Aerodynamic Coefficient Identification of a Space Vehicle from Multiple Free-Flight Tests

Albisser, Marie; Dobre, Simona; Berner, Claude; Thomassin, Magalie; Garnier, Hugues

doi:10.2514/1.a33587

Cited by 12 publications

(5 citation statements)

References 14 publications

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“…PROjectile Design/Analysis System -PRODAS), or wind-tunnel experiments. Their results can be treated as an initial estimation of the aerodynamic coefficients, later to be used in a safety assessment of upcoming free-flight experiments, or in an identification procedure based on collected and measurement data [2,3]. However, complex nonlinear model are problematic: the model fidelity is high, but so is the numerical complexity.…”

Section: Introductionmentioning

confidence: 99%

“…The merit of the work lies in the evaluation of how much do the reference frame transformation and the numerical solver selection influence the accuracy of a trajectory simulation. The evaluation is performed on two models: the nonlinear one in a variable-roll reference frame, similar to these usually used in simulations for the purpose of free-flight experiments [2]; and a quasi-LPV one in a non-rolling frame, resembling these used in control [15]. In order to assess the accuracy of a numerical solution, first a trajectory considered as a reference has been found using a high order fixed-step numerical solver with high sampling frequency.…”

Section: Introductionmentioning

confidence: 99%

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The Analysis of Vehicle’s In-Flight Behaviour Using Quasi-LPV and Nonlinear Models

Machala

Dobre

Albisser

et al. 2019

AIAA Scitech 2019 Forum

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A vehicle's in-flight behaviour can be represented by the Newton-Euler equations of motion: usually, such a model has a nonlinear and continuous description based on ordinary differential equations. The model structure can be altered using analytic transformations and, when the model is implemented, its numerical precision may depend on the selection of a numerical solver. Hence, the selection of a model's structure and an appropriate numerical solver can become the key development issues, if the model's numerical stability, convergence, and computational complexity are to be improved. This paper assesses the influence of a model's reference frame and a numerical solver on the accuracy of calculating a projectile's trajectory, for a case study of free-flight long-range ballistic experiments. The analysis is based on two model structures: the first is a six-degree-of-freedom nonlinear description of a spin-stabilized projectile, expressed in a rolling reference frame; the second is a quasi-LPV reformulation of the same projectile model, but expressed in a non-rolling reference frame. It is shown that inappropriate selection of a numerical solver can hinder the accuracy of the nonlinear model. At the same time, the model represented in a non-rolling reference frame offers a solution with higher accuracy, better convergence properties, and significantly reduced computation time.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The Analysis of Vehicle’s In-Flight Behaviour Using Quasi-LPV and Nonlinear Models

Machala

Dobre

Albisser

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

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“…in [4]). Their results then serve as a first guess of the aerodynamic coefficients, later to be confirmed under a real-world experimentation-ballistic free-flight tests [5].…”

Section: Introductionmentioning

confidence: 85%

Global Sensitivity Analysis for Modeling the Free-Flight Behavior of an Artillery Projectile

Machala

Collin²,

Gilson³

et al. 2020

AIAA Journal

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A vehicle's in-flight behavior can be represented by the Newton-Euler equations of motion: usually, such a model has a nonlinear and continuous description based on ordinary differential equations. The model structure can be altered using analytic transformations-such as transformation into a quasi-LPV structure-and, when the model is supposed to reflect an existing physical system, some of its parameters might be uncertain. This paper's objective is twofold: firstly, to investigate if a quasi-LPV model does accurately replicate the physical behavior of a large-caliber spin-stabilized projectile in free flight; and secondly, to verify if the available embedded sensors data could be used to determine non-identifiability of uncertain model parameters. In order to investigate these prospects, a permutation-based global sensitivity analysis is employed. The proposed study has highlighted the non-identifiable parameters of the model, either during the whole flight or some periods of it. These results can help to enhance the preparation of free flight experiments at the open-range test site of the French-German Research Institute of Saint Louis. Nomenclature M = Mach number V = airspeed, m s −1 α, β, α t = angle of attack, angle of sideslip, total angle of attack, deg C X , C N α , C y pα = axial force, normal force slope, and Magnus force slope coefficients C lp , C mα , C mq , C npα = roll damping, pitch moment slope, pitch damping and Magnus moment slope coefficients

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“…The NSV usually flights in near space (20 -100 km above the earth) with large speed span of Mach number and flight envelope. To further improve the flight performance, the NSV can adopt variable structure such as variable sweep wing and retractable canard wing [4,5]. The controller design for a NSV is challenging due to the For the NSV attitude controller design, many modern control strategies including backstepping control, sliding mode control and neural network based control have been devised by the researchers.…”

Section: Introductionmentioning

confidence: 99%

Switching disturbance rejection attitude control of near space vehicles with variable structure

Gong

Wang

Dong

2019

Journal of Systems Engineering and Electronics

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A switching disturbance rejection attitude control law is proposed for a near space vehicle (NSV) with variable structure. The multiple flight modes, system uncertainties and disturbances of the NSV are taken into account based on switched nonlinear systems. Compared with traditional backstepping design methods, the proposed method utilizes the added integrals of attitude angle and angular rate tracking errors to further decrease the tracking errors. Moreover, to reduce the computation complexity, a rapid convergent differentiator is employed to obtain the derivative of the virtual control command. Finally, for disturbance rejection, based on the idea from the extended state observer (ESO), two disturbance observers are designed by using non-smooth functions to estimate the disturbances in the switched nonlinear systems. All signals of the closed-loop system are proven to be uniformly ultimately bounded under the Lyapunov function framework. Simulation results demonstrate the effectiveness of the proposed control scheme.

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Aerodynamic Coefficient Identification of a Space Vehicle from Multiple Free-Flight Tests

Cited by 12 publications

References 14 publications

The Analysis of Vehicle’s In-Flight Behaviour Using Quasi-LPV and Nonlinear Models

The Analysis of Vehicle’s In-Flight Behaviour Using Quasi-LPV and Nonlinear Models

Global Sensitivity Analysis for Modeling the Free-Flight Behavior of an Artillery Projectile

Switching disturbance rejection attitude control of near space vehicles with variable structure

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