Dynamic Rig for Validation of Control Algorithms at High Angles of Attack

Ignatyev, Dmitry; Sidoryuk, Maria E.; Kolinko, Konstantin Anatolievich; Храбров, А. Н.

doi:10.2514/1.c034167

Cited by 21 publications

(13 citation statements)

References 29 publications

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“…The equations of motion for the aircraft model on the rig are derived and simplified based on the typical equations for a 6-DOF free flight [23], [24] as follows: Though there is a hole on the fuselage's underside for rig support with sufficient maneuver range, the gap between model and rig is minimized beforehand to fit the flight states and reduce the aerodynamic interference. Subsequently, the aerodynamic interference from the rig is not taken into account as the previous studies [13], [18]- [21]. As a result, the external moments ( ) L, M, N in the body-fixed reference frame about the CG can be decomposed into three terms:…”

Section: A Dynamic Modeling Of Aircraft On the Rigmentioning

confidence: 99%

“…Friction moments resulting from the spherical joint are assumed to be a sum of dry and viscous frictions as in Ref. [18].…”

Section: Misalignment and Friction Modelingmentioning

confidence: 99%

“…The results of the free flight test validated the designed control laws and indicated satisfactory flight behavior. One can see that the main idea is to allow the scaled tailless aircraft to fly in a wind tunnel working section freely or with partially constrained motion imposed by a dynamic rig [17], which has previously been used for identification and control investigations of conventional aircraft [18]- [22].…”

Section: Introductionmentioning

confidence: 99%

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An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

Nie¹,

Liu²,

Cen³

et al. 2020

IEEE Access

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Tailless aircraft suffers from limited yaw control power and poor directional stability inherently. To address these issues in the early design process of a tailless configuration with low costs and risks, this paper presents an innovative experimental approach to control law validation and quantitative flying quality evaluation with a dynamically scaled model mounted on a three degree-of-freedom rig in the wind tunnel. The motion equations of the tailless demonstrator on the rig are derived, and then the comparisons of the lateral-directional flight dynamics between the rig constrained model and the free flight model are carried out. Construction of the control augmentation system for yaw and roll motion is accomplished according to the scale modified criteria of flying qualities. Effectiveness of the designed control law is demonstrated with steady pilot-in-the-loop flights at different airspeeds and angles of attack. The achieved closed-loop flying qualities are evaluated by applying multistep maneuvers for low order equivalent system identification. Whereas severe instability is observed in yaw for the open-loop case, the closed-loop flying quality of the Dutch-roll mode can be improved to level 1 at low angle of attack.

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Section: A Dynamic Modeling Of Aircraft On the Rigmentioning

confidence: 99%

“…Friction moments resulting from the spherical joint are assumed to be a sum of dry and viscous frictions as in Ref. [18].…”

Section: Misalignment and Friction Modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

Nie¹,

Liu²,

Cen³

et al. 2020

IEEE Access

View full text Add to dashboard Cite

show abstract

“…Different statistical surveys reported (see, for example, [1]) that loss of control in flight (LOC-I) was the major cause of fatal transport aviation accidents. Thus, many intensive studies are aimed at modeling of aerodynamics in the extended flight envelope in order to support investigations of aircraft dynamics, control system design [2] and to provide realistic pilot training using ground-based simulators in upset conditions [3,4].…”

Section: Introductionmentioning

confidence: 99%

Experimental Study and Neural Network Modeling of Aerodynamic Characteristics of Canard Aircraft at High Angles of Attack

Ignatyev

Храбров

2018

Aerospace

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Flow over an aircraft at high angles of attack is characterized by a combination of separated and vortical flows that interact with each other and with the airframe. As a result, there is a set of phenomena negatively affecting the aircraft's performance, stability and control, namely, degradation of lifting force, nonlinear variation of pitching moment, positive damping, etc. Wind tunnel study of aerodynamic characteristics of a prospective transonic aircraft, which is in a canard configuration, is discussed in the paper. A three-stage experimental campaign was undertaken. In the first stage, a steady aerodynamic experiment was conducted. The influence of a reduced oscillation frequency and angle of attack on unsteady aerodynamic characteristics was studied in the second stage. In the third stage, forced large-amplitude oscillation tests were carried out for the detailed investigation of the unsteady aerodynamics in the extended flight envelope. The experimental results demonstrate the strongly nonlinear behavior of the aerodynamic characteristics because of canard vortex effects on the wing. The obtained data are used to design and test mathematical models of unsteady aerodynamics via different popular approaches, namely the Neural Network (NN) technique and the phenomenological state space modeling technique. Different NN architectures, namely feed-forward and recurrent, are considered and compared. Thorough analysis of the performance of the models revealed that the Recurrent Neural Network (RNN) is a universal approximation tool for modeling of dynamic processes with high generalization abilities.

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“…The FFNN trained better to model the small-amplitude behavior shows poor performance for the large-amplitude subset. This is not satisfactory from the point of view of flight dynamics because a model should guarantee an equivalent level of the model precision in overall simulation domain for proper design a control system [74,75].…”

mentioning

confidence: 99%

Bayesian calibration for multiple source regression model

2018

Self Cite

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In large variety of practical applications, using information from different sources or different kind of data is a reasonable demand. The problem of studying multiple source data can be represented as a multi-task learning problem, and then the information from one source can help to study the information from the other source by extracting a shared common structure. From the other hand, parameter evaluations obtained from various sources can be confused and conflicting. This paper proposes a Bayesian based approach to calibrate data obtained from different sources and to solve nonlinear regression problem in the presence of heteroscedastisity of the multiple-source model. An efficient algorithm is developed for implementation. Using analytical and simulation studies, it is shown that the proposed Bayesian calibration improves the convergence rate of the algorithm and precision of the model. The theoretical results are supported by a synthetic example, and a real-world problem, namely, modeling unsteady pitching moment coefficient of aircraft, for which a recurrent neural network is constructed.

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Dynamic Rig for Validation of Control Algorithms at High Angles of Attack

Cited by 21 publications

References 29 publications

An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

An Innovative Experimental Approach to Lateral-Directional Flying Quality Investigation for Tailless Aircraft

Experimental Study and Neural Network Modeling of Aerodynamic Characteristics of Canard Aircraft at High Angles of Attack

Bayesian calibration for multiple source regression model

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