Sensitivity of Spin Parameters to Uncertainties of the Aircraft Aerodynamic Model

Farcy, Dominique; Храбров, А. Н.; Sidoryuk, Maria E.

doi:10.2514/1.c035882

Cited by 8 publications

(8 citation statements)

References 17 publications

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“…In addition, 20% of measurements were chosen at random to serve as a validation dataset, while the remaining 80% were used for the fitting. These points were chosen at random because of the small number of experiments (8) where each was susceptible to hold unique information.…”

Section: A Data Acquisitionmentioning

confidence: 99%

“…For instance, [7] proposed to solve numerically the Navier-Stokes equations, while [4] uses semiempirical models. Others have proposed fully data-driven models such as locally weighted projection regression [8] or splines [9]. However, while splines present today a powerful tool for accurate and smooth interpolation [10], their complexity make them difficult to use for functional analysis of trim conditions and stable sets.…”

Section: Introductionmentioning

confidence: 99%

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A Hybrid Polynomial Stall Model for the Longitudinal Dynamics of a UAV

Guibert

Condomines

Brunot

et al. 2022

2022 International Conference on Unmanned Aircraft Systems (ICUAS)

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Modeling the longitudinal dynamics of a fixedwing unmanned aerial vehicle (UAV) at high angles of attack is not an easy task. Indeed, when the airplane approaches stall, non-linear effects appear, including transient behaviors and an aerodynamic hysteresis. Although some models are present in the literature to address these aspects, they are usually aerodynamics-based and often too complex for analysis and control applications. Therefore, this paper presents a new hybrid polynomial formulation for the modeling of the aerodynamic coefficients. In addition, a Linearly Constrained Least Squares (LCLS) process guaranteeing continuity at the mode transitions is proposed for the identification of the model. The Hybrid Polynomial Stall Model (HPSM) is finally identified on experimental wind tunnel data, showcasing its ability to accurately predict a UAV's dynamics.

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Section: A Data Acquisitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Hybrid Polynomial Stall Model for the Longitudinal Dynamics of a UAV

Guibert

Condomines

Brunot

et al. 2022

2022 International Conference on Unmanned Aircraft Systems (ICUAS)

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show abstract

“…However, prediction on the stability characteristics of predicted spin modes is unreliable, as all the spin modes tend to be unstable due to the lack of damping terms in the model structure given by equation ( 6). 19 The unreliable picture of stability of the spin modes does not allow predicting adequately aircraft dynamic behavior in post-stall/spin maneuvers. The damping terms are modeled from large-amplitude oscillatory coning motion tests data and incorporated in aircraft flight dynamic model.…”

Section: Dynamic Stability Analysis Of Flat Spinsmentioning

confidence: 99%

“…Because spin modes are equilibrium states, they are numerically computed by simultaneously solving full 6-DOF aircraft equations of motion using the developed aerodynamic model. However, with the assumption that aircraft is in fully developed spin phase with wings level and zero sideslip, three force equations get decoupled from 6-DOF aircraft model and spin modes can be computed by simultaneous solution of 3-DOF model comprising of following moment equations 19 …”

Section: Numerical Prediction Of Spin and Recovery Characteristicsmentioning

confidence: 99%

Objective comparison of numerical spin study with aircraft model free-flight spin tests

Malik

Masud

Akhtar

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper reports on the results of a research project that investigated the spin and recovery characteristics of a multirole fighter aircraft. In the first phase, numerical/computational methods were used to predict full scale aircraft spin and recovery characteristics. The aerodynamic data used in the numerical study was obtained from rotary balance steady coning and oscillatory coning motion dynamic wind tunnel tests conducted on 1/13th scale aircraft dynamic model. All the possible steady spin modes were numerically computed, a complete set of dynamic modes of the spinning aircraft were evaluated and six degree of freedom simulations of predicted flat spins were performed to investigate their dynamic stability and recovery characteristics. In the second phase, free-flight spin trials were conducted using 1/5th scale dynamic model of the understudy aircraft to validate the results of the analytical spin studies. Dynamic characteristics of the analytically predicted flat spins were objectively compared with flat spins found in free-flight spin trials as a validation process. Our results reveal that the numerically predicted full scale aircraft spin and recovery dynamic characteristics correlate well with those estimated from model test flights. The present study is an important step toward objective comparison of numerical spin studies based on dynamic wind tunnel tests data with free-flight spin trials, yielding important guidelines and results for future aircraft spin studies.

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“…The findings of such post-stall/spin research are subsequently used for aircraft airframe modifications and/or flight control system designs to render the aircraft more spin resistant. However, despite significant advances in the state of the art of these experimental techniques, accurate prediction of aircraft post-stall/spin dynamics has continued to be an ongoing challenge due to highly complex aerodynamics associated with such flight conditions (Farcy et al , 2020).…”

Section: Introductionmentioning

confidence: 99%

A review of experimental techniques to predict aircraft spin and recovery characteristics

Malik

Masud

Akhtar

2021

AEAT

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Purpose This paper aims to provide a detailed review of the experimental research on the prediction of aircraft spin and recovery characteristics using dynamically scaled aircraft models. Design/methodology/approach The paper organizes experimental techniques to predict aircraft spin and recovery characteristics into three broad categories: dynamic free-flight tests, dynamic force tests and a relatively novel technique called wind tunnel based virtual flight testing. Findings After a thorough review, usefulness, limitations and open problems in the presented techniques are highlighted to provide a useful reference to researchers. The area of application of each technique within the research scope of aircraft spin is also presented. Originality/value Previous reviews on the prediction of aircraft spin and recovery characteristics were published many years ago and also have confined scope as they address particular spin technologies. This paper attempts to provide a comprehensive review on the subject and fill the information void regarding the state of the art aircraft spin technologies.

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Sensitivity of Spin Parameters to Uncertainties of the Aircraft Aerodynamic Model

Cited by 8 publications

References 17 publications

A Hybrid Polynomial Stall Model for the Longitudinal Dynamics of a UAV

A Hybrid Polynomial Stall Model for the Longitudinal Dynamics of a UAV

Objective comparison of numerical spin study with aircraft model free-flight spin tests

A review of experimental techniques to predict aircraft spin and recovery characteristics

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