Aeroelasticity of a Generic Hypersonic Vehicle

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

doi:10.2514/6.2002-1209

Cited by 26 publications

(32 citation statements)

References 16 publications

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“…ns, N is a typical three-level neural network ed as follows and the set of inputs to the function is restricted to a compact set S of 14 versal function approximation property [32], the nonlinear function of the system oximated as a three-layer network target function as follows ( ) ( ) 1 1 1 1 2 3 4 , , , , , ,…”

Section: Control Design and Closed-loop Error Systemmentioning

confidence: 99%

“…By the universal function approximation property [32], the nonlinear function of the s N can be approximated as a three-layer network target function as follows ( ) ( ) 1 1 1 1 2 3 4 , , , , , , (22). By the universal function approximation property [32], the nonlinear function of the system N can be approximated as a three-layer network target function as follows ( ) ( ) 1 1 1 1 2 3 4 , , , , , ,…”

Section: Control Design and Closed-loop Error Systemmentioning

confidence: 99%

See 1 more Smart Citation

A Continuous Robust Control Strategy for the Active Aeroelastic Vibration Suppression of Supersonic Lifting Surfaces

Zhang

Wang

Behal

et al. 2012

International Journal of Aeronautical and Space Sciences

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The model-free control of aeroelastic vibrations of a non-linear 2-D wing-flap system operating in supersonic flight speed regimes is discussed in this paper. A novel continuous robust controller design yields asymptotically stable vibration suppression in both the pitching and plunging degrees of freedom using the flap deflection as a control input. The controller also ensures that all system states remain bounded at all times during closed-loop operation. A Lyapunov method is used to obtain the global asymptotic stability result. The unsteady aerodynamic load is considered by resourcing to the non-linear Piston Theory Aerodynamics (PTA) modified to account for the effect of the flap deflection. Simulation results demonstrate the performance of the robust control strategy in suppressing dynamic aeroelastic instabilities, such as non-linear flutter and limit cycle oscillations.

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Section: Control Design and Closed-loop Error Systemmentioning

confidence: 99%

Section: Control Design and Closed-loop Error Systemmentioning

confidence: 99%

A Continuous Robust Control Strategy for the Active Aeroelastic Vibration Suppression of Supersonic Lifting Surfaces

Zhang

Wang

Behal

et al. 2012

International Journal of Aeronautical and Space Sciences

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“…9, is determined from an energy balance of the heat fluxes at the wall of the structure: 60,61 q aero =q rad +q cond +q strd (24) whereq…”

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%

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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“…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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Aeroelasticity of a Generic Hypersonic Vehicle

Cited by 26 publications

References 16 publications

A Continuous Robust Control Strategy for the Active Aeroelastic Vibration Suppression of Supersonic Lifting Surfaces

A Continuous Robust Control Strategy for the Active Aeroelastic Vibration Suppression of Supersonic Lifting Surfaces

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

Three-Dimensional CST Parameterization Method Applied in Aircraft Aeroelastic Analysis

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