Segmented penetrator flight dynamics

Schmidt, Edward

doi:10.2514/6.1993-3652

Cited by 5 publications

(8 citation statements)

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“…Reference [10], which provides a comprehensive study on the different aspects of this broad subject, is here adopted for the development of a simple framework to deal with this phenomena. The noninertial vehicle-fixed coordinate frame used to derive the equations of motion is the so-called mean axes.…”

Section: Body Freedom Flutter Modelingmentioning

confidence: 99%

“…However, note that the basic physical features of the rigid-elastic coupling are kept. As shown in [10], the aeroelastic derivatives calculation process is prompted by the same line of reasoning, with integrals employed to take into account variability of the properties along the span. Moreover, it is known [12] that BFF is well predicted using linear models for the aircraft and is not the result of non-linear aerodynamics or structural nonlinearities.…”

Section: Body Freedom Flutter Modelingmentioning

confidence: 99%

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Modeling and robust Body Freedom Flutter Analysis of flexible aircraft configurations

Iannelli

Marcos

Lowenberg

2016

2016 IEEE Conference on Control Applications (CCA)

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Section: Body Freedom Flutter Modelingmentioning

confidence: 99%

Section: Body Freedom Flutter Modelingmentioning

confidence: 99%

Modeling and robust Body Freedom Flutter Analysis of flexible aircraft configurations

Iannelli

Marcos

Lowenberg

2016

2016 IEEE Conference on Control Applications (CCA)

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“…An explicit form of the motion equations is derived for convenience considering the mass properties of the propeller, as explained in Ref. [7].…”

Section: Computational Proceduresmentioning

confidence: 99%

“…The Martinez column update method [9] was selected for the present analyses from trade-off studies. The linearization modules were prepared to compute numerically the linear model at a given trimmed solution by applying small disturbance theory, and the reduced order models can be derived using the truncation or residualization methods [7]. The fourth-order Runge-Kutta and real-time Adams-Moulton (RTAM-3) time integrators were implemented for the flight simulation analyses.…”

Section: Flight Dynamics Analysis Modulesmentioning

confidence: 99%

Flight Dynamics Analyses of a Propeller-Driven Airplane (II): Building a High-Fidelity Mathematical Model and Applications

Kim¹,

Kim²,

Park³

et al. 2014

International Journal of Aeronautical and Space Sciences

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This paper is the second in a series and aims to build a high-fidelity mathematical model for a propeller-driven airplane using the propeller's aerodynamics and inertial models, as developed in the first paper. It focuses on aerodynamic models for the fuselage, the main wing, and the stabilizers under the influence of the wake trailed from the propeller. For this, application of the vortex lattice method is proposed to reflect the propeller's wake effect on those aerodynamic surfaces. By considering the maneuvering flight states and the flow field generated by the propeller wake, the induced velocity at any point on the aerodynamic surfaces can be computed for general flight conditions. Thus, strip theory is well suited to predict the distribution of air loads over wing components and the viscous flow effect can be duly considered using the 2D aerodynamic coefficients for the airfoils used in each wing. These approaches are implemented in building a high-fidelity mathematical model for a propeller-driven airplane. Flight dynamic analysis modules for the trim, linearization, and simulation analyses were developed using the proposed techniques. The flight test results for a series of maneuvering flights with a scaled model were used for comparison with those obtained using the flight dynamics analysis modules to validate the usefulness of the present approaches. The resulting good correlations between the two data sets demonstrate that the flight characteristics of the propeller-driven airplane can be analyzed effectively through the integrated framework with the propeller and airframe aerodynamic models proposed in this study.

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“…The standard approach in the flight simulation community is the mean-axes approximation, [1][2][3][4] which decouples the structural and rigid-body dynamics degrees of freedom (DoF)…”

Section: Introductionmentioning

confidence: 99%

Consistent Structural Linearization in Flexible Aircraft Dynamics with Large Rigid-Body Motion

2014

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This paper investigates the linearization, using perturbation methods, of the structural deformations in the nonlinear flight dynamic response of aircraft with slender, flexible wings. The starting point is the coupling of a displacement-based geometrically nonlinear flexible-body dynamics formulation with a 3D unsteady vortex lattice method. This is followed by a linearization of the structural degrees of freedom, which are assumed to be small in a body-fixed reference frame. The translations and rotations of that reference frame and their time derivatives, which describe the vehicle flight dynamics, can still be arbitrarily large. The resulting system preserves all couplings between rigid and elastic motions and can be projected

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Segmented penetrator flight dynamics

Cited by 5 publications

References 0 publications

Modeling and robust Body Freedom Flutter Analysis of flexible aircraft configurations

Modeling and robust Body Freedom Flutter Analysis of flexible aircraft configurations

Flight Dynamics Analyses of a Propeller-Driven Airplane (II): Building a High-Fidelity Mathematical Model and Applications

Consistent Structural Linearization in Flexible Aircraft Dynamics with Large Rigid-Body Motion

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