Aerospace Science and Technology最新文献

{"title":"Study on the combustion characteristics of high-speed non-premixed reactants enhanced by rotating detonation jet","authors":"Ao Xiong,&nbsp;Yiting Dang,&nbsp;Yunzhen Zhang,&nbsp;Qi Sun,&nbsp;Yuechen Hou,&nbsp;Jianping Wang","doi":"10.1016/j.ast.2025.110207","DOIUrl":"10.1016/j.ast.2025.110207","url":null,"abstract":"<div><div>The afterburner is indispensable for the short-term power enhancement of military engines. In order to achieve stable and efficient combustion in the afterburner and reduce the weight of the combustion chamber, it is very important to explore an efficient combustion organization scheme. Rotating detonation engine is an engine that uses continuous rotating propagation of detonation waves in the combustion chamber to generate a stable thrust and detonation waves can propagate continuously and stably with only one-time ignition. In this study, the in-line injection mode of the injector in the afterburner is taken as the research background, and the scheme of using rotating detonation jet to enhance the mixing and combustion process of fuel cross-flow and high subsonic parallel flow is proposed for the first time. The results show that the rotating detonation jet combustion enhancement scheme is a promising method to achieve efficient combustion of high-speed non-premixed reactants. As far as the current simulated working conditions are concerned, the maximum combustion efficiency of this method can reach 89.93 %. In addition, there is a suitable rotating detonation combustor size and connected domain distance to achieve the best combustion enhancement effect. Improper geometric parameters will affect the baroclinic torque structure, the strength and continuity of the vortex distribution, and the continuity and area of the flame stability zone, thus affecting the combustion enhancement effect. Three main mechanisms for the enhancement of non-premixed combustion by periodic rotating detonation jet are summarized. Combined with the analysis of cases with different connected domain distance, it is found that the formation of specific baroclinic torque structure and the interaction between shock wave and flame are the dominant mechanisms.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110207"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143877273","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 injector geometry on the combustion characteristics and stability of nonpremixed O2/CH4 coaxial flames in a model combustor","authors":"Young Hoo Kim,&nbsp;Tae Won Kim,&nbsp;Ju Han Kim,&nbsp;Hyeon Woo Lee,&nbsp;Jae Hyun Kim,&nbsp;Oh Chae Kwon","doi":"10.1016/j.ast.2025.110205","DOIUrl":"10.1016/j.ast.2025.110205","url":null,"abstract":"<div><div>Effects of injector diameter and lip thickness (<em>t</em>_L) on the combustion characteristics and stability of oxygen (O₂) and methane (CH₄) which is more suitable for reusable rockets are experimentally investigated considering nonpremixed O₂/CH₄ coaxial jet flames in a model combustor through their visualization with varying Reynolds number (Re). Increasing Re exhibits two different flame behaviors: stably attached and oscillating near-blowout flames. In the case that <em>t</em>_L is too small compared to the reaction region near the injector lip, the flame base is tremendously affected by the injected flow so that flame detachment occurs at low injection velocity; however, increasing <em>t</em>_L increases heat losses to the injector plate so that the optimal <em>t</em>_L is necessary to ensure the stably attached flames. At given oxygen-to-fuel mass ratio, the variation in the injector diameter also significantly affects the combustion stability limits due to the change of flow characteristics in the wake region behind the injector lip. A regime diagram of combustion stability is introduced using the effective Reynolds number Re_eff and a newly suggested parameter which is based on Re_eff and the fuel-injector diameter. The parameter is found to be useful to represent the injection conditions of the flame detachment and local flame extinction for the present injectors.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110205"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143823168","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 shape memory polymer composite based corrugated morphing wing flap structure","authors":"A.K. Saurav ,&nbsp;L. Bhola ,&nbsp;P.M. Mujumdar ,&nbsp;P.J. Guruprasad","doi":"10.1016/j.ast.2025.110201","DOIUrl":"10.1016/j.ast.2025.110201","url":null,"abstract":"<div><div>This work presents a multi-objective optimization framework based on a genetic algorithm (GA) for aircraft morphing wing trailing sections made of shape memory polymer composites (SMPCs) based varying height corrugated structure. A morphing wing trailing section is attached to the main wing without any external discontinuity. It offers smooth operation of the aft section repeatedly over the entirety of the flight envelope. The primary variables for the optimization method considered in this work are SMPC ply orientations, number of plies, and number of corrugation elements. The constraint imposed on the structure is the deflection of the trailing section under maximum air pressure load. These variables affect shape memory behavior, structural integrity, and weight of the morphing wing trailing section, and they, in return, provide constraints on the SMPC-based corrugated structure. An equivalent plate formulation has been used to obtain effective corrugation properties of variable amplitude corrugated structure. Optimization work has been carried out on two different NACA 6 series airfoils to draw comparisons and ascertain the effectiveness of the framework.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110201"},"PeriodicalIF":5.0,"publicationDate":"2025-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143858796","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 load alleviation of input-redundant flexible aircraft via nonlinear control allocation over invariant manifold","authors":"Boge Dong ,&nbsp;Yi Zhou ,&nbsp;Molong Duan","doi":"10.1016/j.ast.2025.110199","DOIUrl":"10.1016/j.ast.2025.110199","url":null,"abstract":"<div><div>Flexible aircraft design in modern transport aircraft improves fuel efficiency by increasing lift, reducing drag, and minimizing weight. This design increases structural flexibility, requiring special attention to load at critical locations to prevent failure during intense maneuvers or gusts. Traditional maneuver load alleviation is typically achieved through static allocation of control surface deflections or linear aeroelastic models. It is particularly challenging to separate flexible responses from rigid-body responses due to the nonlinear aerodynamic and geometric characteristics of flexible aircraft. This paper proposes a decoupled dynamic load alleviation strategy for input-redundant flexible aircraft exploiting invariant manifold structures of nonlinear systems. The nonlinear modeling considers static and periodically excited aeroelastic responses of flexible aircraft as a linear parameter-varying system with nonlinear steady-state gain, facilitating a novel nonlinear control allocation framework. This framework manipulates a proxy signal across the invariant manifold structure considering both high-frequency and low-frequency aircraft response components to minimize impact on rigid-body responses, achieving effective decoupling. The proposed nonlinear control allocation further minimizes load violation through output-input-constraint conversion. A flexible aircraft wing prototype is developed and tested through simulations and wind tunnel experiments, demonstrating enhanced load alleviation capabilities without compromising rigid-body responses compared to existing methods.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110199"},"PeriodicalIF":5.0,"publicationDate":"2025-04-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143823169","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":"Effect of bionic passive flow control schemes on compressor cascade performance","authors":"Wen-feng Xu,&nbsp;Cheng-xi Tang,&nbsp;Shi-long Zou,&nbsp;Dan Sun,&nbsp;Guo-zhe Ren","doi":"10.1016/j.ast.2025.110192","DOIUrl":"10.1016/j.ast.2025.110192","url":null,"abstract":"<div><div>This research incorporates the wing features of dragonflies and birds to create endwall bionic chambers, leading-edge vortex generators on the suction side, and tip grooves. A numerical simulation is employed to conduct comparative research, examining the impact pattern and mechanisms of the above three distinct bionic structures on the endwall flow and compressor's overall aerodynamic performance. Rigorous analyses reveal that all three bionic structures can effectively shrink the extent of the low-energy fluid cluster, lift diffusion capacity, mitigate internal flow losses, and ameliorate the airflow state within the cascade passage. Among them, the tip grooves offer the most impressive performance, which can decrease the total pressure loss coefficient of the cascade by 14.4 %. The tip grooves exhibit superior efficacy in corner separation inhibition when compared with the other structures. Besides, how different bionic structures impact flow loss and what differences exist in them at varying incidence angles are also included in this research. The survey found that all three bionic structures demonstrate excellent positive incidence angle characteristics. However, the vortex generators and tip grooves slightly enlarge the corner separation range and deteriorate the cascade flow loss when the incidence angle is below the minimum-loss incidence angle of the original cascade.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110192"},"PeriodicalIF":5.0,"publicationDate":"2025-04-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143817378","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":"PSD INDI and wake gradient based control of high aspect ratio UAVs' close formation flight","authors":"Rui Wang ,&nbsp;Zhou Zhou ,&nbsp;Mihai Lungu ,&nbsp;Linfang Li","doi":"10.1016/j.ast.2025.110198","DOIUrl":"10.1016/j.ast.2025.110198","url":null,"abstract":"<div><div>To enhance the cruising performance of a swarm and to ensure its flight safety, the stability and the control of the Close Formation Flight (CFF) are essential elements. This paper proposed a methodology to improve the accuracy of the dynamic characteristics' analysis and reduce the flight control tracking error for CFF using wake vortex information. Firstly, a criterion for trajectory stability during formation flight is derived based on the wake gradient, and the patterns of modal characteristics changing with the relative position between the leader and the follower under wake interference are analyzed. Then, a novel Partial States Determined Incremental Nonlinear Dynamic Inversion (PSD INDI) control method is proposed for the attitude control loop, which the damping derivatives and the wake gradient of the UAVs are integrated into the Extended State Observer (ESO) to estimate the required angular acceleration, the state estimation error is reduced, the controller performance being thus improved. Next, in the trajectory control loop, a method using distributed propellers and rudders synchronous control is proposed to generate direct lateral force as the feedforward for L1 control; this way, the cross-track error caused by external interference is eliminated. Finally, considering a swarm of tailless high aspect ratio UAVs, featured as low longitudinal and directional stability and sensitive to wake disturbances, a hardware-in-the-loop (HIL) simulation test of CFF is carried out. While encountering sudden changes in wake gradients near the optimal cruising position, the attitude and trajectory disturbances, as well as the throttle demand, are smaller, which prove the robustness, the accuracy, and the feasibility of the proposed flight dynamics’ analysis and control method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110198"},"PeriodicalIF":5.0,"publicationDate":"2025-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143817377","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":"Bird strike-induced damage studies on bio-inspired laminated plates with holes","authors":"Aman Garg ,&nbsp;Neeraj Kumar Shukla ,&nbsp;Mohamed-Ouejdi Belarbi ,&nbsp;Debasis Mukherjee ,&nbsp;M. Pushpavalli ,&nbsp;Roshan Raman ,&nbsp;Mehmet Avcar ,&nbsp;Mandeep Singh Narula ,&nbsp;Li Li","doi":"10.1016/j.ast.2025.110200","DOIUrl":"10.1016/j.ast.2025.110200","url":null,"abstract":"<div><div>Bird strikes can potentially damage the aerospace and aeronautics structures and cause serious damage to the structure. In the present work, damage due to bird-strike in bio-inspired helicoidal laminated composite plates with circular and elliptical holes is predicted using Smoothed Particle Hydrodynamics (SPH)-Finite Element Method (FEM) model in ABAQUS. The Hashin failure model within ABAQUS has been implemented to model the impact-induced damage. The bird is modelled using the concepts of SPH to handle the mesh deformation problem effectively. Helicoidal recursive, exponential, semi-circular, linear, and Fibonacci helicoidal are studied during the present study. The plate is considered with two holes located at a quarter distance along the middle vertical axis of the plate. The damage in exponential, recursive, and linear helicoidal laminates is lesser than in conventional cross-ply and quasi-isotropic laminates. The plate with small dimensions of circular holes tends to deflect the failure in fibres towards the corners, while the plate with many holes arrests the cracks themselves. The plate with elliptical holes deflects the cracks towards themselves thus preventing the damage near the edges but damages the laminate in its vicinity.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110200"},"PeriodicalIF":5.0,"publicationDate":"2025-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143823170","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":"Quantized feedback neuroadaptive control for a non-affine hypersonic flight vehicles system with actuator saturation","authors":"Wei Wang ,&nbsp;Zijian Ni ,&nbsp;Bailin Chen ,&nbsp;Shiwei Chen","doi":"10.1016/j.ast.2025.110189","DOIUrl":"10.1016/j.ast.2025.110189","url":null,"abstract":"<div><div>This paper investigates the attitude tracking control problem of non-affine nonlinear hypersonic vehicles with communication constraints and actuator saturation, taking into account significant unmodeled dynamics and external disturbances. The novelty of this work lies in the proposed adaptive quantized state feedback control strategy, which leverages radial basis function neural networks (RBFNNs) to mitigate communication burdens between the controller and the actuator. Specifically, the design of the quantizer aims to alleviate this communication burden. The controller begins by addressing the non-affine components of the system using the mean value theorem, transforming the attitude tracking problem of a non-affine hypersonic vehicle, characterized by state quantization, input saturation, unmodeled dynamics, and external disturbances, into an affine nonlinear problem with unknown nonlinear functions, unknown control gains, and bounded disturbances. To address this, an adaptive backstepping method is employed, along with the universal approximation capabilities of RBFNNs to approximate the unknown nonlinearities. Adaptive neural compensation terms, derived from the quantized states, are introduced to ensure bounded quantization errors. Further innovations are presented in the design of an auxiliary system to manage actuator saturation, maintaining the controller's saturation characteristics, and in the use of a second-order command filter to mitigate the \"complexity explosion\" issue inherent in backstepping methods. Finally, adaptive gains compensate for bounded disturbances, neural network estimation errors, and quantization errors. In the stability analysis, a recursive method is used to prove the boundedness of quantization errors, and Lyapunov stability theory is applied to demonstrate the stability of the proposed quantization feedback adaptive tracking control system. Simulation results indicate that, under various disturbances and aerodynamic parameter variations, the tracking error remains within a range of 0.05°, and the convergence time is kept under 0.5 s, validating the effectiveness and robustness of the proposed approach.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110189"},"PeriodicalIF":5.0,"publicationDate":"2025-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143808429","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":"Numerical investigation on non-premixed rotating detonation with the induced forward motion shock wave","authors":"Zhipeng Sun,&nbsp;Yue Huang,&nbsp;Han Peng,&nbsp;Sijia Gao,&nbsp;Anjia Song","doi":"10.1016/j.ast.2025.110187","DOIUrl":"10.1016/j.ast.2025.110187","url":null,"abstract":"<div><div>Three-dimensional (3D) numerical simulations were conducted in a non-premixed rotating detonation combustor with an axial inlet duct to study the flow characteristics of the strong motion shock wave induced by the detonation. A transient, implicit density-based solver was applied to solve the 3D unsteady Navier-Stokes equations governing the flow, and led to the identification of the single-wave propagation of the detonation wave and the structure of the forward spiral shock wave. The fresh fuel-filled zone was classified into partial and ideal mixed zones, as well as a fuel-rich zone. The detonation wavefront exhibited folding that consisted of the detonation wave of the trailing edge, the main detonation wave, and the secondary detonation wave. In detail, the analysis also focused on the impact of the forward shock wave on both the air intake into the combustion chamber and the mixing of the reactants. The results showed that when the detonation wave temporarily blocked the passage of fuel, the suppressed effect of the forward shock wave on the incoming air was more notable. Equations were derived to establish correlations between the velocity and angle of the forward shock wave in the axial inlet duct and the intensity of the detonation wave, as well as the thermal parameters of the incoming flow. The relationship was validated based on comparisons under different incoming flow temperatures. Finally, a summary was provided for the fundamental structure of the flow field featured by the coupling of a rotating detonation wave and a forward shock wave.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110187"},"PeriodicalIF":5.0,"publicationDate":"2025-04-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143808554","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":"Reinforcement learning for gust load control of an elastic wing via camber morphing at arbitrary sinusoidal gusts","authors":"Yating Hu ,&nbsp;Yuting Dai ,&nbsp;Jinying Li ,&nbsp;Yuming Zhang ,&nbsp;Chao Yang","doi":"10.1016/j.ast.2025.110174","DOIUrl":"10.1016/j.ast.2025.110174","url":null,"abstract":"<div><div>This paper presents the process of training and validation of deep reinforcement learning (RL) for gust load alleviation (GLA) based on camber morphing. First, a simplified aeroelastic model of the morphing wing considering the gust input is established based on the doublet-lattice method. The simplified model is adopted for GLA control training, and the proximal policy optimization algorithm is employed. When training is completed, the RL-based GLA controller is evaluated in the high-fidelity fluid-structure interaction environment. Results show that the controller effectively suppresses both the structural load and the aerodynamic force. It alleviates wingtip acceleration by 77.4 % at <em>A_g</em>=1m/s, <em>f_g</em>=2 Hz. The flow field suggests that the wing morphing counteracts the pressure distribution change induced by gusts and suppresses the lift fluctuations, thus alleviating the wingtip acceleration. Then, the RL-based GLA controller is tested at sinusoidal gust frequencies 1.5–3 Hz and amplitudes 1–4m/s, demonstrating a respectable alleviation effect within the maximum morphing angle. Finally, the comparison with the traditional PI controller further proves its superior gust alleviation performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110174"},"PeriodicalIF":5.0,"publicationDate":"2025-04-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143873383","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}