Aerospace Science and Technology最新文献

{"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":"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 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}

{"title":"Flow field analysis of a high agility type aircraft aeroelastic wind tunnel model","authors":"Julius Stegmüller,&nbsp;Andreas Molz,&nbsp;Paloma García-Guillén,&nbsp;Christian Breitsamter","doi":"10.1016/j.ast.2025.110177","DOIUrl":"10.1016/j.ast.2025.110177","url":null,"abstract":"<div><div>Modern high-agility aircraft are often affected by the consequences of tail buffeting effects at subsonic speeds and medium to high angles of attack. High pressure fluctuations with distinct frequency contents characterize the flow field downstream of vortex breakdown and are often responsible for the dynamic structural response, which can result in heavy structural damage and degraded handling qualities. For analyzing the flow field and the frequency content of the pressure fluctuations over a modular full-span wind tunnel model with either rigid or aeroelastically scaled double-delta wings and horizontal and vertical tailplanes, stereoscopic particle image velocimetry measurements and measurements with a fast-response aerodynamic pressure probe are performed. The aeroelastically scaled components are 3D-printed from polylactide whereas the rigid components are made of aluminum and serve as a reference case. When comparing the rigid and aeroelastically scaled configurations, significant differences in the axial vortex core velocities in some measurement planes can be detected, while the power spectral densities of the flow field pressure fluctuations show similar characteristics with slight differences in the amplitudes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110177"},"PeriodicalIF":5.0,"publicationDate":"2025-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143747321","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Influence of the fuel jet injection angle on the combustion process of a gel scramjet","authors":"Zhitan Zhou,&nbsp;Taiyu Cao,&nbsp;Ranhui Liang,&nbsp;Yueheng Mi","doi":"10.1016/j.ast.2025.110180","DOIUrl":"10.1016/j.ast.2025.110180","url":null,"abstract":"<div><div>Boron-containing gel propellants have high-energy densities and controllable injection characteristics, can significantly improve ramjet performance, and present a new direction for hypersonic vehicle development. To address the performance optimization problem of boron-containing gel scramjet engines, this study combines supersonic turbulence combustion interaction equations and the multiphase flow equations to make use of a combustion flow simulation method for the internal flow fields of boron particle gel ramjet engines at a multi-grid scale. Numerical simulations of the internal flow field of a combustion chamber at different fuel injection angles were conducted. The results indicated that as the fuel injection angle increased, the fuel jet penetration effect was enhanced, and the obstruction effect on the supersonic airflow became more pronounced. When the injection angle exceeds 35°, the supersonic airflow flows along the lower wall at a particular deflection angle. As the angle increases, the main combustion region of the fuel moves from the end of the combustion chamber to the downstream cavity. When the fuel injection angle reaches 80°, the temperature increase efficiency reaches its optimal value of 71 %. The research findings provide an optimized design solution for boron-containing gel propellant scramjet engines.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110180"},"PeriodicalIF":5.0,"publicationDate":"2025-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760238","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":"Large-Eddy Simulations of kerosene spray combustion in a supersonic jet flow","authors":"Florian Kissel,&nbsp;Guillaume Ribert,&nbsp;Pascale Domingo","doi":"10.1016/j.ast.2025.110164","DOIUrl":"10.1016/j.ast.2025.110164","url":null,"abstract":"<div><div>High-speed reactive two-phase flows, relevant for the development of future scramjet engines, are studied by Large-Eddy Simulations. The present configuration is inspired by the supersonic Cheng's burner replacing hydrogen with kerosene in the gaseous or liquid phase. The sonic kerosene injection is surrounded by a supersonic co-flow of hot vitiated air, ensuring a jet flame's stabilization. The global equivalence of the burner is set to 0.5. A 5-species global mechanism and a more detailed mechanism from the literature involving 19 species and 54 reactions are compared with a new optimized chemistry involving 18 species and 29 reactions. The impact of ignition delay and droplet size on flame stabilization dynamics and combustion modes is discussed. The necessity of a sub-grid closure for the source terms is assessed. Whatever the kerosene phase, the flame structure is dominated by the non-premixed combustion regime, even if a non-negligible contribution of the rich premixed regime is detected.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110164"},"PeriodicalIF":5.0,"publicationDate":"2025-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143744742","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Research on error compensation methods of wing deflection reconstruction based on FBG strain sensors","authors":"Yiheng Yuan,&nbsp;Wang Sun,&nbsp;Yingjie Zhang,&nbsp;Pinghui Wang,&nbsp;Song Han","doi":"10.1016/j.ast.2025.110167","DOIUrl":"10.1016/j.ast.2025.110167","url":null,"abstract":"<div><div>Fiber Bragg Grating (FBG) sensors have the characteristics of compact size, multiplexing capability, and high sensitivity, making them ideal for structural health monitoring of unmanned aerial vehicles (UAVs). However, FBG strain Sensors measure wing strain rather than wing deflection, necessitating the conversion of strain into deflection through a deflection reconstruction algorithm. The deflection reconstruction process is influenced by the number and placement of sensors, as well as the reconstruction algorithm, which may result in measurement errors.</div><div>To reduce reconstruction errors in wing deflection, this study proposes two approaches: the optimization of sensor placement and the application of an error compensation function.</div><div>Firstly, a method for optimizing the location and number of FBG sensors based on a genetic algorithm is proposed. By optimizing the sensor installation location and number to be more consistent with the actual strain distribution characteristics of the wing, the error of wing deflection measurement based on deflection reconstruction algorithm is reduced.</div><div>Additionally, a novel error compensation function based on Fourier Series Fitting is developed. Static loading test validated that this approach achieves high accuracy and robustness under varying load conditions, making it suitable for improving the precision of wing deflection reconstruction.</div><div>Finally, the wing deflection reconstruction system was implemented on a vertical take-off and landing (VTOL) UAV with a wingspan of 4 meters, achieving real-time measurement of wing deflection and twist angle during flight, verifying the effectiveness of both the reconstruction system and the error compensation function through flight testing.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110167"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746875","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 response reconstruction for variable-mode aerospace structures","authors":"Bin Xia,&nbsp;Tianming Cheng,&nbsp;Cheng Wei,&nbsp;Bindi You","doi":"10.1016/j.ast.2025.110170","DOIUrl":"10.1016/j.ast.2025.110170","url":null,"abstract":"<div><div>Due to continuous changes in dynamic parameters and modal characteristics of spatial structures caused by spatial environment effects, the reconstruction and prediction of structural responses based on a time-invariant model are rendered challenging. To enable accurate reconstruction of responses of on-orbit engineering targets using continuously updated dynamic models, a dynamic response reconstruction method is introduced in this paper, which integrates the Finite Element Model (FEM) with Long Short-Term Memory (LSTM) neural networks. The parameters requiring updates are determined through adjoint sensitivity analysis. A neural network is utilized to establish a mapping between structural responses and parameters subject to updates. Frequency modulation is employed for effective mode separation during signal processing. The dynamic response reconstruction is conducted within the framework of the modal superposition method. A spatial truss and a planar antenna are selected as subjects for numerical analysis, and the outcomes are compared with those obtained from the traditional response reconstruction method. Ultimately, ground testing and verification using motion capture systems validate that improved reconstruction accuracy is provided for variable-mode aerospace structures by the proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110170"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760237","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":"Thermo-chemical non-equilibrium flows and aerodynamic loads of Type III shock/shock interaction on blunted lip of a Mach 12 inlet","authors":"Dengke Li ,&nbsp;Bo Sun ,&nbsp;Chunliang Dai ,&nbsp;Xiong Chen ,&nbsp;Yanjin Man","doi":"10.1016/j.ast.2025.110168","DOIUrl":"10.1016/j.ast.2025.110168","url":null,"abstract":"<div><div>The aerothermal challenges are often accentuated by shock/shock interactions (SSI) in the hypervelocity flow. Due to the small scale, the blunted inlet lip is likely to encounter an extremely harsh thermal environment among the components of an airbreathing vehicle. In the present study, an open-source solver named hy2Foam is used to obtain the unexplored flow characteristics of small-scale Type IIIa SSI at Mach 12 with incident shock angle <span><math><mi>β</mi></math></span> of <span><math><msup><mn>12</mn><mo>∘</mo></msup></math></span>, <span><math><msup><mn>15</mn><mo>∘</mo></msup></math></span> and <span><math><msup><mn>18</mn><mo>∘</mo></msup></math></span>. The transition from Type III to Type IV SSI is observed with the increase of dimensionless intercept <span><math><msub><mi>I</mi><mi>r</mi></msub></math></span>. Different from the results in the previous study, the shear layer in Type IIIa SSI doesn't directly attach but deflects twice before the final attachment. This phenomenon stems from the coupling between the shear layer attachment process and the shock wave/shear layer interaction. As <span><math><msub><mi>I</mi><mi>r</mi></msub></math></span> increases, the Mach reflection (MR) within Type IIIa SSI can transform to regular reflection (RR) owing to the decrease of the first deflection angle of shear layer, and the flows remain steady during the transition process from Type IIIa SSI to Type IV SSI. The flow within a valley region between the shear layer and the cylinder surface is the closest to thermal equilibrium and chemical equilibrium in the whole flow field. Due to the strong recompression shock generated by the final attachment of the shear layer, the peak of pressure and heat transfer at the critical state transitioning from Type IIIa to Type IV SSI is the highest for Type IIIa SSI, achieving 30.8 and 40.08 times to the stagnation values in undisturbed flow, respectively. Finally, a new power-law correlation between pressure and heat transfer intensifications for Type III SSI on the blunted lip of a Mach 12 inlet is obtained. Those insights in this research are poised to provide a reference for the thermal protection design of high Mach number inlets.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110168"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746876","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}