Hypersonic vehicle control system design and simulation require models that contain a low number of states. Modeling of hypersonic vehicles is complicated due to complex interactions between aerodynamic heating, heat transfer, structural dynamics, and aerodynamics. Although there exist techniques for analyzing the effects of each of the various disciplines, thesemethods often require solution of large systems of equations, which is infeasible within a control design and evaluation environment. This work presents an aerothermoelastic framework with reducedorder aerothermal, heat transfer, and structural dynamicmodels for time-domain simulation of hypersonic vehicles. Details of the reduced-order models are given, and a representative hypersonic vehicle control surface used for the study is described. Themethodology is applied to a representative structure to provide insight into the importance of aerothermoelastic effects on vehicle performance. The effect of aerothermoelasticity on total lift and drag is found to result in up to an 8% change in lift and a 21% change in drag with respect to a rigid control surface for the four trajectories considered. An iterative routine is used to determine the angle of attack needed to match the lift of the deformed control surface to that of a rigid one at successive time instants.Application of the routine todifferent cruise trajectories shows a maximum departure from the initial angle of attack of 8%.

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Reduced-Order Aerothermoelastic Framework for Hypersonic Vehicle Control Simulation

/pdf/reduced-order-aerothermoelastic-framework-for-hypersonic-1f5kbszw6i.pdf

The ability to perform full-order aerothermoelastic simulations of hypersonic vehicles is hindered by the strong coupling exhibited between the aerodynamics, heat transfer, and structural dynamic response in the hypersonic ight regime. As a result of these interactions, alternative techniques are necessary to obtain computationally tractable systems of governing equations and their solutions. This work addresses the use of proper orthogonal decomposition for reduced-order solution of the heat transfer problem within a hypersonic modeling framework. The specic challenge of handling time-dependent boundary conditions due to transient aerodynamic heating is discussed. An overview of the proper orthogonal decomposition is given and two methods for solution of the reduced system of ordinary dierential equations are outlined. The methodology is applied to a representative hypersonic vehicle control surface model for two cases in which the time-history of the thermal load vector is known a priori: one in which the boundary conditions are time-independent and another in which they are time-varying. Results demonstrate the ability of the reduced-order solution to approximate the full-order solution with reasonable accuracy. Finally, a time-marching hypersonic aerothermoelastic framework is described in which proper orthogonal decomposition is used for the transient thermal solution.

/pdf/proper-orthogonal-decomposition-for-reduced-order-thermal-2u26frq0bl.pdf

Proper orthogonal decomposition for reduced-order thermal solution in hypersonic aerothermoelastic simulations

Hypersonic vehicle design and simulation require models that are of low order. Modeling of hypersonic vehicles is complicated due to complex interactions between aerodynamic heating, heat transfer, structural dynamics, and aerodynamics in the hypersonic regime. This work focuses on the development of ecient modal solutions for structural dynamics of hypersonic vehicle structures under transient thermal loads. The problem is outlined and aerothermoelastic coupling mechanisms are described. A previously developed reducedorder, time-domain aerothermoelastic simulation framework is used as the starting point for this study. This paper focuses on three main modeling areas: 1) The eect of aerodynamic heating on the evolution of free vibration modes shapes and frequencies is examined, 2) A surrogate modeling technique is employed for directly updating the generalized stiness matrix and thermal loads based on the transient temperature distribution and 3) Basis augmentation techniques are employed in order to obtain more accurate solutions for the structural dynamic response. The techniques to be studied are described and applied to a representative hypersonic vehicle elevator structure.

/pdf/enhanced-modal-solutions-for-structural-dynamics-in-55lw6sx4fz.pdf

Enhanced modal solutions for structural dynamics in aerothermoelastic analysis

/pdf/enhanced-modal-solutions-for-structural-dynamics-in-eyhi6zt5o0.pdf

Enhanced Modal Solutions for Structural Dynamics in Aerothermoelastic Analysis

Transonic aeroelastic wind-tunnel models simulating geometric and dynamic properties of lightweight, highly swept hypersonic lifting surfaces have been designed, fabricated, and tested. The aeroelastic model designs were consistent with preliminary designs of lifting surfaces for single-stage-to-orbit vehicles. The models were tested in the NASA Langley Research Center's Transonic Dynamics Tunnel. This article summarizes the design and tests conducted for each of the two models. Wind-tunnel test results are presented showing aeroelastic instability boundaries. Aeroelastic analyses, conducted for correlation with wind-tunnel results, are also presented.

Transonic aeroelastic models of highly swept hypersonic lifting surfaces

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Transonic aeroelastic models of highly swept hypersonic lifting surfaces