CFD-based aeroelastic analysis of the X-43 hypersonic flight vehicle

Gupta, K. K.; Voelker, L. S.; Bach, C.; Doyle, Timothy J.; Hahn, E.

doi:10.2514/6.2001-712

Cited by 51 publications

(54 citation statements)

References 6 publications

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“…This trend of good comparison between Euler aerodynamics and piston theory follows that also observed for the low aspect-ratio wing, and Ref. 19 for the X-43 geometry. For convenient comparison, the results of all the aeroelastic simulations described above are summarized in Table 7.…”

Section: Aeroelastic Behavior Of a Generic Reusable Launch Vehiclesupporting

confidence: 52%

See 1 more Smart Citation

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: Aeroelastic Behavior Of a Generic Reusable Launch Vehiclesupporting

confidence: 52%

“…In Ref. 19, CFD-based flutter analysis was used for the aeroelastic analysis of the X-43 configuration, using system identification based order reduction of the aerodynamic degrees of freedom. Both the structure and the fluid were discretized using the finite element approach.…”

Section: -17mentioning

confidence: 99%

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

View full text Add to dashboard Cite

show abstract

“…The AGARD 445.6 Aeroelastic Wing has been used extensively by several authors to validate computational methods. [16][17][18] Although the aeroelastic behavior of this wing is fairly benign (weakly nonlinear), the aeroelastic data from the flutter test of this wing provides a good starting point for validation of computational techniques. 19 The wing is a 45-degree swept-back wing with a NACA 65A004 airfoil section, panel aspect ratio of 1.65, and a taper ratio of 0.6576.…”

Section: Matched-point Cfd-based Analysesmentioning

confidence: 99%

Recent Enhancements to the Development of CFD-Based Aeroelastic Reduced-Order Models

Silva

2007

48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Recent enhancements to the development of CFD-based unsteady aerodynamic and aeroelastic reduced-order models (ROMs) are presented. These enhancements include the simultaneous application of structural modes as CFD input, static aeroelastic analysis using a ROM, and matched-point solutions using a ROM. The simultaneous application of structural modes as CFD input enables the computation of the unsteady aerodynamic state-space matrices with a single CFD execution, independent of the number of structural modes. The responses obtained from a simultaneous excitation of the CFD-based unsteady aerodynamic system are processed using system identification techniques in order to generate an unsteady aerodynamic state-space ROM. Once the unsteady aerodynamic state-space ROM is generated, a method for computing the static aeroelastic response using this unsteady aerodynamic ROM and a state-space model of the structure, is presented. Finally, a method is presented that enables the computation of matchedpoint solutions using a single ROM that is applicable over a range of dynamic pressures and velocities for a given Mach number. These enhancements represent a significant advancement of unsteady aerodynamic and aeroelastic ROM technology.

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“…Aeroelastic analysis becomes an important process for modern aircraft design [3,4]. Especially in the conceptual design phase, main performance of an aircraft is determined during this phase and, therefore, how to carry out the aeroelastic analysis quickly and stably to improve the integrated performance and the design rationality of the aircraft scheme will help a lot in the following aircraft design.…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional CST Parameterization Method Applied in Aircraft Aeroelastic Analysis

Gong

2017

International Journal of Aerospace Engineering

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Class/shape transformation (CST) method has advantages of adjustable design variables and powerful parametric geometric shape design ability and has been widely used in aerodynamic design and optimization processes. Three-dimensional CST is an extension for complex aircraft and can generate diverse three-dimensional aircraft and the corresponding mesh automatically and quickly. This paper proposes a parametric structural modeling method based on gridding feature extraction from the aerodynamic mesh generated by the three-dimensional CST method. This novel method can create parametric structural model for fuselage and wing and keep the coordination between the aerodynamic mesh and the structural mesh. Based on the generated aerodynamic model and structural model, an automatic process for aeroelastic modeling and solving is presented with the panel method for aerodynamic solver and NASTRAN for structural solver. A reusable launch vehicle (RLV) is used to illustrate the process for aeroelastic modeling and solving. The result shows that this method can generate aeroelastic model for diverse complex three-dimensional aircraft automatically and reduce the difficulty of aeroelastic analysis dramatically. It provides an effective approach to make use of the aeroelastic analysis at the conceptual design phase for modern aircraft.

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CFD-based aeroelastic analysis of the X-43 hypersonic flight vehicle

Cited by 51 publications

References 6 publications

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

Recent Enhancements to the Development of CFD-Based Aeroelastic Reduced-Order Models

Three-Dimensional CST Parameterization Method Applied in Aircraft Aeroelastic Analysis

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