Eigenstructure Assignment for a Tailless Aircraft

Nieto-Wire, Clara

doi:10.2514/6.2007-6417

Cited by 12 publications

(6 citation statements)

References 6 publications

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“…Content may change prior to final publication. A simplified block diagram of the lateral-directional control law developed with the EA [34], [35] control technique is shown in Fig. 12.…”

Section: Control Law Designmentioning

confidence: 99%

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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“…Content may change prior to final publication. A simplified block diagram of the lateral-directional control law developed with the EA [34], [35] control technique is shown in Fig. 12.…”

Section: Control Law Designmentioning

confidence: 99%

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

“…The smaller the value of J e is, the less energy the control system consumes during the aircraft restored to the original flight state. Both the roll control and the yaw control are realized by deflecting two control surfaces at the same angle as given in equation (9) in actual work. If K is rewritten as equation (10)…”

Section: Influence Of Eigenstructure On Energy Consumptionmentioning

confidence: 99%

“…The EA technique has been widely applied to the design of flight control systems (FCS). [8][9][10] Taking into account that the closed-loop system designed by eigenstructure assignment has a poor robustness, the quantitative feedback theory (QFT), analysis and H 1 control are used to solve the robust problem of the closedloop system. [11][12][13] In Peng et al, 14 robust control for flying wing aircraft is solved by eigenvectors assignment.…”

Section: Introductionmentioning

confidence: 99%

Research on lateral-directional stability augmentation system of flying wing aircraft based on reliability model

Pan

Huang

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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Poor lateral-directional stability is a great risk to the design of flying wing aircraft due to the absence of vertical stabilizer. In order to improve the lateral-directional flying quality of this configuration aircraft, eigenstructure assignment technique by state feedback is adopted to design the stability augmentation system. The influence of eigenstructure on energy consumption of the control system is analyzed by citing energy consumption index in this paper. In addition, a reliability model is established to measure the reliability of the control system under uncertain factors. In order to assign eigenvalues and eigenvectors to obtain the control law of the system, a nested optimization model based on coupling degree, energy consumption and reliability is proposed. The outer optimization is used to optimize the eigenstructure, and inner optimization is used to compute the reliability of the control system in optimization process. A flying wing aircraft is used as a basis for the design of the stability augmentation system through the suggested optimization strategy. The optimization results demonstrate the validity of the method, and the lateral-directional flying quality of the aircraft has been improved greatly.

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“…The linear quadratic integral (LQI) controller [6] possesses the advantage of simplicity of design for MIMO systems, particularly with regard to control effort allocation. The EA method is widely used in tailless aircraft control [7,8], but because it is based on the linearized model, it can be challenging to address nonlinear dynamics.…”

Section: Introductionmentioning

confidence: 99%

Extended-State-Observer-Based Angular Acceleration Estimation for Supersonic Aircraft Lateral–Directional Control

et al. 2023

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Large-slenderness-ratio (LSR) aircraft exhibit more severe lateral–directional coupling compared with other aircraft, which poses a significant challenge to their flight safety, especially during high-speed maneuvers. Reliable attitude decoupling control is, therefore, essential for LSR aircraft. In this study, a novel control framework that combines incremental nonlinear dynamic inversion (INDI) and extended state observer (ESO) is proposed for supersonic roll maneuver control of LSR aircraft. The ESO is used to estimate the angular acceleration on the basis of an onboard mathematical model. The acceleration estimator based on ESO achieves superior noise reduction compared with the complementary filter (CF) and reduces the onboard model requirement without significantly sacrificing estimation accuracy. Monte Carlo (MC) simulations and frequency–domain analysis demonstrate the effectiveness and robustness of the proposed controller. The sensitivity of parameter uncertainties is also investigated, revealing that the natural frequency of the actuator is the most critical parameter affecting robustness. Finally, flight tests validate the effectiveness of the proposed control structure.

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Eigenstructure Assignment for a Tailless Aircraft

Cited by 12 publications

References 6 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

Research on lateral-directional stability augmentation system of flying wing aircraft based on reliability model

Extended-State-Observer-Based Angular Acceleration Estimation for Supersonic Aircraft Lateral–Directional Control

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