High Angle of Attack Model Identification with Compressibility Effects

Dias, Joaquim N.

doi:10.2514/6.2015-1477

Cited by 7 publications

(2 citation statements)

References 5 publications

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“…For the Embraer AT-26 Xavante, at Mach = 0.4, these are 0.2 and -0.08 respectively. 43 The value of C DX for the VFW-614 is 0.22 and for the C-160 approximately 0.40. 38 The values that were found, as shown in Figures 22 and 23 are approximately 0.2 and -0.12 for C DX and C mX , respectively, corresponding well with the values found in literature.…”

Section: Vb Aerodynamic Modelmentioning

confidence: 94%

“…Another interesting fact is that C mq is estimated to be positive, whereas a negative value is expected, as is the case for the Embraer AT-26 Xavante. 43 The only pitch rate parameter that could be identified is C Lq , the reason for not doing so is threefold. First it will make the aerodynamic model structure less clear by using a pitch rate term in one equation and not in the others.…”

Section: Vb Aerodynamic Modelmentioning

confidence: 99%

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Aerodynamic Stall and Buffet Modeling for the Cessna Citation II Based on Flight Test Data

Horssen

Visser

Pool

2018

2018 AIAA Modeling and Simulation Technologies Conference

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To meet the required flight simulator-based stall recovery training that will become mandatory for all aircarrier pilots in 2019, many flight simulators will need to be updated with accurate flight models at high anglesof-attack. Using a database of 69 symmetrical and quasi-steady recorded stalls performed with TU Delft's Cessna Citation II laboratory aircraft, this paper aims to show to what extent relevant stall characteristics can still be modeled using flight test data from such "natural" stall flight test data (i.e., without additional flight test inputs). For modeling the (low-frequency) changes to the aerodynamic characteristics, the well-known stall model structure based on Kirchoff's flow separation theory is used. This aerodynamic stall model is augmented with a high-frequency stall buffet model identified based on power spectral density analysis of the flight test linear acceleration data. The stall model identification results obtained from a proposed methodology in which the aerodynamic and buffet model parameters were deliberately jointly estimated shows that the dynamic parameters capturing the stall hysteresis effect can indeed be estimated using quasi-steady stall maneuvers. Aerodynamic terms related to the pitch rate, however, are difficult to estimate for such quasi-steady maneuvers, given the correlation between pitch rate and angle-of-attack. It was found that estimating stall transient effects (i.e., hysteresis time constants), which normally require highly dynamic flight test maneuvers, was found to be improved with with explicit use of the measured accelerations caused by the stall buffet in the identification methodology.

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Section: Vb Aerodynamic Modelmentioning

confidence: 94%

Section: Vb Aerodynamic Modelmentioning

confidence: 99%

Aerodynamic Stall and Buffet Modeling for the Cessna Citation II Based on Flight Test Data

Horssen

Visser

Pool

2018

2018 AIAA Modeling and Simulation Technologies Conference

View full text Add to dashboard Cite

show abstract

Recent Applications of System Identification Techniques at IPEV

Dias¹,

Silva²

2023

Journal of Aircraft

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This paper presents an overview of the system identification techniques developed and applied at the Flight Test and Research Institute during the last decade. System identification techniques have been used extensively to obtain aerodynamic models for a flight-test simulator, which was developed in house and specifically tailored for flight-test instruction and preparation for actual test flights. The methods applied were mostly the output error for data compatibility check and equation error in the time domain for model structure selection and parameter estimation. The most relevant applications are summarized in this paper, including identification of a high angle of attack model with compressibility effects for a jet trainer; estimation of drag polars at high subsonic regime for a jet fighter; identification of aerodynamic model in real-time for a propeller-driven fighter; application of flight-path reconstruction techniques to spin tests, in order to correct errors in the air data sensors; and identification of power effects on the longitudinal stability of a propeller-driven trainer. The examples show that system identification has become crucial to 1) obtain accurate aerodynamic models for training in the flight-test simulator and 2) develop more efficient flight-test techniques.

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Stalls and Splines: Current Trends in Flight Testing and Aerodynamic Model Identification

de Visser,

Pool

2023

Journal of Aircraft

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Aerodynamic model identification remains essential for simulator operations and control system design and operations. In this paper, state-of-the-art methodologies for aerodynamic model identification and validation are presented, together with a number of novel applications of the identified models that were recently investigated and developed at the Faculty of Aerospace Engineering of Delft University of Technology. In particular, this paper focuses on methodologies for identifying models of aerodynamic stall from flight data, as well as multivariate spline-based aerodynamic model identification methods, together with their applications in flight simulation and advanced flight control.

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High Angle of Attack Model Identification with Compressibility Effects

Cited by 7 publications

References 5 publications

Aerodynamic Stall and Buffet Modeling for the Cessna Citation II Based on Flight Test Data

Aerodynamic Stall and Buffet Modeling for the Cessna Citation II Based on Flight Test Data

Recent Applications of System Identification Techniques at IPEV

Stalls and Splines: Current Trends in Flight Testing and Aerodynamic Model Identification

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