVT. It was found that higher taxiing speed does not necessarily mean a better quality TVT, and one must find the optimal speed using the computational framework presented herein. A higher shock absorber damping coefficient was found to increase the amplitude of the response during the TVT without significantly impacting the extracted modes and their frequencies. Also, the quality of the TVT was found to be inversely proportional to the curvature of the bump cross section. The proposed TVT computational framework is validated against the normal modal analysis technique and certain experimental data.</div>

Preface

The 2023 3rd International Conference on Mechatronics Technology and Aerospace Engineering (ICMTAE 2023) took place in Nanchang, China from September 15th to 17th, 2023, with the attendance of about 120 people. The main goal was to bring together scientists, researchers and developers engaged in mechatronics technology and aerospace engineering to bridge the gap between research needs and advanced technological solutions.ICMTAE 2023 focused on research areas such as Aerospace Structures, Aircraft Flight Dynamics, Precision Plastic Forming and Equipment Technology, Spacecraft Thermal Control Technology, Satellite Remote Sensing Technology, etc. The Conference provided an opportunity for researchers and related personnel to present their recent theoretical developments as well as practical applications, discuss unsolved problems, and find solutions to them. And it fostered research and development in mechatronics technology and aerospace engineering.The Program of the Conference was divided into three parts. First day of the Conference was devoted to registration for all the participants. The second day was mainly focused on keynote speeches, oral and poster presentations, as well as free discussion, etc. Academic investigation took place during the third day of the Conference.We would like to highlight the main developments presented at the Conference and introduce the prominent speakers. The keynote speakers of the Conference are Prof. David Doermann (University at Buffalo, US), Prof. Shaojiang Dong (Chongqing Jiaotong University, China), Prof. Baochang Zhang (Beihang University, China), Assoc. Prof. Liping Tang (Southwest Petroleum University, China), Prof. Shaojian Zhang (Nanchang University, China), Prof. Alam Md Mahbub (Harbin Institute of Technology (Shenzhen), China), respectively. They shared remarkable academic achievements in fields related to mechatronics technology and aerospace engineering, and discussed critical challenges and research directions within these domains, triggering heated discussion during the Conference and even in the break.In the final foreword, we would like to thank the members of Technical Program Committee and those of Organizing Committee for giving such a great opportunity for all of us to share scientific ideas and new developments at the Conference. Last but not the least, our special acknowledgement also goes to the editors and staff of Journal of physics: Conference Series, for their kindness and assistance in publishing this Conference Proceedings.The Committee of ICMTAE 2023List of Committee Member are available in this pdf.