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Aerospace
Special Issues
Challenges and Innovations in Aircraft Flight Control
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Challenges and Innovations in Aircraft Flight Control

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 8444

Special Issue Editors

Dr. Nadjim Horri

E-Mail Website
Guest Editor
School of Engineering, University of Leicester, Leicester LE1 7RH, UK
Interests: guidance, navigation, and control for uncrewed aerial vehicles (UAVs); crewed aircraft and electric vertical takeoff and landing vehicles
Dr. Toufik Souanef

E-Mail Website
Guest Editor
School of Aerospace, Transport and Manufacturing, Cranfield University, Cranfield MK43 0AL, UK
Interests: guidance, navigation, and control of aerial systems; robust and adaptive control theory; unmanned traffic management

Special Issue Information

Dear Colleagues,

Recent years have seen a rise in the aircraft performance, safety, and autonomy requirements for both crewed and uncrewed aircraft. This is creating new flight control challenges for different classes of aircraft. Civilian airliners are evolving towards increasing their levels of automation, but this is creating flight control safety challenges. Uncrewed aerial vehicles (UAVs) have also evolved with an unprecedented variety in their designs. Aircraft control systems are also increasingly required to save energy and reduce emissions, particularly in the case of electric aircraft, including urban air mobility.

In this Special Issue, particular prominence will be given to the development of estimation and control methods and algorithms for:

- Fault tolerant aircraft control systems under sensor and actuator faults;

- Optimal aircraft control allocation using multiple actuators;

- Flight envelope protection for enhanced flight safety;

- Optimal aircraft control problems of practical significance, including energy optimality, optimal tradeoffs, time optimality, and optimal coverage path planning;

- Adaptive flight control to handle aircraft parameter variations;

- Aircraft state, fault, disturbance, and model uncertainty estimation using advances in observers, Kalman filters, and other estimation methods;

- Advances in aircraft robust control;

- Hybrid (combined continuous and discrete time) control approaches for flight profiles with multiple flight modes;

- Artificial intelligence in flight control;

- Advances in the control of hybrid (cruise and VTOL) aircraft configurations;

- Combining open-loop and closed-loop aircraft control systems;

- Advances in autonomous and full authority flight control systems.

Review, theoretical, simulation-based, and practical-type papers are all within the scope of this Special Issue. All aircraft types are also within the scope of this Special Issue.

Dr. Nadjim Horri
Dr. Toufik Souanef
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • UAV
  • electric aircraft
  • fault
  • disturbance
  • optimal
  • robust control
  • adaptive
  • hybrid control

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Published Papers (8 papers)

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Research

21 pages, 1681 KiB  
Article
Momentum-Based Adaptive Laws for Identification and Control
by Luke Somers and Wassim M. Haddad
Aerospace 2024, 11(12), 1017; https://doi.org/10.3390/aerospace11121017 - 11 Dec 2024
Viewed by 339
Abstract
In this paper, we develop momentum-based adaptive update laws for parameter identification and control to improve parameter estimation error convergence and control system performance for uncertain dynamical systems. Specifically, we introduce three novel continuous-time, momentum-based adaptive estimation and control algorithms and evaluate their [...] Read more.
In this paper, we develop momentum-based adaptive update laws for parameter identification and control to improve parameter estimation error convergence and control system performance for uncertain dynamical systems. Specifically, we introduce three novel continuous-time, momentum-based adaptive estimation and control algorithms and evaluate their effectiveness via several numerical examples. Our proposed adaptive architectures show faster parameter convergence rates as compared to the classical gradient descent and model reference adaptive control methods. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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20 pages, 3891 KiB  
Article
A Robust Adaptive PID-like Controller for Quadrotor Unmanned Aerial Vehicle Systems
by Ahsene Boubakir, Toufik Souanef, Salim Labiod and James F. Whidborne
Aerospace 2024, 11(12), 980; https://doi.org/10.3390/aerospace11120980 - 27 Nov 2024
Viewed by 526
Abstract
This paper introduces a stable adaptive PID-like control scheme for quadrotor Unmanned Aerial Vehicle (UAV) systems. The PID-like controller is designed to closely estimate an ideal controller to meet specific control objectives, with its gains being dynamically adjusted through a stable adaptation process. [...] Read more.
This paper introduces a stable adaptive PID-like control scheme for quadrotor Unmanned Aerial Vehicle (UAV) systems. The PID-like controller is designed to closely estimate an ideal controller to meet specific control objectives, with its gains being dynamically adjusted through a stable adaptation process. The adaptation process aims to reduce the discrepancy between the ideal controller and the PID-like controller in use. This method is considered model-free, as it does not require knowledge of the system’s mathematical model. The stability analysis performed using a Lyapunov method demonstrates that every signal in the closed-loop system is Uniformly Ultimately Bounded (UUB). The effectiveness of the proposed PID-like controller is validated through simulations on a quadrotor for path following, ensuring accurate monitoring of the target positions and yaw angle. Simulation results highlight the performance of this control scheme. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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26 pages, 3035 KiB  
Article
Nonlinear Extended State Observer and Prescribed Performance Fault-Tolerant Control of Quadrotor Unmanned Aerial Vehicles Against Compound Faults
by Ge Mai, Hongliang Wang, Yilin Wang, Xinghua Wu, Peiyao Jiang and Genyuan Feng
Aerospace 2024, 11(11), 903; https://doi.org/10.3390/aerospace11110903 - 3 Nov 2024
Cited by 1 | Viewed by 1065
Abstract
Addressing trajectory and attitude control challenges in quadrotor UAVs amid compound faults and unknown external disturbances, this paper introduces a fault-tolerant control method predicated on nonlinear extended state observers. Initially, the UAV’s dynamic model is optimized and decoupled, forming a rapid non-singular terminal [...] Read more.
Addressing trajectory and attitude control challenges in quadrotor UAVs amid compound faults and unknown external disturbances, this paper introduces a fault-tolerant control method predicated on nonlinear extended state observers. Initially, the UAV’s dynamic model is optimized and decoupled, forming a rapid non-singular terminal sliding mode surface that circumvents the singular phenomena typical in conventional terminal sliding mode controls. A nonlinear extended state observer is then deployed to estimate the unknown states triggered by compound faults and disturbances within the control system. Theoretical analysis shows that beyond accurately estimating faults and disturbances, the proposed controllers adaptively adjust the system’s dynamic and steady-state performances, ensuring rapid stabilization of all error responses. Numerical simulations indicate significant enhancements in control precision and robustness against compound faults and disturbances, with response times and energy consumption remaining within acceptable limits for practical applications. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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31 pages, 29046 KiB  
Article
Disturbance Observer-Based Backstepping Terminal Sliding Mode Aeroelastic Control of Airfoils
by Shiqian Liu, Congjie Yang, Qian Zhang and James F. Whidborne
Aerospace 2024, 11(11), 882; https://doi.org/10.3390/aerospace11110882 - 25 Oct 2024
Viewed by 539
Abstract
This paper studies aeroelastic control for a two-dimensional airfoil–flap system with unknown gust disturbances and model uncertainties. Open loop limit cycle oscillation (LCO) happens at the post-flutter speed. The structural stiffness and quasi-steady and unsteady aerodynamic loads of the aeroelastic system are represented [...] Read more.
This paper studies aeroelastic control for a two-dimensional airfoil–flap system with unknown gust disturbances and model uncertainties. Open loop limit cycle oscillation (LCO) happens at the post-flutter speed. The structural stiffness and quasi-steady and unsteady aerodynamic loads of the aeroelastic system are represented by nonlinear models. To robustly suppress aeroelastic vibration within a finite time, a backstepping terminal sliding-mode control (BTSMC) is proposed. In addition, a learning rate (LR) is incorporated into the BTSMC to adjust how fast the aeroelastic response converges to zero. In order to overcome the fact that the BTSMC design is dependent on prior knowledge, a nonlinear disturbance observer (DO) is designed to estimate the variable observable disturbances. The closed-loop aeroelastic control system has proven to be globally asymptotically stable and converges within a finite time using Lyapunov theory. Simulation results of an aeroelastic two-dimensional airfoil with both trailing-edge (TE) and leading-edge (LE) control surfaces show that the proposed DO-BTSMC is effective for flutter suppression, even when subjected to gusts and parameter uncertainties. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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23 pages, 3487 KiB  
Article
Design and Experimental Validation of an Adaptive Multi-Layer Neural Network Observer-Based Fast Terminal Sliding Mode Control for Quadrotor System
by Zainab Akhtar, Syed Abbas Zilqurnain Naqvi, Yasir Ali Khan, Mirza Tariq Hamayun and Salman Ijaz
Aerospace 2024, 11(10), 788; https://doi.org/10.3390/aerospace11100788 - 24 Sep 2024
Viewed by 1032
Abstract
This study considers the numerical design and practical implementation of a new multi-layer neural network observer-based control design technique for unmanned aerial vehicles systems. Initially, an adaptive multi-layer neural network-based Luenberger observer is designed for state estimation by employing a modified back-propagation algorithm. [...] Read more.
This study considers the numerical design and practical implementation of a new multi-layer neural network observer-based control design technique for unmanned aerial vehicles systems. Initially, an adaptive multi-layer neural network-based Luenberger observer is designed for state estimation by employing a modified back-propagation algorithm. The proposed observer’s adaptive nature aids in mitigating the impact of noise, disturbance, and parameter variations, which are usually not considered by conventional observers. Based on the observed states, a nonlinear dynamic inversion-based fast terminal sliding mode controller is designed to attain the desired attitude and position tracking control. This is done by employing a two-loop control structure. Numerical simulations are conducted to demonstrate the effectiveness of the proposed scheme in the presence of disturbance, parameter uncertainty, and noise. The numerical results are compared with current approaches, demonstrating the superiority of the proposed method. In order to assess the practical effectiveness of the proposed method, hardware-in-loop simulations are conducted by utilizing a Pixhawk 6X flight controller that interfaces with the mission planner software. Finally, experiments are conducted on a real F450 quadrotor in a secured laboratory environment, demonstrating stability and good tracking performance of the proposed MLNN observer-based SMC control scheme. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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23 pages, 3682 KiB  
Article
Adaptive Incremental Nonlinear Dynamic Inversion Control for Aerial Manipulators
by Chanhong Park, Alex Ramirez-Serrano and Mahdis Bisheban
Aerospace 2024, 11(8), 671; https://doi.org/10.3390/aerospace11080671 - 15 Aug 2024
Cited by 2 | Viewed by 1133
Abstract
This paper proposes an adaptive incremental nonlinear dynamic inversion (INDI) controller for unmanned aerial manipulators (UAMs). A novel adaptive law is employed to enable aerial manipulators to manage the inertia parameter changes that occur when the manipulator moves or picks up unknown objects [...] Read more.
This paper proposes an adaptive incremental nonlinear dynamic inversion (INDI) controller for unmanned aerial manipulators (UAMs). A novel adaptive law is employed to enable aerial manipulators to manage the inertia parameter changes that occur when the manipulator moves or picks up unknown objects during any phase of the UAM’s flight maneuver. The adaptive law utilizes a Kalman filter to estimate a set of weighting factors employed to adjust the control gain matrix of a previously developed INDI control law formulated for the corresponding UAV (no manipulator included). The proposed adaptive control scheme uses acceleration and actuator input measurements of the UAV without necessitating any knowledge about the manipulator, its movements, or the objects being grasped, thus enabling the use of previously developed INDI UAV controllers for UAMs. The algorithm is validated through simulations demonstrating that the adaptive control gain matrix used in the UAV’s INDI controller is promptly updated based on the UAM maneuvers, resulting in effective UAV and robot arm control. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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12 pages, 2007 KiB  
Article
Number of Blades’ Influence on the Performance of Rotor with Equal Solidity in Open and Shrouded Configurations: Experimental Analysis
by Abdallah Dayhoum, Alejandro Ramirez-Serrano and Robert J. Martinuzzi
Aerospace 2024, 11(8), 644; https://doi.org/10.3390/aerospace11080644 - 8 Aug 2024
Viewed by 840
Abstract
This study explores the implications of the number of blades on the performance of both open and shrouded rotors. By conducting a thorough experimental analysis at a fixed solidity ratio, this research seeks to enhance our understanding of rotor dynamics and efficiency. Two-, [...] Read more.
This study explores the implications of the number of blades on the performance of both open and shrouded rotors. By conducting a thorough experimental analysis at a fixed solidity ratio, this research seeks to enhance our understanding of rotor dynamics and efficiency. Two-, three-, four-, and five-bladed rotors were designed and manufactured to have the same solidity ratio. This leads to smaller chord distribution values for higher blade numbers. The experimental analysis aims to quantify the effects of the number of blades and provides a comparative analysis of performance differences between the two rotor configurations (shrouded and open). For the open rotor, results indicate that increasing the number of blades has a minimal impact on overall performance. This is due to the decrease in the tip loss factor being counterbalanced by a decline in efficiency caused by the two-dimensional airfoil performance, which results from a smaller chord and a lower Reynolds number. In contrast, the shrouded rotor exhibits a noticeable performance decay with an increased blade count. Since tip loss is inherently absent in shrouded designs, the decline is primarily attributed to the two-dimensional airfoil performance. This decay occurs while maintaining a constant solidity ratio, highlighting the significant effect of blade count on shrouded rotor efficiency, thereby contributing to the optimization of rotor design in various engineering applications. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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24 pages, 4888 KiB  
Article
Compound Control Design of Near-Space Hypersonic Vehicle Based on a Time-Varying Linear Quadratic Regulator and Sliding Mode Method
by Huan Wang, Di Zhou, Yiqun Zhang and Chaofei Lou
Aerospace 2024, 11(7), 567; https://doi.org/10.3390/aerospace11070567 - 10 Jul 2024
Viewed by 895
Abstract
The design of a hypersonic vehicle controller has been an active research field in the last decade, especially when the vehicle is studied as a time-varying system. A time-varying compound control method is proposed for a hypersonic vehicle controlled by the direct lateral [...] Read more.
The design of a hypersonic vehicle controller has been an active research field in the last decade, especially when the vehicle is studied as a time-varying system. A time-varying compound control method is proposed for a hypersonic vehicle controlled by the direct lateral force and the aerodynamic force. The compound control method consists of a time-varying linear quadratic regulator (LQR) control law for the aerodynamic rudder and a sliding mode control law for the lateral thrusters. When the air rudder cannot continuously produce control force and torque, the direct lateral force is added to the system. To solve the problem that LQR cannot directly obtain the analytical solution of the time-varying system, a novel approach to approximate analytical solutions using Jacobi polynomials is proposed in this paper. Finally, the stability of the time-varying compound control system is proven by the Lyapunov–Krasovskii functional (LKF). The simulation results show that the proposed compound control method is effective and can improve the fast response ability of the system. Full article
(This article belongs to the Special Issue Challenges and Innovations in Aircraft Flight Control)
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Planned Papers

The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.

Title: Autonomous Parafoil Flaring Control System for eVTOL Aircraft
Authors: Stephen Doran; Toufik Souanef; James F. Whidborne
Affiliation: Centre for Aeronautics, Cranfield University, Bedford MK43 0AL, UK
Abstract: Reducing landing kinetic energy during emergency landings is critical for minimising occupant injury in eVTOL aircraft. This study presents the development of an autonomous parafoil control system for impact point targeting and flare control. A model predictive controller (MPC) for 6-degree-of-freedom parafoil and eVTOL payload model, was designed incorporating an inner-loop flare controller for descent speed-based flare height adjustments and an outer-loop nonlinear MPC to minimize line-of-sight error. Two guidance methods were explored: a standard fixed impact point approach and an adaptive method that adjusts the target point dynamically to account for horizontal travel during flaring. The standard method outperformed the uncontrolled system in 79.64% of cases, while the adaptive method achieved success in 40.73% of scenarios, with both methods maintaining vertical landing velocities below 8 m/s in all tested cases. Controller performance degraded under higher wind speeds and large control derivative variations, with the adaptive method position error attributed to flare distance estimation inaccuracies.

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