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Journal articles on the topic 'Flight dynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Philip, Scott Blackwelder. "UAV Flight Dynamics." International Journal of Aeronautical Science & Aerospace Research 2, no. 6 (2015): 81–85. https://doi.org/10.19070/2470-4415-150009.

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In the interest of promoting the integration of hybrid-electric power train into the aviation industry, research is being conducted by North Carolina State University to establish the feasibility of electrified power train in a small scale unmanned aerial vehicle (UAV). To accomplish this, it is first necessary to understand dynamics of the system to calculate the required power associated with each portions of the aircraft’s mission. Though research that has been conducted in the past based power required on published governing equations. However, in the interest of under

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2

Tian, Xian Ke, Shuo Tang, and Qiang Jun Zhu. "Flight Dynamics Modeling and Analysis of Flexible Hypersonic Flight Vehicles." Applied Mechanics and Materials 275-277 (January 2013): 513–17. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.513.

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Facing the difficulty of flight dynamics modeling about flexible hypersonic flight vehicles, from view on the Lagrange’s equations based on dynamic first principle, this paper firstly developed kinetic energy and flexibility potential energy of the vehicle, then achieved concise flight dynamics equations by quasi-coordinates which could fully include coupling characteristics of flight dynamics, and lastly made necessary analysis about the equations. The result of study illustrates that flight dynamics equations of flexible hypersonic flight vehicles based on quasi-coordinates can satisfy the r

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Laurence III, Roger J., and Brian M. Argrow. "Numerical Calibration of a Low-Speed sUAS Flush Air Data System." Journal of Atmospheric and Oceanic Technology 36, no. 8 (2019): 1577–90. http://dx.doi.org/10.1175/jtech-d-18-0208.1.

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AbstractA method using computational fluid dynamics to numerically calibrate a flush air data system is presented. A small unmanned aircraft system (sUAS) has been equipped with a flush air data system and experimentally tested. The flush air data system uses computational fluid dynamics to train neural networks and is validated using the in-flight data that were previously collected. Results of the flight validation are presented, along with ways to improve the accuracy of the system. Several different calibration approaches are presented and compared with each other. The best-case results wi

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4

Cook, M. V. "Dynamics of Flight." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 2 (1997): 129–30. http://dx.doi.org/10.1177/095441009721100202.

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5

Bai, Ye, and Srikanth Gururajan. "Evaluation of a Baseline Controller for Autonomous “Figure-8” Flights of a Morphing Geometry Quadcopter: Flight Performance." Drones 3, no. 3 (2019): 70. http://dx.doi.org/10.3390/drones3030070.

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This article describes the design, fabrication, and flight test evaluation of a morphing geometry quadcopter capable of changing its intersection angle in-flight. The experiments were conducted at the Aircraft Computational and Resource Aware Fault Tolerance (AirCRAFT) Lab, Parks College of Engineering, Aviation and Technology at Saint Louis University, St. Louis, MO. The flight test matrix included flights in a “Figure-8” trajectory in two different morphing configurations (21° and 27°), as well as the nominal geometry configuration, two different flight velocities (1.5 m/s and 2.5 m/s), two

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Lu, Ke, Chunsheng Liu, Chunhua Li, and Renliang Chen. "Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft." International Journal of Aerospace Engineering 2019 (August 14, 2019): 1–15. http://dx.doi.org/10.1155/2019/5737212.

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The tilt-rotor aircraft has often been proposed as a means to increase the maximum speed of the conventional helicopter. The tilt-rotor aircraft consists of three primary flight modes that are the helicopter flight mode in low forward speed flight, airplane flight mode in high forward speed flight, and conversion flight mode. The aim of this paper is to develop a nonlinear flight dynamics mathematical modeling method of tilt-rotor aircraft and investigate the dynamic stability characteristics of tilt-rotor aircraft. First, a nonlinear tilt-rotor aircraft flight dynamics model is developed. The

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Ibrahim, Noureldein A., Mohamed Y. Zakaria, and Ashraf M. Kamal. "Simulation of tilt-rotor UAV flight dynamics in horizontal flight." Journal of Physics: Conference Series 2616, no. 1 (2023): 012006. http://dx.doi.org/10.1088/1742-6596/2616/1/012006.

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Abstract Tilt-rotor unmanned aerial vehicles (UAV) have gained significant importance in the aeronautical industry due to their ability to transition between vertical and horizontal flight. One of the important steps in the development of such UAVs is to assess their performance and stability characteristics. Simulation of flight dynamics is an essential tool that enables the designers to test and optimize the flight characteristics of these UAVs. This paper presents a complete procedure for developing a 6-degree-of-freedom flight dynamics model of a tilt-rotor UAV in fixed-wing mode using a p

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SUZUKI, Kosuke, Masaya KOUJI, and Masato YOSHINO. "Flight dynamics in forward flights of cabbage white butterfly." Journal of Fluid Science and Technology 18, no. 1 (2023): JFST0011. http://dx.doi.org/10.1299/jfst.2023jfst0011.

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9

Smith, Kevin M. "Aerodynamic Essentials for Crew Station Design Teams." International Journal of Aviation Systems, Operations and Training 2, no. 1 (2015): 1–20. http://dx.doi.org/10.4018/ijasot.2015010101.

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Increasing emphasis is being placed on various aspects of flight dynamics in aviation. This includes such things as upset and stall recovery, wind shear recovery, and approach instability recovery. Operators, safety analysts, and designers are now actively discussing “dynamic situation awareness.” Because of this, there is the need to understand the dynamic nature of flight operations, and incorporate this understanding in state-of-the-art flight deck systems and training programs. This article offers designers, operators, and trainers a quick review of some of the most important aspects of fl

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Shamliev, Alexander, Peter Mitrouchev, and Maya Dimitrova. "Atmospheric Boundary Layer Dynamics Evaluation Using Piezo-Resistive Technology for Unpowered Areal Vehicles." International Journal of Cyber-Physical Systems 2, no. 1 (2020): 1–19. http://dx.doi.org/10.4018/ijcps.2020010101.

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The paper presents a method for real-time observing of the convectional processes in the atmosphere boundary layer. The essence of the method is in providing real-time measurement of temperature, humidity, and pressure during the flight of a glider (soaring flight). Based on these measurements, a real-time evaluation of the atmosphere dynamics is presented. Measurements are taken during soaring flight of the glider and during the flight of a remotely controlled quadrocopter. Additionally, a method for atmosphere thermal identification by the measured parameters is introduced. The main applicat

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11

Valasek, John. "Review of Flight Dynamics." Journal of Guidance, Control, and Dynamics 30, no. 6 (2007): 1836–38. http://dx.doi.org/10.2514/1.34515.

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Montalvo, Carlos, and Mark Costello. "Meta Aircraft Flight Dynamics." Journal of Aircraft 52, no. 1 (2015): 107–15. http://dx.doi.org/10.2514/1.c032634.

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Hodgkinson, John. "Review of "Flight Dynamics"." AIAA Journal 43, no. 5 (2005): 1149–50. http://dx.doi.org/10.2514/1.17189.

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14

Macmillen, F. B. J. "Nonlinear flight dynamics analysis." Philosophical Transactions of the Royal Society of London. Series A: Mathematical, Physical and Engineering Sciences 356, no. 1745 (1998): 2167–80. http://dx.doi.org/10.1098/rsta.1998.0268.

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THOMAS, ADRIAN L. R., and GRAHAM K. TAYLOR. "Animal Flight Dynamics I. Stability in Gliding Flight." Journal of Theoretical Biology 212, no. 3 (2001): 399–424. http://dx.doi.org/10.1006/jtbi.2001.2387.

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Verma, Isha. "The Computational Study on the Aerodynamics Behaviour of the Hypersonic Vehicles." International Journal for Research in Applied Science and Engineering Technology 13, no. 3 (2025): 197–205. https://doi.org/10.22214/ijraset.2025.67221.

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Current air-breathing hypersonic flight( AHF) technology programs are primarily concentrated on developing flight test vehicles and functional prototypes that incorporate airframe- integrated scramjet machines. A pivotal aspect of making AHF feasible and effective falsehoods in the design of its control systems. still, the unique dynamic characteristics of air- breathing hypersonic flight vehicles( AHFVs), combined with the aerodynamic complications at hypersonic pets, pose significant challenges for system modeling and regulator development. also, the expansive speed variations during operati

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Kassem, Ayman Hamdy. "Efficient Neural Network Modeling for Flight and Space Dynamics Simulation." International Journal of Aerospace Engineering 2011 (2011): 1–7. http://dx.doi.org/10.1155/2011/247294.

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This paper represents an efficient technique for neural network modeling of flight and space dynamics simulation. The technique will free the neural network designer from guessing the size and structure for the required neural network model and will help to minimize the number of neurons. For linear flight/space dynamics systems, the technique can find the network weights and biases directly by solving a system of linear equations without the need for training. Nonlinear flight dynamic systems can be easily modeled by training its linearized models keeping the same network structure. The train

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18

Yu, Xue Mei, An Ping Zhao, and Xue Li. "Helicopter Aerodynamic Parameter Identification via Flight Dynamics." Applied Mechanics and Materials 327 (June 2013): 246–49. http://dx.doi.org/10.4028/www.scientific.net/amm.327.246.

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A method which can process flight test data by integrating parameter identification and non-dimensional flight dynamic model was proposed to acquire the effective aerodynamic parameters of a helicopter. First of all, a non-dimensional mathematic model considering flight dynamics was deduced for a helicopter in state of level flight, and some important parameters including aerodynamic and correctional were developed. Next, taking helicopter Z-9× for example, the least squares method was adopted to identify these parameters based actual flight test data. Lastly, the identification method was pro

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Meng, Xiaowei, Ming Xue, Honglin Zhang, and Yu Zhu. "Analysis of helicopter dynamic stability based on parameter identification method." Journal of Physics: Conference Series 2965, no. 1 (2025): 012027. https://doi.org/10.1088/1742-6596/2965/1/012027.

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Abstract To analyze the dynamic stability of helicopters in real flight environments and understand the influence of key flight state parameters on dynamic stability, the six-degree-of-freedom equations of helicopter flight dynamics and the small disturbance principle are utilized. The flight test is used to obtain the variations in motion parameters after the helicopter is disturbed. A parameter identification method is then employed to solve the motion equations, yielding the oscillatory mode parameters that characterize the helicopter’s dynamic stability. Sensitivity analysis of the dynamic

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20

Yin, Xinfan, Bowen Nie, Chang Wang, et al. "Flight Dynamics Modeling and Verification for a Novel Compound Rotorcraft Considering Rotor/Propeller/Fuselage Aerodynamic Interference." Drones 9, no. 5 (2025): 329. https://doi.org/10.3390/drones9050329.

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The flight controllability and safety of unmanned compound rotorcraft are closely related to their aerodynamic characteristics. During forward flight, complex aerodynamic interference effects arise among the rotor, propeller, wing, fuselage, and horizontal–vertical tail. These interactions change dramatically with variations in forward speed, which may have a substantial impact on flight performance. This paper investigates aerodynamic interference related to the rotor, propeller, and fuselage of a sample unmanned compound rotorcraft with a novel configuration. On this basis, a flight dynamics

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Fruncillo, Felice, Luigi Federico, Marco Cicala, and Roberto Citarella. "Development and Validation of an Aeropropulsive and Aeroacoustic Simulation Model of a Quadcopter Drone." Drones 6, no. 6 (2022): 143. http://dx.doi.org/10.3390/drones6060143.

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In the present work a dynamic simulation model for a quadcopter drone is developed and validated through experimental flight data. The aerodynamics of the rotors is modeled with the blade element theory combined with the Peters and He dynamic wake model, using an appropriate number of states. The aerodynamic forces and moments thus calculated feed the dynamic equations of a drone and an aeroacoustics model, to obtain an estimate of the noise generated during the flight. Loading and thickness noise are calculated as a time domain solution of the wave equation (Farassat 1A formulation), with mob

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KAWAMURA, Kohei, Yosuke UENO, and Yoshiaki NAKAMURA. "Flight Simulation of Taketombo Based on Computational Fluid Dynamics and Computational Flight Dynamics." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 56, no. 654 (2008): 324–30. http://dx.doi.org/10.2322/jjsass.56.324.

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23

Zhang, Xiaohui, Yuhui Wang, Xingkai Feng, and Yunxin Li. "Dynamic damage analysis of airfoil flutter for a generic hypersonic flight vehicle." Journal of Vibration and Control 25, no. 18 (2019): 2423–34. http://dx.doi.org/10.1177/1077546319856142.

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The main aim of this paper is to establish the relationship between the airfoil flutter with the flight dynamics of a generic hypersonic flight vehicle (HFV) and analyze the airfoil damage variation during the airfoil flutter. Based on the motion equations of the two degrees of freedom airfoil model and the longitudinal dynamics of the HFV, an airfoil dynamic model is established. By using a coupling equation, the relationship between airfoil flutter and the flight dynamics is estimated. According to the stress–strain ([Formula: see text]) model and the strain–fatigue damage ([Formula: see tex

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Wang, Yanjun, Hongfeng Zheng, Fan Wu, Jun Chen, and Mark Hansen. "A Comparative Study on Flight Delay Networks of the USA and China." Journal of Advanced Transportation 2020 (June 2, 2020): 1–11. http://dx.doi.org/10.1155/2020/1369591.

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Recent studies have characterized the structures of air transport network in different countries and regions using complex network metrics. These studies coincided with the trend of increasingly available large empirical flight datasets that enable researchers to investigate the dynamics of the system, such as the propagation of flight delay. However, linking network structure with network dynamics remains a challenging task. In this paper, we proposed a method to construct flight delay networks from operational data. We provided a detailed comparison of the key structural properties of the fl

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Mazhar, Farrukh, Mohammad A. Choudhry, and Muhammad Shehryar. "Nonlinear auto-regressive neural network for mathematical modelling of an airship using experimental data." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 7 (2018): 2549–69. http://dx.doi.org/10.1177/0954410018783131.

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Autonomous flight of an aerial vehicle requires a sufficiently accurate mathematical model, which can capture system dynamics in the presence of external disturbances. Artificial neural network is known for ideal in capturing systems behaviour, where little knowledge about vehicle dynamics is available. In this paper, we explored this potential of artificial neural network for characterizing nonlinear dynamics of an unmanned airship. The flight experimentation data for an outdoor experimental airship are acquired through a series of pre-determined flight tests. The experimental data are subjec

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Yanpeng Wu, Xinmin Wang, and Ying Wu. "Flight Dynamics and Flight Envelope Estimation for Damaged Aircraft." International Journal of Digital Content Technology and its Applications 7, no. 7 (2013): 1062–69. http://dx.doi.org/10.4156/jdcta.vol7.issue7.126.

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Taylor, Graham. "Flight muscles and flight dynamics: towards an integrative framework." Animal Biology 55, no. 1 (2005): 81–99. http://dx.doi.org/10.1163/1570756053276871.

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AbstractHere a conceptual framework is provided for analysing the role of the flight muscles in stability and control. Stability usually refers to the tendency of a system to return to a characteristic reference state, whether static, as in gliding, or oscillatory, as in flapping. Asymptotic Lyapunov stability and asymptotic orbital stability as formal definitions of gliding and flapping flight stability, respectively, are discussed and a limit cycle control analogy for flapping flight control proposed. Stability can arise inherently or through correctional control. Conceptually, inherent stab

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TAYLOR, G. K., and A. L. R. THOMAS. "Animal Flight Dynamics II. Longitudinal Stability in Flapping Flight." Journal of Theoretical Biology 214, no. 3 (2002): 351–70. http://dx.doi.org/10.1006/jtbi.2001.2470.

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29

Oruc, Ilker, Joseph F. Horn, Jeremy Shipman, and Susan Polsky. "Towards real-time pilot-in-the-loop CFD simulations of helicopter/ship dynamic interface." International Journal of Modeling, Simulation, and Scientific Computing 08, no. 04 (2017): 1743005. http://dx.doi.org/10.1142/s179396231743005x.

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This study presents the development of computationally efficient coupling of Navier–Stokes Computational Fluid Dynamics (CFD) with a helicopter flight dynamics model with the ultimate goal of real-time simulation of airwake effects in the helicopter/ship Dynamic Interface (DI). The flight dynamics model is free to move within a computational domain, where the main rotor forces are converted to source terms in the momentum equations of the CFD solution using an actuator disk model. Simultaneously, the CFD solver calculates induced velocities that are fed back to the simulation and affect the ae

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Elhesasy, Mohamed, Rashed Khader, Tarek N. Dief, Mohamed M. Kamra, Mohamed Okasha, and Saeed K. Alnuaimi. "Experimental Identification of the Translational Dynamics of a Novel Two-Layer Octocopter." Drones 8, no. 7 (2024): 286. http://dx.doi.org/10.3390/drones8070286.

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This paper proposes a systematic approach for identifying the translational dynamics of a novel two-layer octocopter. Initially, we derive the non-linear theoretical dynamic model of the conventional octocopter using the Newton–Euler formulation, aimed at obtaining a simplified model suitable for tuning PID gains necessary for controller implementation. Following this, a controller is designed and tested in the Matlab/Simulink environment to ensure stable flight performance of the octocopter. Subsequently, the novel octocopter prototype is developed, fabricated, and assembled, followed by a se

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Sousa, Marcelo Santiago, Pedro Paglione, Roberto Gil Annes Silva, Flavio Luiz Cardoso-Ribeiro, and Sebastião Simões Cunha. "Mathematical model of one flexible transport category aircraft." Aircraft Engineering and Aerospace Technology 89, no. 3 (2017): 384–96. http://dx.doi.org/10.1108/aeat-12-2013-0230.

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Purpose The purpose of this paper is to present a mathematical model of one very flexible transport category airplane whose structural dynamics was modeled with the strain-based formulation. This model can be used for the analysis of couplings between the flight dynamics and structural dynamics. Design/methodology/approach The model was developed with the use of Hamiltonian mechanics and strain-based formulation. Nonlinear flight dynamics, nonlinear structural dynamics and inertial couplings are considered. Findings The mathematical model allows the analysis of effects of high structural defor

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Ogunwa, Titilayo, Ermira Abdullah, and Javaan Chahl. "Modeling and Control of an Articulated Multibody Aircraft." Applied Sciences 12, no. 3 (2022): 1162. http://dx.doi.org/10.3390/app12031162.

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Insects use dynamic articulation and actuation of their abdomen and other appendages to augment aerodynamic flight control. These dynamic phenomena in flight serve many purposes, including maintaining balance, enhancing stability, and extending maneuverability. The behaviors have been observed and measured by biologists but have not been well modeled in a flight dynamics framework. Biological appendages are generally comparatively large, actuated in rotation, and serve multiple biological functions. Technological moving masses for flight control have tended to be compact, translational, intern

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Letzgus, Johannes, Manuel Keßler, and Ewald Krämer. "Simulation of Dynamic Stall on an Elastic Rotor in High-Speed Turn Flight." Journal of the American Helicopter Society 65, no. 2 (2020): 1–12. http://dx.doi.org/10.4050/jahs.65.022002.

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A highly loaded, high-speed turn flight of Airbus Helicopters' Bluecopter demonstrator helicopter is simulated to investigate dynamic stall using a loose computational fluid dynamics/structural dynamics (CFD/CSD) coupling of the flow solver FLOWer and the rotorcraft comprehensive code CAMRAD II. The rotor aerodynamics is computed using a high-fidelity delayed detached-eddy simulation (DDES). A three-degree-of-freedom trim of an isolated rotor is performed, yielding main-rotor control angles that agree well with the flight-test measurements. The flow field in this flight condition is found to b

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Özcan, Abdurrahim Bilal, and Elbrus Caferov. "Frequency Domain Analysis of F-16 Aircraft in a Variety of Flight Conditions." Volume 03 Issue 01 vm03, is01 (2022): 21–34. http://dx.doi.org/10.23890/10.23890/ijast.vm03is01.0103.

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Examining the flight quality of an aircraft to ensure the stability of the aircraft, increase maneuverability, and make the aircraft easier to control by the pilot necessitates an examination of the natural stability of the system. Within the scope of the paper, the frequency domain response of the F-16 aircraft dynamics is analyzed using Simulink models considering two different flight regimes because the frequency-domain methods have many distinct and important advantages over time-domain methods. Aerodynamic, propulsive, and atmospheric databases are used to create the nonlinear model. The

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Özcan, Abdurrahim Bilal, and Elbrus Caferov. "Frequency Domain Analysis of F-16 Aircraft in a Variety of Flight Conditions." Volume 03 Issue 01 vm03, is01 (2022): 21–34. http://dx.doi.org/10.23890/ijast.vm03is01.0103.

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Examining the flight quality of an aircraft to ensure the stability of the aircraft, increase maneuverability, and make the aircraft easier to control by the pilot necessitates an examination of the natural stability of the system. Within the scope of the paper, the frequency domain response of the F-16 aircraft dynamics is analyzed using Simulink models considering two different flight regimes because the frequency-domain methods have many distinct and important advantages over time-domain methods. Aerodynamic, propulsive, and atmospheric databases are used to create the nonlinear model. The

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36

Waszak, Martin R., and David K. Schmidt. "Flight dynamics of aeroelastic vehicles." Journal of Aircraft 25, no. 6 (1988): 563–71. http://dx.doi.org/10.2514/3.45623.

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Донской, А. Д., С. Е. Сабо, and М. А. Щиканов. "Dynamics of cruise missile flight." Informacionno-technologicheskij vestnik, no. 1(27) (March 15, 2021): 30–40. http://dx.doi.org/10.21499/2409-1650-2021-27-1-30-40.

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Рассматривается система уравнений динамики полета крылатой ракеты с учетом всех факторов воздействия на ее движение в атмосфере. A system of equations for the dynamics of a cruise missile flight is considered, taking into account all factors affecting its movement in the atmosphere.

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Bowers, Al. "Review of Computational Flight Dynamics." Journal of Guidance, Control, and Dynamics 22, no. 1 (1999): 191–92. http://dx.doi.org/10.2514/2.4365.

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O'Brien, Robert E. "Semigroup dynamics for flight vectors." International Journal of Dynamical Systems and Differential Equations 10, no. 4 (2020): 358. http://dx.doi.org/10.1504/ijdsde.2020.10031335.

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O', Robert E., and N. A. Brien. "Semigroup dynamics for flight vectors." International Journal of Dynamical Systems and Differential Equations 10, no. 4 (2020): 358. http://dx.doi.org/10.1504/ijdsde.2020.109108.

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Goetzendorf-Grabowski, Tomasz. "Flight dynamics of unconventional configurations." Progress in Aerospace Sciences 137 (February 2023): 100885. http://dx.doi.org/10.1016/j.paerosci.2023.100885.

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Horn, Joseph. "Non-Linear Dynamic Inversion Control Design for Rotorcraft." Aerospace 6, no. 3 (2019): 38. http://dx.doi.org/10.3390/aerospace6030038.

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Flight control design for rotorcraft is challenging due to high-order dynamics, cross-coupling effects, and inherent instability of the flight dynamics. Dynamic inversion design offers a desirable solution to rotorcraft flight control as it effectively decouples the plant model and effectively handles non-linearity. However, the method has limitations for rotorcraft due to the requirement for full-state feedback and issues with non-minimum phase zeros. A control design study is performed using dynamic inversion with reduced order models of the rotorcraft dynamics, which alleviates the full-sta

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Hang, Yan Fang, Jing Lu, and Ying Jun Hu. "Modeling and Control of a Micro Flapping Wing Rotor." Applied Mechanics and Materials 635-637 (September 2014): 1360–63. http://dx.doi.org/10.4028/www.scientific.net/amm.635-637.1360.

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The system of Micro Flapping-wing Rotor to achieve the flapping and rotation motions is first introduced briefly. Then the system dynamic model which includes the flapping rotary flight aerodynamics at a low Reynolds number regime, the body dynamics, the electromagnetic actuator and the control surface is described. This model and system simulation in the preliminary design phase may provide the opportunity for designers to make fundamental design decisions early to improve the flight performance. Also, the simulator is used to study open loop flight dynamics and test a periodic proportional o

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Hadytama, Muhammad Rafi, and Rianto A. Sasongko. "Dynamics Simulation and Analysis of Transition Stage of Tilt-Rotor Aircraft." Applied Mechanics and Materials 842 (June 2016): 251–58. http://dx.doi.org/10.4028/www.scientific.net/amm.842.251.

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This paper presents the flight dynamics simulation and analysis of a tilt-rotor vertical takeoff and landing (VTOL) aircraft on transition phase, that is conversion from vertical or hover to horizontal or level flight and vice versa. The model of the aircraft is derived from simplified equations of motion comprising the forces and moments working on the aircraft in the airplane's longitudinal plane of motion. This study focuses on the problem of the airplane's dynamic response during conversion phase, which gives an understanding about the flight characteristics of the vehicle. The understandi

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Cheng, Lingquan, Yiyang Li, Jiayi Yuan, Jianliang Ai, and Yiqun Dong. "L1 Adaptive Control Based on Dynamic Inversion for Morphing Aircraft." Aerospace 10, no. 9 (2023): 786. http://dx.doi.org/10.3390/aerospace10090786.

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Morphing aircraft are able to keep optimal performance in diverse flight conditions. However, the change in geometry always leads to challenges in the design of flight controllers. In this paper, a new method for designing a flight controller for variable-sweep morphing aircraft is presented—dynamic inversion combined with L1 adaptive control. Firstly, the dynamics of the vehicle is analyzed and a six degrees of freedom (6DOF) nonlinear dynamics model based on multibody dynamics theory is established. Secondly, nonlinear dynamic inversion (NDI) and incremental nonlinear dynamic inversion (INDI

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Mohammed, Tariq O., Xiang Jin Wu, and Dao Chun Li. "Nonlinear Simulation of Aircraft Longitudinal Flight Dynamics." Applied Mechanics and Materials 444-445 (October 2013): 753–58. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.753.

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The purpose of this paper is to simulate flight path of Boeing-747 for longitudinal motion at selected flight conditions using 6 DoF (Degrees of freedom) nonlinear equations with MATLAB and SIMULINK. The equations are solved to compute the flight path within 100 seconds of Boeing 747 at three flight conditions, for cruise flight with different Mach numbers at same altitudes, and then Mach number at high altitude with MATLAB programming (ode45). Simulation results for different conditions are presented and analyzed.

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Ishola, Ademayowa A., James F. Whidborne, and Gilbert Tang. "An Aircraft-Manipulator System for Virtual Flight Testing of Longitudinal Flight Dynamics." Robotics 13, no. 12 (2024): 179. https://doi.org/10.3390/robotics13120179.

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A virtual flight test is the process of flying an aircraft model inside a wind tunnel in a manner that replicates free-flight. In this paper, a 3-DOF aircraft-manipulator system is proposed that can be used for longitudinal dynamics virtual flight tests. The system consists of a two rotational degrees-of-freedom manipulator arm with an aircraft wind tunnel model attached to the third joint. This aircraft-manipulator system is constrained to operate for only the longitudinal motion of the aircraft. Thus, the manipulator controls the surge and heave of the aircraft whilst the pitch is free to ro

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Tong, Shengxiang, Zhiwei Shi, Tao Yun, and Yizhang Dong. "Longitudinal flight dynamics modeling and a flight stability analysis of a monocopter." AIP Advances 12, no. 11 (2022): 115322. http://dx.doi.org/10.1063/5.0130626.

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A monocopter, which is a biology-inspired aircraft based on the samara, has been proved to have passive flight stability. However, due to the asymmetry of its configurations and the constant rotation during flight, its flight dynamics equation is complex. In this paper, the longitudinal stability of a monocopter is systematically analyzed. The longitudinal motion of the monocopter is used as the main research object in this paper. By transforming the body axis coordinate frame to the semi-body axis coordinate frame, its longitudinal dynamics equation is greatly simplified. Then, a fourth-order

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Raissi, K., M. Mani, H. Ghaffari, and A. Nobari. "Analysis of a reversible flight control system response to atmospheric turbulence." Aeronautical Journal 112, no. 1128 (2008): 93–100. http://dx.doi.org/10.1017/s0001924000002025.

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Abstract A mathematical model was developed for the reversible longitudinal control system of a regional commuter aircraft using the available geometry, mass property and kinematics. The model was incorporated into a general multi-body dynamics code and validated using existing manufacturer’s data as well as recorded data from several flights. Analysis of the flight data revealed light atmosphere turbulence level. To investigate the effect of higher turbulence intensity on the reversible flight control system, a sever turbulence level was generated using Von Karman model for the same flight le

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Bhatti, Muhammad Yousaf, Sang-Gil Lee, and Jae-Hung Han. "Dynamic Stability and Flight Control of Biomimetic Flapping-Wing Micro Air Vehicle." Aerospace 8, no. 12 (2021): 362. http://dx.doi.org/10.3390/aerospace8120362.

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This paper proposes an approach to analyze the dynamic stability and develop trajectory-tracking controllers for flapping-wing micro air vehicle (FWMAV). A multibody dynamics simulation framework coupled with a modified quasi-steady aerodynamic model was implemented for stability analysis, which was appended with flight control block for accomplishing various flight objectives. A gradient-based trim search algorithm was employed to obtain the trim conditions by solving the fully coupled nonlinear equations of motion at various flight speeds. Eigenmode analysis showed instability that grew with

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