Numerical studies on the thermal-fluid-structure coupling analysis method of hypersonic flight vehicle

Wang, Weiji; Qian, Wang; Bai, Yuguang; Wang, Kunming

doi:10.1016/j.tsep.2023.101792

Cited by 9 publications

(4 citation statements)

References 25 publications

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“…It can be seen from the figure that when the grid number is greater than 5.69 million, the y+ value is basically less than 1. Wang et al [34] used Fluent 2021 R2 commercial software to perform hypersonic aerothermal calculations using a pressure-based solver and SST turbulence model, pointing out that the accuracy requirements of aerothermal calculations could be met when the value of y+ was kept less than 1. In this paper, the same method is used to perform the calculations and the results are reliable.…”

Section: Grid Independence Verificationmentioning

confidence: 99%

Study on Ground Experimental Method of Stagnation Point Large Heat Flux of Typical Sharp Wedge Leading Edge Structure

Wang,

Lou,

et al. 2023

Aerospace

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In this paper, aimed at the problem of large temperature gradient thermal testing with the typical sharp wedge leading edge structure of a hypersonic vehicle, a subsonic high-temperature combustion gas heating (SHCH) test device is used to conduct a series of experiments on the heat flux simulation ability of subsonic high-temperature combustion gas in the stagnation point region. Firstly, for a hypersonic vehicle with a flying height of 24 km and Mach number range of 4~6.5, the stagnation point heat flux in the head area is obtained by numerical calculation of a typical leading edge structure, which is used as the experimental target of the thermal structure test. Secondly, an experimental specimen with a Gardon heat flux meter is designed with the same shape and size as the specimen in the numerical simulations to prepare for the subsequent SHCH test. Thirdly, a method to determine the combustion gas temperature based on a Kriging surrogate model is proposed. CFD numerical simulation is conducted using the SHCH test model, and the numerical calculation results are used as the training dataset. The Kriging surrogate model is used to establish an approximate fitting relationship between the stagnation point heat flux and experimental parameters under SHCH conditions. The corresponding combustion gas temperature values are found, respectively, with the hypersonic aerodynamic heat flux at Mach 5.0~5.4 as the target value. Finally, stagnation point heat flux testing of low-speed and high-temperature combustion gas is performed at different combustion gas temperatures. The experimental and target values obtained from hypersonic aerodynamic thermal simulations are compared and analyzed to verify the heating capacity of SHCH and the feasibility of hypersonic aerothermal simulation testing.

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Section: Grid Independence Verificationmentioning

confidence: 99%

Study on Ground Experimental Method of Stagnation Point Large Heat Flux of Typical Sharp Wedge Leading Edge Structure

Wang,

Lou,

et al. 2023

Aerospace

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“…mesh types of the fuselage were Quad and Tria, and the number of elements was 11 The mesh types of the main plane were Quad and Tria, and the number of elements 6562. The mesh types of the aileron were Quad, Tria, and Bar, and the number of elem was 944 [25]. For the tri-wing flight vehicle (Figure 1), the Lanczos method was use solve the eigenvalues of the structural dynamic equations of the complex and large s ture, so as to obtain the natural frequencies and mode shapes.…”

Section: Flutter Analysismentioning

confidence: 99%

“…Therefore, studying aileron flutter is necessary and useful. In this paper, a rapid modeling technique of the finite element method was adopted to build a finite element model of a large swept-back tri-wing flight vehicle [25]. The rapid modeling technique was applied to the Automatic Meshing Tool developed by our team.…”

Section: Introductionmentioning

confidence: 99%

Flutter Optimization of Large Swept-Back Tri-Wing Flight Vehicles

Wang,

Qian,

et al. 2023

Aerospace

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The aerodynamic configuration of large swept-back tri-wings is generally adopted for hypersonic vehicles, but the structural stiffness of the ailerons is weak, which may lead to damage due to the flutter behavior. In the initial stage of structural design, studying the flutter characteristics of tri-wing flight vehicles is necessary and can provide the stiffness index of the tri-wing structural design. To assess the flutter characteristics of tri-wing flight vehicles efficiently, a rapid modeling technique of the finite element method was used in this paper. For the structural scheme of large swept-back tri-wing flight vehicles, a structural dynamic model was modeled using the rapid modeling technique, the unsteady aerodynamic was computed using the double-lattice method, and the flutter characteristics were analyzed using the P-K method. Variable parametric studies were conducted to evaluate the effects of the stiffness of the aileron skin, the stiffness of the control mechanism, and the mass distribution of the aileron on the flutter characteristics of large swept-back tri-wing flight vehicles. The results showed that the key flutter coupling modes of such vehicles are symmetric and anti-symmetric combinations of aileron rotation and torsion. Additionally, optimizing the control mechanism stiffness and mass distribution of the aileron could improve the flutter boundary, which can be helpful in the structural design of such vehicles. The flutter optimization technique effectively improved the flutter boundary, significantly enlarged the flight envelope, and accurately provided the stiffness index for the structural design of large swept-back tri-wing flight vehicles.

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“…Firstly, most of the flexible absorbing materials reported in the literature are developed using materials with temperature resistance lower than 200 • C, including rubber, polyethylene terephthalate (PET), polyvinyl chloride (PVC), polydimethylsiloxane (PDMS), and lumped element [2,[21][22][23][24]31]. These materials with limited temperature resistance constrain design freedom and practical applications, particularly in high temperature environments [32]. Secondly, the fabrication process for high temperature resistant absorbents is relatively complex and involves multiple steps [33][34][35].…”

Section: Introductionmentioning

confidence: 99%

A flexible metamaterial absorber with temperature-insensitive design at microwave frequencies

Li,

Lu,

et al. 2023

Smart Mater. Struct.

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Developing a metamaterial absorber (MA) with both flexibility and temperature insensitivity continues to be a challenge in the field of radar stealth. In this paper, we propose a compensation method for designing flexible and temperature-insensitive MA. This method is revealed through the relationship between the square resistance of the resistive film, the permittivity of the substrate, and the temperature. Importantly, the compensation method is applicable to both the MA in the plane state and the bending state. By utilizing the benefits of the compensation mechanism and the flexible designability of the bilayer cross-shaped structure, the flexible MA proposed in this paper can achieve temperature-insensitive absorption across a broad frequency range. Experimental results indicate that the absorption peaks achieve an absorptivity greater than 90% within the frequency of 7.2–9.4 GHz, exhibiting excellent temperature stability from 25 °C to 300 °C. In comparison to previous studies on flexible MAs, this design offers a distinct advantage in high-temperature environments and provides valuable guidelines for the design of integrated multi-functional absorbers in practical applications.

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Numerical studies on the thermal-fluid-structure coupling analysis method of hypersonic flight vehicle

Cited by 9 publications

References 25 publications

Study on Ground Experimental Method of Stagnation Point Large Heat Flux of Typical Sharp Wedge Leading Edge Structure

Study on Ground Experimental Method of Stagnation Point Large Heat Flux of Typical Sharp Wedge Leading Edge Structure

Flutter Optimization of Large Swept-Back Tri-Wing Flight Vehicles

A flexible metamaterial absorber with temperature-insensitive design at microwave frequencies

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