Hypersonic Aerothermoelastic Studies for Reusable Launch Vehicles

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

doi:10.2514/6.2004-1590

Cited by 19 publications

(37 citation statements)

References 43 publications

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“…26, it was determined that the low-aspect ratio wing was prone to thermal buckling due to local deformations along the leading and trailing edges. Therefore, the wing was modified for this study, in order to reduce the susceptibility to thermal buckling.…”

Section: Aerothermoelastic Behavior Of a Three-dimensional Low Aspmentioning

confidence: 99%

“…3 and 4, was developed from a study 26 of grid configurations, where the appropriate computational domain and mesh resolution required for the hypersonic aeroelastic analysis of the low aspect ratio wing were determined. In Ref.…”

Section: F Computational Model For the Three-dimensional Low Aspect mentioning

confidence: 99%

“…In Ref. 26, cell distribution and grid resolution were varied to construct a grid for the hypersonic flow regime that accurately and efficiently captured the flow. Each span section plane of the computational domain extends one-half chord-lengths downstream.…”

Section: F Computational Model For the Three-dimensional Low Aspect mentioning

confidence: 99%

“…26 As a first approximation to the aerothermoelastic system, the heating distribution of the system was assumed to be a parabolic function of the chord. Furthermore, steady-state conditions were assumed, resulting in a unique temperature distribution for each Mach number.…”

Section: -59mentioning

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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Section: Aerothermoelastic Behavior Of a Three-dimensional Low Aspmentioning

confidence: 99%

Section: F Computational Model For the Three-dimensional Low Aspect mentioning

confidence: 99%

Section: F Computational Model For the Three-dimensional Low Aspect mentioning

confidence: 99%

Section: -59mentioning

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

View full text Add to dashboard Cite

show abstract

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

Wang

Guo

et al. 2015

Procedia Engineering

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Effect of thickness and angle-of-attack on the aeroelastic stability of supersonic fins

Firouz-Abadi

Alavi

2012

Aeronaut. j. (1968)

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This paper aims at developing an aeroelastic model for the instability analysis of supersonic thick fins. To this aim the modal analysis technique is used for the structural dynamics modelling of a fin with a general structure. An unsteady aerodynamic model is applied based on the shock/expansion analysis over the flat surfaces of the fin along with local application of the piston theory. Assuming a supersonic fin with an arbitrary polygonal cross-section, thickness and initial angle-of-attack, the steady flow properties (e.g. Mach number, density and temperature) are calculated over the flat surfaces of the fin. Then, assuming small amplitude vibrations, the generalised aerodynamic forces are obtained in terms of the structural modal coordinates. Using the obtained model, the effect of thickness, initial angle-of-attack, taper ratio and sweep angle on the aerodynamic derivatives and aeroelastic stability of the fin are studied which show their remarkable effects on the instability Mach number and its type. Specially, the presented results show that increasing the fin thickness dramatically diminishes the stability margin mainly at low angles of attack. Also a sharp decrease of the divergence Mach number is observed by increasing the fin's incidence angle.

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Hypersonic Aerothermoelastic Studies for Reusable Launch Vehicles

Cited by 19 publications

References 43 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

Effect of thickness and angle-of-attack on the aeroelastic stability of supersonic fins

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