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Vibration Control for Laminated Composite Spherical-Cylindrical-Combined Shells: Theory and Experiment

AIAA JOURNAL 2025年第2期63卷 453-475页

作者： Zang, Jian Zhang, Rong-Yao Yang, Yang Zhang, Zhen Song, Xu-Yuan Zhang, Ye-Wei Chen, Li-Qun Shenyang Aerosp Univ Coll Aerosp Engn Shenyang 110136 Peoples R China Shanghai Univ Shanghai Inst Appl Math & Mech Shanghai 200444 Peoples R China

Considering the structural damage and instability due to extensive vibrations, the present investigation focuses on the dynamic characteristics analysis and vibration control for aerospace structures such as rocket stages and aircraft cowling, modeled as laminated composite spherical-cylindrical-combined shells (SCCSs). The theoretical model of the SCCSs is established by a series of artificial connection and boundary springs. The proposed method's validity is confirmed through finite element analysis and experimental validation. Nickel-titanium-steel wire ropes (NiTi-STs) are then introduced as a passive vibration control method for the SCCSs. Both circumferential and axial NiTi-ST laying schemes demonstrate good vibration control capabilities on the SCCSs. For similar lengths of NiTi-STs, the vibration control effect of circumferential laying schemes is superior to that of the axial one. Furthermore, the vibration control effect of the circumferential schemes is found to be dependent on the number and positioning of NiTi-STs. The influence of the NiTi-ST structural parameters on the vibration control performance is also analyzed;adjusting the structural parameters appropriately is helpful to improve the vibration reduction effect.

关键词： Passive Vibration Control Laminated Composites aircraft components and structure Rockets Vibration Testing Laminated structure Dynamic Analysis Mathematical Models

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Effect of Inlet Geometry on Film-Cooling Effectiveness from Shaped Holes

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JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 2025年第1期39卷 5-14页

作者： Wang, Hanlin Wright, Lesley M. Texas A&M Univ J Mike Walker 66 Dept Mech Engn College Stn TX 77843 USA

Modern gas turbine engines require a sophisticated cooling system design to achieve higher power output and efficiency. This study investigates the potential effect of noncylindrical inlet geometries on the performance of laid-back, fan-shaped film-cooling holes using the pressure-sensitive paint measurement technique on a flat plate. On the basis of a common pattern of outlet geometry, racetrack-shaped inlet geometries with aspect ratios of 2:1 and 4:1 were tested along with traditional cylindrical inlets. The coolant flow conditions range from M = 0.3-1.5 and DR = 1 and 2. The mainstream turbulence intensity is held at 6%. Test results show that the shaped inlets provide a higher area-averaged film-cooling effectiveness over the cylindrical inlet using the same amount of coolant. For the 2:1 inlet, an advantage of 20% higher effectiveness could be maintained for DR = 1, while for DR = 2 this advantage is reduced to 10%. For the 4:1 inlet, when the coolant momentum flux ratio I < 0.5, a similar or slightly higher improvement can be obtained, but when I > 1, the advantage diminishes with the growing I to approximately 5%, at I = 2.25. Regarding discharge coefficients, the 2:1 inlet geometry is similar to the cylindrical inlet. For the 4:1 inlet, it is 2-5% lower or nearly equivalent.

关键词： Cooling Technology High Aspect Ratio Incompressible Flow aircraft components and structure Discharge Coefficient Gas Turbine Engines Free Stream Turbulence Mass Flux Ratio Vortex Dynamics Low Speed Wind Tunnel

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Coupled Aeropropulsive Design Optimization of an Over-wing Nacelle Configuration

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JOURNAL OF aircraft 2025年第1期62卷 94-116页

作者： Abdul-Kaiyoom, Mohamed Arshath Saja Yildirim, Anil Martins, Joaquim R. R. A. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

The over-wing nacelle (OWN) configuration has the potential to improve on the conventional under-wing nacelle (UWN) configuration by enabling higher bypass ratios and increasing noise shielding. To explore this potential, we perform coupled aeropropulsive design optimization to study the coupled analysis and the design tradeoffs between aerodynamics and propulsion. We find that the variations in wing shape are not significant when the OWN configuration is optimized for different fan pressure ratios. Optimizing the OWN configuration using the proposed approach results in 3% less shaft power than optimizing the wing and propulsor separately. The OWN has marginally superior performance over the UWN for the same lower fan pressure ratio. However, this low fan pressure ratio may be unattainable for the UWN configuration because of ground clearance constraints, whereas the OWN configuration is not subject to such constraints. We study the optimal OWN placement and show that placing it aft of the trailing edge and away from the wing root results in lower required shaft power. In this study, we perform single-point optimizations to understand the fundamentals of the OWN configuration in terms of aerodynamics and propulsion. However, multiple operating conditions, structural integrity, and inclusion of the pylon geometry should be considered to assess the net benefit of the OWN configuration. Nevertheless, these advancements in aeropropulsive optimization are critical to OWN configuration design and more sustainable aircraft.

关键词： Aeropropulsive Design Optimization aircraft components and structure aircraft Wing Design Aerodynamic Shape Optimization aircraft Engines aircraft Wing components Structural Integrity Aerodynamic Performance Stagnation Pressure aircraft Design Software

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Retrofit Measures for aircraft Noise Reduction: Simulation Benchmark and Impact Assessment

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JOURNAL OF aircraft 2025年第1期62卷 191-206页

作者： Bertsch, Lothar Pott-Pollenske, Michael Wienke, Felix Kurz, Joscha Delfs, Jan German Aerosp Ctr Inst Aerodynam & Flow Technol Helicopter Dept DLR Bunsenstr 10 D-37073 Gottingen Niedersachsen Germany German Aerosp Ctr Inst Aerodynam & Flow Technol Tech Acoust Dept DLR Lilienthalpl 7 D-38108 Braunschweig Niedersachsen Germany German Aerosp Ctr Inst Flight Syst Flight Dynam & Simulat Dept DLR Lilienthalpl 7 D-37073 Gottingen Niedersachsen Germany German Aerosp Ctr Inst Aerodynam Helicopter Dept DLR Bunsenstr 10 D-38108 Braunschweig Niedersachsen Germany German Aerosp Ctr Inst Aerodynam & Flow Technol Tech Acoust DLR Lilienthalpl 7 D-38108 Braunschweig Niedersachsen Germany

DLR, German Aerospace Center, has developed a low-noise retrofit to reduce noise generation of a conventional midrange transportation aircraft, i.e., measures to the airframe and engine exhaust nozzle. Selected measures have been installed onboard of DLR's flying testbed Advanced Technology Research aircraft and been subject to a flyover noise campaign. The aircraft in its original configuration and the modified aircraft have been tested and measured in flyover campaigns in 2016 and 2019, respectively. Initial simulation models have been derived from the results and previous component simulations and wind tunnel tests to account for the new reduction measures within DLR's system noise prediction tool Parametric aircraft Noise Analysis Module (PANAM). This paper presents the developed measures as selected for the flight test campaigns. An overview of the conducted flight tests is provided. The overall noise simulation process, including aircraft and engine design, flight simulation, and noise prediction, is presented. Simulation results obtained from this process are then compared to the measured levels from the flight campaigns. Estimated simulation uncertainties from PANAM can now be directly compared to differences between measured and simulated levels. Finally, a parameter study is conducted in order to assess the reduction potential of the novel retrofit measures along different simulated flight procedures. Spatial noise distribution in sound exposure level contours is assessed.

关键词： Flight Testing aircraft components and structure aircraft Engine Design Exhaust Nozzles Flight Trajectory Aviation Noise Uncertainty Quantification aircraft Design Supersonic aircraft

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Conceptual Design of aircraft System Routing Architectures Using a Bio-Inspired Algorithm

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JOURNAL OF aircraft 2025年第1期62卷 13-21页

作者： Taneich, Jumpei Rinoie, Kenichi Univ Tokyo Tokyo 1138656 Japan

The increasing complexity of aircraft systems and the shift toward electrical aircraft are driving the introduction of entirely new concepts in aircraft systems and airframe design;it is therefore likely that the evaluation of aircraft systems and their integration with the airframe in the conceptual design phase will play an ever more crucial role in determining the feasibility of a newly proposed aircraft. This paper proposes a bio-inspired design algorithm for allocating space within the airframe to interconnections that supply aircraft systems. The proposed method is an adaptation of an existing pathfinding algorithm, with a novel mechanism to avoid overlap between systems that require segregation. The input required for the proposed method is likely to be available at the conceptual design phase. A detailed description of the proposed method is given, followed by a demonstration using a design problem based on an existing aircraft. Results of the demonstration show that the proposed method is capable of handling redundant systems and their segregation by reducing the overlap between different systems.

关键词： aircraft Systems aircraft components and structure Hydraulic Actuators

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Comparative Research on Landing and Rollout Characteristics of Skid-Equipped and Wheeled aircraft

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JOURNAL OF aircraft 2025年第1期62卷 34-47页

作者： Liang, Taotao Yin, Yin Yin, Qiaozhi Nie, Hong Wei, Xiaohui Nanjing Univ Aeronaut & Astronaut Coll Gen Aviat & Flight Liyang 213300 Peoples R China Nanjing Univ Aeronaut & Astronaut Coll Aerosp Engn State Key Lab Mech & Control Aerosp Struct Key Lab Fundamental Sci Natl Def Adv Design Techno Nanjing 210016 Peoples R China

Skid landing gear is a specialized landing device known for its compact structure and lightweight. However, current research on the dynamic characteristics of skid-equipped aircraft on concrete runways is limited, which raises uncertainties about its practical applications. To address this gap, a general aircraft model based on a modular concept is first constructed, considering the coupling effects of aerodynamic, buffer, and ground forces. On this basis, the differences in motion characteristics between skid-equipped and wheeled aircraft are compared in detail. Then, the impact of various factors on the landing characteristics of skid-equipped aircraft is analyzed, such as initial longitudinal velocity, pitching angle, and friction coefficient of skid. Simulation results show that the lack of buffering capability provided by tires results in a 10.57% increase in overload for skid-equipped aircraft and a 15.39% decrease in the efficiency of the main landing gear buffer. Notably, the initial pitching angle has a critical impact on the landing overload of skid-equipped aircraft. Due to the significant differences in the mechanical properties of the landing gears, the skid-equipped aircraft without nose wheel steering ability is a statically unstable system during the rollout phase. The intervention of asymmetric disturbances would pose a serious threat to the rollout safety.

关键词： Model aircraft aircraft components and structure Friction Coefficient Runways Mechanical Properties Aerodynamic Force Coefficients Slip (Aerodynamics)

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HEMLAB Algorithm Applied to the High-Lift Japan Aerospace Exploration Agency Standard Model

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JOURNAL OF aircraft 2025年第1期62卷 207-218页

作者： Sukas, Hulya Sahin, Mehmet Istanbul Tech Univ Fac Aeronaut & Astronaut TR-34469 Istanbul Turkiye

The high-lift Japan Aerospace Exploration Agency (JAXA) standard model (HL-JSM) has been numerically analyzed in order to further validate the HEMLAB code for realistic aircraft configurations. The numerical algorithm is based on highly efficient edge-based data structure for a vertex-based finite volume algorithm on hybrid meshes. The data pattern is arranged to meet the requirements of a vertex-based finite volume algorithm by considering data access patterns and cache efficiency. A fully implicit version of the numerical algorithm has also been implemented based on the Portable, Extensible Toolkit for Scientific Computation (PETSc) library in order to improve the robustness of the algorithm. The resulting algebraic equations, including the one-equation Spalart-Allmaras, are solved in a monolithic manner using the restricted additive Schwarz preconditioner combined with the flexible generalized minimal residual method [FGMRES(m)] Krylov subspace algorithm. The numerical method is also combined with the metric-based anisotropic mesh refinement library Python Adaptive Mesh Geometry Suite-INRIA (pyAMG) from National Institute for Research in Digital Science and Technology in order to improve the numerical accuracy. The numerical algorithm is initially applied to the two-dimensional L1T2 (National High Lift Programme) high-lift system, and then the calculations around the HL-JSM are carried out at relatively high angles of attack. The numerical results with the anisotropic mesh refinement library pyAMG indicate significant improvements in numerical accuracy.

关键词： Algorithms and Data structures Optimization Algorithm aircraft components and structure Aerodynamic Force Unsteady Reynolds Averaged Navier Stokes Adaptive Mesh Refinement Computational Fluid Dynamics High Performance Computing Fluid Flow Properties

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Full-Field Measurement of Lightweight Nonlinear structures Using Three-Dimensional Scanning Laser Doppler Vibrometry

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AIAA JOURNAL 2025年第4期63卷 1523-1540页

作者： Wang, Xing Yuan, Jie Szydlowski, Michal Schwingshackl, Christoph Sun Yat Sen Univ Sch Aeronaut & Astronaut Shenzhen Campus Shenzhen 518107 Peoples R China Univ Southampton Computat Engn Design Grp Southampton SO17 1BJ England Imperial Coll London Dept Mech Engn London SW7 2AZ England Shenzhen Key Lab Intelligent Microsatellite Conste Shenzhen Peoples R China

Modern noncontact measurement techniques such as the three-dimensional scanning laser Doppler vibrometry (3D SLDV) are advantageous in measuring vibrations of lightweight, thin-walled aerospace structures, which were conventionally deemed as difficult or not feasible to apply using attached transducers. Nevertheless, the full-field measurements using 3D SLDV are still limited to extracting modal properties of linear structures, while measurements of complex nonlinear structures are rarely reported. This paper aims to extend the full-field measurement capability of 3D SLDV and combines it with a multiple-input-single-output vibration controller to deal with nonlinear structures. An advanced test strategy is introduced, which is capable of obtaining amplitude-dependent resonant frequencies, modal damping ratios, and full-field, multiharmonic mode shapes of nonlinear normal modes (NNMs). Conflicting parameters such as the frequency resolution and measurement time are optimized by combining phase separation and phase resonance testing techniques in a coherent strategy. The capabilities of the proposed nonlinear modal testing strategy are demonstrated on a realistic, large-scale fan blade that exhibits softening behaviors. Two of its NNMs were investigated at larger vibration amplitudes. Its nonlinear modal parameters were successfully extracted and validated, highlighting the time efficiency and data accuracy of the proposed strategy for measuring industrial-scale, lightweight nonlinear structures.

关键词： Mechanical and Structural Vibrations Turbomachinery Mechanical Testing Multiple Input Single Output Transducers aircraft components and structure Dynamic Analysis Vibration Measuring Instruments Finite Element Method Communication Technology and Equipment

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Pressure-Sensitive-Paint-Driven Hybrid Unsteady Compressible Flow Simulation

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AIAA JOURNAL 2025年第1期63卷 118-133页

作者： Suzuki, Takao Boeing Co Noise Vibrat & Emiss POB 3707 Seattle WA 98124 USA

A hybrid unsteady compressible computational fluid dynamics simulation (CFD) driven by pressure-sensitive paint (PSP) data is proposed, and the concept is demonstrated in two dimensions. By imposing the wall pressure acquired with PSP as the Dirichlet boundary condition, an unsteady compressible Euler equation solver is marched together with integral boundary-layer equations in time. As a result, an entire flowfield that fits the PSP measurement is created in the CFD domain. This concept is tested by taking PSP data from a past article of a wind-tunnel test using the NASA CRM65 airfoil and the steady and unsteady capabilities of this data-driven hybrid simulation are demonstrated for transonic flows in two dimensions, and the convergence characteristics are also investigated. It is found that a steady shock position, which cannot be accurately predicted by the Euler equation solver with a boundary layer, can be rectified by the hybrid simulation. Moreover, unsteady shock motion due to buffeting can also be captured well by the hybrid simulation.

关键词： aircraft components and structure Wall Modeled Large Eddy Simulation Boundary Layer Equations Unsteady Transonic Flow Supercritical Airfoils Equations of Fluid Dynamics Transonic Wind Tunnel Common Research Model Dirichlet Boundary Condition Particle Tracking Velocimetry

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Data-Driven Full-Field Prediction of Rotorcraft Fuselage Using Measurable Acceleration Response

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AIAA JOURNAL 2025年第4期63卷 1490-1501页

作者： Kim, Hyeongmo Kim, Hyejin Jeong, Inho Kang, Woo-Ram Lee, Hakjin Cho, Haeseong Jeonbuk Natl Univ Dept Aerosp Engn Jeonju Si Jeonbuk Do South Korea Korea Aerosp Ind Korea Rotary Wing Flight Dynamics Team Sacheon Si Gyeongsangnam D South Korea Gyeongsang Natl Univ Sch Aerosp Engn Jinju Si Gyeongsangnam D South Korea

This paper presents a study aimed at predicting the full-field acceleration response of a rotorcraft fuselage. The prediction was achieved from the acceleration response observed at a limited sensor location on the rotorcraft. Moreover, the prediction was realized through a framework that used a data-driven model order reduction and long-short-term memory artificial neural network. To validate the performance of the proposed framework, a rotor/fuselage one-way coupled analysis was performed by considering a fuselage with a utility helicopter configuration and a platform rotorcraft. As a result, the efficiency and accuracy of the full-field prediction performance were confirmed by comparing with the finite element solutions.

关键词： Rotorcrafts aircraft components and structure Finite Element Analysis Artificial Neural Network Acceleration Sensors Helicopters Reduced Order Modelling Proper Orthogonal Decomposition Mechanical and Structural Vibrations Cylindrical Shell structures

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