Aerothermoelastic analysis of a NASP-like vertical fin

Rodgers, John P.

doi:10.2514/6.1992-2400

Cited by 19 publications

(24 citation statements)

References 1 publication

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“…The spike 1 temperature distribution has the lowest flutter speed (Fig. 8), and this is in agreement [34]; therefore it is the only temperature model applied to the structure, because it is the worst case.…”

Section: Resultssupporting

confidence: 77%

Response of a three-degree-of-freedom wing with stiffness and aerodynamic nonlinearities at hypersonic speeds

2015

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In the design of high-speed aircraft particular attention must be given to the effect of stiffness and aerodynamic nonlinearities. Additionally the thermal effects cannot be ignored since the harsh thermal environment influences the dynamic behaviour of a structure. In the current paper the aeroelastic response of a three-degree-of-freedom wing with a control surface, and stiffness and aerodynamic nonlinearities has been analysed. The nonlinear unsteady aerodynamic forces applied to the model are calculated using third-order piston theory and piecewise linear, and cubic stiffening nonlinearities are implemented in the control surface. The effect of temperature on the model is determined by a steady-state analysis with a predefined temperature distribution. The onset of limit cycle oscillations and the bifurcation behaviours is compared for the different nonlinearities. The effect of initial conditions is determined to quantify their impact on the limit cycle behaviour. This article extends the nonlinear analysis of the aeroelastic response of a wing at hypersonic speeds with an added control surface degree of freedom, with the effect of nonlinear aerodynamics and stiffness included in the model. The results show that different nonlinearities influence the response of the system uniquely and heat plays an important role in the order of excited harmonics.

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Section: Resultssupporting

confidence: 77%

Response of a three-degree-of-freedom wing with stiffness and aerodynamic nonlinearities at hypersonic speeds

2015

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“…A linearized approximation is obtained by computing an approximate heat transfer coefficient from two reference flow conditions. [46][47][48][49] One flow condition is used to determine the heat flux at a nominal surface temperature (e.g., free stream conditions). The second flow condition represents adiabatic conditions in order to determine the adiabatic wall temperature.…”

Section: Iiia Linearization Methodsmentioning

confidence: 99%

Robust Treatment of Temperature Feedback in Aerothermodynamic Models for Fluid-Thermal-Structural Analysis

Crowell

Miller

McNamara

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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One of the primary challenges in the development of high-speed systems is accurate and efficient prediction of the aerodynamic heating, particularly for light-weight systems where the aerothermodynamic loads are strongly coupled with the structural response. This study builds upon previous work focused on using CFD surrogates for prediction of aerothermodynamic loads within a tightly integrated fluid-thermal-structural analysis framework. A novel approach is developed that corrects heat flux predictions from a pointwise dependency on surface temperature in order to account for surface temperature gradients. This enables efficient construction of a CFD surrogate for aerodynamic heating without a priori assumptions on the surface temperature profile; while also accurately maintaining the critical feedback behavior of the surface temperature profile for a coupled fluid-thermal-structural analysis. The method is compared, in terms of accuracy and efficiency, with a hierarchy of approaches for aerodynamic heating prediction. Comparison cases include simple flat plate heating, as well as shock impingements in two dimensional and three dimensional flows. Typically the approach yields less than 5% error relative to full-order CFD predictions, and clearly outperforms all other simple prediction methods in terms of accuracy. Furthermore, it maintains excellent computational efficiency, enabling long time record fluid-thermal-structural analysis in complex, three-dimensional flow environments.

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“…The second group of studies in this area was motivated by a previous hypersonic vehicle, namely, the NASP (Rricketts et al, 1993;Spain et al, 1993a, b;Scott and Pototzky, 1993;Rodgers, 1992;Heeg and Gilbert, 1993). However, some of these studies dealt with the transonic regime, because it was perceived to be quite important.…”

Section: Introduction and Problem Statementmentioning

confidence: 97%

“…They found that using effective shapes for the airfoils obtained by adding the boundary layer displacement thickness to the airfoil thickness improved the overall agreement with experiments. Aerothermoelastic analyses of NASP-like vehicles found that aerodynamic heating altered the aeroelastic stability of the vehicle through the degradation of material properties and introduction of thermal stresses (Rodgers, 1992;Heeg and Gilbert, 1993).…”

Section: Introduction and Problem Statementmentioning

confidence: 99%