Relevant bibliographies by topics / Manoeuvre loads

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Manoeuvre loads'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 February 2022

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Journal articles on the topic "Manoeuvre loads"

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Dekker, S., G. Wurzel, and R. Alderliesten. "Reliability modelling for rotorcraft component fatigue life prediction with assumed usage." Aeronautical Journal 120, no. 1232 (July 8, 2016): 1658–92. http://dx.doi.org/10.1017/aer.2016.79.

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ABSTRACTFatigue life is a random variable. Thus, the reliability of a conservative fatigue life prediction for a component in the helicopter dynamic system needs to be substantiated. A standard analytical substantiation method uses averaged manoeuvre loads instead of seeing manoeuvre loads as a random variable whose distribution is estimated with limited precision. This simplification may lead to inaccuracies. A new simulation-based method is developed to conservatively predict fatigue life, while also accounting for the full random distribution and uncertainty of manoeuvre loads. Both methods fully account for uncertain fatigue strength but assume that the mission profile is known or can at least be conservatively estimated. Simulations under synthetic but realistic engineering conditions demonstrate that both methods may be used for accurate substantiation of conservative fatigue life predictions. The simulations also demonstrate that, under the tested conditions, uncertainties from manoeuvre loads may be neglected in fatigue life substantiations as the resulting error is not significant with respect to uncertainties in component fatigue strength.
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Kowaleczko, Grzegorz, and Andrzej Leśniczak. "Modelling of Helicopter Main Rotor Aerodynamic Loads in Manoeuvres." Journal of KONES 26, no. 4 (December 1, 2019): 273–84. http://dx.doi.org/10.2478/kones-2019-0118.

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AbstractThe article discusses the method of modelling of the helicopter main rotor aerodynamic loads during steady state flight and manoeuvres. The ability to determine these loads was created by taking into account the motion of each blade relative to the hinges and was a result of the applied method of aerodynamic loads calculating. The first part of the work discusses the basic relationships that were used to build the mathematical model of helicopter flight. The focus was also on the method of calculating of the aerodynamic forces generated by the rotor blades. The results of simulations dedicated to the “jump to hover” manoeuvre were discussed, showing the possibilities of analysing aerodynamic loads occurring in unsteady flights. The main rotor is considered separately in an “autonomous” way and treated as a source of averaged forces and moments transferred to the hub. The motion of individual blades is neglected, and their aerodynamic characteristics are radically simplified. The motion of individual blades is neglected, and their aerodynamic characteristics are radically simplified. This can lead to significant errors when attempting to model dynamic helicopter manoeuvres. The more complex model of helicopter dynamics is discussed.
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Irving, P. E., J. E. Strutt, R. A. Hudson, K. Allsop, and M. Strathern. "The contribution of fatigue usage monitoring systems to life extension in safe life and damage tolerant designs." Aeronautical Journal 103, no. 1030 (December 1999): 589–95. http://dx.doi.org/10.1017/s0001924000064228.

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Abstract Fatigue usage monitoring systems (Fums) offer considerable potential for life extension of aircraft parts. In this work the life extension benefits of Fums is assessed by adopting a probabilistic approach. The roles of damage law type and of service usage variability is explored. It is shown by analysis that in the absence of cycle to cycle load interaction effects, load sequence has no effect on eventual life in either linear or non linear damage laws, provided that the function describing the rate of damage growth has separable variables of stress and damage. This condition includes fracture mechanics crack growth laws. Monte Carlo simulations have been conducted of fatigue life distributions in helicopter rotor components. Variability in manoeuvre damage, when summed over a large number of manoeuvres, has little effect on scatter in overall lives. A fixed manoeuvre usage spectrum will result in very small scatter in lives, whereas keeping the usage constant for each helicopter and allowing it to vary between helicopters, produces a significantly increased variability. The influence of load factors on life is also assessed. The extent of possible maintenance credits is discussed together with the use of Bayesian updating to make optimum use of both prior design data and current loads or damage information provided by Fums.
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Bordogna, Marco Tito, Paul Lancelot, Dimitri Bettebghor, and Roeland De Breuker. "Static and dynamic aeroelastic tailoring with composite blending and manoeuvre load alleviation." Structural and Multidisciplinary Optimization 61, no. 5 (January 9, 2020): 2193–216. http://dx.doi.org/10.1007/s00158-019-02446-w.

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AbstractIn aircraft design, proper tailoring of composite anisotropic characteristics allows to achieve weight saving while maintaining good aeroelastic performance. To further improve the design, dynamic loads and manufacturing constraints should be integrated in the design process. The objective of this paper is to evaluate how the introduction of continuous blending constraints affects the optimum design and the retrieval of the final stacking sequence for a regional aircraft wing. The effect of the blending constraints on the optimum design (1) focuses on static and dynamic loading conditions and identifies the ones driving the optimization and (2) explores the potential weight saving due to the implementation of a manoeuvre load alleviation (MLA) strategy. Results show that while dynamic gust loads can be critical for wing design, in the case of a regional aircraft, their influence is minimal. Nevertheless, MLA strategies can reduce the impact of static loads on the final design in favour of gust loads, underlining the importance of considering such load-cases in the optimisation. In both cases, blending does not strongly affect the load criticality and retrieve a slightly heavier design. Finally, blending constraints confirmed their significant influence on the final discrete design and their capability to produce more manufacturable structures.
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Barbieri, Nilson, Rubem Penteado de Melo, Key Fonseca de Lima, and Gabriel de Sant’Anna Vitor Barbieri. "Dynamical analysis of B-train vehicle combination with liquid cargo." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 14 (March 21, 2019): 3871–81. http://dx.doi.org/10.1177/0954407019838127.

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In this work, a combination of B-train type vehicle is dynamically analysed through lateral movement at low speed manoeuvre known as Lane Change Manoeuvre. The analyses were conducted for a vehicle with liquid loads of 100%, 80%, 60% and 40% capacity. The analyses involve adjusting the steer angle through an objective function taking into account the numerical and experimental lateral acceleration of the tractor vehicle. The movement of the liquid (slosh) during the manoeuvres are approximated using the software Pasimodo and trammel pendulum. Considering the upper surface of the liquid inside the tank as a straight line, it is possible to obtain the centre of gravity variation and the moment of inertia through polynomial adjustments. In this way, it is possible to analyse numerically the behaviour of the vehicle with liquid load in a curved trajectory. To obtain modal parameters, the operational modal analysis technique is used. With the applied methodology, it was possible to find good agreement between the numerical and experimental values of the acceleration signals in four different positions in the vehicle combination. Through the analyses of the vehicle with fluid in movement, it was possible to verify a great variation of load in the wheels due to transfer of load of the vehicle travelling by curved trajectories or due to evasive manoeuvres. This is a critical condition that can lead the vehicle to rollover condition. The experimental data were obtained for the vehicle at constant speed (between 30 and 40 km/h) and under these conditions, the vehicle is considered stable by analysing the eigenvalues.
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Kowaleczko, Grzegorz, Tomasz Kwaśniak, Mirosław Nowakowski, and Mirosław Michalczewski. "Analysis of aerodynamics and main rotor loads under stalled conditions of helicopter’s main rotor during the pull-up manoeuvre." Journal of KONBiN 48, no. 1 (December 1, 2018): 7–29. http://dx.doi.org/10.2478/jok-2018-0045.

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Abstract The article discusses the main features of the applied simulation model of helicopter flight indicating references, where it was elaborated in detail. It focuses on presenting the simulation results of pull-up manoeuvre during which the helicopter does not respond correctly. The reasons for the behaviour as mentioned above were explained based on the results of calculations. The capabilities of the simulation model were used to determine the current loads of particular blades of the helicopter’s main rotor. The results were illustrated by maps of the angles of attack and aerodynamic lift on the surface of the main rotor and the distributions of these parameters along blades on characteristic azimuth for individual manoeuvre phases.
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Popov, G., S. Sankar, T. S. Sankar, and G. H. Vatistas. "Dynamics of Liquid Sloshing in Horizontal Cylindrical Road Containers." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 207, no. 6 (November 1993): 399–406. http://dx.doi.org/10.1243/pime_proc_1993_207_147_02.

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A study of the liquid behaviour in horizontal cylindrical road containers undergoing a steady turning manoeuvre is presented and discussed. The steady state solutions are derived analytically from the hydrostatic equations. The transient solutions are obtained by numerical integration of the Navier-Stokes, continuity and free-surface equations. The non-dimensional governing equations are solved in primitive variables by using a modified marker-and-cell technique which involves the interpolation-reflection type boundary conditions developed for this investigation. The mathematical model of the liquid motion includes all essential non-linear effects and allows the damped natural frequencies of liquid vibrations to be obtained as well as the magnitudes of the liquid slosh loads. This study also enables the coupled directional dynamics of the ‘vehicle-liquid tank’ system undergoing different road manoeuvres to be investigated by integrating the non-linear fluid slosh model and an appropriate vehicle model simultaneously.
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Sinha, Kautuk, Thomas Klimmek, Matthias Schulze, and Vega Handojo. "Loads analysis and structural optimization of a high aspect ratio, composite wing aircraft." CEAS Aeronautical Journal 12, no. 2 (February 7, 2021): 233–43. http://dx.doi.org/10.1007/s13272-021-00494-x.

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AbstractComposite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials in the primary aircraft structure it is imperative to have corresponding design tools to simplify the design process. In the present work, a simplified implementation for composite optimization has been developed within the DLR-AE (German Aerospace Centre, Institute of Aeroelasticity) automated aeroelastic structural design framework cpacs-MONA. This paper presents the results of structural optimization of a high aspect ratio composite wing aircraft model developed in the DLR project ATLAs. The generation of almost all involved simulation models for this study is done using the in-house DLR tool ModGen. An aeroelastic trim analysis is conducted for various manoeuvre and gust conditions. A load selection process is used to determine the most relevant sizing load cases. A comparison is made between the optimization results of a composite wing and an aluminium wing to demonstrate the more favourable strength to weight ratio of the composite wing. A manoeuvre load alleviation procedure has been introduced in the load calculation process. The results show further weight savings in the design process when load alleviation is utilized due to reduction in the span wise bending moment.
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Leonelli, Luca, Stefano Cattabriga, and Silvio Sorrentino. "Driveline instability of racing motorcycles in straight braking manoeuvre." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 232, no. 17 (September 28, 2017): 3045–61. http://dx.doi.org/10.1177/0954406217730093.

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Experimental evidence shows that a self-excited vibration may appear during braking manoeuvres performed by road-racing motorcycles. It involves vertical oscillation of front and rear wheel axles as well as angular oscillation of the driveline in a frequency range between 17 and 22 Hz. As a consequence, severe oscillations of the tyre-ground vertical loads can be observed, leading to a loss of grip and ultimately weakening the vehicle overall performance. Several contributions on this topic can be accounted for in the literature; however, a comprehensive description of the phenomenon has not been given yet. The present work is aimed at simulating the above vibration with a planar multibody motorcycle model, and then at analyzing its driving mechanism. Stability maps are drawn for time-invariant braking manoeuvres, and validated with respect to time domain simulations.
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Stanisławski, Jarosław. "Simulation of Boundary States of Helicopter Flight." Journal of KONES 26, no. 2 (June 1, 2019): 137–44. http://dx.doi.org/10.2478/kones-2019-0042.

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Abstract Results of simulation of main rotor blade loads and deformations, which can be generated during boundary states of helicopter flight, are presented. Concerned cases of flight envelope include hover at maximum height, level flight at high velocity, pull-up manoeuvres applying cyclic pitch and mixed collective and cyclic control. The simulation calculations were executed for data of light helicopter with three-bladed articulated rotor. For analysis, the real blades are treated as elastic axes with distributed masses of blade segments. The model of deformable blade allows for out-of-plane bending, in plane bending, and torsion. For assumed flight state of helicopter, the equations of rotor blades motion are solved applying Runge-Kutta method. According to Galerkin method, for each concerned azimuthal position of blade the parameters of its motions are assumed as a combination of considered bending and torsion eigen modes of the blade. The loads of rotor blades generated during flight depend due to velocity of flight, helicopter mass, position of rotor axis in air and deflections of swashplate that correspond to collective and cyclic pitch angle applied to rotor blades. The results of simulations presenting rotor loads and blade deformations are shown in form of time-runs and as plots of rotor-disk distributions. The simulations of helicopter flight states may be useful for prediction the conditions of flight-tests without exceeding safety boundaries or may help to define limitations for manoeuvre and control of helicopter.
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Dissertations / Theses on the topic "Manoeuvre loads"

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Carn, Cheril, and cheril Carn@dsto defence gov au. "The inverse determination of aircraft loading using artificial neural network analysis of structural response data with statistical methods." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080109.090600.

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An artificial Neural Network (ANN) system has been developed that can analyse aircraft flight data to provide a reconstruction of the aerodynamic loads experienced by the aircraft during flight, including manoeuvre, buffet and distributed loading. For this research data was taken from the International Follow-On Structural Test Project (IFOSTP) F/A-18 fatigue test conducted by the Royal Australian Air Force and Canadian Forces. This fatigue test involved the simultaneous application of both manouevre and buffet loads using airbag actuators and shakers. The applied loads were representative of the actual loads experienced by an FA/18 during flight tests. Following an evaluation of different ANN types an Ellman network with three linear layers was selected. The Elman back-propagation network was tested with various parameters and structures. The network was trained using the MATLAB 'traingdx' function with is a gradient descent with momentum and adaptive learning rate back-propagation algorithm. The ANN was able to provide a good approximation of the actual manoeuvre or buffet loads at the location where the training loads data were recorded even for input values which differ from the training input values. In further tests the ability to estimate distributed loading at locations not included in the training data was also demonstrated. The ANN was then modified to incorporate various methods for the calculation and prediction of output error and reliability Used in combination and in appropriate circumstances, the addition of these capabilities significantly increase the reliability, accuracy and therefore usefulness of the ANN system's ability to estimate aircraft loading.To demonstrate the ANN system's usefulness as a fatigue monitoring tool it was combined with a formulae for crack growth analysis. Results inficate the ANN system may be a useful fatigue monitoring tool enabling real time monitoring of aircraft critical components using existing strain gauge sensors.
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Cochrane, Jodie L. "Training to alter the risk of anterior cruciate ligament injuries in sporting manoeuvres." University of Western Australia. School of Human Movement and Exercise Science, 2006. http://theses.library.uwa.edu.au/adt-WU2007.0035.

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[Truncated abstract] Anterior cruciate ligament injuries are a major problem in sport. The purpose of this thesis was to investigate the causative factors of ACL injuries and to study the effect of various types of lower-limb training on underlying neuromuscular mechanisms involved in stabilisation and risk of ACL injury. Investigation of the mechanisms was conducted on controlled balance and strength tests as well as in sporting manoeuvres. It was aimed to assess if the neuromuscular changes map over into the performance of sporting manoeuvres and if potential for loading on the ACL and risk of injury was reduced or exacerbated . . . ACL strain can be decreased through reduction in the applied loads and greater knee flexion. Further to this, muscle activation has the ability to reduce loading on the ACL through co-contraction and selective activation patterns. This thesis demonstrated differing neuromuscular adaptations from various training types that map over into the performance of sporting manoeuvres. The research indicated that the Balance-Training was the most favourable in reducing potential for injury risk on the ACL. Alternatively strength training elicited neuromuscular changes that were likely to increase the risk of force on the ACL. The Machine+Balance training resulted in some negative and positive outcomes with the balance training tending to counteract the negative affects of machine weights training resulting in small improvements in muscular support and load reduction. This study provides us with better understanding of the underlying mechanisms from various training types and their potential affect on risk of ACL injury.
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Books on the topic "Manoeuvre loads"

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Advisory Group for Aerospace Research and Development. Structures and Materials Panel. Working Group 27 on Evaluation of Loads from Operational Flight Maneuvers. Final Working Group report of Working Group 27 on Evaluation of Loads from Operational Flight Maneuvers =: L'evaluation des charges resultant des manoeuvres en vol. Neuilly-sur-Seine: Agard, 1996.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel. Working Group 27. Structures and Materials Panel Working Group 27 on evaluation of loads from operational flight maneuvers: Final Working Group report (L'évaluation des charges résultant des manoeuvres en vol.). Neuilly-sur-Seine: AGARD, 1996.

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Book chapters on the topic "Manoeuvre loads"

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"Ground Manoeuvre Loads." In Introduction to Aircraft Aeroelasticity and Loads, 495–500. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.ch24.

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"Flight Manoeuvre and Gust/Turbulence Loads." In Introduction to Aircraft Aeroelasticity and Loads, 481–93. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.ch23.

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"Equilibrium Manoeuvres." In Introduction to Aircraft Aeroelasticity and Loads, 219–51. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.ch12.

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"Dynamic Manoeuvres." In Introduction to Aircraft Aeroelasticity and Loads, 253–97. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.ch13.

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"Ground Manoeuvres." In Introduction to Aircraft Aeroelasticity and Loads, 337–65. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.ch15.

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"H MATLAB/SIMULINK Programs for Flight/Ground Manoeuvres and Gust/Turbulence Encounters." In Introduction to Aircraft Aeroelasticity and Loads, 1–15. Chichester, UK: John Wiley & Sons Ltd, 2015. http://dx.doi.org/10.1002/9781118700440.app8.

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Artyszuk, J. "Simulation of load distribution along a quay during unparallel berthing manoeuvres." In Marine Navigation and Safety of Sea Transportation. CRC Press, 2009. http://dx.doi.org/10.1201/9780203869345.ch15.

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"7 Simulation of load distribution along a quay during unparallel berthing manoeuvres." In Marine Navigation and Safety of Sea Transportation, 111–18. CRC Press, 2009. http://dx.doi.org/10.1201/9780203869345-21.

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Conference papers on the topic "Manoeuvre loads"

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Fonte, Federico, Giuseppe Iannaccone, Nicola Cimminiello, Ignazio Dimino, and Sergio Ricci. "Active Load Control of a Regional Aircraft Wing Equipped With Morphing Winglets." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-8167.

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Morphing winglets are innovative aircraft devices capable to adaptively enhance aircraft lift distribution throughout the flight mission while providing augmented roll and yaw control capability. Within the scope of the Clean Sky 2 REG IADP, this paper deals with nonlinear simulations of a regional aircraft wing equipped with active morphing winglets in manoeuvring conditions. The fault tolerant morphing winglet architecture is based on two independent and asynchronous control surfaces with variable camber and differential settings capability. The mechanical system is designed to face different flight static and dynamic situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed by means of static aeroelastic analyses, using a feedforward manoeuvre load alleviation controller. An electro-mechanical Matlab/Simulink model of the actuation architecture is used as design tool to preliminary evaluate the complete system performance and the ability to cope with the expected morphing aeroshapes. Then, the aeroelastic model of the aircraft is combined with the nonlinear simulator of the response of the winglet actuation system to evaluate a symmetric and asymmetric manoeuvres obtained by a sudden deflection of the main control surfaces. The use of the morphing winglet tabs shows to alleviate the wing loads in such conditions. The introduction of the dynamic actuator model leads to a reduction of the performances with respect to predictions of the static analyses but a reduction of the manoeuvre loads can still be observed.
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Kier, Thiemo M. "An Integrated Modelling Approach for Flight Dynamics, Manoeuvre- and Gust-Loads Analysis." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2209.

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Ferreira González, Daniel, Matthias Lemmerhirt, Moustafa Abdel-Maksoud, Marcel König, and Alexander Düster. "Numerical and Experimental Investigation Regarding the Landing Manoeuvre of a Catamaran Vessel at an Offshore Wind Turbine in Waves." In ASME 2015 34th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/omae2015-42071.

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In this work, the landing manoeuvre of a catamaran vessel at a monopile foundation is investigated by experiments compared with numerical simulations. Therefore, a method is presented which allows simulating the described landing manoeuvre at offshore structures. The simulation in the time domain is based on potential theory using a boundary element method (BEM) and it computes the motions of the rigid body due to the hydrodynamic loads which consist of the incoming waves and the diffraction caused by the monopile. Further, a fender model is implemented, considering the reaction forces due to the friction and the deformation of the fender. The model is further able to distinguish between slip and non-slip condition of the fender. Apart from this, model tests of the landing manoeuvre were carried out with a catamaran model. During the tests the model pushed its fender against an equally scaled monopile. The motions of the vessel and the forces at the attachment of the fender were measured in regular and irregular waves. The obtained data which leads to a better understanding of the hydrodynamic effects during a landing manoeuvre is compared with the simulation results in order to improve the numerical method. The validation with experimental results shows that the method is applicable to quantify the risk of the fender suddenly slipping.
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Ferrari, V., A. Kisjes, and F. H. H. A. Quadvlieg. "Quantifying the Uncertainty of the Crabbing Capability." In ASME 2018 37th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/omae2018-78429.

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Crabbing is a critical manoeuvre that requires all of the ship’s propulsors to counteract environmental forces. It is a complex hydrodynamic scenario in which it is difficult to assess the factors, nonetheless the crabbing capability is often calculated by means of simple static calculations which consider only means values. The ship designer or master should instead be aware of how much the crabbing capability can change when the propulsors are less efficient than expected or the wind loads are higher. The present paper details the application of sensitivity and uncertainty methods to the crabbing manoeuvre of a ship. The objective is to estimate the sensitivity of the main parameters involved in a crabbing calculation and express the results in terms of uncertainty range. To this purpose, first a sensitivity analysis is performed, showing how the maximum sustainable wind speed of a test-case ship varies. The curves derived from this analysis are then used to estimate numerically the relation between wind speed and a variation in each parameter. Typical values of uncertainty of these parameters are presented, and finally the crabbing capability calculated taking into account the uncertainties.
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Sutulo, Serge, and C. Guedes Soares. "Simulation of the Hydrodynamic Interaction Forces in Close-Proximity Manoeuvring." In ASME 2008 27th International Conference on Offshore Mechanics and Arctic Engineering. ASMEDC, 2008. http://dx.doi.org/10.1115/omae2008-57938.

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A code for simulating hydrodynamic interaction forces in manoeuvring simulating systems has been created. The algorithm takes into account potential forces only and is based on the Hess and Smith panel method. Own inertial hydrodynamic forces were estimated through pre-calculation of the added masses followed by use of the Thomson–Tait–Kirchhoff equations. Comparative computations of the added masses, surge and sway interaction forces and yaw interaction moments with varying number of surface computational panels showed that on a typical modern PC, an acceptable accuracy in terms of the integrated loads can be reached with a relatively small number of panels permitting real-time simulations with the developed algorithm in the loop. Importance of the account for the local time derivative of the potential has been demonstrated on comparative calculations in simulation of a passing-by manoeuvre. The code can be used for predicting interaction loads with any number of moving objects and fixed obstacles.
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Sutulo, Serge, and C. Guedes Soares. "Hydrodynamic Interaction Forces on Ship Hulls Equipped With Propulsors." In ASME 2012 31st International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/omae2012-84181.

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Typically, study of hydrodynamic interaction between vessels navigating in close proximity to each other is limited to hydrodynamics of bare hulls. Meanwhile, ship propulsors, especially heavily loaded, which may happen in accelerating motion, can alter substantially the flow and distribution of pressure on the hulls which can be viewed as generalization of the thrust deduction phenomenon. The 3D doubled body potential interaction code based on the source panel method developed earlier by the authors has been enhanced to include the effect of a propeller on each of the interacting ships under the assumption that the propeller jets (slipstreams) are not involved into the interaction. Each propeller is simulated by a disk of sinks further approximated with a polygon composed of identical triangular panels with identical constant sink density linked to the thrust of the propulsor according to the actuator disk theory. Comparative computations were carried out for two identical tanker vessels in the close-proximity overtaking manoeuvre at various values of the loading coefficient of each propeller. The loading coefficient is not supposed to be necessarily defined by the steady propulsion point. Numerical results demonstrate that a heavily loaded propeller substantially modifies the pressure distribution on both hulls resulting in alteration of the hydrodynamic interaction loads, especially of the surge force and yaw moment.
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Sodja, Jurij, Noud Werter, and Roeland De Breuker. "Design of a flying demonstrator wing for manoeuvre load alleviation with cruise shape constraint." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2153.

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Williams, C. D., T. L. Curtis, J. M. Doucet, M. T. Issac, and F. Azarsina. "Effects of Hull Length on the Hydrodynamic Loads on a Slender Underwater Vehicle during Manoeuvres." In OCEANS 2006. IEEE, 2006. http://dx.doi.org/10.1109/oceans.2006.306884.

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Sindha, Jigneshsinh, Basab Chakraborty, and Debashish Chakravarty. "Simulation Based Trajectory Analysis for the Tilt Controlled High Speed Narrow Track Three Wheeler Vehicle." In ASME 2018 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/detc2018-85087.

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Small sized three wheeler electric vehicles (EVs) are gaining popularity in many developing countries because of its low cost operation and excellent manoeuvrability. However, usage of such a 3Ws usage is limited to low speed application such as last mile public transport. Vehicles with such configuration are not well accepted for personal mobility. If the safe speed of such a vehicles are improved, such a vehicles can also become viable to personal transport. Active tilt control (ATC) systems are seen as one of the possible solution to improve safe speed of narrow track 3Ws.Literature indicates that many attempts have been made for establishing active tilt control system on 3W vehicles for enhancing stability of ATC vehicles and promising results were obtained. This paper presents simulation based analysis of the ATC 3W electric vehicle. This work is part of full scale experimental prototype development for the narrow track ATC 3W vehicle with one wheel in front configuration. The primarily focus of this work is to address vehicle dynamics and trajectory related issue of the tilting 3Ws. A multi-body model of ATC 3W vehicle using single track lateral dynamic model with nonlinear tire characteristics was prepared in SimMechanics. The lateral dynamic outputs in terms of the trajectory followed by vehicle were compared for the constant steering inputs given to non-tilting vehicle, tilting vehicle with direct tilt control (DTC) system and tilting vehicle with Steering direct tilt control (SDTC) system. Two critical driving scenarios of U-turn and Lane change manoeuvre are analyzed. It is observed from the results that there is certain trade-off in selecting a tilt actuator and controller so as to minimize the jerks in the perceived acceleration due to high gain and minimize the tilt angle error to ensure proper stability improvement. It is also identified that the controller must be tuned to the predictable trajectory control, in addition to the main task of reducing the load transfer across the rear wheel axle. The model presented in the paper is used to understand the performance of DTC and SDTC control strategies during potentially dangerous manoeuvres. The desired path following ability of the vehicle is the main measures considered for the analysis.
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10

Edefur, Henrik, Fredrik Haglind, and Stefan Olsson. "Design of an Air-Launched Tactical Missile for Three Different Propulsion Systems: ATR, Rocket and Turbojet." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27844.

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The objective of this paper is to assess the feasibility of a solid propellant Air Turbo Rocket (ATR), in comparison with a conventional turbojet engine or a solid rocket motor, as power source for a medium range tactical air-launched missile from an overall system point of view. A sizing method for missiles is developed, which together with flight performance calculations and engine performance data determines the final size and weight of the missile and its engine. The results suggest that an ATR engine is more favourable than a jet engine when the ratio between maximum (manoeuvre) thrust and minimum (cruise) thrust is large; for example for a mission including a cruise segment and a high load factor manoeuvre made at constant speed. For the missile range investigated in this paper no breakpoint in distance has been found beyond which the ATR engine becomes impractical. The rocket motor can produce a huge amount of thrust, thus giving it a very large maximum to minimum thrust ratio. However, it has a disadvantage in its low fuel efficiency and high combustion temperature, making it impracticable for missions requiring any longer duration. Altogether the choice of propulsion system has a large impact on maximum take-off weight, size and performance of the missile.
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