Aerospace Science and Technology最新文献_第4页

Numerical study on dense-phase powder conveying in the feeding system of powder fueled ramjets

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109782

Haibin Zhang, Shilin Gao, Bofeng Bai

{"title":"Numerical study on dense-phase powder conveying in the feeding system of powder fueled ramjets","authors":"Haibin Zhang, Shilin Gao, Bofeng Bai","doi":"10.1016/j.ast.2024.109782","DOIUrl":"10.1016/j.ast.2024.109782","url":null,"abstract":"<div><div>A better understanding of gas-solid flow in the pneumatic conveying of dense powders is an essential prerequisite for effective design and operation of conveying systems in powder fueled ramjets. This paper presents a resistance modified model applicable to the dense-phase powder conveying in gas-driven piston powder feeding system based on Two-Fluid Model (TFM), and the dynamic grid techniques related to the output powder mass flow rate has been applied on gas-driven piston boundary. The validity of the modified model is confirmed by comparing the predicted powder mass flow rate with data obtained from the experiment. The resistance modified model, which incorporates a comprehensive consideration of gas momentum loss by accounting for local solid fraction, interphase slip velocity, and powder diameter, is proved to significantly improve the accuracy of predicting dense powder conveyance. The features of gas-solid flow evolution in gas-driven piston powder feeding systems are numerical explored. The formation of the fluidizing gas cavity and its radial diffusion characters are studied and the influences of the total pressure of fluidizing gas on mass flow rate of powders are obtained. And choked occurs in gas-powder two-phase conveying to realize a stable propellant feeding under specific pressure ratio conditions. Moreover, pressure ratio determines pressure distribution in nozzle pipe revealing the transition of the flow pattern from core flow to annular flow corresponds directly to the pressure ratio.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109782"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134143","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}

引用次数: 0

Effect of cavity depth on air-breathing rotating detonation engine fueled by liquid kerosene

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109780

Haolong Meng , Baoxing Li , Yanbing Tang , Jiayang Gu , Quan Zheng , Chunsheng Weng

{"title":"Effect of cavity depth on air-breathing rotating detonation engine fueled by liquid kerosene","authors":"Haolong Meng , Baoxing Li , Yanbing Tang , Jiayang Gu , Quan Zheng , Chunsheng Weng","doi":"10.1016/j.ast.2024.109780","DOIUrl":"10.1016/j.ast.2024.109780","url":null,"abstract":"<div><div>In our recent experimental investigation, the feasibility of a liquid-kerosene-fueled air-breathing/ramjet rotating detonation engine featuring a cavity-based annular combustor has been experimentally demonstrated. Achieving stable operation and organized detonation combustion within the rotating detonation combustor presents significant challenges that demand further investigation. Thus, this study aimed to deepen our understanding of the optimal geometrical configuration of a cavity-based annular combustor operating in air-breathing mode. Numerous experiments were conducted to evaluate the impact of varying cavity depths on combustion performance under a supersonic incoming flow with a total temperature of 860 K. The findings indicate that adequate cavity depth is essential for the generation of kerosene-fueled rotating detonation waves in air-breathing mode. Notably, a kerosene–air rotating detonation wave was achieved in combustors with cavity depths ranging from 10 to 30 mm while maintaining a supersonic heated air mass flow rate of approximately 1000 g/s and a minimum equivalence ratio of 0.77. However, at a cavity depth of 10 mm, both the propagation velocity and peak pressure of the rotating detonation waves were significantly lower compared to those at 20 and 30 mm, thereby suggesting that the depth of 10 mm may require optimization. Additionally, optical observations revealed that the detonation reaction zone was located further from the combustor head as cavity depth increased. This indicates that deeper cavity depths allow for longer mixing and preheating times of the combustible mixture before detonation, thereby enhancing detonation performance. This study clarifies how cavity depth influences liquid-fueled rotating detonation and provides guidelines for designing cavity-based annular combustors in air-breathing rotating detonation engines.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109780"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134205","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}

引用次数: 0

Distributed adaptive control of spacecraft formation near an asteroid with input quantization

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109869

Yuedong Wu , Shufan Wu , Hongxu Zhu , Christopher J. Damaren , Wei Wang

引用次数: 0

Assessing the retrieval procedure of complex-valued forces from airborne pressure fields by means of DIC-based full-field receptances in simplified pseudo-inverse vibro-acoustics

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109757

Alessandro Zanarini

{"title":"Assessing the retrieval procedure of complex-valued forces from airborne pressure fields by means of DIC-based full-field receptances in simplified pseudo-inverse vibro-acoustics","authors":"Alessandro Zanarini","doi":"10.1016/j.ast.2024.109757","DOIUrl":"10.1016/j.ast.2024.109757","url":null,"abstract":"<div><div>Lightweight structural components in many engineering fields can be severely excited by airborne pressure fields, becoming a concern for their structural dynamics and reliability. Nowadays, the quality reached by optical measurements, in contactlessly estimating - as maps of displacements over force - complex-valued full-field receptances, allows an accurate description of the structural dynamics in a broad frequency domain, without any numerical structural model. This is even more relevant for lightweight components, otherwise affected by potential distortions, coming from the inertia of more traditional transducers. High-speed DIC structural testing is here combined with acoustic propagation in direct and pseudo-invertable vibro-acoustic FRFs, obtained by the simple Rayleigh integral approximation, here re-formulated to take advantage of the experiment-based full-field receptances, when a force excites a vibrating surface, which radiates sound pressure into air and vice-versa. Starting from airborne pressure fields, known in their spectra, the pseudo-inverse vibro-acoustics aims at identifying the force, with a broad frequency band, which can be transmitted to the excitation locations, previously used in defining the vibro-acoustic FRFs in the direct problem. Extended details and considerations on this full-field receptance-based vibro-acoustic approximation are thoroughly provided, with special attention to its complex-valued nature, to numerical precision and to broad dynamics' excitation signature, thanks to the accurate DIC-based testing of a real thin plate.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109757"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134982","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}

引用次数: 0

Exterior penalty indirect method for collision avoidance among multiple satellites

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109864

Di Wu , Xiang Guo , Zichen Zhao , Hexi Baoyin

{"title":"Exterior penalty indirect method for collision avoidance among multiple satellites","authors":"Di Wu , Xiang Guo , Zichen Zhao , Hexi Baoyin","doi":"10.1016/j.ast.2024.109864","DOIUrl":"10.1016/j.ast.2024.109864","url":null,"abstract":"<div><div>This paper considers the collision avoidance problem among multiple continuous-thrust satellites considering the pursuit-evasion game. First, the problem is formulated as an optimal control problem subject to high-fidelity dynamics and pure state constraints for the collision avoidance between evaders and pursuers. Analytical derivations reveal that the propellant-optimal collision avoidance maneuvers are of bang-bang control structure, and the number and sequence of the constrained arcs must be pre-identified, as each constrained arc introduces at least four more unknowns. To solve this, an exterior penalty indirect method is proposed, incorporating the constraints into the performance index with an activation function. A two-point boundary-value problem is then established and solved by the shooting method, where the constrained arcs are automatically identified without the need for additional shooting variables. By gradually increasing the penalty coefficient, the optimal solution is efficiently obtained starting with the solution neglecting collision. The proposed method is validated through three numerical examples, showing a significant reduction in computational time—cutting it from 2 hours to just 1 minute compared to the widely-used GPOPS. The results demonstrate excellent agreement with GPOPS and previous studies, with relative errors in propellant consumption under 1.0%. Additionally, it is shown that cooperative collision avoidance can reduce fuel consumption by 2.4%, while the presence of pursuers can significantly increase fuel consumption, potentially by several times.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109864"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134238","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}

引用次数: 0

Optimization of mechanical deployable reentry vehicle based on multi-fidelity aerodynamic-trajectory coupling model

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109777

Junjie Sun , Hao Zhu , Haohuan Han , Dajun Xu , Guobiao Cai

{"title":"Optimization of mechanical deployable reentry vehicle based on multi-fidelity aerodynamic-trajectory coupling model","authors":"Junjie Sun , Hao Zhu , Haohuan Han , Dajun Xu , Guobiao Cai","doi":"10.1016/j.ast.2024.109777","DOIUrl":"10.1016/j.ast.2024.109777","url":null,"abstract":"<div><div>As the aerospace industry continues to advance, the demand for round-trip transportation between Earth and space, as well as deep space exploration missions, is increasing. The mechanical deployable reentry vehicle, a complex multidisciplinary system, experiences parameter coupling between trajectory design and aerodynamic simulation. The calculation of trajectory and the design of aerodynamic layout directly impact the flight process. To address issues such as biased trajectory data obtained without considering disciplinary coupling and the high computational costs associated with overall aerodynamic layout optimization, this paper fully considers the impact of global aerodynamic drag on the flight trajectory. A multi-fidelity optimization model for reentry vehicles, named Multi-Fidelity Aerodynamics-Trajectory Coupling (MF-ATC), is proposed. The model uses a large number of low-accuracy model samples to control computational costs, without considering the coupling relationship, and a small number of high-accuracy model samples to ensure approximation accuracy, achieving fast and precise prediction of flight trajectories. The results demonstrate that the MF-ATC model improves trajectory prediction accuracy and efficiently accomplishes aerodynamic shape optimization, effectively enhancing the vehicle's performance. The model shows great potential for engineering applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109777"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134983","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}

引用次数: 0

Penetration of oblique shock wave through different thickness boundary layers

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109863

Shushen Wang , Senhong Xiao , Lifeng Tian

{"title":"Penetration of oblique shock wave through different thickness boundary layers","authors":"Shushen Wang , Senhong Xiao , Lifeng Tian","doi":"10.1016/j.ast.2024.109863","DOIUrl":"10.1016/j.ast.2024.109863","url":null,"abstract":"<div><div>Compression flows, characterized by high Reynolds numbers, typically sustain intense temperature gradients along the wall-normal near the surface due to high viscous dissipation, resulting in a thicker, more unstable developing turbulent boundary layer. In scenarios with large streamwise scales, such as scramjet inlets, where numerous shock waves are present, interactions between varying boundary layer thicknesses and oblique shocks are prevalent. This study investigates these interactions using a configuration involving two different plate turbulent boundary layers, generated by roughness elements arrayed at the leading edge of the plate, and a 37.5° oblique shock. Flow visualization, conducted using Nano-tracer Planar Laser Scattering (NPLS), shows that vortex heads are squeezed into small-scale structures by the discontinuous shock. Velocity fields, measured by Particle Image Velocimetry (PIV), combined with a novel density calibration scheme proposed in this study, are employed to quantitatively analyze the impact of shock waves on the two different thickness boundary layers. The separation region exhibits a similar wall-normal direction scale in both cases, while the streamwise scale extends to 3.4 mm in the thin boundary layer and 4.4 mm in the thicker one. Significant density fluctuations are observed in the reattachment region. Spectral analysis at four wall-normal positions highlights notable distinctions depending on boundary layer thickness. Due to the impingement of the strong oblique shock, the turbulent boundary layer downstream of separation region, originating from the reattachment region, becomes more unstable than the upstream boundary layer, with the power of the universal spectrum increasing by 5-10 times compared to upstream regions. These findings indicate that turbulent boundary layers downstream of multiple shock-wave boundary layer interaction regions exhibit more complex and unstable characteristics, distinct from naturally developing boundary layers.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109863"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134240","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}

引用次数: 0

Global stabilization of circular orbit rendezvous by bounded linear feedback

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109814

Weiwei Luo , Wenbo Fu , Song Zhu , Chuanchuan Xu

引用次数: 0

Fault-tolerant control method for carrier landing with actuator and structural faults

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109872

Heng Wang, Bowen Duan, Jianliang Ai

{"title":"Fault-tolerant control method for carrier landing with actuator and structural faults","authors":"Heng Wang, Bowen Duan, Jianliang Ai","doi":"10.1016/j.ast.2024.109872","DOIUrl":"10.1016/j.ast.2024.109872","url":null,"abstract":"<div><div>This paper studies the autonomous carrier landing problem of carrier-based unmanned aerial vehicle (UAV) under unexpected actuator and structural faults. An adaptive fault-tolerant control method is developed for carrier-based UAV, accounting for both external disturbances and internal faults. Initially, the impacts of unexpected faults on the UAV's physical and aerodynamic characteristics are analyzed, focusing on the loss of actuator efficiency, variations in the inertia matrix, and the generation of additional forces and moments. The effects of wave motion and carrier airwake on the carrier landing process are considered. Subsequently, an automatic landing control system (ALCS) based on the L1 adaptive nonlinear dynamic inversion (L1ANDI) method is proposed to address the challenge of safe landing control under these conditions. The L1ANDI controller combines the nonlinear dynamic inversion (NDI) baseline controller, which addresses known nonlinearities, with the L1 adaptive module to account for unknown nonlinearities introduced by environmental disturbances and UAV faults. The stability of this approach is proven using the Lyapunov function. Finally, comparative simulation experiments are conducted in three scenarios, benchmarking the proposed L1ANDI against NDI and L1 adaptive control, to validate its effectiveness. The results demonstrate that the proposed method exhibits superior control performance and robustness to disturbances and uncertainties compared to other methods. These results indicate that the proposed method enables the safe landing of carrier-based UAV under both external disturbances and internal faults.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109872"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134236","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}

引用次数: 0

Rotor-force controller for multirotors under aerodynamic interferences 气动干扰条件下多旋翼飞行器的旋翼力控制器

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-01 DOI: 10.1016/j.ast.2024.109861

Antonio Gonzalez-Morgado , Pedro J. Sanchez-Cuevas , Guillermo Heredia , Anibal Ollero

{"title":"Rotor-force controller for multirotors under aerodynamic interferences","authors":"Antonio Gonzalez-Morgado , Pedro J. Sanchez-Cuevas , Guillermo Heredia , Anibal Ollero","doi":"10.1016/j.ast.2024.109861","DOIUrl":"10.1016/j.ast.2024.109861","url":null,"abstract":"<div><div>The use of multirotors for inspection tasks requires the ability to perform high-precision flights close to the environment, where aerodynamic effects appear and make control of the platform difficult. This paper presents a control solution for multirotors to deal with aerodynamic effects and other disturbances produced at a motor level. It combines the inclusion of a mechatronic system embedded in the multirotor power plant and a new control architecture focused on enabling a Rotor-Force Controller (RFC) at a motor level. Unlike model-based solutions developed in recent years, our solution can be used with any type of motor perturbation, such as ground and ceiling aerodynamic effects, wind effects, battery discharge and rotor damage effects. The implementation of both parts, the mechatronics system and the Rotor-Force Controller, are presented in this paper and experimentally validated in a custom testbench. The experiment shows that the proposed Rotor-Force Controller reduces the impact of aerodynamic effects on platform attitude approximately 80% compared with the results without the Rotor-Force Controller.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109861"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142825352","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}

引用次数: 0