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"Flight control systems"
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Review of dynamic soaring: technical aspects, nonlinear modeling perspectives and future directions
In this paper, we present a comprehensive and detailed review of dynamic soaring process, and in particular, its application to unmanned aerial vehicles (UAVs). We start by explaining the biological inspiration that comes from soaring birds and how researchers have tried to utilize the dynamic soaring phenomenon/maneuver and apply it to UAVs. We present and discuss the fundamentals of wind shear models in both the linear and nonlinear cases. Moreover, a comprehensive parametric characterization of the key performance parameters for the dynamic soaring maneuver is given. Numerical methods for nonlinear trajectory optimization are summarized and methodologies capable of generating rapid solutions suitable for real-time implementation, are presented. Additionally, the paper introduces mathematical modeling and procedure to generate the optimized dynamic soaring trajectory. Through this paper, a consolidated platform is built, which not only covers technical aspects of advancements made over the passage of time, but also identifies and discusses the existing challenges. These challenges which are encountered by UAVs curtail the potential utility of dynamic soaring. Integrating dynamic soaring with morphology and inclusion of nonlinear control theory in the flight control system are introduced as a possible future research directions that may overcome the existing limitations.
Journal Article
Flight mechanics modeling and analysis
\"Flight Mechanics Modelling and Analysis comprehensively covers flight mechanics and flight dynamics using a systems approach. The book focuses on applied mathematics and control theory in its discussion of flight mechanics to build a strong foundation for solving design and control problems in the areas of flight simulation and flight data analysis. The second edition has been expanded to include two new chapters and coverage of aeroservoelastic topics and engineering mechanics, presenting more concepts of flight control and aircraft parameter estimation. The book is intended for senior undergraduate aerospace students taking Aircraft Mechanics, Flight Dynamics & Controls, and Flight Mechanics courses. It will also be of interest to research students and R&D project-scientists of the same disciplines. Including end-of-chapter exercises and illustrative examples with a MATLAB® based approach, the book also includes a Solutions Manual and Figure Slides for adopting instructors. Features : covers flight mechanics, flight simulation, flight testing, flight control, and aeroservoelasticity. Features artificial neural network- and fuzzy logic-based aspects in modelling and analysis of flight mechanics systems : aircraft parameter estimation, and reconfiguration of control. Focuses on a systems-based approach. Includes two new chapters, numerical simulation examples with MATLAB® based implementations, and end-of-chapter exercises. Includes a Solutions Manual and Figure Slides for adopting instructors\"-- Provided by publisher.
Book
Simulation and analysis of stability of UAV control system based on PID control under different wind forces
The four-rotor UAV has attracted the attention of various fields and has been applied in more areas due to its advantages of low cost, high reliability and simple structure. Nowadays, more complex environment and interference factors put forward higher requirements for the accuracy and stability of the flight control system of UAV. At present, the most widely used four-rotor UAV flight control system is PID control system. This paper constructs a UAV control system based on PID algorithm to analyse and study the dynamic stability control effect of UAV under different wind impact scenarios. MATLAB is used to simulate and analyze the system, and the future development is expected according to the simulation results.
Journal Article
Simultaneous UAV having actively sweep angle morphing wing and flight control system design
Purpose
The purpose of this paper is to improve autonomous flight performance of an unmanned aerial vehicle (UAV) having actively sweep angle morphing wing using simultaneous UAV and flight control system (FCS) design.
Design/methodology/approach
An UAV is remanufactured in the ISTE Unmanned Aerial Vehicle Laboratory. Its wing sweep angle can vary actively during flight. FCS parameters and wing sweep angle are simultaneously designed to optimize autonomous flight performance index using a stochastic optimization method called as simultaneous perturbation stochastic approximation (SPSA). Results obtained are applied for flight simulations.
Findings
Using simultaneous design process of an UAV having actively sweep angle morphing wing and FCS design, autonomous flight performance index is maximized.
Research limitations/implications
Authorization of Directorate General of Civil Aviation in Turkey is crucial for real-time UAV flights.
Practical implications
Simultaneous UAV having actively sweep angle morphing wing and FCS design process is so beneficial for recovering UAV autonomous flight performance index.
Social implications
Simultaneous UAV having actively sweep angle morphing wing and FCS design process achieves confidence, high autonomous performance index and simple service demands of UAV operators.
Originality/value
Composing a novel approach to improve autonomous flight performance index (e.g. less settling and rise time, less overshoot meanwhile trajectory tracking) of an UAV and creating an original procedure carrying out simultaneous UAV having actively sweep angle morphing wing and FCS design idea.
Journal Article
Geometric control formulation and nonlinear controllability of airplane flight dynamics
Linear controllability conditions for linearized systems are not necessary. That is, there exists a class of nonlinear systems that are linearly uncontrollable but nonlinearly controllable. Geometric control theory provides useful tools for analyzing nonlinear controllability of dynamical systems. In particular, it allows for identification of the ability to generate motions along unactuated (non-intuitive) directions through specific interactions between the system dynamics and control inputs. In this work, the six-degrees-of-freedom, rigid-airplane flight dynamics is considered and formulated in a geometric control framework. Then, nonlinear controllability analysis is performed. The analytical tools of geometric control theory allowed scrutiny of the system dynamics to assess the relation between airplane configuration and controllability. Moreover, new rolling and pitching mechanisms that can be exploited at high angles of attack (e.g., stall recovery) are identified. Finally, a thrust-only flight control system is analyzed in this framework.
Journal Article
L1 Adaptive Structure-Based Nonlinear Dynamic Inversion Control for Aircraft with Center of Gravity Variations
Due to the reliance on model knowledge and the lack of compensation mechanism, Nonlinear Dynamic Inversion (NDI) control does not provide the essential robustness in the face of disturbances such as the Center of Gravity (CG) sudden change. To overcome this deficiency, a novel adaptive NDI control approach based on the L1 adaptive structure, called L1 Adaptive Nonlinear Dynamic Inversion (L1-ANDI), is presented, which can guarantee the desired dynamic performance while overcoming the influence of disturbances and uncertainties. In particular, the introduction of a low-pass filter makes the L1-ANDI control realize the decoupling of fast adaptation and robustness. Furthermore, the effect of CG variations on the aircraft is analyzed from the aerodynamic perspective, and the L1-ANDI-based flight controller is designed to eliminate the influence of the CG variations. A series of simulation results demonstrate that the designed flight controller can achieve satisfactory performance and is robust to the disturbance of CG sudden variations.
Journal Article
Autonomous flight performance maximization for slung load carrying rotary wing mini unmanned aerial vehicle
Purpose
This research study aims to minimize autonomous flight cost and maximize autonomous flight performance of a slung load carrying rotary wing mini unmanned aerial vehicle (i.e. UAV) by stochastically optimizing autonomous flight control system (AFCS) parameters. For minimizing autonomous flight cost and maximizing autonomous flight performance, a stochastic design approach is benefitted over certain parameters (i.e. gains of longitudinal PID controller of a hierarchical autopilot system) meanwhile lower and upper constraints exist on these design parameters.
Design/methodology/approach
A rotary wing mini UAV is produced in drone Laboratory of Iskenderun Technical University. This rotary wing UAV has three blades main rotor, fuselage, landing gear and tail rotor. It is also able to carry slung loads. AFCS variables (i.e. gains of longitudinal PID controller of hierarchical autopilot system) are stochastically optimized to minimize autonomous flight cost capturing rise time, settling time and overshoot during longitudinal flight and to maximize autonomous flight performance. Found outcomes are applied during composing rotary wing mini UAV autonomous flight simulations.
Findings
By using stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads over previously mentioned gains longitudinal PID controller when there are lower and upper constraints on these variables, a high autonomous performance having rotary wing mini UAV is obtained.
Research limitations/implications
Approval of Directorate General of Civil Aviation in Republic of Türkiye is essential for real-time rotary wing mini UAV autonomous flights.
Practical implications
Stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads is properly valuable for recovering autonomous flight performance cost of any rotary wing mini UAV.
Originality/value
Establishing a novel procedure for improving autonomous flight performance cost of a rotary wing mini UAV carrying slung loads and introducing a new process performing stochastic optimization of AFCS for rotary wing mini UAVs carrying slung loads meanwhile there exists upper and lower bounds on design variables.
Journal Article
Flight control system design of UAV with wing incidence angle simultaneously and stochastically varied
Purpose
This study aims to simultaneously and stochastically maximize autonomous flight performance of a variable wing incidence angle having an unmanned aerial vehicle (UAV) and its flight control system (FCS) design.
Design/methodology/approach
A small UAV is produced in Iskenderun Technical University Drone Laboratory. Its wing incidence angle is able to change before UAV flight. FCS parameters and wing incidence angle are simultaneously and stochastically designed to maximize autonomous flight performance using an optimization method named simultaneous perturbation stochastic approximation. Obtained results are also benefitted during UAV flight simulations.
Findings
Applying simultaneous and stochastic design approach for a UAV having passively morphing wing incidence angle and its flight control system, autonomous flight performance is maximized.
Research limitations/implications
Permission of the Directorate General of Civil Aviation in Turkish Republic is necessary for real-time flights.
Practical implications
Simultaneous stochastic variable wing incidence angle having UAV and its flight control system design approach is so useful for maximizing UAV autonomous flight performance.
Social implications
Simultaneous stochastic variable wing incidence angle having UAV and its flight control system design methodology succeeds confidence, excellent autonomous performance index and practical service interests of UAV users.
Originality/value
Creating an innovative method to recover autonomous flight performance of a UAV and generating an innovative procedure carrying out simultaneous stochastic variable wing incidence angle having UAV and its flight control system design idea.
Journal Article
EVTOL Flight Control System Safety: An Example of Application Using MBSA
Electrical Vertical Takeoff and Landing (eVTOL) vehicles hold great promises for revolutionizing urban mobility. Their emergences as a transformative transportation technology has led multiple Original Equipment Manufacturers (OEM) competing for market share, with important variety of technical solutions, all necessitating to demonstrate the compliance to safety requirements and regulations. Model Based Safety Analysis (MBSA), newly introduced in ARP4761A and based on compositional and modular representation of failure propagation paths within one system, provides a unique opportunity to increase efficiency by maximizing the possible reuse of safety analyses elements across multiple architectures (“product line” philosophy). Generic library of safety models for elements of variant architectures can be efficiently constructed using MBSA techniques that can then support safety analyses on variant architectures or architectures trade-off. This approach can facilitate a safety process that enable customized safety solutions without complete re-engineering of the safety analyses for each architecture.
The purpose of this paper is to present and illustrate one work performed on the definition of a safe Flight Control System for eVTOL, leveraging the capacity of a MBSA based approach to ensure high level of agility and rapid responsiveness. The first sections will present the need, the MBSA approach and a general modelling process that can be used to employ MBSA methodology. Then, an example of eVTOL Flight Control System architecture and safety analyses will be detailed to picture how MBSA, coupled with a generic component library, can provide an easily adaptable safety solution. Finally, we discuss some possible next steps and future work identified in order to certify a solution thanks to this method.
Journal Article