Aerospace Science and Technology最新文献

{"title":"Numerical study on the control of flow in the rudder-body junction region using High-energy jet array","authors":"Yi Zhou,&nbsp;Zhenbing Luo,&nbsp;Qiang Liu,&nbsp;Yan Zhou,&nbsp;Wei Xie","doi":"10.1016/j.ast.2025.110335","DOIUrl":"10.1016/j.ast.2025.110335","url":null,"abstract":"<div><div>The maneuverability of high-speed aircrafts in flight needs to be improved. However, conventional control methods for rudder deflection have disadvantages such as poor control effect and low control efficiency. In this paper, the ability of using high energy jet arrays to change the structure of the rudder plate flow field and enhance the control efficiency of the rudder is numerically simulated and analyzed. The high-energy jet arrays are arranged along the flow direction on the windward side of the rudder, which are the upstream high-energy jet array, the midstream high-energy jet array, and the downstream high-energy jet array. The control effects of three position high energy jet arrays were compared and analyzed. The results show that the vortex pair behind the upstream high-energy jet array is fully developed due to its proximity to the leading edge of the rudder, resulting in an increase in the area of the low-pressure region behind the exit of the jet, and that the pressure on the rudder varies significantly with time. The high energy jet arrays in the midstream and downstream do not cause significant periodic changes in the pressure on the windward side of the rudder, while the position close to the downstream allows the two controls to raise the area of the high-pressure region on the windward side of the rudder more and reduce the area of the low-pressure region caused by the vortex pair behind the jet. But with high-energy jet array control, jets close to the area of the plate create additional side forces on the surface of the plate. In this study, numerical simulations were used to analyze the effect of applying high-energy jet arrays in different flow direction positions to improve the effectiveness of high-speed aircraft rudders. In this paper, a new concept of using active flow control method to improve the control efficiency of high-speed aircrafts is proposed. These findings can provide a reference for future research on rudder efficiency of high-speed aircraft.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110335"},"PeriodicalIF":5.0,"publicationDate":"2025-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144125294","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":"Optimization of three-dimensional waypoint ordering for energy-optimal multirotor operation","authors":"Nicolas Michel ,&nbsp;Ayush Patnaik ,&nbsp;Peng Wei ,&nbsp;Zhaodan Kong ,&nbsp;Xinfan Lin","doi":"10.1016/j.ast.2025.110348","DOIUrl":"10.1016/j.ast.2025.110348","url":null,"abstract":"<div><div>Air mobility enabled by multirotor aircraft is an emerging transportation mode with wide real-world applications. Maximum range and flight duration are critical aspects of the performance, governed by the vehicle energy efficiency. This paper studies the energy-optimal planning of the multirotor, which aims at finding the optimal ordering of waypoints with the minimum energy consumption for missions in 3D space. The study uses a system model capturing first-principle energy dynamics of the multirotor. It is found that in most cases (up to 95%) the energy-optimal order is different from the minimum-distance order, which is the solution to the traditional traveling salesman problem. The difference can be as high as 14.9%, with the average at 1.6%-3.4% and 90th percentile at 3.8%-6.6% depending on the range and other parameters of the mission. To validate these results, three sample missions were tested in real-world flight, and the minimum-energy order was shown to reduce energy cost by 3.9%-9.4% relative to the minimum-distance order. These results were used to identify and explain the key features of the minimum-energy order by correlating to the underlying flight energy dynamics. It is shown that instead of minimizing the distance, coordination of vertical and horizontal motion to promote aerodynamic efficiency is the key to optimizing energy consumption. In addition, the combination of minimum-energy order planning and energy-optimal trajectory control could achieve energy savings of up to 29.9% over the combined minimum-distance order and a commonly used type of baseline controller.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110348"},"PeriodicalIF":5.0,"publicationDate":"2025-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144138901","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":"A homogenized plate model for dual-scale analysis of integrated thermal protection system panels","authors":"Nazim Khan,&nbsp;Pritam Chakraborty","doi":"10.1016/j.ast.2025.110345","DOIUrl":"10.1016/j.ast.2025.110345","url":null,"abstract":"<div><div>Sandwich structure with corrugated core configuration is amicable for Integrated Thermal Protection System (ITPS) panels of Reusable Launch Vehicles (RLVs), since it can provide sufficient stiffness, strength and thermal insulation. These panels can experience spatial and temporal variation of temperature resulting in vehicle location dependent transient stresses. Thus, spatially optimized design of sandwich structure configuration and properties is desirable, which can be achieved using Finite Element Method (FEM) analysis. However, detailed FEM analysis of ITPS panels along with sandwich structure geometry is computationally intractable due to the vastly different length scales. To address this challenge, a plate model for ITPS panels with properties obtainable from direct homogenization is proposed in this work. The novelty of this work lies in extending the shear and normal deformation plate theories to incorporate location dependent thickness-wise temperature distribution, thus significantly reducing the number of sandwich structure-scale simulations to obtain the homogenized properties. An unit cell approach has also been devised to obtain the sandwich structure-scale stress distribution from the plate-level responses. Simulations with different temperature distributions are performed to elucidate the accuracy of the homogenized First-order Shear and Second-order Normal Deformation Theory (FSSNDT) based plate model to capture both the deflection and local stresses in the sandwich structure.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110345"},"PeriodicalIF":5.0,"publicationDate":"2025-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117115","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":"Enhance uniform observation ability of remote sensing constellation using ground track configuration allocation","authors":"Jihe Wang ,&nbsp;Tianjie Liu ,&nbsp;Chengxi Zhang ,&nbsp;Jinxiu Zhang","doi":"10.1016/j.ast.2025.110344","DOIUrl":"10.1016/j.ast.2025.110344","url":null,"abstract":"<div><div>Conventional ground track-based constellation designs focus on the distribution of ascending and descending nodes, addressing only the relative spacing of ground tracks. This study for the first time introduces an analytic constellation design framework that allocates ground track configurations by examining the distribution of independent intersection points, pioneering a comprehensive analysis of ground track configurations and their impact on coverage performance. This solution enables the fulfillment of mission objectives with a minimal number of satellites. Furthermore, by optimizing the initial positions of satellites within designated ground track configurations, this approach ensures greater uniformity in average revisit time (ART) and maximum revisit time (MRT). The proposed method significantly reduces the design search space and enhances efficiency. Simulation results demonstrate a 31% reduction in satellite count and substantial decreases in the standard deviations of ART and MRT by 52.99% and 66.53%, respectively, compared to genetic algorithm-based optimization methods.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110344"},"PeriodicalIF":5.0,"publicationDate":"2025-05-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117119","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":"Autonomous maneuver decision-making algorithm for UCAV based on generative adversarial imitation learning","authors":"Chaoran Jiang,&nbsp;Heng Wang,&nbsp;Jianliang Ai","doi":"10.1016/j.ast.2025.110313","DOIUrl":"10.1016/j.ast.2025.110313","url":null,"abstract":"<div><div>This paper studies the autonomous maneuver decision-making problems of unmanned combat aerial vehicles (UCAVs) engaged in one-to-one within visual range (WVR) air combat. Based on expert experience, we construct a relative situation-based air combat maneuver decision tree to generate expert databases. A generative adversarial imitation learning (GAIL) based decision-making method is developed for UCAVs, using the expert database for decision support. Initially, the one-to-one air combat simulation environment based on the observation-orientation-decision-action (OODA) loop is established, focusing on the six-degree-of-freedom (6DoF) UCAV model, air combat model, missile hit probability model, and maneuver choose model. Subsequently, an autonomous maneuver decision-making method based on the GAIL algorithm is proposed to make autonomous maneuver decisions under the use of expert databases. The training process of the GAIL algorithm combines the imitation learning method with the Markov decision process to account for the lack of expert policy guidance where explicit reward functions are unknown or not explicitly defined. Finally, comparative simulation experiments are conducted in two databases, benchmarking the proposed GAIL algorithm against the behavior cloning (BC) algorithm and the polynomial regression (PR) algorithm to validate its effectiveness. The results demonstrate that the proposed GAIL method exhibits better learning performance and efficiency compared to other methods. These results indicate that the proposed method enables autonomous maneuver decision learning from expert databases under a WVR one-to-one air combat environment.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"164 ","pages":"Article 110313"},"PeriodicalIF":5.0,"publicationDate":"2025-05-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144146974","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":"Effects of transition on the near-field unsteady flows and far-field noise past a three-element wing","authors":"Shihe Jia,&nbsp;Zhixiang Xiao","doi":"10.1016/j.ast.2025.110353","DOIUrl":"10.1016/j.ast.2025.110353","url":null,"abstract":"<div><div>The laminar–turbulent transition has an important effect on the near-field flows past high-lift devices, but its effects on the far-field noise are not fully clear. To explore the influence of the transition on both flows and noise, the improved delayed detached eddy simulation (IDDES) method based on the k-ω-γ transition model (Tr-IDDES) is applied to simulate the flows past a finite-span wing with the multi-element foil of 30P30N, while the Ffowcs Williams and Hawkings (FW-H) equation is solved to obtain the acoustic properties. Moreover, the data from the available measurements and IDDES based on the full turbulent model (FT-IDDES) are compared. First, the Tr-IDDES method is validated by simulating the near-field unsteady flow past the 30P30N foil at a Reynolds number of 9.0 × 10⁶ through a comparison of velocity profiles at several streamwise sections. Tr-IDDES performs much better than FT-IDDES. The unsteady flows and noise past the same configuration at a Reynolds number of 1.7 × 10⁶ are then simulated using Tr-IDDES and FT-IDDES. The instantaneous flow structures, mean pressure and velocity profiles, pressure fluctuations and far-field noise are compared and analysed with and without transition effects. The slat noise predicted by Tr-IDDES is close to that by FT-IDDES, but the main wing noise is lower than that by FT-IDDES, resulting in lower total far-field noise.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110353"},"PeriodicalIF":5.0,"publicationDate":"2025-05-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144169217","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":"Parameter identification for turbulence models in shock wave boundary layer interference using an improved Bayesian neural network","authors":"Jiahuan Peng ,&nbsp;Maotao Yang ,&nbsp;Ye Tian ,&nbsp;Hua Zhang","doi":"10.1016/j.ast.2025.110352","DOIUrl":"10.1016/j.ast.2025.110352","url":null,"abstract":"<div><div>Driven by the limitations of current turbulence models in predicting Shock Wave Boundary Layer Interference (SWBLI) flows with high accuracy, this study introduces an enhanced Bayesian Neural Network (RBNN)-assisted optimization framework designed to rapidly and accurately identify SST turbulence model parameters. To explore various SWBLI conditions under different shock intensities, a compressed corner flow configuration was selected for investigation. The parameter identification capabilities of Artificial Neural Networks (ANN), Residual Networks (ResNet), and traditional Bayesian Neural Networks (BNN) were systematically compared and analyzed. The results demonstrated that, across different training sample sizes, the RBNN consistently delivered superior identification accuracy, achieving a coefficient of determination (R²) value of over 0.997 for the test set and maintaining a root mean square error (RMSE) for wall pressure predictions below 0.013. When applied to conditions of Ma = 2.85 and a 24° compression corner, the RBNN-optimized turbulence model parameters significantly enhanced prediction accuracy, achieving a 65.5 % reduction in RMSE for wall pressure (from 0.6029 to 0.2080) compared to standard parameter calculations, and realizing a 40 % decrease in wall friction coefficient error (from 0.0010 to 0.0006), with results showing the highest agreement with experimental data. Furthermore, the model parameters calibrated for the 24° compression corner condition demonstrated excellent transferability, successfully extending to other ramp angles (20°, 16°, and 8°) under the same Mach number. This research provides an efficient and reliable intelligent algorithm framework for optimizing turbulence models under complex flow conditions, highlighting its broader applicability and robust performance in addressing challenging fluid dynamics problems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110352"},"PeriodicalIF":5.0,"publicationDate":"2025-05-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117114","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 Earth-pointing satellites employing novel hybrid actuator configurations","authors":"Tanya Krishna Kumar,&nbsp;Anirudh Etagi,&nbsp;Dipak Kumar Giri","doi":"10.1016/j.ast.2025.110333","DOIUrl":"10.1016/j.ast.2025.110333","url":null,"abstract":"<div><div>This paper presents an attitude control system for an Earth-pointing satellite, applicable to both circular and elliptical orbits. Two actuator configurations are proposed in this work: one utilizing two reaction wheels, three magnetorquers, and three pairs of Coulomb shells, and a reduced configuration with a single reaction wheel alongside the same set of magnetorquers and Coulomb shells. The magnetorquers and Coulomb shells, aligned along the principal body axes, rely on the Earth's geomagnetic field, making them inherently underactuated. In the first configuration, the reaction wheels generate torque along two axes, while the magnetorquers and Coulomb shells provide control along the remaining axis. In the reduced configuration, a single reaction wheel controls one axis, requiring the magnetic actuators to handle the other two. A control law is developed to estimate the required torques and efficiently distribute them among the actuators. The global asymptotic stability of this control strategy is shown to be valid for all initial angular velocity conditions. Numerical simulations are performed for both circular and elliptical orbits under varying initial conditions. The results validate the effectiveness of both configurations in achieving stable attitude control while optimizing actuator usage and minimizing system complexity.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110333"},"PeriodicalIF":5.0,"publicationDate":"2025-05-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117116","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":"Enhancing drone propellers: practical insights from BEM-based pitch optimization","authors":"Maciej Podsędkowski,&nbsp;Damian Obidowski,&nbsp;Michał Lipian","doi":"10.1016/j.ast.2025.110332","DOIUrl":"10.1016/j.ast.2025.110332","url":null,"abstract":"<div><div>The article presents the analysis of pitching moment in a drone propeller. This aspect of blade design process is not frequently considered, as variable pitch propellers (VPPs) aren’t usually implemented in small-size aerial vehicles due to their mass and reliability issues. The research shows a potential for addressing these issues for both active- and passive VPP systems by pivot point displacement. Discussed herein are the principles of the developed BEM-based optimisation tool for the blade analysis, confronted with an in-house experiment. The analysis then follows towards practical implications of the obtained results. The article contributes to the general design know-how of drone propellers and shows a potential for wider implementation of the VPP technologies for the miniature-scale propellers.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110332"},"PeriodicalIF":5.0,"publicationDate":"2025-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144117112","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":"A new method for heat reduction design using the offset phenomenon of the peak heat flux and recombination structure of the blunt body on the ground","authors":"Yangliang Wang ,&nbsp;Tianchen Huang ,&nbsp;Bin Xu ,&nbsp;Jianbin Jing ,&nbsp;Taohong Ye ,&nbsp;Chuanxia Zhang ,&nbsp;Kang Li","doi":"10.1016/j.ast.2025.110330","DOIUrl":"10.1016/j.ast.2025.110330","url":null,"abstract":"<div><div>The rocket sled is an experimental ground-based device for hypersonic vehicles, which uses rocket boosters with strong thrust to obtain the aerodynamic characteristics of the load. In order to accurately predict the heat flux of the rocket sled at Mach 8–10, a geometrically similar blunt body configuration was analyzed in this study. Computational fluid dynamics (CFD) simulations were utilized to investigate aerodynamic heating under ground-level conditions. Using the Gupta chemical reaction model, the effects of incoming temperature, Mach number, bluntness, and wall temperature on aerodynamic heating at standard atmosphere are analyzed. The results showed that the maximum surface heat flux of the blunt body is not at the stagnation point, and deviates from it under the ground environment. The position of the maximum heat flux is only dependent on the bluntness and not on other parameters. And based on this peculiar phenomenon, using two kinds of blunt bodies (the radius of a blunt body is <em>r_b</em>, and the other is <em>r_n</em>) forms a new structure to reduce heat at the ground. And the intersection point (<em>Po</em>_ins) can be at three different locations. The <em>Po_ins</em> were taken downstream of the heat flux offset point (<em>X_ins</em>=0.005 m), heat flux offset point (<em>X_ins</em> = 0.02 m), and upstream of the heat flux offset point (<em>X_ins</em>=0.08 m). When the <em>r_b</em>/ <em>r_n</em> is 2 and the <em>X_ins</em> is 0.005 m, the peak of heat flux is 99.6 MW/m², which is 18.1 % lower than the highest heat flux of the single blunt body of a radius of <em>r_b</em>. For <em>X_ins</em> = 0.05 m and 0.08 m, the peak of heat flux is close to the heat flux of the peak offset point of the single blunt body with a radius of <em>r_b</em>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110330"},"PeriodicalIF":5.0,"publicationDate":"2025-05-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144105602","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}