Gotowe bibliografie tematyczne / Manoeuvre loads

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Gotowa bibliografia na temat „Manoeuvre loads”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 15 lutego 2022

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Artykuły w czasopismach na temat "Manoeuvre loads"

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

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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 d

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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

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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 conditi

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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

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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 l

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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

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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 comp

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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 b

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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-plan

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Rozprawy doktorskie na temat "Manoeuvre loads"

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 representativ

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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

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Książki na temat "Manoeuvre loads"

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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Części książek na temat "Manoeuvre loads"

"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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Streszczenia konferencji na temat "Manoeuvre loads"

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 differen

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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

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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 cra

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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 integr

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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

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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 indicat

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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 an

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