Relevant bibliographies by topics / Helicopter dynamic systems

Academic literature on the topic 'Helicopter dynamic systems'

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Published: 14 March 2023

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Journal articles on the topic "Helicopter dynamic systems"

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Khalesi, Mohammad Hossein, Hassan Salarieh, and Mahmoud Saadat Foumani. "System identification and robust attitude control of an unmanned helicopter using novel low-cost flight control system." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 234, no. 5 (August 27, 2019): 634–45. http://dx.doi.org/10.1177/0959651819869718.

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In recent years, unmanned aerial systems have attracted great attention due to the electronic systems technology advancements. Among these vehicles, unmanned helicopters are more important because of their special abilities and superior performance. The complex nonlinear dynamic system (caused by main rotor flapping dynamics coupled with the rigid body rotational motion) and considerable effects of ambient disturbance make their utilization hard in actual missions. Attitude dynamics have the main role in helicopter stabilization, so implementing proper control system for attitude is an important issue for unmanned helicopter hovering and trajectory tracking performance. Besides this, experimental utilization of low-cost flight control system for unmanned helicopters is still a challenging task. In this article, dynamic modeling, system identification, and robust control system implementation of roll and pitch dynamics of an unmanned helicopter is performed. A TRex-600E radio-controlled helicopter is equipped with a novel low-cost flight control system designed and constructed based on Raspberry Pi Linux-based microcomputer. Using Raspberry Pi makes this platform simpler to utilize and more time and cost-effective than similar platforms used before. The experiments are performed on a 5-degree-of-freedom testbed. The robust control system is designed based on [Formula: see text] method and is evaluated in real flight tests. The experiment results show that the proposed platform has the ability to successfully control the roll and pitch dynamics of the unmanned helicopter.
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Fahimi, Farbod. "Full formation control for autonomous helicopter groups." Robotica 26, no. 2 (March 2008): 143–56. http://dx.doi.org/10.1017/s0263574707003670.

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SUMMARYThis paper reports the design of sliding-mode control laws for controlling multiple small-sized autonomous helicopters in arbitrary formations. Two control schemes, which are required for defining arbitrary three-dimensional formation meshes, are discussed. In the presented leader–follower formation control schemes, each helicopter only needs to receive motion information from at most two neighboring helicopters. A nonlinear six-degree-of-freedom dynamic model has been used for each helicopter. Four control inputs, the main and the tail rotor thrusts, and the roll and pitch moments, are assumed. Parameter uncertainty in the dynamic model and wind disturbance are considered in designing the controllers. The effectiveness and robustness of these control laws in the presence of parameter uncertainty in the dynamic model and wind disturbances are demonstrated by computer simulations.
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Abu Zarim, Mohamad Abu Ubaidah Amir, and Marja Azlima Omar. "Dynamic Mechanics of Rigid Helicopter Systems During Ditching." Transactions on Maritime Science 10, no. 2 (October 21, 2021): 439–47. http://dx.doi.org/10.7225/toms.v10.n02.013.

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Aircraft and helicopter often fly above open waters and thus have to observe regulations to ensure safe water landing under emergency conditions. This practice is also referred to as ditching - one of several types of slamming problems that are under review by the current regulations of the Federal Aviation Administration (FAA) and the European Aviation Safety Agency (EASA). Ditching is related to the controlled landing on water, with distinctive features such as hydrodynamic slamming loads, complex hydromechanics at tremendous forward speeds, as well as the interaction of multiphase fluid dynamics (air, water, and vapor). This paper presents the knowledge on system mechanics during helicopter ditching. The discussion begins with the fundamental kinetics of the rigid body, and then delves into dynamic relations to describe the effect of forces on motions. In the end, the paper discusses several relevant theories to further contribute to the understanding of the problem of impact.
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Liu, Jianbo, Rongqiang Guan, Yongming Yao, Hui Wang, and Linqiang Hu. "A Novel Comprehensive Kinematic and Inverse Dynamic Model for the Flybar-Less Swashplate Mechanism: Application on a Small-Scale Unmanned Helicopter." Symmetry 12, no. 11 (November 9, 2020): 1849. http://dx.doi.org/10.3390/sym12111849.

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In this paper, we propose a novel kinematic and inverse dynamic model for the flybar-less (FBL) swashplate mechanism of a small-scale unmanned helicopter. The swashplate mechanism is an essential configuration of helicopter flight control systems. It is a complex, multi-loop chain mechanism that controls the main rotor. In recent years, the demand for compact swashplate designs has increased owing to the development of small-scale helicopters. The swashplate mechanism proposed in this paper is the latest architectures used for hingeless rotors without a Bell-Hiller mixer. Firstly, the kinematic analysis is derived from the parallel manipulators concepts. Then, based on the principle of virtual work, a methodology for deriving a closed-form dynamic equation of the FBL swashplate mechanism is developed. Finally, the correctness and efficiency of the presented analytical model are demonstrated by numerical examples and the influence factors of the loads acted on actuators are discussed.
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Gildish, Eli, Michael Grebshtein, Yehudit Aperstein, Alex Kushnirski, and Igor Makienko. "Helicopter Bolt Loosening Monitoring using Vibrations and Machine Learning." PHM Society European Conference 7, no. 1 (June 29, 2022): 146–55. http://dx.doi.org/10.36001/phme.2022.v7i1.3322.

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The existing helicopter Health and Usage Management Systems (HUMS) collect and process flight operational parameters and sensors data such as vibrations to provide health monitoring of the helicopter dynamic assemblies and engines. So far, structure-related mechanical faults, such as looseness in bolted structures, have not been addressed by vibration-based condition monitoring in existing HUMS systems. Bolt loosening was identified as a potential risk to flight safety demanding periodical visual monitoring, and increased maintenance and repair expenses. Its automatic identification in helicopters by using vibration measurements is challenging due to the limited number of known events and the presence of high-energy vibrations originating in rotating parts, which shadow the low-level signals generated by the bolt loosening. New developed bolt loosening monitoring approach was tested on HUMS vibrations data recorded from the IAF AH-64 Apache helicopters fleet. ML-based unsupervised anomaly detection was utilized in order to address the limited number of faulty cases. The predictive power of health features was significantly improved by applying the Harmonic filtering differentiating between the high-energy vibrations generated by rotating parts compared with the low-energy structural vibrations. Different unsupervised anomaly detection techniques were examined on the dataset. The experimental results demonstrate that the developed approach enable successful bolt loosening monitoring in helicopters and can potentially be used in other health monitoring applications.
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Ma, Rui, Li Ding, and Hongtao Wu. "Dynamic Decoupling Control Optimization for a Small-Scale Unmanned Helicopter." Journal of Robotics 2018 (June 27, 2018): 1–12. http://dx.doi.org/10.1155/2018/9897684.

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This article presents design and optimization results from an implementation of a novel disturbance decoupling control strategy for a small-scale unmanned helicopter. Such a strategy is based on the active disturbance rejection control (ADRC) method. It offers an appealing alternative to existing control approaches for helicopters by combining decoupling and disturbance rejection without a detailed plant dynamics. The tuning of the control system is formulated as a function optimization problem to capture various design considerations. In comparison with several different iterative search algorithms, an artificial bee colony (ABC) algorithm is selected to obtain the optimal control parameters. For a fair comparison of control performance, a well-designed LQG controller is also optimized by the proposed method. Comparison results from an attitude tracking simulation against wind disturbance show the significant advantages of the proposed optimization control for this control application.
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Wang, Jialiang, Hai Zhao, Yuanguo Bi, Shiliang Shao, Qian Liu, Xingchi Chen, Ruofan Zeng, Yu Wang, and Le Ha. "An Improved Fast Flocking Algorithm with Obstacle Avoidance for Multiagent Dynamic Systems." Journal of Applied Mathematics 2014 (2014): 1–13. http://dx.doi.org/10.1155/2014/659805.

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Flocking behavior is a common phenomenon in nature, such as flocks of birds and groups of fish. In order to make the agents effectively avoid obstacles and fast form flocking towards the direction of destination point, this paper proposes a fast multiagent obstacle avoidance (FMOA) algorithm. FMOA is illustrated based on the status of whether the flocking has formed. If flocking has not formed, agents should avoid the obstacles toward the direction of target. If otherwise, these agents have reached the state of lattice and then these agents only need to avoid the obstacles and ignore the direction of target. The experimental results show that the proposed FMOA algorithm has better performance in terms of flocking path length. Furthermore, the proposed FMOA algorithm is applied to the formation flying of quad-rotor helicopters. Compared with other technologies to perform the localization of quad-rotor helicopter, this paper innovatively constructs a smart environment by deploying some wireless sensor network (WSN) nodes using the proposed localization algorithm. Finally, the proposed FMOA algorithm is used to conduct the formation flying of these quad-rotor helicopters in the smart environment.
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Bittanti, Sergio, Fabrizio Lorito, and Silvia Strada. "An LQ Approach to Active Control of Vibrations in Helicopters." Journal of Dynamic Systems, Measurement, and Control 118, no. 3 (September 1, 1996): 482–88. http://dx.doi.org/10.1115/1.2801171.

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In this paper, Linear Quadratic (LQ) optimal control concepts are applied for the active control of vibrations in helicopters. The study is based on an identified dynamic model of the rotor. The vibration effect is captured by suitably augmenting the state vector of the rotor model. Then, Kalman filtering concepts can be used to obtain a real-time estimate of the vibration, which is then fed back to form a suitable compensation signal. This design rationale is derived here starting from a rigorous problem position in an optimal control context. Among other things, this calls for a suitable definition of the performance index, of nonstandard type. The application of these ideas to a test helicopter, by means of computer simulations, shows good performances both in terms of disturbance rejection effectiveness and control effort limitation. The performance of the obtained controller is compared with the one achievable by the so called Higher Harmonic Control (HHC) approach, well known within the helicopter community.
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De Pratti, Giovanni Maria. "Airfoil to Improve Aerodynamic Performance OF Aileron Reduced Spanwise in Combat Helicopter." E3S Web of Conferences 197 (2020): 11003. http://dx.doi.org/10.1051/e3sconf/202019711003.

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Combat helicopters frequently operate in the part of Planetary Boundary Layer (PBL) characterised by the presence of dust and many other aggressive agents, particularly, in desertic areas and in marine sites, so the aerodynamic performance of their ailerons reduced spanwise, carrying out weapon systems, may be reduced within unacceptable values and consequent relevant risks for the stability of the copter. According to some experts, ailerons for weapon systems of helicopter are not involved in the global lift of the copter, but their operative function is only to carry the combat systems..Nevertheless, some crash occurred to US combat helicopters suggest a different point of view, and an aileron damage, perhaps due to a kind of dynamic stall phenomenon, seems have been caused the copter fall. These problems may be avoided using particularly airfoil for the section of aileron instead of classic ones as NACA four digit series (as 00120018). These profiles may be FFA-W1-XXX series, characterised by a double curvature of camber-line. In the present paper, after a deep analysis of operative conditions of modern combat helicopters, the aerodynamic performance of aileron section as NACA 0018 and FFA-W1-182 have been analysed and compared, and the results of tests carried out on a water table test bench are exposed and discusses.
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Guivarch, D., E. Mermoz, Y. Marino, and M. Sartor. "Creation of helicopter dynamic systems digital twin using multibody simulations." CIRP Annals 68, no. 1 (2019): 133–36. http://dx.doi.org/10.1016/j.cirp.2019.04.041.

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Dissertations / Theses on the topic "Helicopter dynamic systems"

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Kontitsis, Michail. "Design and implementation of an integrated dynamic vision system for autonomous systems operating in uncertain domains." [Tampa, Fla] : University of South Florida, 2009. http://purl.fcla.edu/usf/dc/et/SFE0002852.

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Samal, Mahendra Engineering &amp Information Technology Australian Defence Force Academy UNSW. "Neural network based identification and control of an unmanned helicopter." Awarded by:University of New South Wales - Australian Defence Force Academy. Engineering & Information Technology, 2009. http://handle.unsw.edu.au/1959.4/43917.

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This research work provides the development of an Adaptive Flight Control System (AFCS) for autonomous hover of a Rotary-wing Unmanned Aerial Vehicle (RUAV). Due to the complex, nonlinear and time-varying dynamics of the RUAV, indirect adaptive control using the Model Predictive Control (MPC) is utilised. The performance of the MPC mainly depends on the model of the RUAV used for predicting the future behaviour. Due to the complexities associated with the RUAV dynamics, a neural network based black box identification technique is used for modelling the behaviour of the RUAV. Auto-regressive neural network architecture is developed for offline and online modelling purposes. A hybrid modelling technique that exploits the advantages of both the offline and the online models is proposed. In the hybrid modelling technique, the predictions from the offline trained model are corrected by using the error predictions from the online model at every sample time. To reduce the computational time for training the neural networks, a principal component analysis based algorithm that reduces the dimension of the input training data is also proposed. This approach is shown to reduce the computational time significantly. These identification techniques are validated in numerical simulations before flight testing in the Eagle and RMAX helicopter platforms. Using the successfully validated models of the RUAVs, Neural Network based Model Predictive Controller (NN-MPC) is developed taking into account the non-linearity of the RUAVs and constraints into consideration. The parameters of the MPC are chosen to satisfy the performance requirements imposed on the flight controller. The optimisation problem is solved numerically using nonlinear optimisation techniques. The performance of the controller is extensively validated using numerical simulation models before flight testing. The effects of actuator and sensor delays and noises along with the wind gusts are taken into account during these numerical simulations. In addition, the robustness of the controller is validated numerically for possible parameter variations. The numerical simulation results are compared with a base-line PID controller. Finally, the NN-MPCs are flight tested for height control and autonomous hover. For these, SISO as well as multiple SISO controllers are used. The flight tests are conducted in varying weather conditions to validate the utility of the control technique. The NN-MPC in conjunction with the proposed hybrid modelling technique is shown to handle additional disturbances successfully. Extensive flight test results provide justification for the use of the NN-MPC technique as a reliable technique for control of non-linear complex dynamic systems such as RUAVs.
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Lopes, Darby Freitas de Albuquerque. "Estimativa da atitude e posição e controle robusto de um helicóptero autônomo." Universidade de São Paulo, 2010. http://www.teses.usp.br/teses/disponiveis/18/18153/tde-08022011-095400/.

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Este trabalho aborda o estudo de um sistema de referência inercial de posição e atitude e um sistema de controle para um helicóptero autônomo utilizando, como base para formulação e testes, o modelo linearizado da aeronave Yamaha R-MAX. Um sistema de referência inercial (INS) e um sistema de referência de atitude e orientação (AHRS) são utilizados para estimar a posição e atitude da aeronave, e estimadores robustos baseados no filtro de Kalman são empregados para minimizar os efeitos de incertezas paramétricas. É utilizada uma estratégia de controle em cascata com três malhas consistindo de uma malha interna para garantir a estabilidade do helicóptero (são utilizadas as técnicas LQR e H \'INFINITO\', separadamente), uma malha intermediária baseada em linearização por realimentação (FLC) para desacoplar os pares entrada/saída e uma malha externa baseada em um controlador proporcional-derivativo (PD) para permitir o rastreamento da trajetória. Resultados de simulação são apresentados para avaliar o desempenho de cada abordagem.
This work concerns the study of an inertial reference system and a control system for an autonomous helicopter using, as basis for the formulation and testing, the linearized mo del of the aircraft Yamaha R-MAX. An inertial navigation system (INS) and an attitude and orientation reference system (AHRS) are used to estimate the position and attitude of the aircraft and robust estimators based on Kalman filter are employed to minimize the effects of parametric uncertainties. A cascaded control architecture with three control methodologies is used, consisting of an inner-loop to ensure stability of the helicopter (the LQR and H \'INFINITE\' techniques are used, separately), a mid-loop based on linearization feedback (FLC) to decouple the dynamics ofthe lateral, longitudinal, vertical and heading axes and an outer-loop based on a proportional-derivative (PD) controller to enable trajectory tracking. Simulation results are presented to evaluate the performance of each approach.
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Guivarch, Damien. "Méthodes et outils d'aide à l'estimation des efforts sur les ensembles mécaniques en phase d'architecture. Application aux hélicoptères." Electronic Thesis or Diss., Toulouse, INSA, 2019. http://www.theses.fr/2019ISAT0053.

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Les nouveaux outils logiciels permettent de simuler le comportement dynamique transitoire des systèmes mécaniques multi-corps. Pourraient-ils produire une bonne prévision des efforts qui prennent place dans les systèmes de voilures tournantes des hélicoptères? Les travaux développés dans cette thèse apportent des éléments de réponse à cette question, sachant que le contexte considéré est porteur de nombreuses difficultés : flexibilités des corps, liaisons mécaniques complexes, hyperstatismes…L’enjeu est important car le cycle de développement de ces ensembles mécaniques serait fortement réduit par une bonne estimation d’efforts dès les premières étapes de la conception d’une nouvelle architecture. Dans ce cadre, un nouveau niveau de modélisation est introduit, centré sur les systèmes dynamiques à l’étude. La présentation de l’approche multi-échelle proposée implique le recours à des modèles locaux simplifiés. L’étude s’appuie sur le système de voilure tournante de l’hélicoptère H160 actuellement en phase d’industrialisation chez Airbus Helicopters et qui comprend les pales, le rotor principal et les actionneurs de commande hydrauliques. Trois développements majeurs sont détaillés : modélisations d’un sous-ensemble plateaux cycliques, des pales et du système de voilure tournante. Le nouveau cadre de modélisation ainsi constitué permet d’estimer les interefforts au niveau des liaisons mécaniques du système, et de suivre leurs évolutions au cours du temps
New software tools are used to simulate the transient dynamic behaviour of multi-body mechanical systems. Could they provide a good forecast of loads applied on helicopter rotary wing system? The work developed in this thesis provides some answers to this question, knowing that the context considered presents many difficulties: flexible bodies, complex mechanical links, hyperstatisms… The stakes are high because the development cycle of these mechanical assemblies would be greatly reduced by a correct estimation of loads during the first steps of the design of a new architecture. In this context, a new level of modeling is introduced, focusing on the dynamic systems studied. Since this level is part of a multi-scale approach, it is necessary to feed it with simplified models of the subassemblies that form the studied system, and this leads to so-called local studies. The presentation of this work is based on the rotary wing system of H160 helicopter, currently in industrialization phase at Airbus Helicopters, which includes the blades, the main rotor and the hydraulic control actuators. Three major developments are detailed: modelling of a swashplates sub-assembly, blades and the rotary wing system.The new modelling framework thus created allows the loads estimation at the level of the mechanical links of these systems and the monitoring of their evolution over time
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Potter, James Jackson. "Input-shaped manual control of helicopters with suspended loads." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50342.

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A helicopter can be used to transport a load hanging from a suspension cable. This technique is frequently used in construction, firefighting, and disaster relief operations, among other applications. Unfortunately, the suspended load swings, which makes load positioning difficult and can degrade control of the helicopter. This dissertation investigates the use of input shaping (a command-filtering technique for reducing vibration) to mitigate the load swing problem. The investigation is conducted using two different, but complementary, approaches. One approach studies manual tracking tasks, where a human attempts to make a cursor follow an unpredictably moving target. The second approach studies horizontal repositioning maneuvers on small-scale helicopter systems, including a novel testbed that limits the helicopter and suspended load to move in a vertical plane. Both approaches are used to study how input shaping affects control of a flexible element (the suspended load) and a driven base (the helicopter). In manual tracking experiments, conventional input shapers somewhat degraded control of the driven base but greatly improved control of the flexible element. New input shapers were designed to improve load control without negatively affecting base control. A method for adjusting the vibration-limiting aggressiveness of any input shaper between unshaped and fully shaped was also developed. Next, horizontal repositioning maneuvers were performed on the helicopter testbed using a human-pilot-like feedback controller from the literature, with parameter values scaled to match the fast dynamics of the model helicopter. It was found that some input shapers reduced settling time and peak load swing when applied to Attitude Command or Translational Rate Command response types. When the load was used as a position reference instead of the helicopter, the system was unstable without input shaping, and adding input shaping to a Translational Rate Command was able to stabilize the load-positioning system. These results show the potential to improve the safety and efficiency of helicopter suspended load operations.
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Mittal, Manoj. "Modeling and control of a twin-lift helicopter system." Diss., Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/12174.

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Bangalore, Ashok K. "Computational fluid dynamic studies of high lift rotor systems using distributed computing." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12949.

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Nygren, Kip P. "An investigation of helicopter higher harmonic control using a dynamic system coupler simulation." Diss., Georgia Institute of Technology, 1986. http://hdl.handle.net/1853/12082.

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Weiner, Steven David 1956. "The effect of improved aircraft efficiency on helicopter sales using system dynamics." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/91712.

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Brown, Sean M. "Determination of Human Powered Helicopter Stability Characteristics using Multi-Body System Simulation Techniques." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/874.

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Multi-Body System Simulation combined with System Identification was developed as a method for determining the stability characteristics of a human powered helicopter(HPH) configurations. HPH stability remains a key component for meeting competition requirements, but has not been properly treated. Traditional helicopter dynamic analysis is not suited to the HPH due to its low rotation speeds and light weight. Multi-Body System Simulation is able to generate dynamic response data for any HPH configuration. System identification and linear stability theory are used to determine the stability characteristics from the dynamic response. This thesis focuses on the method development and doesn't present any HPH analysis results.
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Books on the topic "Helicopter dynamic systems"

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Jorgensen, Charles C. Analysis of tasks for dynamic man/machine load balancing in advanced helicopters. Oak Ridge, Tenn: Oak Ridge National Laboratory, 1987.

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P, Townsend Dennis, Oswald Fred B, and United States. National Aeronautics and Space Administration., eds. Experimental and analytical evaluation of dynamic load and vibration of a 2240-kW (3000-hp) rotorcraft transmission. [Washington, DC: National Aeronautics and Space Administration, 1987.

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P, Townsend Dennis, Oswald Fred B, and United States. National Aeronautics and Space Administration., eds. Experimental and analytical evaluation of dynamic load and vibration of a 2240-kW (3000-hp) rotorcraft transmission. [Washington, DC: National Aeronautics and Space Administration, 1987.

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United States. National Aeronautics and Space Administration., ed. Studies of the dynamics of the twin-lift system: Interim report. Princeton, NJ: Dept. of Mechanical and Aerospace Engineering, Princeton University, 1989.

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L, Wilbur Matthew, U.S. Army Research Laboratory., and Langley Research Center, eds. Wind-tunnel evaluation of the effect of blade nonstructural mass distribution on helicopter fixed-system loads. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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C, Curtiss H., and United States. National Aeronautics and Space Administration., eds. An analytic modeling and system identification study of rotor/fuselage dynamics at hover. [Washington, DC: National Aeronautics and Space Administration, 1993.

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K, Remple Robert, ed. Aircraft and rotorcraft system identification: Engineering methods with flight test examples. 2nd ed. Reston, VA: American Institute of Aeronautics and Astronautics, 2012.

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K, Remple Robert, ed. Aircraft and rotorcraft system identification: Engineering methods with flight-test examples aircraft and rotorcraft system identification engineering methods with flight-test examples. Reston, VA: American Institute of Aeronautics and Astronautics, 2006.

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V, Cook M., Rycroft Michael J, Institute of Mathematics and its Applications., and Conference on Aerospace Vehicle Dynamics and Control (1992 : Cranfield Institute of Technology), eds. Aerospace vehicle dynamics and control: Based on the proceedings of a conference organized by the Institute of Mathematics and its Applications on aerospace vehicle dynamics and control, held at the Cranfield Institute of Technology, in September 1992. Oxford: Clarendon Press, 1994.

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Boden, Fritz. Advanced In-Flight Measurement Techniques. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013.

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Book chapters on the topic "Helicopter dynamic systems"

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Zhang, Ke, Bin Jiang, and Peng Shi. "Helicopter Platform Applications." In Observer-Based Fault Estimation and Accomodation for Dynamic Systems, 157–66. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-33986-8_8.

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Ren, Beibei, Shuzhi Sam Ge, Chang Chen, Cheng-Heng Fua, and Tong Heng Lee. "Dynamic Altitude Synchronization Using Graph Theory." In Modeling, Control and Coordination of Helicopter Systems, 195–216. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-1563-3_8.

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Zhou, Jing, Lantao Xing, and Changyun Wen. "Adaptive Attitude Control of Helicopter with Quantization." In Adaptive Control of Dynamic Systems with Uncertainty and Quantization, 179–94. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003176626-16.

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de Lope, Javier, Juan José San Martín, and José A. Martín H. "Helicopter Flight Dynamics Using Soft Computing Models." In Computer Aided Systems Theory – EUROCAST 2007, 621–28. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75867-9_78.

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Yue, Yi. "A System Dynamics Model for Helicopter Operations." In Operations Research/Management Science at Work, 405–21. Boston, MA: Springer US, 2002. http://dx.doi.org/10.1007/978-1-4615-0819-9_26.

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Ren, Beibei, Shuzhi Sam Ge, Chang Chen, Cheng-Heng Fua, and Tong Heng Lee. "Altitude Control of Helicopters with Unknown Dynamics." In Modeling, Control and Coordination of Helicopter Systems, 59–92. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-1563-3_4.

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Masarati, Pierangelo, Andrea Zanoni, Vincenzo Muscarello, Rita Paolini, and Giuseppe Quaranta. "Helicopter Pilot Biomechanics by Multibody Analysis." In Nonlinear Dynamics of Structures, Systems and Devices, 439–47. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-34713-0_44.

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Ren, Beibei, Shuzhi Sam Ge, Chang Chen, Cheng-Heng Fua, and Tong Heng Lee. "Attitude Control of Uncertain Helicopters with Actuator Dynamics." In Modeling, Control and Coordination of Helicopter Systems, 121–46. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-1563-3_6.

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Ren, Beibei, Shuzhi Sam Ge, Chang Chen, Cheng-Heng Fua, and Tong Heng Lee. "Altitude and Yaw Control of Helicopters with Uncertain Dynamics." In Modeling, Control and Coordination of Helicopter Systems, 93–119. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-1563-3_5.

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Zhang, Ruimin, Junbo Zhao, and Jingang Dong. "Simulation of Flight Dynamics for Helicopter Icing." In Proceedings of the 14th International Conference on Man-Machine-Environment System Engineering, 341–48. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-662-44067-4_41.

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Conference papers on the topic "Helicopter dynamic systems"

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Kumar, Anil, and Pinhas Ben-Tzvi. "An Inertial Sensor to Measure Wind Turbulence With RC Helicopters." In ASME 2017 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/dscc2017-5354.

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This paper presents a wireless sensor system developed to use RC helicopter dynamics to measure wind turbulence. Wind turbulence is a safety concern for naval helicopter operations due to typical scarcity of landing/takeoff area on naval vessels. Wind turbulence affects the dynamics of helicopters by creating uneven thrust on the rotor blades. The proposed telemetry system, when retrofitted on an RC helicopter, extracts these external disturbances in the helicopter’s dynamics and maps the wind conditions. This study focuses on learning the helicopter’s dynamics in controlled wind conditions using machine learning algorithms. The presented telemetry system uses sensors such as an Inertial Measurement Unit (IMU), optical trackers, and GPS sensors to measure the dynamics of the flying RC helicopter. The system also measures the pilot’s radio inputs to account for pilot inputs in the helicopter’s dynamics. The telemetry system is trained and tested in a large indoor facility where turbulent wind conditions were created artificially using large wind circulation fans.
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Potter, James, Ryan Simpson, and William Singhose. "Dynamic Modeling and Simulation of a Remote-Controlled Helicopter With a Suspended Load." In ASME 2013 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/dscc2013-3998.

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A planar helicopter testbed has been constructed to study the dynamic effects of loads suspended below the helicopter by cables. A dynamic model of the helicopter-load system is presented, as well as a procedure to estimate the unknown model parameters. The simulated helicopter is controlled by a virtual pilot with attributes that are scaled to match the model helicopter’s fast dynamics. Initial simulations show that the presence of a heavy load makes it difficult to maintain a steady hover position after a horizontal movement.
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Tekes, Ayse, Adeel Khalid, Niko Giannakakos, and Alexander Bryant. "Helicopter Swashplate Design and Analysis Using Semi Compliant Mechanism." In ASME 2018 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/dscc2018-8944.

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The swashplate of a model helicopter consists of stationary and rotating plates separated by ball bearings. This mechanism enables the swashplate to tilt in all directions and move vertically as one unit. The lower stationary plate is mounted on the main rotor mast and connected to the cyclic and collective controls by a series of pushrods. There are similar pushrods known as pitch links connected to the upper rotating plate. These pitch links are connected to the pitch horns and control the pitch of individual blades. In this study, the pitch links of the model helicopter are replaced by a semi compliant mechanism. This mechanism is directly connected to the pitch horns to control the pitch of the individual blades. The actuation of the bars can be achieved by using high torque stepper or servo motors. These precise low and high amplitude outputs are specifically required for the cyclic and collective controls of the helicopter swashplate. The compliant swashplate mechanism can be fabricated as a single piece using an injection molding technique or by 3D printing. The mechanism is modeled by two similar vector loops in two different planes. The mathematical model of the plate motion and the forces on the mechanism links are developed and simulated using MATLAB and Simulink, and initial results are discussed in this paper. This mechanism would be applied to the helicopter directional control where the plate in the pitch-roll mechanism would serve as the swash plate of the helicopter.
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Kuntz, Noah R., and Paul Y. Oh. "Development of Autonomous Cargo Transport for an Unmanned Aerial Vehicle Using Visual Servoing." In ASME 2008 Dynamic Systems and Control Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/dscc2008-2203.

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This paper presents the design and testing of systems for autonomous tracking, payload pickup, and deployment of cargo via a UAV helicopter. The tracking system uses a visual servoing algorithm and is tested using open loop velocity control of a 3DOF gantry system with a camera mounted via a pan-tilt unit on the end effecter. The pickup system uses vision to control the camera pan tilt unit as well as a second pan tilt unit with a hook mounted on the end of the arm. The ability of the pickup system to hook a target is tested by mounting it on the gantry while recorded helicopter velocities are played back by the gantry. A preliminary semi-autonomous deployment system is field tested, where a manually controlled RC truck is transported by a UAV helicopter under computer control that is manually directed to GPS waypoints using a ground station.
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Taylor, James H., and Saied S. Sharif. "Chaos in nonlinear dynamic systems: Helicopter vibration mechanisms." In 2007 Mediterranean Conference on Control & Automation. IEEE, 2007. http://dx.doi.org/10.1109/med.2007.4433847.

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Pounds, Paul E. I., and Aaron Dollar. "Hovering Stability of Helicopters With Elastic Constraints." In ASME 2010 Dynamic Systems and Control Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/dscc2010-4166.

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Aerial vehicles are difficult to stabilize, especially when acted upon by external forces. A hovering vehicle in contact with objects and surfaces must maintain flight stability while subject to forces imparted to the airframe through the point of contact. These forces couple with the motion of the aircraft to produce distinctly different dynamics from free flight. While external contact is generally avoided, extending aerial robot functionality to include contact with the environment during flight opens up new and useful areas such as perching, object grasping and manipulation. In this paper, we present a general elastic contact constraint model and analyze helicopter stability in the presence of those contacts. As an example, we evaluate the stability of a proof-of-concept helicopter system for manipulating objects using a compliant gripper that can be modeled as an elastic linkage with angular reaction forces. An off-the-shelf PID flight controller is used to stabilize the helicopter in free flight, as well as during the aerial manipulation task. We show that the planar dynamics of the object-helicopter system in vertical, horizontal and pitch motion around equilibrium are shown to remain stable, within a range of contact stiffnesses, under unmodified PID control.
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Parsons, Matthew R., and Robert G. Langlois. "Stability Analysis of a Two-dimensional Tethered Helicopter." In International Conference of Control, Dynamic Systems, and Robotics. Avestia Publishing, 2016. http://dx.doi.org/10.11159/cdsr16.128.

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Molina, Javier, and Shinichi Hirai. "Dynamic landing gear for balancing a multirotor helicopter." In 2017 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2017. http://dx.doi.org/10.1109/icuas.2017.7991346.

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Seo, Joohwan, and Jongeun Choi. "Output Feedback Control Synthesis for a Helicopter Using Explicit Nonlinear Model Predictive Control, Dynamic Inversion and Extended High Gain Observers." In ASME 2019 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/dscc2019-9036.

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Abstract Control design for a helicopter is a challenging problem because of its non-affine inputs, complicated dynamics and it is an under-actuated system. To solve a control problem of the helicopter under model uncertainties and disturbance present environments, an Explicit Nonlinear Model Predictive Control (ENMPC), a dynamic inversion and an Extended High-Gain Observers (EHGO) are combined in a multi-time-scale fashion. The multi-time scaled structrue and the ENMPC provides the framework of the control design, the dynamic inversion deals with non-affine control inputs, and the EHGO estimates the unmeasured states and uncertainties. In addition, a discretization scheme using the saturation and adding low pass filters to the control inputs is presented. Finally, the numerical simulation of a fixed sampling period has been carried out to demonstrate the validity of the proposed multi-time-scale control design and the discretization scheme.
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Kumar, Anil, and Pinhas Ben-Tzvi. "Extraction of Impact of Wind Turbulence on RC Helicopters Using Machine Learning." In ASME 2016 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/detc2016-59384.

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This paper presents a new cost effective wireless telemetry system capable of estimating ambient air turbulence using RC helicopters. The proposed telemetry system correlates the RC helicopter’s flight dynamics with ship air wake patterns generated by cruising naval vessels. The telemetry system consists of two instrumentation units each equipped with aviation grade INS/IMU sensors to measure dynamics of the helicopter with respect to the concerned naval vessel. The presented telemetry system extracts ship air wake patterns by removing the helicopter dynamic effects from actual measurements. This paper presents a comprehensive comparison between popular machine learning algorithms in eliminating effects of pilot inputs from helicopter’s dynamics measurements. The system was tested on data collected in a wide range of wind conditions generated by modified YP676 naval training vessel in the Chesapeake Bay area over a period of more than a year.
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