ACT/FHS System Identification Including Rotor and Engine Dynamics

Seher-Weiß, Susanne

doi:10.4050/jahs.64.022003

Cited by 5 publications

(4 citation statements)

References 10 publications

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“…A thorough discussion of the different variants of lead/lag modeling that also includes another formulation with only one complex dipole is found in Ref. [77].…”

Section: Regressive Lead/lagmentioning

confidence: 99%

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Retrospective and Recent Examples of Aircraft and Rotorcraft System Identification at DLR

Deiler

Mönnich

Seher-Weiß

et al. 2023

Journal of Aircraft

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Aircraft system identification has a five-decades-long tradition at German Aerospace Center (DLR). Over the last two decades, the research covered various topics related to system identification of fixed- and rotary-wing aircraft, nonconventional applications and atmospheric effects, the development of new flight-test procedures for system identification purposes, and specific aircraft model enhancements and corresponding parameter estimation. Comprehensive tools were developed that support this research and can be applied to a variety of different problems and types of vehicles. The paper starts with a short description of the different system identification methods used at DLR and the corresponding tools. The discussion of flight-test procedures and maneuver design as well as sensor fusion and flight-path reconstruction provides information on how to optimize the flight tests for system identification and to arrive at a consistent flight-test database. The examples for fixed-wing aircraft provide information on identification including abnormal conditions such as icing and interaction with atmospheric disturbances as well as modeling of structural mechanics and loads. The identification of high-order rotorcraft models that account for rotor and engine dynamics and even structural modes is discussed, and the identification of rotor mast moments as well as the identification of non-physics-based models and their integration into physics-based models are also covered. A final section shows that system identification can also be used to derive models for gyroplanes and parachutes as well as to derive control equivalent turbulence input models and to estimate complex wind field geometries. Thus, a broad overview of possible applications of system identification is given.

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“…A thorough discussion of the different variants of lead/lag modeling that also includes another formulation with only one complex dipole is found in Ref. [77].…”

Section: Regressive Lead/lagmentioning

confidence: 99%

“…The extraction of the CETIs was performed using the inverse model approach based on high-fidelity identified models as described in Ref. [77].…”

Section: Ceti Turbulence Models For Rotorcraftmentioning

confidence: 99%

Retrospective and Recent Examples of Aircraft and Rotorcraft System Identification at DLR

Deiler

Mönnich

Seher-Weiß

et al. 2023

Journal of Aircraft

Self Cite

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“…The engine dynamics improve the yaw rate response to both pedal and collective coupling, especially in hover. A detailed derivation of the equations of the 17th-order model can be found in [18].…”

Section: Linear System Modelsmentioning

confidence: 99%

Improving a real-time helicopter simulator model with linear input filters

Scepanovic

Döring

2021

CEAS Aeronaut J

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For a broad range of applications, flight mechanics simulator models have to accurately predict the aircraft dynamics. However, the development and improvement of such models is a difficult and time consuming process. This is especially true for helicopters. In this paper, two rapidly applicable and implementable methods to derive linear input filters that improve the simulator model are presented. The first method is based on model inversion, the second on feedback control. Both methods are evaluated in the time domain, compared to recorded helicopter flight test data, and assessed based on root mean square errors and the Qualification Test Guide bounds. The best results were achieved when using the first method.

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“…As detailed in [1] the system identification is performed in the time domain which determines a huge part of the conducted flight maneuvers. Many flight test campaigns in this scale have been performed for identification in the frequency domain as described in [2] [3] and [4]. For this purpose, mostly frequency sweeps are applied and the time domain specific square wave maneuvers are mainly used for validation purposes.…”

Section: Introductionmentioning

confidence: 99%