Aerospace Science and Technology最新文献

{"title":"Use of Multi-Test Strategy to Obtain Heat Transfer Coefficient and Adiabatic Wall Temperature Simultaneously in Shock Tunnel for Transonic Flow over a Flat Plate","authors":"Wei Zeng (Doctoral student),&nbsp;Yizhi Fang (Doctoral student),&nbsp;Haiteng Ma (Associate Professor)","doi":"10.1016/j.ast.2025.110057","DOIUrl":"10.1016/j.ast.2025.110057","url":null,"abstract":"<div><div>Shock tunnel is a viable facility to produce high-temperature environment, but its heat transfer experimentation is in general challenged by the extremely short test duration (several milliseconds), and one particular problem is the determination of adiabatic wall temperature in such short time. Current technique of transient thermal measurement in shock tunnel (single-test method) prescribes adiabatic wall temperature to be a constant, which is calculated mostly from the analytical solution for high-speed boundary layer on a flat plate under several ideal assumptions, but fails to account for realistic effects in shock tunnel testing. To address this issue, this paper introduced a new method (multi-test strategy) to obtain adiabatic wall temperature and heat transfer coefficient simultaneously in shock tunnel, by linearly regressing data pairs of wall temperature and heat flux from runs with multiple initial wall temperatures. Transient thermal measurements were conducted at seven initial wall temperatures of the flat plate, over which a transonic flow is established in shock tunnel. Wall temperature history is recorded by coaxial thermocouple during each test, from which heat flux is reconstructed. Data pairs of wall temperature and heat flux from runs with all the seven initial wall temperatures are used in multi-test strategy, while those from the run at only one initial wall temperature are employed in single-test method. It is found that the streamwise distribution of heat transfer coefficient is qualitatively different between the two methods, due to the distinct principle to determine adiabatic wall temperature. Quantitatively, heat transfer coefficient from multi-test strategy is generally higher than that from single-test method owing to the lower adiabatic wall temperature than the prescribed value. A correction to multi-test strategy is proposed to align the heat transfer coefficient and adiabatic wall temperature more closely with the results from single-test method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110057"},"PeriodicalIF":5.0,"publicationDate":"2025-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143418960","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Model incremental learning of flight dynamics enhanced by sample management","authors":"Tengjie Zheng,&nbsp;Lin Cheng,&nbsp;Shengping Gong,&nbsp;Xu Huang","doi":"10.1016/j.ast.2025.110049","DOIUrl":"10.1016/j.ast.2025.110049","url":null,"abstract":"<div><div>In this study, our focus is on investigating the utilization of real-time collected flight data to enhance the accuracy of dynamical models that are traditionally dominated by offline first-principles. The necessity and practicality of data-driven model correction/learning has been recognized in an increasing number of aerospace and industrial control scenarios. However, the issue of learning stability should be specifically emphasized. Thus, we propose an online incremental learning method for dynamical models that incorporates first-principle knowledge and data-driven correction mechanisms. To the best of our knowledge, this is the first work in which the convergence conditions of closed-loop learning systems involving Gaussian Process (GP) models are provided. Moreover, we propose an online sample management algorithm to optimize the spatial and temporal distribution of dataset samples for model training, thereby improving the model's ability to fit globally on the whole sample space. Finally, we provide three simulation examples to demonstrate the effectiveness of the proposed techniques, resulting in a data-driven model incremental learning algorithm with promising potential applications in adaptive control, optimal control, and model-based reinforcement learning.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110049"},"PeriodicalIF":5.0,"publicationDate":"2025-02-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143430271","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Adaptive actor-critic network-based appointed-time attitude stabilization under actuator faults and dual-state constraints","authors":"Zhongbo Chen ,&nbsp;Xuebo Yang ,&nbsp;Hanlin Dong","doi":"10.1016/j.ast.2025.110051","DOIUrl":"10.1016/j.ast.2025.110051","url":null,"abstract":"<div><div>In this article, adaptive dynamic programming (ADP)-based attitude stabilization is achieved in the presence of external disturbances, actuator failures, and kinematic constraints. First, we design a new appointed-time convergence performance constraint function to constrain the transient and steady-state performance of attitude and angular velocity. Next, the attitude control system with state constraints is transformed into an unconstrained system through state mapping. Then, combining the extended state observer (ESO) and the integral sliding mode (ISM), an adaptive integral sliding mode controller is designed to eliminate disturbances and actuator failures to ensure that the system can move toward the nominal surface. Finally, the actor-critic network employs the adaptive weight update law to approximate the optimal value function and the optimal controller of the nominal system, respectively, without relying on the persistent excitation (PE) condition. The uniformly ultimately bounded (UUB) stability of the nominal system is obtained via the Lyapunov method. Moreover, it can be found from the numerical simulation that under the proposed control scheme, the attitude control system's attitude angle and attitude angular velocity both meet the performance constraints, and the cost consumption is much lower than other control schemes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110051"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143437903","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Aerodynamics and ice tolerance of the large passenger aircraft advanced rear end forward swept horizontal tailplane with leading edge extension","authors":"James H. Page ,&nbsp;Isik Ozcer ,&nbsp;Alessandro Zanon ,&nbsp;Michele De Gennaro ,&nbsp;Raul C. Llamas-Sandin","doi":"10.1016/j.ast.2025.110018","DOIUrl":"10.1016/j.ast.2025.110018","url":null,"abstract":"<div><div>The advanced rear end (ARE) forward swept horizontal tailplane (FSHT) may allow a more compact empennage, reducing weight, drag, and, thus, fuel burn. Large passenger aircraft (LPA) empennages are typically sized up to satisfy performance and handling requirements under critical icing conditions. One such requirement is sufficient low speed (negative) lifting performance for the roundout manouevre following 45 min of flight in a holding pattern in icing conditions. The FSHT geometry has the possibility to include a leading edge extension (LEX) in the droplet shadow zone of the fuselage contraction where it could have some protection from icing, allowing tail size reduction. This paper addresses the topics of three-dimensional inflight icing simulation and CFD analysis of iced tails in the industrial environment, inflight icing of the FSHT with LEX, and lifting performance and aerodynamics of the iced FSHT with LEX. Full aircraft air flow and droplet calculations were carried out using the finite element method with solution error-based anisotropic mesh adaptation, on a single geometry, to calculate inlet and outlet condition profiles for an empennage-only icing simulation domain. Full aircraft-representative, three-dimensional, multishot icing simulations were then carried out to calculate 45 min ice accretion in a holding pattern in Appendix C glaze icing conditions, for eight different FSHT geometries. Following that, three-dimensional CFD with the k-ω SST turbulence model was used to calculate the lifting performance and aerodynamics of each geometry, with and without ice, in a roundout flight condition from 0° to -15° angle of attack (AoA). The practice and feasibility of using three-dimensional multishot icing simulation in the LPA design environment are described. Analysis is then presented for three variations in FSHT forward sweep with a fixed gothic LEX, three variations in LEX chord with a 10° FSHT, and three variations in LEX span with a 10° FSHT. Iced lifting performance is found to correlate positively with forward sweep and exhibit a more nuanced relationship to LEX chord and span. In addition to the expected LEX vortex, a tip leading edge vortex is identified as a key ice tolerant FSHT lifting flow mechanism. Detailed flow field analysis provides insight into the complex interplay between the two flow mechanisms and the implications for iced lifting performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110018"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143593809","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"6-D pose tracking within a quadplane swarm using particle filter with KAPAO network and 3D-error enhancement","authors":"Chujun Li ,&nbsp;Xiangpeng Xu ,&nbsp;Sheng Zhuge ,&nbsp;Bin Lin ,&nbsp;Xia Yang ,&nbsp;Xiaohu Zhang","doi":"10.1016/j.ast.2025.110048","DOIUrl":"10.1016/j.ast.2025.110048","url":null,"abstract":"<div><div>Accurately measuring the relative 6-D pose between unmanned aerial vehicles (UAVs) within a formation is fundamental for UAV swarms to execute tasks effectively. Existing monocular 6-D pose estimation and tracking methods struggle with pose ambiguity when UAVs are widely spaced. This paper proposes an improved particle filtering method for quadplane 6-D pose tracking to eliminate ambiguity and enhance accuracy. Our method integrates a KAPAO network as an observation model to handle complex image backgrounds, combined with a constant velocity motion model to adapt to the diverse motion states of quadplanes. We utilize the 3D object-space collinearity errors for weight updating to enhance adaptability to the images captured by an airborne zoom camera and fully leverage quadplane motion information to prevent algorithm divergence. Both point and line errors in updating the weights for position and orientation separately help mitigate their mutual coupling effects, ultimately enhancing overall accuracy. Our approach performs exceptionally well on quadplane datasets by eliminating pose ambiguity and maintaining the upper bounds and medians of the 3D error box plots respectively below 3.19 and 0.96 meter for distances ranging from 31.6 to 100.0 meters between two quadplanes. Furthermore, the ADD and Rete accuracy indicators are also <span><math><mn>1</mn><mo>−</mo><mn>3</mn></math></span> times higher than some top-tier methods, with a runtime of just 35.2 milliseconds. This positions it as a promising solution for practical air-to-air quadplane missions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110048"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143419234","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Singularity-avoidance adaptive interval type-2 fuzzy predefined-time cooperative formation control for multiple QUAVs","authors":"Xiaona Song ,&nbsp;Chenglin Wu ,&nbsp;Choon Ki Ahn ,&nbsp;Shuai Song ,&nbsp;Binbin Yan","doi":"10.1016/j.ast.2025.110041","DOIUrl":"10.1016/j.ast.2025.110041","url":null,"abstract":"<div><div>In this work, the singularity-avoidance predefined-time cooperative formation control for multiple quadrotor unmanned aerial vehicles with preassigned accuracy is investigated. First, an improved fixed-time performance function is introduced in the formation design framework to achieve the convergence constraint on the formation neighborhood tracking error at a specified time. Then, interval type-2 fuzzy logic systems are utilized to approximate the nonlinear function on the controlled vehicles, and a compensation function is presented to weaken the impact of approximation errors and unknown disturbances. In contrast to traditional dynamic surface control schemes, a predefined-time filter is devised to guarantee that the filter error converges within a predefined time. Furthermore, a singularity-avoidance interval type-2 fuzzy predefined-time formation control protocol is developed to achieve the predefined time convergence property of the formation tracking error and to eliminate the difficulty of adjusting the settling time existing in finite/fixed-time control strategies. The boundedness of all signals in the closed-loop system is assured by stability analysis. Finally, the practicality and superiority of the presented control protocol are verified by simulation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110041"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402512","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Adaptive fuzzy finite-time control for a QUAV with tracking error constraints and unknown actuator faults","authors":"Fangzheng Li ,&nbsp;Zhen Liu ,&nbsp;Quanmin Zhu","doi":"10.1016/j.ast.2025.110054","DOIUrl":"10.1016/j.ast.2025.110054","url":null,"abstract":"<div><div>This article presents an adaptive finite-time (FT) tracking control strategy for a quadrotor unmanned aerial vehicle (QUAV) under asymmetric time-varying tracking error constraints (TECs) and unknown actuator faults (AFs). Firstly, a fractional-order nonsingular terminal sliding surface is designed and the fuzzy logic system (FLS) approximation mechanism is employed to cope with the unknown AFs and nonlinear perturbations, then relevant adaptive updating laws are provided to generate the estimation of the unknown bounds. In addition, TECs are adopted to ensure specified transient performance of the QUAV system. Specifically, an asymmetric initial state-independent barrier function is constructed, yielding a modified output constraint method, which eliminates the initial condition-dependent restriction in most of existing reports on TECs. Further, based on the synthesized adaptive controller and FT stability theory, the reachability of the designed sliding surface is achievable, and the FT convergence of the tracking error can be actualized then. Eventually, simulation results reveal that the developed control strategy can keep the tracking errors within the predefined boundaries and achieve the FT tracking with high accuracy in spite of unknown AFs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110054"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143419236","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Dynamic event-triggered prescribed-time optimized backstepping attitude consensus tracking control for multiple spacecrafts","authors":"Ying Zhou ,&nbsp;Yuanxin Li ,&nbsp;Zhongsheng Hou ,&nbsp;Choon Ki Ahn","doi":"10.1016/j.ast.2025.110050","DOIUrl":"10.1016/j.ast.2025.110050","url":null,"abstract":"<div><div>This paper aims to address the event-triggered optimized attitude consensus tracking control problem for multiple spacecraft with prescribed setting time. To ensure the convergence of the consensus tracking error within a prescribed time, a transformation function is constructed by using a time-varying constraining function related to the prescribed time and accuracy. To optimize control performance, a class of Hamilton-Jacobi-Bellman (HJB) equations are constructed to derive a reinforcement learning (RL)-based optimal control law, where the fuzzy logic system (FLS) is employed to approximate the optimal solution within the actor-critic architecture. In addition, the dynamic event-triggered mechanism is adopted for the controller to decrease communication resource utilization. Based on the Lyapunov stability analysis, the consensus tracking error is proved to be semi-globally uniformly ultimately bounded (SGUUB) with adjustable error bounds. Finally, a simulation example is given to demonstrate the effectiveness of the proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110050"},"PeriodicalIF":5.0,"publicationDate":"2025-02-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402743","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Aircraft dynamics modeling at high angle of attack incorporating residual transformer autoencoder and physical mechanisms","authors":"Jinyi Ma,&nbsp;Qianqian Zhu,&nbsp;Tao Xue,&nbsp;Jianliang Ai,&nbsp;Yiqun Dong","doi":"10.1016/j.ast.2025.110045","DOIUrl":"10.1016/j.ast.2025.110045","url":null,"abstract":"<div><div>Aircraft dynamics modeling is an important part of advanced control law design and flight safety. To address the challenge of longitudinal dynamics modeling using a small amount of flight test data under high-angle-of-attack (AOA) conditions, we propose an effective approach that integrates machine learning with physical mechanisms. First, a low-fidelity aircraft dynamics model based on physical analysis is established. Second, a Residual Transformer (ResTrans) autoencoder is designed to extract temporal and spatial features from flight motion history under high-AOA conditions. These features are then used to compensate for the modeling errors of the low-fidelity model through a deep neural network (DNN)-based fusion module, resulting in a high-fidelity aircraft dynamics model. Moreover, a physics-informed closed-loop multi-step dynamics evolution (PI-CMDE) paradigm is developed for constructing loss functions, ensuring stable and efficient parameter optimization of the high-fidelity model. Finally, a simulation model of a scaled F-16 aircraft is used to generate a small set of high-AOA flight test data for training and testing the high-fidelity model. Experimental results demonstrate that, compared to three representative aircraft dynamics modeling baseline methods, the proposed approach achieves higher modeling accuracy and better generalization performance, highlighting its advanced capabilities.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110045"},"PeriodicalIF":5.0,"publicationDate":"2025-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402742","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Attitude control of variable swept-wing aircraft: A novel composite control strategy","authors":"Xiaoming Chen,&nbsp;Lisha Meng,&nbsp;Jiaji Liu,&nbsp;Danqing Shen","doi":"10.1016/j.ast.2025.110043","DOIUrl":"10.1016/j.ast.2025.110043","url":null,"abstract":"<div><div>To address the complex issues of discontinuous disturbances, parameter uncertainties, actuator deadzone, and saturation nonlinearity in Variable Swept-Wing Near Space Vehicles (NSV), an attitude controller combining reinforcement learning and adaptive switching sliding mode control is proposed, along with an adaptive threshold event-triggered mechanism to reduce the actuator executing frequency. Firstly, the motion characteristics of the Variable Swept-Wing NSV across the full range of operating modes are modeled as a nonlinear switched system. Secondly, a nonlinear switched disturbance observer is employed to estimate the composite disturbances caused by discontinuous disturbances and parameter uncertainties. By introducing a deadzone right inverse function and designing an auxiliary system, the composite nonlinearity of the actuator are effectively addressed. An adaptive multi-modal switching sliding mode controller is then proposed based on the backstepping method to achieve basic control. Subsequently, considering the higher dimensionality of aerodynamic control surfaces and the increased complexity of aerodynamic characteristics in the subsonic mode, which imposes stricter control requirements, a reinforcement learning-based controller is designed. Leveraging the self-learning and optimization capabilities of reinforcement learning, which does not rely on an accurate model, the controller achieves end-to-end control of the horizontal canard. Finally, an event-triggered mechanism with an adaptively varying threshold is also developed. The multi-Lyapunov stability theory and the average dwell-time theory are employed to guarantee the stability of the closed-loop nonlinear switched system while excluding the undesired Zeno behavior. Simulations and comparative experiments demonstrate that the proposed method achieves superior tracking accuracy and control performance, while the adaptive threshold event-triggered mechanism effectively reduces data transmission.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110043"},"PeriodicalIF":5.0,"publicationDate":"2025-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143418961","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}