Modeling Approaches to Hypersonic Aerothermoelasticity with Application to Reusable Launch Vehicles

Thuruthimattam, Biju J.; Friedmann, Peretz P.; McNamara, Jack J.; Powell, Kenneth G.

doi:10.2514/6.2003-1967

Cited by 23 publications

(41 citation statements)

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“…These results appear reasonable, however, since it has been shown in Ref. 25 there are only small differences between the aeroelastic behavior of double-wedge typical section when either Euler or Navier-Stokes aerodynamics are used. Note that these results were generated on a 0.63x10 6 cell grid, requiring 16.5 hours of CPU time using 12 AMD Athlon 2000MP CPUs, where 500 time steps were used to generate 0.125 seconds of transient response.…”

mentioning

confidence: 58%

“…First, however, the effectiveness of three time domain damping and frequency identification techniques is studied using aeroelastic data generated from a simple typical section analysis using unsteady Navier-Stokes aerodynamics. 25 Next, the low aspect ratio wing is used to compare the aeroelastic behavior generated using third order piston theory, Euler and Navier-Stokes aerodynamics. Furthermore, the sensitivity of the aeroelastic behavior to several parameters related to time stepping is studied using Euler aerodynamics.…”

Section: Resultsmentioning

confidence: 99%

“…It has been shown, 25 that for the unheated case, a small angle of attack will not significantly alter the flutter boundary of a two dimensional typical section. When aerodynamic heating is considered, however, angle of attack is an important consideration since it introduces asymmetry in the temperature distribution between the upper and lower surfaces of a wing, and therefore introduces thermal stresses not present in zero degree angle of attack cases.…”

Section: Aerothermoelastic Behavior Of a Three-dimensional Low Aspmentioning

confidence: 99%

“…However, Ref. 25 has indicated that introducing a small constant angle of attack in hypersonic flow, for the case of a two-dimensional double-wedge airfoil, produces only a slight change in the flutter boundary of the airfoil section. Figure 42 shows the surface pressures on the typical cross-sections of the rigid and flexible configurations at equilibrium in inviscid flow, and it is evident from the figure that these are quite different.…”

Section: Aeroelastic Behavior Of a Generic Reusable Launch Vehiclementioning

confidence: 99%

“…[24][25][26] The computational tool consisted of a combination of the CFL3D code 27 and a finite element model of both a generic hypersonic vehicle, and three-dimensional wing, utilizing MSC.NASTRAN. This paper continues to explore fundamental aspects of hypersonic aeroelasticity and aerothermoelasticity using computational tools and it focuses on three-dimensional low aspect ratio wing and complete generic hypersonic vehicle configurations.…”

Section: -17mentioning

confidence: 99%

See 4 more Smart Citations

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

McNamara

Friedmann

Powell

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The aeroelastic and aerothermoelastic behavior of three-dimensional configurations in hypersonic flow regime are studied. The aeroelastic behavior of a low aspect ratio wing, representative of a fin or control surface on a generic hypersonic vehicle, is examined using third order piston theory, Euler and Navier-Stokes aerodynamics. The sensitivity of the aeroelastic behavior generated using Euler and Navier-Stokes aerodynamics to parameters governing temporal accuracy is also examined. Also, a refined aerothermoelastic model, which incorporates the heat transfer between the fluid and structure using CFD generated aerodynamic heating, is used to examine the aerothermoelastic behavior of the low aspect ratio wing in the hypersonic regime. Finally, the hypersonic aeroelastic behavior of a generic hypersonic vehicle with a lifting-body type fuselage and canted fins is studied using piston theory and Euler aerodynamics for the range of 2.5 ≤ M ≤ 28, at altitudes ranging from 10,000 feet to 80,000 feet. This analysis includes a study on optimal mesh selection for use with Euler aerodynamics. In addition to the aeroelastic and aerothermoelastic results presented, three time domain flutter identification techniques are compared, namely the moving block approach, the least squares curve fitting method, and a system identification technique using an Auto-Regressive model of the aeroelastic system. In general, the three methods agree well. The system identification technique, however, provided quick damping and frequency estimations with minimal response record length, and therefore offers significant reductions in computational cost. In the present case, the computational cost was reduced by 75%. The aeroelastic and aerothermoelastic results presented illustrate the applicability of the CFL3D code for the hypersonic flight regime.

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mentioning

confidence: 58%

Section: Resultsmentioning

confidence: 99%

Section: Aerothermoelastic Behavior Of a Three-dimensional Low Aspmentioning

confidence: 99%

Section: Aeroelastic Behavior Of a Generic Reusable Launch Vehiclementioning

confidence: 99%

Section: -17mentioning

confidence: 99%

See 3 more Smart Citations

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

McNamara

Friedmann

Powell

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

Self Cite

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show abstract

CFD/CSD Approach to Predict Hypersonic Aerothermoelastic Response of a Wing

Wang

Guo

et al. 2015

Procedia Engineering

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Fuzzy Approximation by a Novel Levenberg–Marquardt Method for Two-Degree-of-Freedom Hypersonic Flutter Model

Wang

Zhu²,

et al. 2014

Journal of Vibration and Acoustics

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The two-degree-of-freedom (2DOF) hypersonic flutter dynamical system has strong aeroelastic nonlinearities, and it is very difficult to obtain a more precise mathematical model. By considering varying learning rate and σ-modification factor, a novel Levenberg– Marquardt (L–M) method is proposed, based on which, an online fuzzy approximation scheme for 2DOF hypersonic flutter model is established without any human knowledge. Compared with the standard L–M method, the proposed method can obtain faster converge speed and avoid parameter drift. Numerical simulations approve the advantages of the proposed scheme.

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Modeling Approaches to Hypersonic Aerothermoelasticity with Application to Reusable Launch Vehicles

Cited by 23 publications

References 0 publications

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

CFD/CSD Approach to Predict Hypersonic Aerothermoelastic Response of a Wing

Fuzzy Approximation by a Novel Levenberg–Marquardt Method for Two-Degree-of-Freedom Hypersonic Flutter Model

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