Aircraft nonlinear stability analysis and multidimensional stability region estimation under icing conditions

Liang, Qiyu; Li, Yinghui; Xu, Haojun; Zhang, Dengcheng; Yuan, Guoqiang

doi:10.1016/j.cja.2017.02.003

Cited by 12 publications

(3 citation statements)

References 8 publications

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“…For systems higher than three-dimensional, the calculation of stable manifold is quite expensive, and visualization of stable manifold is challenging. We tried to calculate the stability region of a five-dimensional system in Qu et al 47 However, in order to ensure that the calculation can be completed in an acceptable time, we have to sacrifice the calculation accuracy. In addition, the visualization of the results is not ideal and it is not convenient to analyze the effects of icing in a vivid manner.…”

Section: Longitudinal Dynamics Of the F-16mentioning

confidence: 99%

Determination of the flight dynamic envelope via stable manifold

Yuan

2019

Measurement and Control

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The flight envelope plays an important role in flight safety. The concept of posing the flight envelope as a region of attraction is explored further, and it is investigated whether the stable manifold for the region of attraction computation is an efficient method for determining envelope. The stable manifold describes the flight dynamic envelope of an aircraft in an explicit representation, which means that the computation needs to be done only on the envelope, not the entire state space. In this paper, the stable manifold is computed by using a fast method which reduces the computation to solving a system of partial differential equation. Then, the stable manifold grows in the way of advancing front mesh generation framework. The stable manifold is then applied to the envelope determination of a nonlinear F-16 model. The result is compared to the results obtained with the level set method, demonstrating that the stable manifold provides a feasible and accurate result to the dynamic envelope. The proposed method is then used to investigate the effect of actuator failure on the flight safety. The proposed method can also be used as a safety assessing tool during the design phase of an aircraft.

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Section: Longitudinal Dynamics Of the F-16mentioning

confidence: 99%

Determination of the flight dynamic envelope via stable manifold

Yuan

2019

Measurement and Control

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“…Characteristics. The change rules of aerodynamic parameters and stability derivatives and nonlinear and stall conditions after icing were studied [15][16][17]. The dynamic response characteristics under different ice severity and distribution conditions [18,19] and icing influence on the overall performance, maneuverability and stability of the aircraft [20] were explored.…”

Section: (2) Effect Of Icing On Aerodynamic and Flight Mechanicsmentioning

confidence: 99%

On Flight Risk Quantitative Evaluation under Icing Conditions

Xue

et al. 2019

Mathematical Problems in Engineering

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The quantitative assessment of flight risk under icing conditions was taken as the research object. Based on multifactor coupling modeling idea, the pilot-aircraft-environment coupling system was built. Considering the physical characteristics and randomness of aircraft icing, the extreme values of critical flight risk parameters were extracted by the Monte Carlo flight simulation experiment. The flight characteristics were studied comprehensively and heavy-tail characteristics and the distributions of different flight parameters were verified. Flight risk criterion was developed and one-dimensional extreme flight risk probability was calculated. Further, in order to solve the limitation of one-dimensional extreme value, with the Copula theory, the joint distribution model of flight parameters with three distinct distribution types was built. The optimal Copula model was selected by identification of unknown parameters and goodness of fit tests, and the three-dimensional extreme flight risk probability was defined. Based on the quantitative flight risk, the accident induction mechanism under icing conditions was discussed. Airspeed and roll angle under asymmetry icing conditions were more sensitive and had a more significant impact on flight safety. This method can provide reference for safety manipulation, boundary protection, and risk warning during icing flight.

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“…In recent years, a lot of effort about aircraft icing problem has been made, including ice wind tunnel experiment 5 , dynamic inverse control 6 , stability region estimation 7 , icing protection system 8 , etc. However, the above literature only focuses on the robustness of control system to aircraft icing, ignoring the convergence rate of tracking errors.…”

Section: Introductionmentioning

confidence: 99%

Fixed-time angle of attack constrained control for aircraft considering dynamic icing process

Dong,

Da,

et al. 2024

Sci Rep

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Aircraft icing deteriorates aerodynamic performance and reduces stall angle of attack, the fast convergence rate of tracking error is required to stabilize the aircraft when aircraft icing occurs. The state-of-the-art control methods for icing aircraft mostly assume that the icing of aircraft is instantaneous. Aiming at these issues, a fixed-time angle of attack-constrained control strategy is designed considering dynamic icing process. In order to explore the variation of aerodynamic coefficients in the process of dynamic icing, an ice wind tunnel experiment is implemented, and the relationship between lift coefficient, drag coefficient and pitching moment coefficient with angle of attack and icing intensity is obtained by fitting method. In order to prevent the stalling problem caused by the decrease of the stalling angle of attack in the process of dynamic icing, a method to determine the stalling angle of attack based on deep neural network is proposed. Considering the asymmetric and time-varying angle of attack constraint, a fixed-time convergent angle of attack-constrained robust control method is designed. The ice wind tunnel experiment shows the process of dynamic icing of the airfoil, and the simulation results verify the effectiveness of the proposed control method.

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Aircraft nonlinear stability analysis and multidimensional stability region estimation under icing conditions

Cited by 12 publications

References 8 publications

Determination of the flight dynamic envelope via stable manifold

Determination of the flight dynamic envelope via stable manifold

On Flight Risk Quantitative Evaluation under Icing Conditions

Fixed-time angle of attack constrained control for aircraft considering dynamic icing process

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