该杂志致力于通过传播揭示新的理论发展和/或实验结果的原始档案研究论文来促进航天和航空科学技术的进步。主题包括气动声学、空气动力学、燃烧、推进基础、流体力学和反应流、航空航天环境的基本方面、流体动力学、激光和相关现象、等离子体、研究仪器和设施、结构力学和材料、优化以及热力学和热化学。还寻求以密集方式审查上述任何主题的最新研究发展结果的论文。

The AIAA Journal is dedicated to advancing aerospace and aeronautical science and technology by disseminating original research papers that reveal new theoretical developments and/or experimental results. Topics include aeroacoustics, aerodynamics, combustion, propulsion fundamentals, fluid mechanics and reactive flows, fundamental aspects of the aerospace environment, hydrodynamics, lasers and related phenomena, plasma, research instruments and facilities, structural mechanics and materials, optimization, as well as thermodynamics and thermochemistry. The journal also seeks papers that review the latest research developments in any of the aforementioned topics in depth.

AIAA Journal 是一本致力于通过传播新的理论发展和实验结果的原创研究论文，促进航天和航空科学技术进步的期刊。其主题涵盖气动声学、空气动力学、燃烧、推进基础、流体力学和反应流、航空航天环境的基本方面、流体动力学、激光及相关现象、等离子体、研究仪器和设施、结构力学与材料、优化，以及热力学和热化学。此外，期刊还欢迎对上述任何主题的最新研究发展进行深入审查的论文。

AIAA Journal

Nomenclature A = coefficient defined in Eq. (A40) A Q = area B = magnetic field c = speed of light C = correlation function Cn = index of refraction structure function constant Cp = specific heat D = diameter of aperture D = electric displacement E = spectrum E = electric field H = magnetic induction / = intensity // = Bessel function of order / k = wave number / = turbulence scale size L = path length

George W. Sutton

Aero-optical foundations and applications

Accurate predictions of the spray angle play a significant role in the design and operation of the pintle injectors. However, existing prediction models are often based on idealized assumptions and expressed as the functions of the jet-to-film momentum ratio corrected by different coefficients, which result in the weak generalization abilities of these models. In the present study, a prediction model for the spray angle of the liquid–liquid pintle injector was established and verified. The initial interactions between the radial jet column and the axial jet film were considered, and the deflected trajectory of the transverse jet column was derived theoretically; then, the spray angle of the pintle injector was thus obtained. Specially designed experiments were carried out, and the spray angles were extracted by using high-speed photography. The comparisons between the experimental and the predicted results clearly exhibit the limitations of the traditional models that are based on the momentum ratio only, and they prove the accuracy of our new model.

Fan Zhao

Haibin Zhang

Liang Zhao

Bofeng Bai

A New Modeling Method for Spray Angle Prediction of Liquid–Liquid Pintle Injector

Unstable buckling leads to the failure of thin-walled cylinders under axial compression. Because of the manufacturing and loading imperfections, a significant variation was observed between experimental and theoretical buckling load. The current design criteria use a knockdown factor to estimate the buckling load of thin-walled structures. However, the design criteria employed a very conservative knockdown factor, because it is difficult to be accurately predicted. To improve the certainty of the knockdown factor, in this paper, a physics-informed artificial neural network (PANN) was employed to predict the thin-walled cylinder buckling load using experimental data collected by Seide. PANN has the potential to improve prediction and enforce some physical laws. A beam problem was presented to demonstrate the PANN capability. Then, the cylinder buckling analysis was carried out with PANN. An inequality constraint was applied to force the neural-network-predicted buckling load to be equal or smaller than the corresponding experimental data. The result shows that PANN can reach excellent prediction accuracy and is able to predict the buckling load equal to or smaller than the corresponding experimental buckling load. Additionally, both ANN and PANN are able to take the unique influential parameters as inputs and do not have presumed expression and thus have the potential to yield a less conservative prediction than the statistical equation.

Fei Tao

Xin Liu

Haodong Du

Wenbin Yu

Physics-Informed Artificial Neural Network Approach for Axial Compression Buckling Analysis of Thin-Walled Cylinder

New experimental data are used to show that the direct simulation Monte Carlo (DSMC) method provides an accurate description of a low-density flow in the nozzle and the near-field expansion of a small rocket for two slightly different experimental configurations. These results verify the DSMC method in an expansion flow for the first time. From a number of different gas/surface interaction models, it is found that fully diffuse reflection gives the best agreement with experiment.

lain D. Boyd

Paul F. Penko

Dana L. Meissner

Kenneth J. DeWitt

Experimental and numerical investigations of low-density nozzle and plume flows of nitrogen

An inviscid, rotational flow model for incompressible jet impingement is formulated in terms of vector and scalar potentials and the vector vorticity. The set of four elliptic partial-differential equations governing the kinematics of the flow and three coupled hyperbolic equations for the vorticity are solved numerically for the impingement of fully developed round jets upon a plane wall at incidence angles of 90 (normal), 75, and 60 deg. The finite-difference computations are consistent with both existing rotational stagnation point analysis and reported data on stagnation point location, wall pressure, and, to a lesser extent, azimuthal distribution of momentum efflux.

A. Rubel

Computations of the oblique impingement of round jets upon a plane wall

Mistuning in bladed disk structures disrupts their cyclic symmetry, potentially resulting in high cycle fatigue. The stochastic nature of mistuning greatly increases the computational cost of related studies. To improve computational efficiency, previous research has primarily focused on reduced-order models based on finite element methods, whereas the increasing demand for rapid computation and precise predictions has led to the emergence of data-driven approaches. These methods directly use vibration data from bladed disks, eliminating the need for building complex physical models. The accuracy of these methods is dependent on the size of the data, which, however, are often difficult to obtain. To overcome the challenge of insufficient data, this study introduces a Physics-Informed Neural Network Surrogate Model for Small-Sample Mistuned Bladed Disk (PINN-SMBD). This new method combines neural networks with the knowledge of bladed disk dynamics mainly reflected in the following three features: the integration of the governing equations of a mistuned bladed disk in the network architecture, the selection of the input and output according to the frequency independence of the response, and the data augmentation using the cyclic characteristic of bladed disks. Moreover, a dataset construction strategy is proposed that the use of datasets with high variance of mistuning can speed up model convergence and improve accuracy. Finally, a PINN-SMBD model for a dummy bladed disk is built by using only 30 samples which demonstrates remarkable accuracy.

Yu Fan

Jiasen Fan

Anlue Li

Yaguang Wu

Wenjun Wang

Physics-Informed Neural Network Surrogate Model for Small-Sample Mistuned Bladed Disk

小样本失谐叶盘的物理信息神经网络代理模型

This study investigates the differences in plume-surface interaction (PSI) cratering behavior between Earth atmospheric (101,325 Pa) and subatmospheric (33 Pa) ambient pressures. A stereo-photogrammetry technique was used to nonintrusively obtain 3D, time-resolved measurements of the full-domain crater geometry. Tests were conducted inside an optically accessible vacuum chamber where the PSI process was simulated using a sonic jet impinging on a bed of regolith simulant. Crater geometry measurements were taken at nozzle heights of 4.6 to 55.6 nozzle diameters above the simulant surface. Results show that the highly underexpanded plume under subatmospheric conditions resulted in broad and shallow craters compared to craters formed under Earth atmosphere. Some craters under subatmospheric conditions exhibited lobed geometry characterized by azimuthal depth variations. In these same cases, the deepest portion of the crater was located radially away from the center, and particles were observed moving toward the center resulting in fountain-like particle movement. Craters formed under Earth atmospheric conditions had an axisymmetric parabolic geometry with the location of maximum depth at the center. In general, subatmospheric crater growth was slower than Earth atmospheric. However, subatmospheric crater formation at nozzle heights of 9.3D and below was characteristically like Earth atmospheric crater formation at large nozzle heights.

Daniel C. Stubbs

Lokesh Silwal

Vikas N. Bhargav

Brian S. Thurow

Vrishank Raghav

David E. Scarborough

The Effect of Reduced Ambient Pressure on Plume-Surface Interaction Cratering Dynamics

减小环境压力对羽流-表面相互作用撞击坑动力学的影响

Improving the vibration isolation performance of the helicopter’s main gearbox strut can reduce the vibration level transmitted to the aircraft body and the level of structural noise radiation. This article proposes a piezoelectric stack periodic strut (PSPS) scheme based on the piezoelectric stack and rubber periodic arrangement. Piezoelectric stack actuators can achieve active vibration and noise control, and the periodic structure of the piezoelectric stack actuators and rubber also has wideband stopband characteristics for reducing vibration and noise. Therefore, PSPS has active and passive hybrid control capabilities, which has advantages in vibration and noise reduction performance, the power of active control, volume and mass, etc. This article presents a full-parameter model that can describe the electromechanical coupling dynamic performance of PSPS. The correctness of the model was verified by the finite element software, and the concept of optimal isolation potential of PSPS was proposed and evaluated. Finally, the hybrid control capability of PSPS for single-frequency and wide-frequency noise was verified through experiments. The results show that compared with the noise level of the cabin using an ordinary strut, PSPS has wideband vibration reduction and noise reduction performance above 500 Hz, with a maximum noise attenuation exceeding 25 dB. When applying active noise control to the PSPS on the helicopter model, a control effect of 12.63–15.56 dB at 900 Hz was achieved.

Huiyu Yue

Hongtao Xue

Dongpo Yang

Fengjiao Wang

Yang Lu

Hybrid Noise Control in Helicopter Cabin with Piezoelectric Stack Periodic Strut

直升机舱室压电堆周期支柱混合噪声控制

Ella Wu

Charles A. Mader

Joaquim R. R. A. Martins

Clarification: Sensitivity-Based Geometric Parametrization and Automatic Scaling for Aerodynamic Shape Optimization

澄清：基于敏感性的几何参数化和气动外形优化的自动缩放

In this report, we investigate the onset of chaotic flutter in laminar and turbulent flows over a two-dimensional semi-infinite panel using time-accurate fluid–structure interaction (FSI) simulations of shock–boundary-layer interactions (SBLIs). Results indicate that the critical dynamic pressure and the nature of the panel dynamics strongly depend on the static pressure differential across the shock, the local loading, the viscous and turbulent damping in the flow, and the formation of dynamic flow separation bubbles due to the SBLIs. The structural system undergoes local instability (Hopf bifurcation) when the local loading due to panel deformation overcomes the static pressure differential across the shock. In the absence of external fluid instabilities, the structural oscillations will induce unsteadiness in the flowfield, resulting in low-frequency limit-cycle oscillations. Viscous and turbulent damping in the boundary layer also delays the bifurcation and reduces the amplitude of the oscillations. Sufficiently strong shocks can produce localized flow separations, which drive additional boundary-layer instabilities, resulting in an early bifurcation. In the presence of external fluid instabilities, the behavior of the FSI strongly depends on the nonlinear coupling of their instabilities. Chaotic oscillations are observed when the fluid instabilities are dominant enough to induce structural oscillations with broadband frequencies.

Abbreviation
Journal Impact	2.24
Quartiles(Global)	ENGINEERING, AEROSPACE(Q2)

ISSN	0001-1452, 1081-0102, 1533-385X
h-index	180

Publication Information	Publisher: American Institute of Aeronautics and Astronautics Inc. (AIAA)，Publishing cycle: Monthly，Journal Type: journal，Open Access Journals: No
Basic data	Year of publication: 1963，Proportion of original research papers: 99.44%，Self Citation Rate:14.30%， Gold OA Rate: 3.15%
Average review cycle	网友分享经验：一般,3-6周
Average recruitment ratio	网友分享经验：容易

AIAA Journal

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