Aerospace Science and Technology最新文献

{"title":"On the describing functions for dampers with freeplay and dry friction for studying nonlinear oscillations","authors":"Breno M. Castro ,&nbsp;Wellington L. Paulo Jr ,&nbsp;Douglas D. Bueno ,&nbsp;Paulo J. Paupitz Gonçalves","doi":"10.1016/j.ast.2025.110191","DOIUrl":"10.1016/j.ast.2025.110191","url":null,"abstract":"<div><div>This work presents a novelty in the mathematical formulation of a damper with freeplay for structural dynamics analysis in the frequency domain. This theoretical model represents the basis for the application of the harmonic balance technique for simulating problems with nonlinear characteristics. The predictions of the mathematical model proposed in this work are confronted with results obtained on a ground test of an apparatus composed of a damper and an attachment with a fixed amount of freeplay. The results indicate that the proposed mathematical model can capture the nonlinear characteristics of a damper with freeplay and, therefore, be used for nonlinear structural dynamics analyses, mainly focused on aeroelastic stability.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110191"},"PeriodicalIF":5.0,"publicationDate":"2025-04-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792657","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 rotor tip assembly clearance prediction method considering multi-sources uncertainties","authors":"Yingzhi Zhang ,&nbsp;Huibin Sun ,&nbsp;Xiaoxia Zhang ,&nbsp;Wanxuan Liu ,&nbsp;Kai Chen ,&nbsp;Cheng Yan","doi":"10.1016/j.ast.2025.110186","DOIUrl":"10.1016/j.ast.2025.110186","url":null,"abstract":"<div><div>Rotor Tip Assembly Clearance (RTAC) significantly affects the aerodynamic performance and safety of aero-engines. Accurate prediction of RTAC is essential for effective control. However, existing prediction models fail to consider multi-sources uncertainty induced by limited measurement data and process execution. To address this issue, this paper proposes a prediction method for RTAC under multi-sources un-certainties. The uncertainties related to the RTAC and the quantification method are studied. Based on the deterministic prediction model and probability box theory, the formation mechanism of RTAC uncertainty is revealed. RTACs and their distribution at different phases, blades and stages are predicted and analyzed. Furthermore, the estimation methods for probability of RTAC overproof are proposed based on prediction responses. The feasibility of the proposed method is verified through a case study. The results provide more reliable reference for engineers in decision-making.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110186"},"PeriodicalIF":5.0,"publicationDate":"2025-04-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792645","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 mechanism of acoustic natural resonant characteristics affecting self-sustained combustion oscillations in bluff body diffusion flames","authors":"Yunpeng Liu ,&nbsp;Longchao Xu ,&nbsp;Dan Zhao ,&nbsp;Yingwen Yan","doi":"10.1016/j.ast.2025.110183","DOIUrl":"10.1016/j.ast.2025.110183","url":null,"abstract":"<div><div>Bluff body diffusion flames are widely employed in the afterburners of aircraft engines. However, the combustion oscillations induced by these flames poses significant risks to the operational stability and structural integrity. This study investigates the influence mechanism of the combustion oscillations in bluff body diffusion flames from the perspective of combustion chamber acoustic characteristics. Experimental methods combined with acoustic simulations were used to analyze the effects of changes in the acoustic characteristics on combustion oscillations. The results show that the dominant frequency of combustion oscillation is affected by the system's acoustic characteristics but deviates from the natural acoustic frequency of the system by &gt;60 Hz. This deviation is jointly determined by the phase delay of heat release rate oscillations and the acoustic pressure feedback. The length of the combustion chamber and the position of the flame significantly impact the characteristics of combustion oscillations. Shortening the chamber length reduces low-frequency acoustic pressure feedback, suppresses oscillation amplitude, and shifts the dominant frequency. Notably, relocating the flame position reduces oscillatory pressure amplitude by &gt;95 %, effectively eliminating the limit cycle oscillation state. The phase delay in the dynamic response of the flame is identified as a critical factor in determining thermoacoustics. This study reveals the coupling mechanism between acoustic characteristics and combustion oscillations in bluff body diffusion flames, providing technical support for suppressing combustion oscillations in afterburners.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110183"},"PeriodicalIF":5.0,"publicationDate":"2025-04-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792647","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":"Neural prescribed formation-containment control for air-breathing hypersonic vehicles with input saturation and actuator faults","authors":"Guan Wang ,&nbsp;Honglin Liu ,&nbsp;Zhe Dong ,&nbsp;Shuaibin An ,&nbsp;Kai Liu","doi":"10.1016/j.ast.2025.110190","DOIUrl":"10.1016/j.ast.2025.110190","url":null,"abstract":"<div><div>This study proposes a neural prescribed formation-containment control for air-breathing hypersonic vehicles (AHVs) with input saturation and actuator faults. The proposed method employs key functions to achieve flexible prescribed performance for an AHV swarm system by adjusting of a time-varying scaling function. To avoid the inherited fragility problem of prescribed formation-containment control, an auxiliary system is constructed to adjust performance boundaries under input saturation and external disturbances. Additionally, neural networks are integrated into the design of a distributed extended state observer, which manages unavailable flight states, unpredictable faults, and lumped disturbances. Numerical simulations demonstrate the effectiveness and superiority of the proposed AHV formation-containment control strategy.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110190"},"PeriodicalIF":5.0,"publicationDate":"2025-04-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792646","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":"Investigation of rapid detonation initiation under injection mixing conditions with downstream low-energy ignition strategies","authors":"Xinxin Wang ,&nbsp;Xiaodong Cai ,&nbsp;Rong Hong ,&nbsp;Haorui Liu ,&nbsp;Wandong Zhao","doi":"10.1016/j.ast.2025.110178","DOIUrl":"10.1016/j.ast.2025.110178","url":null,"abstract":"<div><div>This study investigates the deflagration-to-detonation transition (DDT) under injection mixing conditions using high-resolution numerical simulations and a downstream ignition strategy. We analyze the effects of inflow Mach number, fuel equivalence ratio (ER), ignition duration, and ignition location on mixing and detonation initiation. Results show that lower Mach numbers enhance transverse mixing, while higher Mach numbers facilitate faster detonation onset via stronger shear-induced energy deposition. Near-stoichiometric ER reduces initiation distance and boosts detonation velocity, whereas deviations impede flame propagation. Additionally, a new initiation mechanism emerges under low-energy ignition and low internal energy mixtures: a Mach stem forms during flame acceleration, leading to autoignition behind it. Reflected shocks further promote detonation by intensifying interactions with flame fronts. This mechanism demonstrates a pathway to rapid detonation using minimal ignition energy. Furthermore, appropriate ignition duration and location accelerate upstream flame propagation, with suboptimal placement risking poor mixing and detonation failure. These findings provide comprehensive insights into optimizing conditions for efficient detonation initiation under realistic supersonic combustion systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110178"},"PeriodicalIF":5.0,"publicationDate":"2025-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143747366","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":"Uncertainty quantification of compressibility corrections on SA turbulence model for high Mach number flows","authors":"Yunlong Xue ,&nbsp;Yongliang Feng ,&nbsp;Xiaojing Zheng","doi":"10.1016/j.ast.2025.110184","DOIUrl":"10.1016/j.ast.2025.110184","url":null,"abstract":"<div><div>Uncertainty quantification (UQ) of turbulence models for compressible flows with strong compressibility effects is crucial for accurately predicting the aerothermodynamic performance of hypersonic vehicles. In this paper, the Non-Intrusive Polynomial Chaos (NIPC) method is employed to quantify the uncertainties of the various compressibility correction terms of the Spalart-Allmaras(SA) turbulence model in high Mach number flows. Six correction terms are statistically assessed using Sobol indices, focusing on pressure profiles, heat flux profiles, and the separation region in hypersonic compression corner cases. Building upon the uncertainty quantification and dimensional analysis on the wall law of SA model with the compressibility correction term, a locally constrained correction is proposed by introducing a compression-expansion sensor on SA turbulence model. Re-quantification on constrained correction shows that the sensitivity rules of the six correction terms remain consistent across multiple Quantities of Interest (QoIs) at different corner cases. The proposed correction model significantly reduces the sensitivity coefficient of the correction term and improves the performance of SA model in high Mach number flows with strong compressibility effects. These results reveal the effects and mechanisms of the various correction terms, providing further understanding for future turbulence model development of hypersonic flows.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110184"},"PeriodicalIF":5.0,"publicationDate":"2025-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760239","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 of swept turbulent shockwave boundary layer interactions","authors":"Luz E. Castillo Gomez,&nbsp;Andreas Gross","doi":"10.1016/j.ast.2025.110185","DOIUrl":"10.1016/j.ast.2025.110185","url":null,"abstract":"<div><div>Swept turbulent shockwave boundary layer interactions are common to inlet flows and fin flows among others. Away from the inception region, the interaction can exhibit either conical or cylindrical similarity. The relevant parameters and onset boundaries that determine what similarity occurs are not well understood. As part of a combined experimental (at University of Arizona) and numerical (at New Mexico State University) research project, Reynolds-averaged Navier-Stokes calculations of swept shockwave boundary layer interactions were carried out for different tunnel total pressures, freestream Mach numbers, inviscid pressure rises (impinging shock strength), and shock generator sweep angles. By keeping three parameters constant and varying the remaining parameter, the parameter space is systematically explored. All swept interactions display conical similarity. Flow separation is diminished with increasing sweep angle. The present simulations reveal undulations of the separation line for certain parameter combinations. This behavior is observed beyond a critical Reynolds number and pressure rise magnitude. The effect is attenuated by sweep and Mach number. The undulations are accompanied by owl-face skin-friction line patterns similar to those for stall cells on airfoils in the post-stall regime.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110185"},"PeriodicalIF":5.0,"publicationDate":"2025-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143823178","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":"Finite energy reachable set and its optimal ellipsoid approximations in relative orbital dynamics","authors":"Jianye Sun,&nbsp;Dong Ye,&nbsp;Yan Xiao","doi":"10.1016/j.ast.2025.110188","DOIUrl":"10.1016/j.ast.2025.110188","url":null,"abstract":"<div><div>To prevent distortions in estimation caused by abnormal thrust magnitudes, finite energy reachable sets are essential for estimating the maximum state range of a spacecraft during engine failures. This paper examines finite energy reachable sets defined by a combination of initial state sets and weighted energy constraints. Through rigorous mathematical proofs, it is demonstrated that the reachable boundaries form the union of several convex sets. Due to the computational complexity involved in determining the envelope of this union, which poses challenges for real-time engineering applications, an equivalent transformation of the finite energy reachable set into the Minkowski sum of the initial state gain set and the control gain set is proposed. Recognizing the lower computational power of space-grade processors compared to personal computers, this paper develops optimal trace inner and outer ellipsoid approximations of the ellipsoidal Minkowski sum, avoiding reliance on matrix eigenvalue computations through matrix analysis. The result is a significant improvement in the accuracy of the approximate solution with comparable efficiency.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110188"},"PeriodicalIF":5.0,"publicationDate":"2025-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760240","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":"Experimental investigation of the control of shock/boundary layer interaction based on dynamic vortex generator","authors":"Yue Zhang ,&nbsp;Mingzhu Chen ,&nbsp;Ziyun Wang ,&nbsp;Mingchi Pang ,&nbsp;Huijun Tan ,&nbsp;Haicheng Zhu ,&nbsp;Mengge Wang","doi":"10.1016/j.ast.2025.110175","DOIUrl":"10.1016/j.ast.2025.110175","url":null,"abstract":"&lt;div&gt;&lt;div&gt;The shock wave/boundary layer interaction (SWBLI) is an important flow characteristic in high-speed aircraft flow fields. However, the boundary layer separation caused by SWBLI will have a negative impact on the performance of the inlet. In this paper, the dynamic vortex generator (hereinbelow referred to as the dynamic VG) is designed and realized. Wind tunnel experiments are conducted to demonstrate the control capability of the array of dynamic VGs on SWBLI, while also investigating the influence of different shock impingement positions. To analyse the flow characteristics of the flow field more clearly, numerical methods are employed in this paper. Initially, the flow field in the uncontrolled case is investigated with a flow turning angle (&lt;span&gt;&lt;math&gt;&lt;mi&gt;α&lt;/mi&gt;&lt;/math&gt;&lt;/span&gt;) set at 10 ° and a streamwise distance from the shock impingement position to the origin (&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;D&lt;/mi&gt;&lt;mi&gt;p&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt;) of 25 times the maximum lift height of vortex generator (&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mi&gt;v&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt;). The experimental results indicate that SWBLI causes large-scale flow separation in the boundary layer. The maximum distance between separation line and reattachment line (&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;L&lt;/mi&gt;&lt;mrow&gt;&lt;mi&gt;s&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;mi&gt;p&lt;/mi&gt;&lt;/mrow&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt;) is 13.8&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mi&gt;v&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt;, which negatively impacts the performance of hypersonic inlet. After the introduction of the array of dynamic VGs for control, the size of the separation zone decreases, confirming its effective control. This improvement is attributed to the VG-induced flow vortex pairs, which augment momentum in the near-wall region, thereby enhancing resistance to adverse pressure gradient and mitigating boundary layer separation. Moreover, the array of dynamic VGs exhibits superior flow control compared to the array of traditional VGs. This enhanced capability stems from a variable-strength pulsating vortex system generated by the dynamic VG, which diminishes the strength of the separation induced vortex in the SWBLI, thereby improving flow control effectiveness. Additionally, its unique “suction” and “extrusion” effects of the array of dynamic VGs continuously energize the airflow. At &lt;span&gt;&lt;math&gt;&lt;mi&gt;t&lt;/mi&gt;&lt;/math&gt;&lt;/span&gt; = 0.5&lt;span&gt;&lt;math&gt;&lt;mi&gt;T&lt;/mi&gt;&lt;/math&gt;&lt;/span&gt;, when the array of dynamic VGs reaches its maximum height, the control effect on flow separation is optimal, with an &lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;L&lt;/mi&gt;&lt;mrow&gt;&lt;mi&gt;s&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;mi&gt;p&lt;/mi&gt;&lt;/mrow&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt; = 11&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mi&gt;v&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt;, a reduction of 2.8&lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mi&gt;v&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt; compared to the uncontrolled case. Furthermore, the study elucidated the impact of varying shock impingement positions on the control capabilities of the array of dynamic VGs. The best control effect is achieved at &lt;span&gt;&lt;math&gt;&lt;msub&gt;&lt;mi&gt;D&lt;/mi&gt;&lt;mi&gt;p&lt;/mi&gt;&lt;/msub&gt;&lt;/math&gt;&lt;/span&gt; = 22","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110175"},"PeriodicalIF":5.0,"publicationDate":"2025-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143808428","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":"Experimental and numerical investigation of a novel strut-mounted roller-screw inerter for helicopter vibration attenuation","authors":"Aykut Tamer ,&nbsp;Pierangelo Masarati ,&nbsp;Michele Zilletti ,&nbsp;Luigi Bottasso","doi":"10.1016/j.ast.2025.110172","DOIUrl":"10.1016/j.ast.2025.110172","url":null,"abstract":"<div><div>A prominent problem of helicopters is the high vibrational levels due to the high-amplitude excitation forces originating from the main rotor. The ideal solution to reduce vibrations transmitted through the struts is to isolate the fuselage from the main rotor excitation at gearbox struts; therefore the overall vibration attenuation is achieved rather than local solutions. However, the limited available volume around the struts limits the application of existing vibration dampers. To solve the challenge, this work proposes a novel vibration attenuation idea that can effectively perform in confined spaces. Based on the inerter concept of roller-screw type, the axisymmetric design encloses the strut and shares its attachment points, providing a compact solution. The concept is demonstrated through experiments to identify realistic characteristics and rigorous numerical analysis using lumped-parameters and high-fidelity aeroelastic helicopter models to demonstrate vibration mitigation. The results show that the non-linear effects due to friction reduce the effectiveness at low excitation amplitudes; however, satisfactory vibration attenuation levels are achievable at high vibratory loads, a more critical condition for vibration alleviation performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110172"},"PeriodicalIF":5.0,"publicationDate":"2025-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143747320","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}