A Hypersonic Vehicle Model Developed With Piston Theory

Oppenheimer, Michael W.; Doman, David B.

doi:10.2514/6.2006-6637

Cited by 49 publications

(41 citation statements)

References 5 publications

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“…18 The top and bottom skin layers are each equipped with two 3.8 mm thick thermal protection system layers, and thus the thickness of the outer mold line is 4% chord length plus the 15.2 mm of thermal protection system material. The chord length at the root is 5.2 m. (17 ft.) 19 and the leading edge makes an angle of 34…”

Section: Iiib Control Surface Modelmentioning

confidence: 99%

Effect of Control Surface-Fuselage Inertial Coupling on Hypersonic Vehicle Flight Dynamics

Falkiewicz

Frendreis

Cesnik

2011

AIAA Atmospheric Flight Mechanics Conference

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A simulation framework is developed for assessing the effect of control surface inertial loads on hypersonic vehicle response. The framework is based on a partitioned, timemarching approach in which the fuselage and control surface equations of motion are integrated independently and forces/motion at the interface are exchanged between the two systems at pre-determined time intervals. This approach is advantageous in that it does not require direct coupling of the fuselage and control surface models, and therefore allows for the models to be of dissimilar form. Equations of motion for both the fuselage and control surface are presented and a formulation for coupling the two systems is outlined which includes iterations within each aeroelastic time step. The methodology is applied to a representative hypersonic vehicle elevator control surface model which includes aerothermoelastic effects and is attached to a single degree of freedom oscillator representing the fuselage. Results show that control surface inertial effects lead to a departure of the instantaneous control surface lift force by up to a factor of eight with respect to the static value. Investigation of the system response under a commanded change in control surface deflection angle shows that control surface inertia results in departure of the instantaneous control surface pitching moment by up to a factor of 500 with respect to the static value. Nomenclature B= body-fixed reference frame c = generalized damping matrix c p = specific heat d = control surface elastic modal coordinates E = modulus of elasticity, Earth-fixed reference frame F = physical load vector f = generalized load vector f i = fuselage ordinary natural frequencies g = gravitational acceleration H(t) = Heaviside step function H i = coefficient matrices in control surface integration scheme h = altitude h i = thickness of i-th layer of thermal protection system I i = coefficient matrices in fuselage integration scheme

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Section: Iiib Control Surface Modelmentioning

confidence: 99%

Effect of Control Surface-Fuselage Inertial Coupling on Hypersonic Vehicle Flight Dynamics

Falkiewicz

Frendreis

Cesnik

2011

AIAA Atmospheric Flight Mechanics Conference

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“…However, the downfall of this approach was that there was no means by which one could calculate the aerodynamic damping derivatives or the unsteady aerodynamic forces and moments due to the fluid-structure interaction that arises when the vehicle vibrates. To remedy this, linear piston theory has been utilized to capture the unsteady components of the flow field [6], [7]. Additionally, because the original model assumed inviscid flow, an analytical skin friction model using Eckert's reference temperature method has been incorporated into the model [8] to give more realistic drag estimates.…”

Section: First-principles Modelling For Dynamics and Control Analmentioning

confidence: 99%

An overview on dynamics and controls modelling of hypersonic vehicles

Bolender

2009

2009 American Control Conference

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Abstract-In order to appropriately design control laws for hypersonic vehicles, it is paramount to understand how the flight dynamics are impacted by the interactions between the aerothermodynamics, propulsion system, structural dynamics, and control system. To this end, there has been a significant investment into the modelling of these sub-systems and their integration into a comprehensive model that can be used to the characterize the flight dynamics of scramjet-powered hypersonic aircraft and still remain amenable to control law design and analysis. In this paper, the development of a comprehensive model of the longitudinal dynamics of generic hypersonic vehicle with an outward-turning, two-dimensional inlet is described. The sub-system models, for the most part, are simple models derived from first-principles and are intended to capture the interactions between the different sub-systems to provide a representative vehicle model. We also will discuss the areas that are important to realizing a hypersonic modelling approach that can take any given vehicle geometry and permit a thorough analysis of its stability and control characteristics and any practical constraints on its operability, the design of a control law, an assessment of it closed-loop performance.

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“…due to rotation and flexing) are captured using linear piston theory 8,50 . The idea here is that flow velocities induce pressures just as the pressure exerted by a piston on a fluid induces a velocity.…”

Section: Description Of Nonlinear Modelmentioning

confidence: 99%

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Dickeson

Rodriguez

Sridharan

et al. 2010

AIAA Guidance, Navigation, and Control Conference

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Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. The impact of elevator size and placement on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic properties (e.g. instability and right half plane zero associated with flight path angle) are examined. Elevator usage has been examine for a class of typical hypersonic trajectories.

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A Hypersonic Vehicle Model Developed With Piston Theory

Abstract: This report is published in the interest of scientific and technical information exchange, and its publication does not constitute the Government's approval or disapproval of its ideas or findings.

Cited by 49 publications

References 5 publications

Effect of Control Surface-Fuselage Inertial Coupling on Hypersonic Vehicle Flight Dynamics

Effect of Control Surface-Fuselage Inertial Coupling on Hypersonic Vehicle Flight Dynamics

An overview on dynamics and controls modelling of hypersonic vehicles

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

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