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Aerospace
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Aeroelasticity, Volume IV
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Aeroelasticity, Volume IV

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (20 September 2024) | Viewed by 6253

Special Issue Editor

Dr. Enrico Cestino

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Politecnico di Torino, 10129 Turin, Italy
Interests: aeroelasticity; aircraft design; aerospace structural analysis
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Aviation’s contribution to global CO2 emissions has come under scrutiny since the early 2000s. For this purpose, new aircraft configurations with greater energy efficiency are being developed. One way to increase energy efficiency is to reduce structural weight and the increase the wing aspect ratio.

The resulting slender, lighter, and highly flexible structures are prone to exhibit aeroelastic instabilities and require radically different structural and manufacturing concepts. The extensive use of anisotropic materials can play a crucial role in enhancing aircraft performance with no additional penalties on weight. To this end, aeroelastic tailoring is a fundamental tool. Potential enabling technologies are functionally graded materials (FGM), variable angle tow (VAT), curvilinear stiffeners, and foldable wings. The ongoing revolution in computer-aided design and manufacturing technologies has broken down barriers and paved the way for a variety of innovative solutions. The use of additive manufacturing (AM) can lead to numerous advantages either in terms of time and costs saving or the possibility of increasing the mould’s complexity and customization.

Uncertainties associated with the prediction of flight loads and manufacturing processes are not negligible, especially during the conceptual design phases due to the lack of information about the new product to be designed. Methods to quantify adequate design margins to account for the various sources of uncertainty are essential in order to satisfy safety levels imposed by regulations. Finally, experimental tests will provide the opportunity to verify the effectiveness of the design choices.

Research in this field is characterized by a highly multidisciplinary approach including theoretical, computational, and experimental studies.

Potential topics include but are not limited to the following:

  • New design concepts for future aircrafts;
  • Advanced numerical model development for aero-structural analyses and process simulation;
  • Optimization of composite structures;
  • Innovative morphing wing concepts to improve aeroservoelastic behaviour and active wing technology;
  • Uncertainty in composite aerostructures’ design;
  • Aeroelastic experimental tests.

Dr. Enrico Cestino
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

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Related Special Issues

Published Papers (5 papers)

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Research

26 pages, 8694 KiB  
Article
Semianalytical Research on Aerothermoelastic Behaviors of Functionally Graded Plates under Arbitrary Temperature Fields in Hypersonic Vehicles
by Chang Li, Zhiqiang Wan, Xiaozhe Wang, Chao Yang and Keyu Li
Aerospace 2024, 11(7), 572; https://doi.org/10.3390/aerospace11070572 - 12 Jul 2024
Viewed by 791
Abstract
Hypersonic vehicles are susceptible to considerable aerodynamic heating and noticeable aerothermoelastic effects during flight due to their high speeds. Functionally graded materials (FGMs), which enable continuous changes in material properties by varying the ratio of different materials, provide both thermal protection and load-bearing [...] Read more.
Hypersonic vehicles are susceptible to considerable aerodynamic heating and noticeable aerothermoelastic effects during flight due to their high speeds. Functionally graded materials (FGMs), which enable continuous changes in material properties by varying the ratio of different materials, provide both thermal protection and load-bearing capabilities. Therefore, they are widely used in thermal protection structures for hypersonic vehicles. In this work, the aerothermoelastic behaviors of functionally graded (FG) plates under arbitrary temperature fields are analyzed via a semianalytical method. This research develops a method considering the influence of thermal loading, specifically the decrease in stiffness due to thermal stresses, as well as the correlation between material properties and temperatures under arbitrary temperature fields, based on Ritz’s method. The classical plate theory, von–Karman’s large defection plate theory and piston theory are employed to formulate the strain energy, kinetic energy and external work functions of the system. This paper presents a novel analysis of static aerothermoelasticity of FG plates, in addition to the linear/nonlinear flutter under arbitrary temperature fields, such as uniform, linear and nonlinear temperature fields. In addition, the effects of the volume fraction index, dynamic pressure, and temperature increase on the aerothermoelastic characteristics of FG plates are analyzed. Full article
(This article belongs to the Special Issue Aeroelasticity, Volume IV)
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23 pages, 8853 KiB  
Article
Fluid–Structure Interactions between Oblique Shock Trains and Thin-Walled Structures in Isolators
by Xianzong Meng, Ruoshuai Zhao, Qiaochu Wang, Zebin Zhang and Junlei Wang
Aerospace 2024, 11(6), 482; https://doi.org/10.3390/aerospace11060482 - 18 Jun 2024
Viewed by 682
Abstract
Understanding aeroelastic issues related to isolators is pivotal for the structural design and flow control of scramjets. However, research on fluid–structure interactions (FSIs) between thin-walled structures and the isolator flow remains limited. This study delves into the FSIs between thin-walled panels and the [...] Read more.
Understanding aeroelastic issues related to isolators is pivotal for the structural design and flow control of scramjets. However, research on fluid–structure interactions (FSIs) between thin-walled structures and the isolator flow remains limited. This study delves into the FSIs between thin-walled panels and the isolator flow, as characterized by an oblique shock train, by quantitatively analyzing 11 flow parameters assessing the structural response, separation zones, shock structures, flow symmetry, and performance. The results reveal that an FSI triggers panel flutter under oblique shock train conditions, with the panel shapes exhibiting a combination of first- and second-mode responses, peaking at 0.75 of the panel length. Compared to rigid wall conditions, isolators with a flexible panel at the bottom wall experience downstream movement of the separation zones and shock structures, reduced flow symmetry, and minor changes in performance. Transient fluctuations occur due to the panel flutter. Two flexible panels at the top and bottom walls have a comparatively lesser influence on the averaged parameters but exhibit more violent transient fluctuations. Furthermore, the FSI effects under oblique shock train conditions are contrasted with those under normal shock train conditions. The flutter response under normal shock train conditions is more pronounced, with a larger amplitude and higher frequency, driven by the heightened participation of the first-mode response. The effects of FSIs under normal shock train conditions on the averaged parameters are the opposite (with a larger influence) to those under oblique shock train conditions, with significantly more drastic transient fluctuations. Overall, this study sheds light on the complex and substantial influence of FSIs on the isolator flow, emphasizing the necessity of considering FSIs in future isolator design and development endeavors. Full article
(This article belongs to the Special Issue Aeroelasticity, Volume IV)
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17 pages, 13709 KiB  
Article
Effect of Intake Acoustic Reflection on Blade Vibration Characteristics
by Hui Yang, Hui Liang and Yun Zheng
Aerospace 2024, 11(5), 358; https://doi.org/10.3390/aerospace11050358 - 29 Apr 2024
Viewed by 1093
Abstract
Recent studies in turbomachinery have shown that the phase of acoustic wave reflection within an intake can have either positive or negative effects on the aeroelastic stability of fan rotor blades. However, the typical flow structures, such as the shock wave, within rotor [...] Read more.
Recent studies in turbomachinery have shown that the phase of acoustic wave reflection within an intake can have either positive or negative effects on the aeroelastic stability of fan rotor blades. However, the typical flow structures, such as the shock wave, within rotor blade passages with acoustic wave reflection remain unclear. The aim of this research was to address this gap by investigating how these flow structures impact blade aeroelastic stabilities with acoustic wave reflections. The focus of this study was the NASA Rotor 67 blade with an extended intake. Moreover, a bump is incorporated on the shroud at different distances from the fan to reflect acoustic waves of varying phases. Utilizing the energy method, variations in the aerodynamic work density on blade surfaces were calculated under different phases of reflected acoustic waves. Analysis indicates that the spatial position of the shock wave undergoes periodic changes synchronized with the phase of acoustic reflection, marking the first instance of such an observation. This synchronization is identified as the primary factor causing variations in the aeroelastic stability of blades due to acoustic wave reflection, contributing to a deeper understanding of the mechanism behind acoustic flutter. The acoustic–vortex coupling at the blade tip leads to unpredictable variations in unsteady pressures on the blade suction surface, although its effect on blade aeroelastic stabilities is relatively limited compared to that of the shock wave. Full article
(This article belongs to the Special Issue Aeroelasticity, Volume IV)
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22 pages, 1745 KiB  
Article
A Nonlinear Beam Finite Element with Bending–Torsion Coupling Formulation for Dynamic Analysis with Geometric Nonlinearities
by Cesare Patuelli, Enrico Cestino and Giacomo Frulla
Aerospace 2024, 11(4), 255; https://doi.org/10.3390/aerospace11040255 - 25 Mar 2024
Viewed by 1388
Abstract
Vibration analysis of wing-box structures is a crucial aspect of the aeronautic design to avoid aeroelastic effects during normal flight operations. The deformation of a wing structure can induce nonlinear couplings, causing a different dynamic behavior from the linear counterpart, and nonlinear effects [...] Read more.
Vibration analysis of wing-box structures is a crucial aspect of the aeronautic design to avoid aeroelastic effects during normal flight operations. The deformation of a wing structure can induce nonlinear couplings, causing a different dynamic behavior from the linear counterpart, and nonlinear effects should be considered for more realistic simulations. Moreover, composite materials and aeroelastic tailoring require new simulation tools to include bending–torsion coupling effects. In this research, a beam finite element with bending–torsion coupling formulation is used to investigate the effects of the deflection of beam structures with different aspect ratios. The nonlinear effects are included in the finite element formulation. The geometrical effect is considered, applying a deformation dependent transformation matrix. Stiffness effects are introduced in the stiffness matrix with Hamilton’s Principle and a perturbation approach. The results obtained with the beam finite element model are compared with numerical and experimental evidence. Full article
(This article belongs to the Special Issue Aeroelasticity, Volume IV)
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22 pages, 12009 KiB  
Article
Experiments of Lift-Bending Response on a Slender UAV Wing Structure with Control Surface under Extreme Flow Turbulence
by Wolduamlak Ayele, Victor Maldonado and Siva Parameswaran
Aerospace 2024, 11(2), 131; https://doi.org/10.3390/aerospace11020131 - 2 Feb 2024
Viewed by 1570
Abstract
The aeroelastic response of lightweight low-speed aircrafts with slender wings under extreme flow turbulence intensity is not well understood. Experiments on a commercial unmanned aerial vehicle (UAV) with a 3 m wingspan and aspect ratio of 13.6 were performed in a large open-return [...] Read more.
The aeroelastic response of lightweight low-speed aircrafts with slender wings under extreme flow turbulence intensity is not well understood. Experiments on a commercial unmanned aerial vehicle (UAV) with a 3 m wingspan and aspect ratio of 13.6 were performed in a large open-return wind tunnel with extreme flow turbulence intensity of ≈10%. The wing bending displacement and the flow beneath the wing were measured by using laser-displacement sensors and tomographic particle image velocimetry (PIV) techniques, respectively. The unsteady lift produced by the wing was also measured by using a high-capacity load cell at an angle of attack of two degrees for three freestream velocities of 13.4 m/s, 17.9 m/s, and 26.8 m/s, representing the UAV’s stall speed, a speed approximately equal to the cruise speed, and a speed considerably higher than the cruise speed, respectively. It was found that a high flow turbulence intensity with large integral length scales relative to the wing chord plays a dominant role in the large unsteady lift and wing displacements measured. The power spectral density (PSD) of the wing structural vibration shows that flow shedding from the wing and the integral length scales have a significant impact on the overall power inherent in the bending vibration of the wing. Computations of the vorticity isosurfaces in the flow measurement volume surrounding the aileron reveal a striking observation: an aileron deflection of 10° becomes less effective in producing additional spanwise vorticity, which is proportional to circulation and lift at 26.8 m/s since the freestream already has elevated levels of vorticity. A paradigm shift in design is suggested for light aircraft structures with slender wings operating in highly turbulent flow, which is to employ multiple control surfaces in order to respond to this flow and mitigate large bending or torsion displacements and the probability of structural failure. Full article
(This article belongs to the Special Issue Aeroelasticity, Volume IV)
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