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Aerospace science and technology
Elsevier Science: Editions Scientifiques et Medicales Elsevier
Aerospace science and technology

Elsevier Science: Editions Scientifiques et Medicales Elsevier

1270-9638

Aerospace science and technology/Journal Aerospace science and technologySCIEI
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    Parameter correction and ground testing of large-scale space structure

    Ce ZhaoNaihan YangDongfang ZhuWenyu Feng...
    110022.1-110022.9页
    查看更多>>摘要：This paper investigates the modeling and testing of large-scale space structure on the ground, simulating the zero-gravity environment of space. Large-scale space structure is widely utilized for their advantages such as light weight, excellent extensibility, and high stability. Applications include deployable truss antenna structures on satellite platforms, space station frameworks, and extendable arms on space structures. A large-scale space structure was established at actual scale on the ground for accurate simulation and experimental validation. Initially, a ground-based motion simulation test system for the large-scale space structure was developed, and sweep frequency tests were conducted. The collected experimental data were then analyzed using the covariance-driven stochastic subspace system identification method to obtain the modal information of the large-scale space structure. Subsequently, both the full-scale and equivalent models of the large-scale space structure were established. To more accurately obtain the equivalent modeling parameters, a hybrid particle swarm optimization algorithm was employed, using the experimental modal data as the target to correct the initial material and geometric parameters of the model. Finally, a hexapod was used to simulate the satellite attitude maneuvers, driving the large-scale space structure, and the collected experimental data were compared with the simulation results to verify the effectiveness of the equivalent model.
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    Multiphysics coupling in the thermoacoustically unstable PRECCINSTA burner described using Doak's Momentum Potential Theory

    Raffaele D'AnielloSylvain C. HumbertSimon GoevertKarsten Knobloch...
    110140.1-110140.12页
    查看更多>>摘要：This study uses a novel approach, based on Doak's so-called "Momentum Potential Theory (MPT)", to describe the unstable behaviour of a lab-scale model combustor. The main advantages of using this approach are that of enabling an unambiguous decomposition of vortical, acoustic, and entropic fluctuations, and providing a reliable description of the system's acoustics despite the highly-turbulent, non-isentropic environment. These properties of the MPT-based approach are employed for the first time to characterise a self-excited unstable thermoacoustic feedback-loop, occurring in the PRECCINSTA burner, whose flow dynamics are simulated by large-eddy simulation. Within this framework, two types of decomposition are employed to separate vortical, acoustic, and entropic fluctuations: one in terms of momentum fluctuations, which is able to highlight typical hydrodynamic features of the flow and one in terms of total fluctuating enthalpy, which delivers a cleaner representation of the system state. Utilising such concepts, the following main results are demonstrated: (ⅰ) the proposed decomposition of the fluctuations is able to retrieve the unstable behaviour of the combustor, characterised in the considered case by a frequency close to 390 Hz and its successive harmonics; (ⅱ) since entropic and acoustic fluctuations are almost in phase at the injection only, the coupling in this region can be considered as one of the main driving mechanisms of the thermoacoustic feedback-loop; (ⅲ) the acoustics is dominated by a bulk oscillation inside the combustion chamber, which may result from the interplay between an ITA mode and an Helmholtz mode of the chamber; (ⅳ) typical dynamical features of the flow, like flame roll-up or destruction / construction of central vortex core and central recirculation bubble can be identified from vortical and entropic fluctuations. All of these findings contribute to demonstrate the suitability of the MPT - especially regarding the decomposition in terms of total fluctuating enthalpy - to obtain a comprehensive description of thermoacoustic oscillations in unstable combustors.
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    A few-shot deep learning framework for predicting high-velocity impact response of ultra-high molecular weight polyethylene fiber-reinforced composites

    Haibo JiYongqian ZhangXin WangLiutong Qin...
    110152.1-110152.13页
    查看更多>>摘要：Ultra-high molecular weight polyethylene (UHMWPE) fiber-reinforced composites have been extensively employed in aerospace situations requiring outstanding impact resistance. In real scenarios, high-velocity im-pactors may strike the UHMWPE laminates from diverse angles, possibly resulting in unpredictable protection performance changes. However, when considering this issue, existing experimental and simulation methods are resource-intensive, while theoretical approaches lack broad applicability. To this end, this study establishes a deep learning framework, trained on a small dataset, to predict not only the ballistic limit but also the penetration process of the UHMWPE composite plates subjected to oblique impact by flat-nosed projectiles. The effectiveness of the deep learning model is fully validated by both experimental observations and numerical simulations. It is demonstrated that the model consisting of CNN, BiLSTM, and Attention mechanism captures the ballistic limit velocities, contact force histories, and residual velocity evolutions with a reasonable correlation (i. e., the average R~2 ≥ 0.97) using only 30 samples, addressing the challenge of limited experimental data in ballistic research. Additionally, the prediction time of the current model is significantly reduced to 20.7 s, compared to the hours required for conventional experimental or computational efforts. Based on the model, it is indicated that for the UHMWPE composites of any thickness, the ballistic limit initially decreases and then increases with the impact angle; the physical mechanism underlying this non-monotonic trend is attributed to the nonlinear variation in the contact force histories. Overall, by revealing the mechanisms governing angle-dependent ballistic performance, this paper provides a novel data-driven approach and new physical insights for optimizing impact-resistance materials and structures based on the UHMWPE composites.
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    Prediction of compressor blade cascade flow field based on Fourier neural operator

    Lixiang JiangXinlong FengQuanyong Xu
    110208.1-110208.13页
    查看更多>>摘要：This study employs the Fourier Neural Operator (FNO), a machine learning framework, to achieve fast prediction of cascade flow fields, accounting for variable cascade geometries and flow conditions. Based on the NACA65 airfoil, we sampled design parameters to generate 300 different cascade geometries. Subsequently, several sets of flow field data were generated by varying the inlet flow velocity and inlet angle of attack, of which 1500 sets were selected for model training and validation. For the geometric representation of the cascade, a coordinate transformation method was used, which can provide the geometric information of the airfoil more accurately and improve the prediction accuracy of the blade wall region. To further enhance the representation of geometric information, a signed distance function (SDF) was additionally introduced. Variations in cascade flow conditions were primarily reflected by adjustments to the inlet airflow velocity and angle of attack. The loss function was designed to comprehensively account for multiple factors, including norm-based loss, gradient-weighted loss, wall-layer-weighted loss, and periodic boundary constraint loss. By incorporating these constraints, the model achieved an MSE error magnitude of 10~(-6), with significantly improved prediction accuracy near the blade walls. In summary, this study demonstrates the effectiveness and high accuracy of the fourier neural operator in the prediction of the flow field of complex cascades, and provides a fast and reliable computational method for the design and optimization of cascades, which has an important value for engineering applications.
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    Effective emission control of aero-engines via nonlinear dual-estimators for uncertain states and parameters

    Anthony Siming ChenGuido HerrmannReza IslamMatthew Turner...
    110210.1-110210.11页
    查看更多>>摘要：This paper proposes an effective emission control strategy for an aero-engine using nonlinear dual-estimators, which aims to address challenges arising from state and parameter uncertainties. Transient air-fuel ratio (AFR) regulation issues, primarily caused by the wall-wetting and manifold-filling phenomena, are mitigated by a novel approach leveraging dual nonlinear estimators: (ⅰ) an extended Kalman filter (EKF) and (ⅱ) an unknown dynamics estimator (UDE). The EKF estimates the fuel mass flow rate and unknown internal parameters, while the UDE compensates for nonlinear air-filling dynamics by estimating a lumped term involving the second derivative of air mass flow. The control framework is built upon a modified mean value engine model (MVEM), tailored to capture the unique dynamics of the rotary aero-engine. Building upon the foundational concepts developed in earlier research, this work moves toward practical application by demonstrating the proposed strategy through real-world experiments conducted on an AIE 225CS rotary aero-engine under a standard driving cycle, marking a significant step forward from theory to application. Furthermore, it introduces a complete stability analysis that addresses the coupling of dual-estimation errors, an aspect not explored in prior work. Comparative experimental results against an industry-standard gain-scheduling PID controller demonstrate the proposed method's performance in achieving improved AFR regulation and significant emissions reduction.
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    Numerical research on mixing combustion characteristic of vortex flow pancake hybrid rocket motor

    Zhiyuan ZhangWenhe LiaoHanyu DengYu Cheng...
    110211.1-110211.14页
    查看更多>>摘要：Vortex flow pancake hybrid rocket motor has advantages of compact structure, high combustion efficiency and little shift of oxidizer-to-fuel ratio, which bringing it broadly application prospect in hybrid propulsion system of micro/nano satellite. In order to optimize design and improve performance, it is essential to have a deeper understanding of the mixing combustion characteristics in vortex flow pancake hybrid rocket motor. In this paper, three-dimensional numerical simulation was conducted to investigate the mixing combustion characteristic of vortex flow pancake hybrid rocket motor through a pressure-based finite volume solver based on the OpenFOAM. The heat transfer process between the solid fuel and the combustion flow field was considered and fire experiment was carried out to validate the solver by a lab scale motor. On this basis, the effect of diameter, number and angle of oxidizer injection orifice on flow characteristic, flow field distribution, fuel regression rate and combustion performance of vortex flow pancake hybrid rocket motor were evaluated. The results indicate that high injection velocity of oxidizer can extremely enhance the mixing of oxidizer and fuel gas in combustion chamber, which further improve the combustion efficiency. However, the fuel consumption along the oxidizer flow path also significantly increases and results in uneven fuel profile on grain surface. Increasing the number of oxidizer injection orifice can make this problem caused by oxidant flow get some mitigated, and the mixing and combustion performance of the motor are slightly reduced as the number of oxidizer injection orifice increasing. Too large or small injection orifice angles seem both not conducive to the mixing and combustion in combustion chamber. When the injection orifice angle is 30°, the characteristic velocity and combustion efficiency are maximum.
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    Design of an automatic landing strategy for fixed-wing aircraft based on longitudinal and lateral collaborative hierarchical control

    Zhaolei PanYangjun Pi
    110217.1-110217.15页
    查看更多>>摘要：Aircraft automatic landing control technology faces several challenges, including the complexity of nonlinear dynamic modeling, inadequate response to external environmental disturbances (such as wind speed), the difficulty of multivariable control, and the difficulty of meeting high-precision control requirements. To address these issues, this paper proposes an automatic landing control system based on a longitudinal-lateral collaborative hierarchical control strategy, with a focus on the fixed-wing twin-engine transport aircraft. The nonlinear mathematical models of its longitudinal and lateral motion are constructed. Unlike traditional independent longitudinal or lateral control strategies, this approach combines classical Proportional-Integral-Derivative (PID) control and Model Predictive Control (MPC), where the outer-loop PID controller is responsible for trajectory tracking and the inner-loop MPC controller optimizes attitude control, fully leveraging the advantages of both in terms of dynamic response and steady-state performance. This longitudinal-lateral collaborative hierarchical control method effectively addresses flight path deviations and attitude changes while ensuring stable landings under complex meteorological conditions, such as crosswinds and turbulence. Simulation results demonstrate that, compared to traditional single control methods, the proposed strategy not only improves the system's robustness and stability in complex environments but also optimizes energy efficiency, offering high adaptability and real-time performance suitable for a wide range of practical flight missions. This research provides new theoretical support for automatic landing technology in fixed-wing aircraft and offers strong support for the design and implementation of next-generation intelligent flight control systems.
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    Suppressing complex flow fields and losses in a transonic compressor with micro-structures

    Zhiyuan CaoNa YangXi GaoZhipeng Li...
    110223.1-110223.14页
    查看更多>>摘要：This paper focuses on a highly-loaded compressors with microstructures that are utilized to control the flow with the aim of enhancing the compressor efficiency and elucidating its complex internal flow mechanism. To this end, numerical simulations are employed to examine the flow mechanism in the near endwall zone of the highly-loaded compressor blade and to investigate the secondary flow and corner separation of the endwall under operating conditions. The impacts of influential micro-vortex generator (MVG) mechanisms on the secondary flow, as well as corner separation and laminar flow on the blade surface of the a highly-loaded compressor are investigated in some detail. The obtained results reveal that the vortex generator (VG) is capable of effectively controlling the blade surface flow separation and corner separation. Compared with the original compressor, after installing the VG, its efficiency is effectively enhanced such that the largest increase is obtained as high as 0.63 %, and its margin increase reaches 25.1 %. As the VG is installed near the leading edge of the rotor blade, it exhibits the best effect on the efficiency improvement, and when the VG is installed in the middle of the rotor blade, the largest effect is observed on the margin. The VG will induce vortices in its wake, which alters the vortex structure within the passage. This modification enhances the mixing of low-momentum fluid with the mainstream flow in the endwall region. As a result, it helps to prevent corner separation, ultimately improving overall flow performance.
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    Assessing the structural design of fixed-wing airframes for next-generation electric aircraft

    Kathrin SchulteSteven O'KeefeMaksym RybachukSascha Stegen...
    110224.1-110224.20页
    查看更多>>摘要：The aviation industry faces a major push for a technology transformation to electric propulsion systems as current worldwide environmental requirements demand a shift from fossil fuels to sustainable energy. To achieve this, improved airframe and propulsion systems must be developed, while keeping the strict regulations and standards of the aviation safety authorities in mind. This paper focusses on the introduction of traction batteries and electric motors in the general and civil aviation industry by assessing the potential of proven airframe designs as well as unconventional concepts for electric aircraft. First, hybrid and all-electric propulsion system concepts are examined by evaluating the feasibility and integration challenges based on a comparative analysis of existing electric aircraft which provide insights into current industry practices. Also, general principles of aircraft design are explored, which can be tailored to electric propulsion systems, highlighting key structural modifications required for optimized performance. In this study, the impact of suitable State-of-the-Art as well as future battery and motor performances on the range, mass and aircraft structure are investigated. For this approach, two aircraft of different sizes and use are taken into consideration. The Cessna 172S for recreational purposes and the ATR72-600 for regional passenger transport. The findings of the investigation and calculations offer a holistic perspective on the design as well as operational considerations necessary for advancing electric aircraft. Thus, this paper provides a comprehensive current picture of the transition to sustainable aviation solutions and a guide for future innovations.
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    Establishment and stabilization of ethylene-air flames in a strut-fueled supersonic combustor: with and without oxygen supplementation

    Zhuoxin WanYouyin WangHongchao QiuShiqi Zhang...
    110237.1-110237.14页
    查看更多>>摘要：This study investigates the ignition characteristics and stable combustion behavior of ethylene fuel in a strut-fueled scramjet combustor under supersonic conditions. The role of oxygen supplementation at the strut's trailing edge in enhancing combustion was examined. Through combined experimental and numerical approaches under Mach 2.8 inflow conditions at the isolator inlet, flame dynamics and pressure distributions were characterized using high-speed imaging and pressure measurement techniques. Results demonstrate that flame stabilization without oxygen supplementation relies solely on shear layer combustion at the strut extremities. Oxygen supplementation significantly enhanced mixing efficiency, inducing a dual-mode combustion pattern combining shear layer and strut wake flames while reducing flame establishment time by 78.8%. Further analysis reveals that supplying oxygen extends the ignition boundary of the global fuel-air equivalence ratio from 0.4 to 0.55. Spatiotemporal analysis of flame imaging identifies an attenuation oscillation process in combustion intensity post-oxygen supplementation. These findings provide critical insights for optimizing flame stabilization strategies in scramjet combustor design.
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