Aerospace Science and Technology最新文献

{"title":"Comparative study on the laser-induced combustion behavior and product characteristics of catalytically modified double-base propellants under varying pressures","authors":"Fan Zhang,&nbsp;Jian-zhong Liu","doi":"10.1016/j.ast.2025.111050","DOIUrl":"10.1016/j.ast.2025.111050","url":null,"abstract":"<div><div>This study investigates the ignition and combustion mechanisms of four modified double-base propellants (MODH1, MODH2, AMRDH2, AMDH3) and examines how formulation, pressure, and storage time influence combustion behavior and catalytic performance. Using a custom-designed solid propellant ignition and combustion system combined with non-contact optical diagnostics, we analyzed flame dynamics, ignition delay, combustion duration, and combustion product characteristics. Results show that under atmospheric pressure, MODH1 demonstrates a shorter ignition delay and higher combustion intensity due to the catalytic effect of magnesium oxide (MgO). MODH2 exhibits longer ignition delays and reduced intensity, attributed to catalyst degradation during aging. AMRDH2 displays enhanced combustion, especially at 1 MPa and 2 MPa, where the synergy of hexahydro-1,3,5-trinitro-1,3,5-triazine (RDX) and magnesium (Mg) leads to higher flame temperatures, denser flame structures, and improved efficiency. AMDH3 shows milder combustion with anthraquinone (AQ)-based energetic ionic salts offering effective catalysis and cleaner products. Increased pressure shortens ignition delay and combustion duration for all propellants, indicating enhanced reaction completeness and efficiency. Spectral analysis reveals stronger emission intensity at higher pressures, suggesting faster reaction rates and higher localized temperatures. Morphological analysis shows that MODH1 and MODH2 form honeycomb-like porous structures under high pressure, AMRDH2 develops a coral-like morphology, and AMDH3 presents a coiled structure. Elemental analysis highlights pressure- and formulation-dependent variations in elemental distribution, particularly for Mg, lead (Pb), and nickel (Ni). This work reveals the catalytic impact on combustion behavior, emphasizing catalyst stability, pressure effects, and composition-dependent combustion product characteristics, providing a theoretical basis for propellant optimization and performance enhancement.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111050"},"PeriodicalIF":5.8,"publicationDate":"2025-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265579","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":"Multiple input tangential interpolation-driven damage detection of a jet trainer aircraft","authors":"Gabriele Dessena ,&nbsp;Marco Civera ,&nbsp;Andrés Marcos ,&nbsp;Bernardino Chiaia ,&nbsp;Oscar E. Bonilla-Manrique","doi":"10.1016/j.ast.2025.111032","DOIUrl":"10.1016/j.ast.2025.111032","url":null,"abstract":"<div><div>The problem of damage detection and identification is of interest for many aerospace and aeronautical engineering systems. However, relevant literature mostly focuses on subsystems and parts, rather than full airframes. In structural dynamics, modal parameters, such as natural frequencies and mode shapes, from any structure are the main building blocks of vibration-based damage detection. However, traditional comparisons of these parameters are often ambiguous in large systems, complicating damage detection and assessment. The modified total modal assurance criterion (MTMAC), an index well-known in the field of finite element model updating, is extended to address this challenge and is proposed as an index for damage identification and severity assessment. To support the requirement for precise and robust modal identification of Structural Health Monitoring (SHM), the improved Loewner Framework (iLF), known for its reliability and computational performance, is pioneeringly employed within SHM. Since the MTMAC is proposed solely as a damage identification and severity assessment index, the coordinate modal assurance criterion (COMAC), also a well-established tool, but for damage localisation using mode shapes, is used for completeness. The iLF SHM capabilities are validated through comparisons with traditional methods, including least-squares complex exponential (LSCE) and stochastic subspace identification with canonical variate analysis (SSI-CVA) on a numerical case study of a cantilever beam. Furthermore, the MTMAC is validated against the traditional vibration-based approach, which involves directly comparing natural frequencies and mode shapes. Finally, an experimental dataset from a BAE Systems Hawk T1A jet trainer ground vibration test is used to demonstrate the iLF and MTMAC capabilities on a real-life, real-size SHM problem, showing their effectiveness in detecting and assessing damage.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111032"},"PeriodicalIF":5.8,"publicationDate":"2025-10-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265732","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":"Study on the aerodynamic performance and rivulet characteristics of a compressor cascade with rain ingestion","authors":"Yonghao Yu ,&nbsp;Qionglei Hu ,&nbsp;Kim Tiow Ooi ,&nbsp;Qun Zheng ,&nbsp;Mingcong Luo","doi":"10.1016/j.ast.2025.111030","DOIUrl":"10.1016/j.ast.2025.111030","url":null,"abstract":"<div><div>Rain ingestion significantly impacts axial compressor performance by modifying blade-surface water distribution and local aerodynamic loads. This study employs a linear-cascade two-phase flow test rig combined with high-speed imaging and a computer-vision algorithm to quantify rivulet and water-film dynamics under varying droplet sizes, water air ratio (WAR), cascade geometries, and attack angles. Results indicate that higher WAR and larger droplets increase total pressure loss, deviation-angle fluctuations, and early tendency of flow separation. Blade geometry amplifies these effects, with positive attack angle producing fewer but higher rivulets, and negative attack angle generating more numerous yet lower rivulets. Nonlinear correlations between rivulet height and local static pressure highlight the complex multiphase–aerodynamic interaction. These insights offer quantitative guidance for blade design and performance mitigation under wet-air conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111030"},"PeriodicalIF":5.8,"publicationDate":"2025-10-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266479","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":"Three-dimensional fault-tolerant cooperative guidance law with constraints on relative impact velocity and attack angle","authors":"Zhanpeng Gao,&nbsp;Jun Liu,&nbsp;Jian Huang,&nbsp;Wenwen Wang,&nbsp;Wenjun Yi,&nbsp;Shusen Yuan","doi":"10.1016/j.ast.2025.111003","DOIUrl":"10.1016/j.ast.2025.111003","url":null,"abstract":"<div><div>In the context of electronic countermeasures and precision strikes, this paper proposes a three-dimensional fault-tolerant cooperative (FTC) guidance law with constraints on relative impact velocity and attack angle to further improve the stability and strike capability of a missile swarm. The guidance law uses Fractional Power Extended State Observer (FPESO) to estimate the acceleration of the enemy target online, and introduces a nonlinear term into the traditional PIDSMC to derive the novel nonlinear PID sliding mode surface (NPIDSMC). Considering that communication in the cooperative process is prone to interference, different solutions are proposed for varying levels of interference. Simulation results show that, under ideal conditions and light interference, the proposed FTC-NPIDSMC-FPESO cooperative guidance law can achieve cooperative strikes with the desired impact velocity and attack angle. Under light interference, communication interference and node failures are handled through topology switching. In the case of severe communication interference, a fault-tolerant backup option is switched to fixed-time open-loop cooperative strikes to ensure the successful execution of the strike mission. Monte Carlo simulations further verify that the fault-tolerant cooperative guidance law exhibits strong adaptability and stability in electronic countermeasure environments.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111003"},"PeriodicalIF":5.8,"publicationDate":"2025-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265744","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":"Test and numerical simulation of damage on an aircraft wing leading edge impacted by an unmanned aerial vehicle","authors":"Jiacheng Sheng ,&nbsp;Shengli Lv ,&nbsp;Kai Feng ,&nbsp;Xinnian Wang ,&nbsp;Chunyang Zhang ,&nbsp;Zhibin Wu ,&nbsp;Yifan Wang ,&nbsp;Jun Liu","doi":"10.1016/j.ast.2025.111036","DOIUrl":"10.1016/j.ast.2025.111036","url":null,"abstract":"<div><div>The increasing prevalence of Unmanned Aerial Vehicles (UAVs) in airspace has highlighted critical threats to aircraft flight safety. This study establishes a methodological framework for quantifying dynamic impact loads generated by UAV strikes. The controlled impact tests between UAVs and aircraft wing leading edges were carried out by a new test setup, the deformation characteristics and failure modes of composite wing structures were systematically documented. A high-fidelity numerical model was developed using the explicit finite element analysis software PAM-CRASH, enabling detailed simulation of the temporal-spatial evolution of impact dynamics. Validation analysis demonstrated strong concordance between simulation and test results. Expanding the scope beyond UAV impacts, this research pioneers a comparative analysis framework by incorporating equivalent-mass bird strike simulations under identical kinetic conditions. Further parametric studies examined the influence of impact velocities and UAV flight attitudes on structural damage patterns. The multidisciplinary approach provides aviation regulators with empirically validated computational models and impact scenario databases, directly supporting the development of next-generation airworthiness standards for UAV-integrated airspace systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111036"},"PeriodicalIF":5.8,"publicationDate":"2025-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265733","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":"The flexible kinematic modeling method and aerodynamic performance of dragonfly wings","authors":"Lishuang Wang (王力爽) ,&nbsp;Zhiwei Shi (史志伟) ,&nbsp;Weilin Zhang (张伟麟) ,&nbsp;Sinuo Chen (陈思诺) ,&nbsp;Weiyuan Zhang (张维源)","doi":"10.1016/j.ast.2025.111037","DOIUrl":"10.1016/j.ast.2025.111037","url":null,"abstract":"<div><div>Dragonflies demonstrate intricate wing motions and structural deformations during flight. To investigate the unsteady aerodynamic mechanisms, this paper establishes a kinematic modeling framework that precisely characterizes the instantaneous flexible deformation of the wings. First, we propose a set of tailored deformation functions to satisfy the geometric constraints of inextensibility and root continuity during wing flapping and twisting. Based on these functions, the model quantitatively describes flexible deformations such as bending, warping, and cambering of the wing. Second, we examined how twist phase, twist amplitude, and camber influence the aerodynamic performance of the wing through numerical simulations. Finally, by analyzing the three-dimensional flow structures under various motion conditions, we reveal the physical mechanisms through which each parameter influences the aerodynamic forces. The results indicate that although rigid and flexible wings exhibit similar mean aerodynamic forces, the rigid wing fails to satisfy the biological geometric constraint of root continuity. In contrast, the flexible wing maintains these geometric constraints while exhibiting smoother aerodynamic force curves and sustaining stronger leading-edge vortices (LEVs). Further analysis shows that advancing the twist phase, increasing twist amplitude, and enhancing camber all help strengthen the aerodynamic force component normal to the stroke plane. Twisting angle not only significantly alters the direction of aerodynamic forces but also promotes a more uniform distribution of LEV strength along the wingspan, thereby maintaining a larger low-pressure region on the wing surface. Meanwhile, camber further stabilizes the outer LEV and enhances suction over the wing. This study provides a theoretical basis for understanding the coupled morphological and kinematic mechanisms of dragonfly wings, and is expected to offer new insights for the design and aerodynamic optimization of bio-inspired flying devices.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111037"},"PeriodicalIF":5.8,"publicationDate":"2025-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266478","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":"Coupled flight dynamics and aeroelasticity research of flexible flying wing aircraft with folding wingtips","authors":"Jun Liu ,&nbsp;Xinyu Ai ,&nbsp;Wei Qian ,&nbsp;Xing Li ,&nbsp;Yize Zhao ,&nbsp;Xin Hu","doi":"10.1016/j.ast.2025.111042","DOIUrl":"10.1016/j.ast.2025.111042","url":null,"abstract":"<div><div>In recent years, increasing attention has been paid to the application of folding wingtips on transport aircraft. However, there is a lack of research about folding wingtips on unmanned aerial vehicles (UAVs). This study investigates the effects of folding wingtips on the flight dynamics and aeroelastic stability of high-aspect-ratio (HAR) flying wing UAVs. A modeling method of coupled flight dynamics and aeroelasticity (CFA) in a mean-axis frame is established, integrating the doublet lattice method (DLM) and rational function approximation (RFA). Validated against published data, the method is used to analyze 11 aircraft configurations varying in wingtip folding angles. It was found that folding wingtips significantly alter modal characteristics, inducing frequency variation and mode reordering, which in turn modify flutter phenomena. It is also demonstrated that the body freedom flutter (BFF) speed increases as the folding angles increase, thereby enhancing flight safety. Furthermore, in longitudinal dynamics, large folding angles degrade static stability margins, and there is a positive correlation between the pitching damping ratio and folding angles. Finally, the comparison of the time responses of flight attitudes, with and without considering the structure elasticity, reveals that the coupling between flight dynamics and aeroelasticity yields pronounced oscillatory behavior with different convergence rates, posing greater challenges for flight control systems. The findings emphasize the necessity of considering the effects of folding wingtips and structural elasticity on the flight dynamics and aeroelastic stability in flight control strategies.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111042"},"PeriodicalIF":5.8,"publicationDate":"2025-10-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266517","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 characteristics of aerial refueling hose-drogue system under lateral gust","authors":"Zexian Nie ,&nbsp;Suxia Zhang ,&nbsp;Siyi Meng ,&nbsp;Xiangfeng Wu ,&nbsp;di Wu","doi":"10.1016/j.ast.2025.111041","DOIUrl":"10.1016/j.ast.2025.111041","url":null,"abstract":"<div><div>Aerial refueling technology plays a pivotal strategic role in extending fighter aircraft’s operational range and combat radius, particularly for long-range strike and rapid deployment missions. The hose-drogue refueling system, however, remains susceptible to disturbances from complex airflow conditions, which significantly threaten refueling operations. This paper presents a comprehensive investigation into the dynamic behavior of the hose-drogue system under lateral gust conditions. The Kane theory was employed to establish the multibody dynamic model by discretizing the hose into serially connected rigid links joined by spherical joints, with the drogue rigidly attached to the terminal link. The application of Kane’s method avoids the Lagrangian function computations in analytical mechanics or cumbersome internal force analysis in classical mechanics. The equilibrium analysis introduces a novel position index correlated with the system’s towing configuration, offering direct guidance for tanker flight parameter optimization and maximum hose tension estimation. Dynamic response studies reveal several critical phenomena: the hose exhibits a whipping phenomenon under lateral gust loads, with the whipping intensity progressively increasing along the length of the hose; the maximum dynamic tension fluctuation remains within 3 % of the equilibrium tension value, which pose no structural safety concerns; and most notably, extreme fluctuations in the lateral aerodynamic components of drogue loads dominate system’s dynamics behavior. Through detailed analyses of phase diagrams and spatial trajectories, the results demonstrate the drogue’s violent motion characteristics during whipping episodes, which render docking procedures unfeasible. These findings provide theoretical support for optimal tanker flight parameter selection, accurate tension prediction, and the development of advanced drogue active control systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111041"},"PeriodicalIF":5.8,"publicationDate":"2025-10-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145266519","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":"Vortex behavior over a tailless forward-swept wing with chine forebody configuration","authors":"Eiman B. Saheby,&nbsp;Li Jialu,&nbsp;Chen Wang,&nbsp;Shen Xing","doi":"10.1016/j.ast.2025.111026","DOIUrl":"10.1016/j.ast.2025.111026","url":null,"abstract":"<div><div>The aim of this study is to investigate the necessity of a swing-wing system to maximize the aerodynamic efficiency of an unconventional tailless VTOL platform. This is accomplished by comparing the aerodynamics of two different wing configurations mounted on an identical fuselage with a chine forebody, using both wind tunnel tests and numerical simulations. To assess and compare lift, drag, and the behavior of vortical flow structures in cruise mode, two subscale models were designed: one featuring a straight leading-edge wing representative of the cruise configuration in a variable-sweep design, and the other with a fixed 58-degree forward-swept wing representing a non-variable fixed-wing solution. Wind tunnel experiments included force measurements and particle image velocimetry at a Reynolds number of 1.706 × 10⁵. The results reveal substantial differences not only in lift-to-drag characteristics but also in the behavior of vortical patterns on the aft-body, driven by interactions between the chine vortices and wing-generated turbulence. These interactions produce distinctly different flow structures, including oscillating vortex cores and varying breakdown patterns. Details regarding post-processing and data quantification are presented in this paper.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111026"},"PeriodicalIF":5.8,"publicationDate":"2025-10-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265740","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 CFD study of the aerodynamic characteristics of a DrivAer fastback model","authors":"Thanh-Long Le ,&nbsp;Thanh-Phuc Phan ,&nbsp;Duc Tran ,&nbsp;Viet-Thang Vu ,&nbsp;Le-Hung-Toan Do","doi":"10.1016/j.ast.2025.111043","DOIUrl":"10.1016/j.ast.2025.111043","url":null,"abstract":"<div><div>This study focuses on improving the aerodynamic performance of a passenger vehicle by incorporating an aerodynamic add-on device. Specifically, a cambered rear wing based on the NACA 8612 airfoil is mounted at the rear of the DrivAer fastback model to enhance its aerodynamic characteristics. Then, the computational fluid dynamics (CFD) approach is employed to investigate the fluid dynamic behavior and evaluate the aerodynamic performance improvements resulting from the rear wing installation. The analysis also examines the effects of operational conditions and wing configuration parameters, such as freestream velocities, mounting heights, and angles, on the drag and lift coefficients. Numerical simulation results reveal that applying a rear wing with a configuration of a/b = 0.8 and α = 5° at a vehicle speed of 30 m/s leads to a significant improvement in aerodynamic stability compared to the original model, as evidenced by the reduction in the lift area coefficient from 0.291 to -0.124, at the cost of a slight drag area coefficient increase from 0.503 to 0.515. Overall, the findings in this study aim to contribute to a deeper understanding of how aerodynamic add-on devices influence a vehicle’s aerodynamic performance. In particular, the analysis of various wing configuration parameters offers valuable insights for the development of active aerodynamic control systems, particularly in designing effective control strategies.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111043"},"PeriodicalIF":5.8,"publicationDate":"2025-10-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265578","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}