Long-distance space systems generate enormous amounts of bigdata.These bigdata can be used to generate intelligent that can help us better understand the behavior of space systems.There is currently no such tool for p...Long-distance space systems generate enormous amounts of bigdata.These bigdata can be used to generate intelligent that can help us better understand the behavior of space systems.There is currently no such tool for precisely understanding and predicting the behavior of aerospace systems.In this study,three different aerospace systems are analyzed to build the respective artificial intelligence(AI)models to understand and predict their space behavior using the deep learning(DL)ecosystem.We studied the pulsed plasma thruster(PPT),an electric space propulsion system;the ARTEMIS-P1 spacecraft sensor array;and the UAV battery system.Three sets of comparative analyses are carried out to assess the model accuracy.A number of tests are utilized to assess and predict the exact physical behavior.The comparison and test results show that DLbased artificial models are capable enough(>99%)to mimic the exact system behaviors.This DL-based approach provides a novel means of understanding and predicting the real behavior of the aerospace systems.展开更多
Correction to:Aerospace Systems https://doi.org/10.1007/s42401-021-00089-8 Due to an unfortunate oversight the Eq.(8),Tables 2 and 4 has been given erroneously.It should read(Tables 2 and 4)
This paper introduces the current and new Satellite solutions for local and global tracking of ships for enhanced Ship Traffic Control(STC)and Ship Traffic Management(STM)at sea,in sea passages,approaching to the anch...This paper introduces the current and new Satellite solutions for local and global tracking of ships for enhanced Ship Traffic Control(STC)and Ship Traffic Management(STM)at sea,in sea passages,approaching to the anchorages and inside of seaports.All transportation systems and especially for maritime applications require far more sophisticated technology solutions,networks and onboard equipment for modern Satellite ship tracking than current standalone the US Global Positioning System(GPS)or Russian Global Navigation Satellite System(GLONAS)networks.The forthcoming Global Ship Tracking(GST),Satellite Data Link(SDL),Maritime GNSS Augmentation SDL(GASDL)and Maritime Satellite Automatic Dependent Surveillance-Broadcast(SADS-B)networks with Space and Ground Segment infrastructures for all three systems are discussed including benefits of these new technologies and solution for improved STC.展开更多
This study aimed to develop an approach for the understanding of the relationship between the contact interaction properties of lugs and their strength and mass to design efficient and lightweight lugs for aerospace c...This study aimed to develop an approach for the understanding of the relationship between the contact interaction properties of lugs and their strength and mass to design efficient and lightweight lugs for aerospace components.Lugs are crucial components of many aerospace mechanisms,and their properties are closely linked to their contact interactions with bushings.The approach taken in this study involved modeling the adhesive layer between the lug and bushing and optimizing the dimensions of the polymer lug and metal bushing to minimize the lug’s mass while maintaining adequate strength.Finite element analysis(FEA)and cohesive zone modeling(CZM)were used to simulate the effects of primary properties of contact interaction between lug body and bushing on the strength and mass of the lug,and both gradient-free and gradient-based optimization algorithms were employed to minimize the lug’s mass while maintaining its strength.The results showed that increasing shear and tensile contact strengths reduced the resulting mass,with tangential stress having the greatest effect.Moreover,increasing contact strength reduced the required dimensions of the lug and bushing,indicating the possibility of reducing the mass of the bushing–lug assembly using rougher bushings or ribbing.展开更多
The method presented in the article is based on a complex simulation model of gas-dynamic processes that take place in sectioned cabins during depressurization.This model allows the theoretical calculation of decompre...The method presented in the article is based on a complex simulation model of gas-dynamic processes that take place in sectioned cabins during depressurization.This model allows the theoretical calculation of decompression parameters(decompression time,cabin pressure,gas leakage from the cabin)depending on flight parameters and design features of the aircraft pressurised cabin(height,cabin volume,defect area,etc.)and determine the interdependence of pressure control parameters in critical operating modes.In computational experiments simulating decompression during depressurisation,the rate of cabin pressure drop as a function of the defect area,residual overpressure,decompression time,values of drops between compartment sections and mass flow rate during pressure changes;safe descent height and other parameters were determined.On the basis of computational experiments,a methodology for assessing the portability of decompression was developed,taking into account different levels of impact tolerance,allowing for a rational choice of hermetic and gas dynamic parameters of the cabin,as well as flight performance characteristics,taking into account the possible decompression of the cabin in flight or,conversely,with the specified parameters of the cabin and flight data at the design stage of the aircraft to assess the degree of danger in case of depressurization and to provide in advance a set of security measures.The transition for decompression safety analysis along the Chadov V.I.curve has advantages since it is applicable for various types of aircraft from spacecraft to aircraft and for various atmospheres with different combinations of pressures and concentrations.展开更多
The relevance of the transition from preventive maintenance of aviation equipment to predictive maintenance is substantiated.Various methods for building predictivemaintenance systems are considered:linear regression,...The relevance of the transition from preventive maintenance of aviation equipment to predictive maintenance is substantiated.Various methods for building predictivemaintenance systems are considered:linear regression,digital twins,machine learning,artificial neural networks,etc.It is shown that today there is no unified approach to the issues of predicting the technical condition of aircraft units based on data obtained during operation.An approach to the predictive analysis of failure and prefailure states of aircraft units using data obtained during their operation is proposed.An approach to the predictive analysis of failure and pre-failure states of aircraft units using data obtained during their operation is proposed.This approach is based on the joint application of such technologies and methods as a digital twin,linear regression,k-nearest neighbors,and event-based mathematical model.In the example of the analysis of a certain array of flight information obtained during the operation of the aircraft,the efficiency of the proposed approach is shown.展开更多
The manuscript discusses issues related to the use of mathematical modeling to substantiate the reliability and safety of the Superjet-100 aircraft during the emergency landing.The problem of the passenger airplane ai...The manuscript discusses issues related to the use of mathematical modeling to substantiate the reliability and safety of the Superjet-100 aircraft during the emergency landing.The problem of the passenger airplane airframe dynamic deformation in the landing with partially removed and released the landing gear under given initial conditions of touching the runway of the airfield.Confirmation of the adequacy and reliability of modeling and the accuracy of numerical results are considered.展开更多
This paper discusses the concept,general structure and functions of the Digital Platform for AircraftWeight Design,resulting from joined effort of several organizations with the leading role of theMoscow Aviation Inst...This paper discusses the concept,general structure and functions of the Digital Platform for AircraftWeight Design,resulting from joined effort of several organizations with the leading role of theMoscow Aviation Institute.The paper briefly describes the main tasks of weight analysis,methods of their solution,as well as the architecture of the created system.The structure and main components of aircraft weight model are presented.The paper reports the methods for developing a digital platform and its components using a project approach to the creation of information systems.In the Conclusion section,an assessment of the place of the developed digital platform in the training of specialists in the field of weight analysis and the possibility of its application to a real aircraft project is discussed.展开更多
The paper examines computational schemes for calculating the gradient of fluid dynamic quantities using grids of various types.The Green–Gaussmethod and the least squares method(LSM)used to develop a hybrid gradient ...The paper examines computational schemes for calculating the gradient of fluid dynamic quantities using grids of various types.The Green–Gaussmethod and the least squares method(LSM)used to develop a hybrid gradient calculation scheme are considered.It is demonstrated that the accuracy of gradient calculations may vary depending on the geometry of the control volume:the Green–Gauss method exhibits lower errors for strongly elongated thin cells and cells with curved edges,while for cells with orthogonal edges,it is preferable to use LSM.In order to improve the accuracy of calculations on unstructured grids,a hybrid gradient calculation scheme is proposed.This scheme computes the gradient by summing values derived from both the Green–Gauss method and LSM,given the weight function that incorporates the geometry of the control volume.The paper presents a formula for the weight function,which determines the contribution of each method within the hybrid scheme.The developed scheme is applied to the problem of supersonic flow around a cylinder with a needle on two unstructured grids,namely truncated hexagons and tetrahedra.It is shown that the proposed hybrid scheme reduces the error in calculating the aerodynamic characteristics of a streamlined object.展开更多
This article discusses the challenge of defining the geometry parameters for minimum mass stiffened aircraft panels made of composite materials.The thickness and size of the panel elements are unknown variables,and th...This article discusses the challenge of defining the geometry parameters for minimum mass stiffened aircraft panels made of composite materials.The thickness and size of the panel elements are unknown variables,and the optimal design is based on the condition of equal buckling.To solve this problem,the authors reduce the optimal design problem to the investigation of the weight function with multiple variables using analytical methods and refined buckling theory restrictions.The article introduces novel mathematical relationships for investigating the buckling of structurally anisotropic composite panels.The model couples bending with a plane stress state,resulting in a boundary value problem that involves solving an eighth-order partial differential equation within a rectangular field.To facilitate this,a software package was developed using theMATLAB operating environment.A set of computer programs was created to conduct multi-criteria optimization of the optimal design of structurally anisotropic aircraft composite panels.The study also examines the impact of design parameters on the critical buckling forces for both bending and torsion modes.The results of a new implementation of an optimal size-weight project for carbon-epoxy skin are given.A project with restrictions on the refined buckling theory for structurally anisotropic aircraft panels made of composite materials has been manipulated in terms of plies thicknesses.Optimal solutions are obtained.展开更多
The article deals with issues related to the application of modeling in the interests of aircraft certification.The technique of numerical flood modeling based on the numerical solution of Navier–Stokes equations wit...The article deals with issues related to the application of modeling in the interests of aircraft certification.The technique of numerical flood modeling based on the numerical solution of Navier–Stokes equations with a free surface is proposed.Verification of the technique was carried out on the tasks about water fluctuations in the tank under the action of gravity,cylinder movement in the liquid and ball drop in the liquid.In all cases,good convergence of simulation results with experimental data is shown.Validation of the method was performed on the task of sinking the vessel model with damage in the bottom and on board.Complex model hull movements were studied due to changing buoyancy properties as a result of water leakage inside the hull during the sinking.Comparison of calculated and experimental data shows their qualitative and quantitative consistency at the initial stage of the dive.By the example of modeling the flooding of the passenger aircraft model,the practical application of the developed method for certification is shown.It was found that at the initial moment of time after an unplanned landing on the water,the front and rear emergency exits are located above the waterline,and the buoyancy time of the aircraft is sufficient for its emergency exit.展开更多
Unmanned systems,capable of performing missions autonomously without human intervention or with human cooperation,have gained fast development in recent years.Aerospace unmanned systems(AUS)such as unmanned aircraft,s...Unmanned systems,capable of performing missions autonomously without human intervention or with human cooperation,have gained fast development in recent years.Aerospace unmanned systems(AUS)such as unmanned aircraft,spacecraft,near-space vehicles,service robots and manipulators play a key role for leading the development.To pursue reliability and autonomy for AUS,advanced or intelligent methodologies should be paid great attention,particularly on sensing and control that are critical issues of the unmanned systems for data processing and information decision.Also,to establish environmental adaptability,sensing and control need to be integrated into an intelligent framework for technical use.展开更多
This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilit...This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilitate morphing of the aerofoil shape in response to varying flight conditions.The NACA 2412 aerofoil is chosen for its camber adaptability,and CFD simulations are employed to assess the efficacy of FBM integration.The k-ω SST turbulence model is adopted for its ability to combine the strengths of the k-ω and k-ε models.The investigation encompasses a systematic exploration of geometric configurations,including trailing edge deflection at various chord lengths(0.6c,0.65c,0.70c,0.75c,and 0.80c)and deflection angles(4°,8°,and 12°).The results reveal that FBM aerofoils exhibit a consistent increase in maximum lift coefficient compared to conventional aerofoils across all deflection points and angles.Additionally,improvements in lift-todrag ratio are observed.Furthermore,the stalling angle remains unaffected by deflection point variations,while deflection angle increments lead to corresponding increases in maximum lift coefficient.The morphing aerofoil with a 0.60c deflection point demonstrates themost significant enhancement in maximum lift coefficient,achieving a 13% increase at a 12°deflection angle.These findings establish the aerodynamic efficiency of FBM aerofoils,characterized by superior lift-to-drag ratios and increased maximum lift coefficients.展开更多
Aerial GlidingVehicles(AGVs)play a crucial role in military operations owing to their versatile and multipurpose capabilities.Achieving accurate modeling of AGVs is paramount for understanding their behavior and optim...Aerial GlidingVehicles(AGVs)play a crucial role in military operations owing to their versatile and multipurpose capabilities.Achieving accurate modeling of AGVs is paramount for understanding their behavior and optimizing performance.While nonlinear models excel in capturing intricate phenomena,their complexity and computational demands make them less suitable for control system design.Hence,the utilization of linear models becomes imperative,offering a more comprehensible depiction of AGV dynamics and facilitating effective control system analysis and design.This study aims to develop a precise linear model for AGVs,providing a clear and interpretable framework for analysis and control system development.The constructed linear model serves as the foundation for devising various control strategies,significantly enhancing our comprehension of AGV behavior.Moreover,a comprehensive investigation into the AGV’s actuation system is conducted,employing advanced system identification techniques to establish an accurate actuation model.This phase is critical for ensuring the precise and efficient operation of the control system.The research encompasses the design and evaluation of two distinct AGV control strategies.Firstly,the Modified Proportional-Integral-Derivative(PI-D)controller,a conventional approach widely employed in control systems,serves as a stable benchmark for comparison.Secondly,the innovative Fuzzy-PI-D(F-PI-D)controller is introduced,harnessing fuzzy logic to augment control accuracy and responsiveness,particularly advantageous for complex systems like AGVs.To validate the performance of these control strategies,the study adopts the robust Processor in the Loop(PIL)methodology,integrating LabVIEW and an embedded device to conduct reliable testing and verification of control systems in a simulated environment.PIL offers the distinct advantage of evaluating control strategies under diverse conditions without the necessity of costly and hazardous real-world flight tests.Simulation outcomes furnish valuable insights into the efficacy of these control strategies.Significantly,the F-PI-D controller emerges as the preferred choice for enhancingAGVflight stability,precision,and responsiveness,thus contributing to the advancement ofAGVcontrol systems and their utility in military operations.展开更多
The article proposes a nonlinear optimal(H-infinity)control method for a hypersonic aerial vehicle(HSV).The dynamic model of the hypersonic vehicle undergoes approximate linearization around a temporary operating poin...The article proposes a nonlinear optimal(H-infinity)control method for a hypersonic aerial vehicle(HSV).The dynamic model of the hypersonic vehicle undergoes approximate linearization around a temporary operating point which is recomputed at each iteration of the control method.This operating point consists of the present value of the system’s state vector and of the last value of the control inputs vector that was applied on the HSV.The linearization relies on Taylor series expansion and on the computation of the associated Jacobian matrices.For the approximately linearized model of the hypersonic aerial vehicle,an optimal(H-infinity)feedback controller was designed.To compute the controller’s feedback gains,an algebraic Riccati equation had to be repetitively solved at each iteration of the control algorithm.The global asymptotic stability of the control method is proven through Lyapunov analysis.The control scheme remains robust against model uncertainties an external perturbations.展开更多
A methodology and results of fatigue life assessment of a structure containing continuous welding joint under random kinematic loading taking into account the influence of residual welding stresses have been presented...A methodology and results of fatigue life assessment of a structure containing continuous welding joint under random kinematic loading taking into account the influence of residual welding stresses have been presented.Realizations of random stress processes in the welding joint area and dependences for amplitude repeatability of reduced regular stress cycles have been constructed on the basis of numerical simulation.Characteristics of durability of the structure by two theories of accumulation of fatigue damages have been determined.Significant influence of residual welding stress levels on durability is shown.展开更多
Microelectromechanical systems’(MEMS)inertial measurement unit(IMU)is widely used in many scenarios for its small size,low weight,and low-power consumptions.However,it possesses relatively low positioning accuracy co...Microelectromechanical systems’(MEMS)inertial measurement unit(IMU)is widely used in many scenarios for its small size,low weight,and low-power consumptions.However,it possesses relatively low positioning accuracy compared with other high-grade IMUs,as errors accumulate quickly over time.This paper mainly focuses on the error characteristics of the gyro part of MEMS IMU by analyzing different kinds of error parameters.As there is no published standard for MEMS gyro error characterization,three dominant error parameters are selected and investigated,namely,scale factor,in-run bias stability,and angular random walk.In addition,Allan variance analysis is deployed as an important part of the scheme with relative results presented in this paper.Not only is theoretical analysis presented,but experimental verification is also carried out correspondingly with an ADIS16490 MEMS IMU.By comparison,we find that the results of in-run bias stability exceed the given features by up to ten times,while the rest of the results agree quite well with the given features.Possible reasons for the exceeding part are given.Calibration testing results not only provide concrete characterization for MEMS gyro errors,but also enhance the importance of overall calibration of MEMS IMU before use.展开更多
The electrical power subsystem(EPS)is one of the most critical subsystems in a spacecraft(SC).It provides the power needed for SC loads.Any failure in the EPS leads to SC mission failure.However,power budget calculati...The electrical power subsystem(EPS)is one of the most critical subsystems in a spacecraft(SC).It provides the power needed for SC loads.Any failure in the EPS leads to SC mission failure.However,power budget calculation is necessary for the analysis of the energy flow of the SC subsystems for in-orbit nominal operation and to ensure the adequacy of solar array(SA)power and storage battery capacity.The average power generated by SA of a SC should be carefully calculated to accurately estimate the energy budget process.Nevertheless,SC operational scenarios should be designed and then justified by the power budget calculation.The investigation of power capability is to satisfy the mission requirements for all nominal operating modes of the SC.The solar illumination and orbit shadow period,as well as EPS parameters including SA output power,bus voltage,load profile,and storage battery capacity graph during in-orbit nominal operation,are all taken into consideration.In this paper,a mission profile with the worst-case scenario(WCS)for EPS of a Low-earth orbit(LEO)Cube-Sat is demonstrated.Moreover,a novel energy management strategy is developed using artificial intelligence to justify the power budget calculation of SC EPS.展开更多
For a long time,space research has been a significant field,wherein the entire world has competed.The space research includes the ability to predict natural occurrences,such as weather changes,imminent draughts,and ts...For a long time,space research has been a significant field,wherein the entire world has competed.The space research includes the ability to predict natural occurrences,such as weather changes,imminent draughts,and tsunamis;ground surveying,communication systems,and,most recently,Cyber-Physical systems.The research in the domain is rising as a result of recent privatizations,such as SpaceX,Blue Origin,and others.With the aircraft communication and satellite systems advancement,new edge-cutting technologies in demand and new approaches to system components are necessary.Satellite communications,RADAR,DTH communication and astronomical observations all use the Ku band.High-resolution,shortrange and high-throughput radars operate in this frequency band.For airspace applications,low-profile antenna structures are critical.Microstrip antennas are utilized in a wide range of applications,including communication systems,satellites,aircrafts and medical devices.In this paper,a triband H shaped rectangular patch antenna with U in feed line is modeled and simulated for IEEE Ku band and EU J band applications.The proposed design has gain of 7.1 dB and return loss of−16.5 at 15 GHz frequency.The 3 dB angular width of main beam is 25.2°.Proposed antenna is multiband with useable bands of 6.1–6.6 GHz,10.9–11.1 GHz and 13.1–16 GHz and is capable for working in C band,X band and Ku or J band.The proposed antenna also shows ultra-wide band characteristics in its third band from 12.1 to 16 GHz.展开更多
This paper investigates the circulation,vorticity,and oblique shock waves generated by the airfoil with a spoiler.In this regard,the effects of the geometric parameters of the airfoils,such as the attack angle,shock w...This paper investigates the circulation,vorticity,and oblique shock waves generated by the airfoil with a spoiler.In this regard,the effects of the geometric parameters of the airfoils,such as the attack angle,shock wave angle,and Mach number etc.,are studied first.We have introduced the conformal mapping technique,which has helped transform the flow past a circular cylinder to an airfoil shape.Based on the Kutta conditions,we have solved the unsteady flow in the region of an airfoil.The results show that the flow patterns form a strong vortex after the spoiler when the attack angle of the airfoil changes from 0°to 10°at a spoiler angle of 85°.Furthermore,we have used the shock wave expansion method,and the deflection angle has been found to increase with increasing the shock wave angle for a certain Mach number.A higher shock wave angle is obtained for a lower Mach number at any deflection angle.In addition,it is also found that the post Mach number is decreased with the increasing shock wave angle for fixed pre Mach number.展开更多
文摘Long-distance space systems generate enormous amounts of bigdata.These bigdata can be used to generate intelligent that can help us better understand the behavior of space systems.There is currently no such tool for precisely understanding and predicting the behavior of aerospace systems.In this study,three different aerospace systems are analyzed to build the respective artificial intelligence(AI)models to understand and predict their space behavior using the deep learning(DL)ecosystem.We studied the pulsed plasma thruster(PPT),an electric space propulsion system;the ARTEMIS-P1 spacecraft sensor array;and the UAV battery system.Three sets of comparative analyses are carried out to assess the model accuracy.A number of tests are utilized to assess and predict the exact physical behavior.The comparison and test results show that DLbased artificial models are capable enough(>99%)to mimic the exact system behaviors.This DL-based approach provides a novel means of understanding and predicting the real behavior of the aerospace systems.
文摘Correction to:Aerospace Systems https://doi.org/10.1007/s42401-021-00089-8 Due to an unfortunate oversight the Eq.(8),Tables 2 and 4 has been given erroneously.It should read(Tables 2 and 4)
文摘This paper introduces the current and new Satellite solutions for local and global tracking of ships for enhanced Ship Traffic Control(STC)and Ship Traffic Management(STM)at sea,in sea passages,approaching to the anchorages and inside of seaports.All transportation systems and especially for maritime applications require far more sophisticated technology solutions,networks and onboard equipment for modern Satellite ship tracking than current standalone the US Global Positioning System(GPS)or Russian Global Navigation Satellite System(GLONAS)networks.The forthcoming Global Ship Tracking(GST),Satellite Data Link(SDL),Maritime GNSS Augmentation SDL(GASDL)and Maritime Satellite Automatic Dependent Surveillance-Broadcast(SADS-B)networks with Space and Ground Segment infrastructures for all three systems are discussed including benefits of these new technologies and solution for improved STC.
基金financially supported by the Russian Science Foundation,project no.22-79-10309.
文摘This study aimed to develop an approach for the understanding of the relationship between the contact interaction properties of lugs and their strength and mass to design efficient and lightweight lugs for aerospace components.Lugs are crucial components of many aerospace mechanisms,and their properties are closely linked to their contact interactions with bushings.The approach taken in this study involved modeling the adhesive layer between the lug and bushing and optimizing the dimensions of the polymer lug and metal bushing to minimize the lug’s mass while maintaining adequate strength.Finite element analysis(FEA)and cohesive zone modeling(CZM)were used to simulate the effects of primary properties of contact interaction between lug body and bushing on the strength and mass of the lug,and both gradient-free and gradient-based optimization algorithms were employed to minimize the lug’s mass while maintaining its strength.The results showed that increasing shear and tensile contact strengths reduced the resulting mass,with tangential stress having the greatest effect.Moreover,increasing contact strength reduced the required dimensions of the lug and bushing,indicating the possibility of reducing the mass of the bushing–lug assembly using rougher bushings or ribbing.
文摘The method presented in the article is based on a complex simulation model of gas-dynamic processes that take place in sectioned cabins during depressurization.This model allows the theoretical calculation of decompression parameters(decompression time,cabin pressure,gas leakage from the cabin)depending on flight parameters and design features of the aircraft pressurised cabin(height,cabin volume,defect area,etc.)and determine the interdependence of pressure control parameters in critical operating modes.In computational experiments simulating decompression during depressurisation,the rate of cabin pressure drop as a function of the defect area,residual overpressure,decompression time,values of drops between compartment sections and mass flow rate during pressure changes;safe descent height and other parameters were determined.On the basis of computational experiments,a methodology for assessing the portability of decompression was developed,taking into account different levels of impact tolerance,allowing for a rational choice of hermetic and gas dynamic parameters of the cabin,as well as flight performance characteristics,taking into account the possible decompression of the cabin in flight or,conversely,with the specified parameters of the cabin and flight data at the design stage of the aircraft to assess the degree of danger in case of depressurization and to provide in advance a set of security measures.The transition for decompression safety analysis along the Chadov V.I.curve has advantages since it is applicable for various types of aircraft from spacecraft to aircraft and for various atmospheres with different combinations of pressures and concentrations.
文摘The relevance of the transition from preventive maintenance of aviation equipment to predictive maintenance is substantiated.Various methods for building predictivemaintenance systems are considered:linear regression,digital twins,machine learning,artificial neural networks,etc.It is shown that today there is no unified approach to the issues of predicting the technical condition of aircraft units based on data obtained during operation.An approach to the predictive analysis of failure and prefailure states of aircraft units using data obtained during their operation is proposed.An approach to the predictive analysis of failure and pre-failure states of aircraft units using data obtained during their operation is proposed.This approach is based on the joint application of such technologies and methods as a digital twin,linear regression,k-nearest neighbors,and event-based mathematical model.In the example of the analysis of a certain array of flight information obtained during the operation of the aircraft,the efficiency of the proposed approach is shown.
文摘The manuscript discusses issues related to the use of mathematical modeling to substantiate the reliability and safety of the Superjet-100 aircraft during the emergency landing.The problem of the passenger airplane airframe dynamic deformation in the landing with partially removed and released the landing gear under given initial conditions of touching the runway of the airfield.Confirmation of the adequacy and reliability of modeling and the accuracy of numerical results are considered.
文摘This paper discusses the concept,general structure and functions of the Digital Platform for AircraftWeight Design,resulting from joined effort of several organizations with the leading role of theMoscow Aviation Institute.The paper briefly describes the main tasks of weight analysis,methods of their solution,as well as the architecture of the created system.The structure and main components of aircraft weight model are presented.The paper reports the methods for developing a digital platform and its components using a project approach to the creation of information systems.In the Conclusion section,an assessment of the place of the developed digital platform in the training of specialists in the field of weight analysis and the possibility of its application to a real aircraft project is discussed.
基金support of the national project“Science and Universities”within the framework of the pro-gram of the Ministry of Science and Higher Education of the Russian Federation for the creation of laboratories for young scientists No.FSWE-2024-0001(scientific topic:“Development of numerical methods,models and algorithms for description of fluid flows under natural conditions and normal and critical operating conditions of industrial facilities using exa-and zetta-scale supercomputers”)the program for development of the world-class scientific center“Supersonic”in 2020-2025 with the financial support of the Ministry of Science and Higher Education of the Russian Federation(Agreement dated April 20,2022,No.075-15-2022-309).
文摘The paper examines computational schemes for calculating the gradient of fluid dynamic quantities using grids of various types.The Green–Gaussmethod and the least squares method(LSM)used to develop a hybrid gradient calculation scheme are considered.It is demonstrated that the accuracy of gradient calculations may vary depending on the geometry of the control volume:the Green–Gauss method exhibits lower errors for strongly elongated thin cells and cells with curved edges,while for cells with orthogonal edges,it is preferable to use LSM.In order to improve the accuracy of calculations on unstructured grids,a hybrid gradient calculation scheme is proposed.This scheme computes the gradient by summing values derived from both the Green–Gauss method and LSM,given the weight function that incorporates the geometry of the control volume.The paper presents a formula for the weight function,which determines the contribution of each method within the hybrid scheme.The developed scheme is applied to the problem of supersonic flow around a cylinder with a needle on two unstructured grids,namely truncated hexagons and tetrahedra.It is shown that the proposed hybrid scheme reduces the error in calculating the aerodynamic characteristics of a streamlined object.
基金the implementation of the program for the creation and development of the World-Class Research Center“Supersonic”for 2020-2025 funded by the Ministry of Science and Higher Education of the Russian Federation(Grant agreement of April 20,2022№075-15-2022-309).
文摘This article discusses the challenge of defining the geometry parameters for minimum mass stiffened aircraft panels made of composite materials.The thickness and size of the panel elements are unknown variables,and the optimal design is based on the condition of equal buckling.To solve this problem,the authors reduce the optimal design problem to the investigation of the weight function with multiple variables using analytical methods and refined buckling theory restrictions.The article introduces novel mathematical relationships for investigating the buckling of structurally anisotropic composite panels.The model couples bending with a plane stress state,resulting in a boundary value problem that involves solving an eighth-order partial differential equation within a rectangular field.To facilitate this,a software package was developed using theMATLAB operating environment.A set of computer programs was created to conduct multi-criteria optimization of the optimal design of structurally anisotropic aircraft composite panels.The study also examines the impact of design parameters on the critical buckling forces for both bending and torsion modes.The results of a new implementation of an optimal size-weight project for carbon-epoxy skin are given.A project with restrictions on the refined buckling theory for structurally anisotropic aircraft panels made of composite materials has been manipulated in terms of plies thicknesses.Optimal solutions are obtained.
基金supported by grants of the President of the Russian Federation for state support of research projects by leading scientific schools of the Russian Federation(NSh-2485.2020.5)by the Russian Foundation for Basic Research(17-05-00067 and 20-05-00162).
文摘The article deals with issues related to the application of modeling in the interests of aircraft certification.The technique of numerical flood modeling based on the numerical solution of Navier–Stokes equations with a free surface is proposed.Verification of the technique was carried out on the tasks about water fluctuations in the tank under the action of gravity,cylinder movement in the liquid and ball drop in the liquid.In all cases,good convergence of simulation results with experimental data is shown.Validation of the method was performed on the task of sinking the vessel model with damage in the bottom and on board.Complex model hull movements were studied due to changing buoyancy properties as a result of water leakage inside the hull during the sinking.Comparison of calculated and experimental data shows their qualitative and quantitative consistency at the initial stage of the dive.By the example of modeling the flooding of the passenger aircraft model,the practical application of the developed method for certification is shown.It was found that at the initial moment of time after an unplanned landing on the water,the front and rear emergency exits are located above the waterline,and the buoyancy time of the aircraft is sufficient for its emergency exit.
文摘Unmanned systems,capable of performing missions autonomously without human intervention or with human cooperation,have gained fast development in recent years.Aerospace unmanned systems(AUS)such as unmanned aircraft,spacecraft,near-space vehicles,service robots and manipulators play a key role for leading the development.To pursue reliability and autonomy for AUS,advanced or intelligent methodologies should be paid great attention,particularly on sensing and control that are critical issues of the unmanned systems for data processing and information decision.Also,to establish environmental adaptability,sensing and control need to be integrated into an intelligent framework for technical use.
文摘This study investigates the potential of Fish Bone Morphing(FBM)technology for enhancing the aerodynamic performance of aerofoils.FBM is a bio-inspired concept that incorporates flexible structural elements to facilitate morphing of the aerofoil shape in response to varying flight conditions.The NACA 2412 aerofoil is chosen for its camber adaptability,and CFD simulations are employed to assess the efficacy of FBM integration.The k-ω SST turbulence model is adopted for its ability to combine the strengths of the k-ω and k-ε models.The investigation encompasses a systematic exploration of geometric configurations,including trailing edge deflection at various chord lengths(0.6c,0.65c,0.70c,0.75c,and 0.80c)and deflection angles(4°,8°,and 12°).The results reveal that FBM aerofoils exhibit a consistent increase in maximum lift coefficient compared to conventional aerofoils across all deflection points and angles.Additionally,improvements in lift-todrag ratio are observed.Furthermore,the stalling angle remains unaffected by deflection point variations,while deflection angle increments lead to corresponding increases in maximum lift coefficient.The morphing aerofoil with a 0.60c deflection point demonstrates themost significant enhancement in maximum lift coefficient,achieving a 13% increase at a 12°deflection angle.These findings establish the aerodynamic efficiency of FBM aerofoils,characterized by superior lift-to-drag ratios and increased maximum lift coefficients.
文摘Aerial GlidingVehicles(AGVs)play a crucial role in military operations owing to their versatile and multipurpose capabilities.Achieving accurate modeling of AGVs is paramount for understanding their behavior and optimizing performance.While nonlinear models excel in capturing intricate phenomena,their complexity and computational demands make them less suitable for control system design.Hence,the utilization of linear models becomes imperative,offering a more comprehensible depiction of AGV dynamics and facilitating effective control system analysis and design.This study aims to develop a precise linear model for AGVs,providing a clear and interpretable framework for analysis and control system development.The constructed linear model serves as the foundation for devising various control strategies,significantly enhancing our comprehension of AGV behavior.Moreover,a comprehensive investigation into the AGV’s actuation system is conducted,employing advanced system identification techniques to establish an accurate actuation model.This phase is critical for ensuring the precise and efficient operation of the control system.The research encompasses the design and evaluation of two distinct AGV control strategies.Firstly,the Modified Proportional-Integral-Derivative(PI-D)controller,a conventional approach widely employed in control systems,serves as a stable benchmark for comparison.Secondly,the innovative Fuzzy-PI-D(F-PI-D)controller is introduced,harnessing fuzzy logic to augment control accuracy and responsiveness,particularly advantageous for complex systems like AGVs.To validate the performance of these control strategies,the study adopts the robust Processor in the Loop(PIL)methodology,integrating LabVIEW and an embedded device to conduct reliable testing and verification of control systems in a simulated environment.PIL offers the distinct advantage of evaluating control strategies under diverse conditions without the necessity of costly and hazardous real-world flight tests.Simulation outcomes furnish valuable insights into the efficacy of these control strategies.Significantly,the F-PI-D controller emerges as the preferred choice for enhancingAGVflight stability,precision,and responsiveness,thus contributing to the advancement ofAGVcontrol systems and their utility in military operations.
基金Funding was provided by Unit of Industrial Automation/Industrial Systems Institute(Grant no.Ref 5352/Nonlinear Control and Filtering).
文摘The article proposes a nonlinear optimal(H-infinity)control method for a hypersonic aerial vehicle(HSV).The dynamic model of the hypersonic vehicle undergoes approximate linearization around a temporary operating point which is recomputed at each iteration of the control method.This operating point consists of the present value of the system’s state vector and of the last value of the control inputs vector that was applied on the HSV.The linearization relies on Taylor series expansion and on the computation of the associated Jacobian matrices.For the approximately linearized model of the hypersonic aerial vehicle,an optimal(H-infinity)feedback controller was designed.To compute the controller’s feedback gains,an algebraic Riccati equation had to be repetitively solved at each iteration of the control algorithm.The global asymptotic stability of the control method is proven through Lyapunov analysis.The control scheme remains robust against model uncertainties an external perturbations.
文摘A methodology and results of fatigue life assessment of a structure containing continuous welding joint under random kinematic loading taking into account the influence of residual welding stresses have been presented.Realizations of random stress processes in the welding joint area and dependences for amplitude repeatability of reduced regular stress cycles have been constructed on the basis of numerical simulation.Characteristics of durability of the structure by two theories of accumulation of fatigue damages have been determined.Significant influence of residual welding stress levels on durability is shown.
文摘Microelectromechanical systems’(MEMS)inertial measurement unit(IMU)is widely used in many scenarios for its small size,low weight,and low-power consumptions.However,it possesses relatively low positioning accuracy compared with other high-grade IMUs,as errors accumulate quickly over time.This paper mainly focuses on the error characteristics of the gyro part of MEMS IMU by analyzing different kinds of error parameters.As there is no published standard for MEMS gyro error characterization,three dominant error parameters are selected and investigated,namely,scale factor,in-run bias stability,and angular random walk.In addition,Allan variance analysis is deployed as an important part of the scheme with relative results presented in this paper.Not only is theoretical analysis presented,but experimental verification is also carried out correspondingly with an ADIS16490 MEMS IMU.By comparison,we find that the results of in-run bias stability exceed the given features by up to ten times,while the rest of the results agree quite well with the given features.Possible reasons for the exceeding part are given.Calibration testing results not only provide concrete characterization for MEMS gyro errors,but also enhance the importance of overall calibration of MEMS IMU before use.
文摘The electrical power subsystem(EPS)is one of the most critical subsystems in a spacecraft(SC).It provides the power needed for SC loads.Any failure in the EPS leads to SC mission failure.However,power budget calculation is necessary for the analysis of the energy flow of the SC subsystems for in-orbit nominal operation and to ensure the adequacy of solar array(SA)power and storage battery capacity.The average power generated by SA of a SC should be carefully calculated to accurately estimate the energy budget process.Nevertheless,SC operational scenarios should be designed and then justified by the power budget calculation.The investigation of power capability is to satisfy the mission requirements for all nominal operating modes of the SC.The solar illumination and orbit shadow period,as well as EPS parameters including SA output power,bus voltage,load profile,and storage battery capacity graph during in-orbit nominal operation,are all taken into consideration.In this paper,a mission profile with the worst-case scenario(WCS)for EPS of a Low-earth orbit(LEO)Cube-Sat is demonstrated.Moreover,a novel energy management strategy is developed using artificial intelligence to justify the power budget calculation of SC EPS.
文摘For a long time,space research has been a significant field,wherein the entire world has competed.The space research includes the ability to predict natural occurrences,such as weather changes,imminent draughts,and tsunamis;ground surveying,communication systems,and,most recently,Cyber-Physical systems.The research in the domain is rising as a result of recent privatizations,such as SpaceX,Blue Origin,and others.With the aircraft communication and satellite systems advancement,new edge-cutting technologies in demand and new approaches to system components are necessary.Satellite communications,RADAR,DTH communication and astronomical observations all use the Ku band.High-resolution,shortrange and high-throughput radars operate in this frequency band.For airspace applications,low-profile antenna structures are critical.Microstrip antennas are utilized in a wide range of applications,including communication systems,satellites,aircrafts and medical devices.In this paper,a triband H shaped rectangular patch antenna with U in feed line is modeled and simulated for IEEE Ku band and EU J band applications.The proposed design has gain of 7.1 dB and return loss of−16.5 at 15 GHz frequency.The 3 dB angular width of main beam is 25.2°.Proposed antenna is multiband with useable bands of 6.1–6.6 GHz,10.9–11.1 GHz and 13.1–16 GHz and is capable for working in C band,X band and Ku or J band.The proposed antenna also shows ultra-wide band characteristics in its third band from 12.1 to 16 GHz.
文摘This paper investigates the circulation,vorticity,and oblique shock waves generated by the airfoil with a spoiler.In this regard,the effects of the geometric parameters of the airfoils,such as the attack angle,shock wave angle,and Mach number etc.,are studied first.We have introduced the conformal mapping technique,which has helped transform the flow past a circular cylinder to an airfoil shape.Based on the Kutta conditions,we have solved the unsteady flow in the region of an airfoil.The results show that the flow patterns form a strong vortex after the spoiler when the attack angle of the airfoil changes from 0°to 10°at a spoiler angle of 85°.Furthermore,we have used the shock wave expansion method,and the deflection angle has been found to increase with increasing the shock wave angle for a certain Mach number.A higher shock wave angle is obtained for a lower Mach number at any deflection angle.In addition,it is also found that the post Mach number is decreased with the increasing shock wave angle for fixed pre Mach number.
