• 专利附录
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    • 专利摘要:
    Device (10, 20, 30, 40) for reproduction and simulation of actions and aerodynamic and inertial loads configured to be coupled to the test model of a supporting structure (11), such that said supporting structure (11) comprises a support (12) and a base structure (13), and thus study the dynamic response of the base structure (13) or of the load-bearing structure (11) before wind actions and forces of inertial origin, comprising: - at least two propulsion units (24, 34, 44) comprising a propulsion propeller (25, 35, 45) and a motor (26, 36, 46); - a central frame (27, 37), comprising at least one arm (28, 38) and a central support (29, 39); - and an additional control system configured to individually control the speed of each motor (26, 36, 46) and its propulsion propeller (25, 35, 45). (Machine-translation by Google Translate, not legally binding)
    公开号:ES2632187A1
    申请号:ES201700010
    申请日:2016-12-28
    公开日:2017-09-11
    发明作者:Raúl；GUANCHE GARCÍA；Claudio GÓMEZ MARTÍNEZ
    申请人:Fundacion Ih；Fund Ih；Vazquez Y Torres Ingenieria；Universidad de Cantabria；
    IPC主号:
    专利说明:

     5 10 15 20 25 30 DEVICE FOR REPRODUCMING AND SIMULATING AERODYNAMIC AND INERTIAL ACTIONS AND CHARGES FIELD OF THE INVENTION / TECHNICAL FIELD The present invention belongs to the field of test instrumentation, and specifically to the instruments or devices that reproduce and simulate loads and external actions (aerodynamic and inertial) that affect the test model of a supporting structure, BACKGROUND OF THE INVENTION Advances in technology allow addressing the manufacture of structural solutions for increasingly complex applications.  The calculation and sizing of advanced structures for special applications, requires tools and computational calculation models whose results must be accompanied by tests.  These tests allow validating the calculation models and the results obtained, and predicting the behavior of a structure design before proceeding to its materialization.  These tests are particularly relevant when the behavior of a structure must be modeled against actions of difficult quantification, such as aerodynamic loads, hydrodynamic loads, inertial loads and their combination.  An example of this is the wind sector, which is moving towards technological solutions that allow the implementation of production systems in marine or Jshore locations through floating structures or structures fixed to the seabed, to validate the dynamic behavior of the designs of these structures and their models of predictive calculation, tests are performed, preferably scaled according to5 10 15 20 25 30 Froude's law, in which models of the structures are subjected to external actions that reproduce the charges that occur in real conditions of service and throughout the useful life of the structure.  Said charges have an aerodynamic nature derived from the actions that the wind generates mainly on the bearing structure and the elements that it supports (rotor of an turbine in the case that the bearing structure is an aeroturbine tower), and a hydrodynamic nature derived of the incidence of currents and waves when the structure is ojJshore or marine.  The systems of reproduction of hydrodynamic loads, currents and waves such as those described in the article ["Design of a multidirectional wave and current tank for reduced, intermediate and indefinite depths", written by C. are known and technologically mature.  Vidal P.  Lomónaco, R.  Medina, JJ Losada as a summary of the CAC-2007-28 project of the Ministry of Science and Innovation of the Government of Spain}, based on tanks or channels of waves and currents.  The aerodynamic load reproduction systems are also known and technologically mature.  Specifically, this aerodynamic load reproduction technology is based on wind tunnels, such as those described in ["Low Speed Wind Tunnel Testing" BARLOW.  B.  J; RAE W H, POPE A.  (1999), Technical University of Prague].  However, the solutions capable of reproducing aerodynamic loads and hydrodynamic loads are very poorly developed or very incipient.  This is because the integration of a conventional wind tunnel over a tank or swell channel as described in the article ["Ocean-atmosphere interaction channel (C1AO)" of S.  Grandson of the Group of Dynamics of Environmental Flows (GDFA).  Interuniversity Research Institute of! Sistema Tierra of the University of Granada], is an excessively complex option from a technical and economic point of view, in addition to presenting significant limitations such as the5 10 15 20 25 30 simulation of the entire spectrum of combined actions of wind loads, waves and currents, in their different directions of incidence of the loads.  As a solution to the inability to integrate a wind tunnel over a tank or wave channel and currents, the systems and devices for the reproduction of aerodynamic loads that can excite a test model, in isolation or simultaneously and in interaction with the wind, are known. hydrodynamic load reproduction systems, as described in the invention patent CN 105003395 A, where the process of testing wind turbine floating structures subject to the joint wave and wind actions of a wind-structure assembly is defined bearing  This invention contemplates the integration of a known amplianlent system and device for the reproduction of aerodynamic loads, which implements a subsystem composed of lmo or several axial fans housed in a fairing structure.  The fairing structure, confines and directs the flow of air generated by the fans, making it affect the test model of the supporting structure and the elements supported by it, or the rotor model of an turbine and its tower when what is intended to test is the supporting structure of said aeroturbine.  However, these fairing structures with integrated axial fans have technical limitations such as the reproduction of uniform winds in space, as well as the reproduction of specific series of turbulent wind or of variable magnitude over time.  In addition to the technical limitations, application restrictions are identified due to their high investment cost and the large size of the infrastructure required for its implementation.  Likewise, the use of fairing structures with integrated axial fans is associated with the development of a complex rotor model of an turbine, as described in the thesis ["Development of a Scale Model Wind Turbine for testing of offshore floating Wind Turbine Systems ", from the Doctor from the University of Maine5 10 15 20 25 30 Heather Rae Martin, year 2011].  The rotor model is integrated over the ton'e model and / or structure.  When exposed to the action of the air source produced by the axial fans of the fairing structure, aerodynamic loads occur on the rotor that are transmitted to the structure model to assess its dynamic response.  However, the results obtained from these tests do not reflect the real response of the structures to aerodynamic action, since as stated in the article ["'RolOr Aerodynamicsfor Tank Testing ofScaledfloating Wind Turbines" published as a result of the European subproject Po. 1D 088 (INNWIND) by José Azcona and Frank Sandner, researchers at the National Center for Renewable Energy CENER and the University of Stuttgart respectively], significant loads such as the aerodynamic torque, or torque in the direction of the incident wind, cannot be reproduced on The test model.  Other devices for the reproduction of aerodynamic loads are also known, as described in the same document "Rotor Aerodynamics for Tank Testing of scaled floating Wind Turbines".  They dispense with fairing structures with integrated axial fans.  For this they replace the rotor model of an turbine with a propeller.  The drive of this drive propeller, governed by a control system, generates a reaction against the surrounding air mass.  The reaction thus generated is equivalent to the aerodynamic thrust that is desired to reproduce, and which is transmitted to the structure model to evaluate its dynamic response.  The latter being the most economical device with the capacity to reproduce aerodynamic thrusts associated with turbulent wind series, neither does it solve the reproduction of significant aerodynamic stresses such as aerodynamic moments.  It is concluded that the existing systems and solutions in the state of the art for5 10 15 20 25 30 reproduce aerodynamic loads and do so if possible within a tank or swell channel, they are able to reproduce with certain precision thrust forces or drag forces, that is, forces in the direction of incidence of wind that It wants to reproduce.  However, these systems do not accurately reproduce the thrust forces caused by turbulent winds, which vary over time.  Nor are they capable of accurately and reliably reproducing other loads of aerodynamic origin, such as moments of aerodynamic origin, and especially moments in the direction of the incident wind, and greatly, when the elements carried by the structure are in motion with respect to it. .  On the other hand, as a consequence of the swell actions, the structures exposed to these actions can present relative movements that give rise to inertial loads.  If the floating structures carry elements in motion relative to them, such as the rotor of a rotating turbine, these inertial forces become complex, giving rise to gyroscopic moments etc.  These inertial loads have an influence on the dynamic response of the supporting structure under study, and it is necessary to be able to reproduce them to obtain more reliable tests.  There is no integral solution with the capacity to reproduce all the components of a load of aerodynamic origin and that simultaneously can reproduce all loads of inertial origin that occur in the test model of a structure.  SUMMARY OF THE INVENTION The present invention seeks to solve the aforementioned drawbacks by means of a device for reproducing and simulating actions and loads5 10 15 20 25 30 aerodynamic and inertial configured to fit the test model of the supporting structure, such that said bearing structure comprises support and a base structure, and thus study the dynamic response of the base structure or of the bearing structure before the actions of wind and forces of inertial origin, comprising: -at least two propulsion units which in turn comprise a propulsion propeller blade and a motor, such that the propulsion propeller is fixed to the motor rotor and is driven by said engine; -till central frame configured to provide physical support to the propulsion units and allow transmission of the reaction force generated by said propulsion units to the model of the bearing structure to be tested, which comprises at least till arm and lm sop0l1e central, such that each arm is attached to the central support, such that each propulsion unit is attached to the arm, two or more propulsion units may exist in the same arm, and such that the central support and the arms form a structurally rigid conjtillto; - and an additional control system configured to individually govern the speed of each engine and its propulsion propeller so that said control system governs the reaction that each propulsion propeller generates on the surrounding mass of air and the force transmitted to the central frame, and through it, the force and momentum that it transmits to the test model of the supporting structure; the reference system of the device being the one that considers the X axis, till an axis that crosses the central frame with the supporting structure, has a direction parallel to that of the predominant wind whose actions are desired to reproduce; to the Z axis a vertical axis that passes through the center of the center frame with the test bearing structure; and to the Y-axis, till horizontal axis perpendicular to the XyZ axes.  In a possible embodiment, the base structure is a floating structure located in flotation and configured to study the dynamic interaction of aerodynamic and inertial forces, with the hydrodynamic forces originated by the liquid flotation medium.  Alternatively, the base structure is a structure fixed to the bottom of a liquid medium in a rigid or elastic manner and configured to study the dynamic interaction of aerodynamic and inertial forces, with hydrodynamic forces originated by the liquid medium in the one that is partially submerged.  In W1a possible embodiment, the control system is configured so that the force transmitted by the device to the support is the force to which the rotor of an air turbine is subjected.  In W1a possible embodiment, the motors are electric.  In a possible embodiment, the central support and the arms form a single piece that transmits in full the forces generated by the propulsion units.  In one possible embodiment, at least one of the propulsion units has its axis of rotation parallel to the X axis of the normal ortho coordinate system of the device, said implementation being configured to reproduce at least one force in the X direction.  Alternatively, there are at least three propulsion units - preferably four - and at least three propulsion units have their axis of rotation parallel and not coincident with the X axis of the device's orthonormal coordinate system and are distributed in the YZ plane of said system of orthonormal coordinates of the device or in parallel parallel plane lID, said implementation being configured to reproduce the pushing force in the X direction and moments in the directions along the Y and Z axes.  In the possible embodiment, the propulsion qualities are distributed such that the center of mass of the device is coincident with the X axis of the device's orthonormal coordinate system.  In a possible embodiment, an even number of propulsion units have their axis of rotation parallel and not coincident with the Z axis of the OItononnal coordinate system of the device5 10 15 20 25 30 and are distributed in the YZ plane of said normal ortho coordinate system of the device or in a parallel plane and close to it, said implementation being configured to reproduce momentum in the X direction and a force according to the direction Z.  In one possible embodiment, the propulsion units are on both sides of the plane XZ of the orthodox coordinate system J of the device and equidistant to said plane.  In one possible embodiment, the propulsion units are aligned on the Y axis of the orthonomla1 coordinate system of the device.  In one possible embodiment, at least one propulsion unit has such an orientation of the propulsion propeller that generates the positive reaction force of the Z axis of the orthonormal coordinate system of the device, and the at least one propulsion unit generates a negative reaction force of the Z axis of the device's orthonormal coordinate system.  In one possible embodiment, at least one of the propulsion units has its axis of rotation parallel to the Y axis of the normal ortho coordinate system of the device, said implementation being configured to reproduce the force in the Y direction.  In a possible embodiment, said at least one propulsion unit has its axis of rotation coinciding with the Y axis of the orthonormal coordinate system of the device.  BRIEF DESCRIPTION OF THE FIGURES In order to help a better understanding of the features of the invention, in accordance with a preferred example of practical realization thereof, and to complement this description, a set of parts is attached as an integral part thereof. drawings, whose character is illustrative and not limiting.  In these drawings: Figure 1 shows a diagram of the device of the invention coupled to the test model of a supporting structure, according to a possible embodiment.  Figure 10 shows a diagram of the device of the invention, according to a possible embodiment, comprising six propulsion units and Lill central frame.  Figure 3 shows a diagram of the device of the invention, according to another possible embodiment of the invention, comprising three propulsion units and a central frame.  Figure 4 shows 1m scheme of the device of the invention, according to the embodiment of Figure 2, where the forces and moments generated have been represented.  DETAILED DESCRIPTION OF THE INVENTION In this text, the term "comprises" and its variants should not be understood in an exclusive sense, that is, these terms are not intended to exclude other technical characteristics, additives, components or steps.  In addition, the terms "approximately", "substantially", "around", "ones", etc.  they should be understood as indicating values close to which these terms accompany, since due to calculation or measurement errors, it is impossible to achieve those values with complete accuracy.  The following preferred embodiments are provided by way of illustration, and are not intended to be limiting of the present invention.  In addition, the present invention covers all possible combinations of particular and preferred embodiments indicated herein.  For those skilled in the art, other objects, advantages and features of the invention will be derived partly from the description and partly from the practice of the invention.  Next, the device 10 of the invention is described according to a basic scheme thereof depicted in Figure 1, which gives solution to the problems.5 10 15 20 25 30 identified of the current state of the art, and that it is a device for the reproduction and simulation of aerodynamic and inertial actions and loads configured to fit the test model of a bearing structure 11, and thus study the response dynamics of said supporting structure II or of its base structure 13 before wind actions and forces of inertial origin.  The bearing structure 11 comprises a support 12 (for example an aeroturbine tower) and the base structure 13.  In the possible embodiment the base structure 13 is a floating structure (for example a ship or the platform of an aeroturbine) located in flotation and configured to study the dynamic interaction of the aerodynamic and inertial forces, with the hydrodynamic forces originated by the liquid medium of flotation.  In another possible embodiment, the base structure 13 is a structure fixed to the bottom of a liquid medium in a rigid or elastic manner and configured to study the dynamic interaction of the aerodynamic and inertial forces, with the hydrodynamic forces oliginated by the liquid medium in which It is partially sWllergida.  In any case, one skilled in the art will understand that the characteristics of the bearing structure 11 are a function of the designs that are intended to be validated experimentally, being outside the scope of the present invention.  The device 20 of the invention comprises at least two propulsion units 24 which in turn comprise a propulsion propeller 25 and a motor 26, such that the propulsion propeller 25 is fixed to the rotor of the motor 26 and is driven by said motor 26 .  Preferably, the motors are electric.  Figure 2 shows a diagram of the device 20 of the invention formed by six propulsion units 24.  These propulsion units 24 are fixed to a centml frame 27 configured to give physical support to them and allow the transmission of the reaction force generated by said propulsion units 24 to the model of the bearing structure to be tested.  The central frame 27 comprises at least one arm 28 and a central support 29, such that each arm 28 is attached to the central support 29, such that each propulsion unit 24 is joined. gives5 10 15 20 25 30 to one arm 28, two or more propulsion units 24 may exist in the same arm 28, and such that the central support 29 and the arms 28 form a structurally rigid assembly.  In a possible embodiment, the central support 29 and the arms 28 confominate a single piece that fully transmutes the forces generated by the propulsion units 24.  The device 20 of the invention is configured to join the test model of the supporting structure directly through its central frame 27, making use of known mechanical solutions, such as bolted joints.  Figure 3 shows a possible embodiment of the device of the invention, formed by three propulsion units 34, two arms 38 and a central support 39.  The device 10, 20, 30 of the invention further comprises an additional control system configured to individually govern the speed of each engine 26, 36 and its propulsion propeller 25, 35 so that said control system governs the reaction that each propulsion propeller 25, 35 generates on the surrounding air mass and the force that it transmits to the central frame 27, 37, and through it, the force and momentum that it transmits to the test model of the supporting structure 11.  In a possible embodiment, the control system is configured so that the force transmitted by the device 10, 20, 30 to the support 12 is the force to which the rotor of an air turbine is subjected.  As can be seen in Figs. 2 and 3, one skilled in the art will understand that the normal coordinate system of the device 20, 30 is that which considers the X axis, an axis that crosses the junction point of the central frame 27, 37 with the p011 structure, has a direction parallel to that of the prevailing wind whose actions you want to reproduce; to the Z axis a vertical axis that passes through the junction point of the central frame 27, 37 with the test structure; and to the Y axis, a horizontal axis perpendicular simultaneously to the X and Z axes.  In a possible embodiment at least one of the propulsion units 24, 34 has its axis of rotation parallel to the X axis of the orthonormal coordinate system of the device 20, 30,5 10 15 20 25 30 said implementation being configured to reproduce at least the force in the X direction.  The wind action on object W1 generates a drag force or thrust force that is usually one of the most relevant and significant aerodynamic forces.  This force has the same direction as the direction of incidence of the wind.  Having defined the X axis of the orthonormal system, as the axis parallel to the direction of incidence of the wind, in this preferred embodiment the device 20, 30 can reproduce W1a force in this X direction, in order to have the ability to reproduce with the As much reliability as possible, the aerodynamic loads to which objects and their structures are subjected.  Therefore, and because the propulsion units 24, 34, and more specifically the propellers of the propulsion units 25, 35, generate an aerodynamic reaction in the direction of their axis of rotation, if at least one of the units of Propulsion 24, 34 has its axis of rotation parallel to the X axis, the generated reaction force can be equivalent to the drag force or pushing force that the device 20, 30 must reproduce.  In another possible embodiment, there are at least three propulsion units 24, 34 and at least three propulsion units 24, 34 have their axis of rotation parallel but not coincident with the X axis of the orthonormal coordinate system of the device 20, 30 and are distributed in the YZ plane of said orthonormal coordinate system of the device 20, 30 or in a parallel plane and close to it, said implementation being configured to reproduce the thrust force in the X direction and moments in the directions along the Y and z axes .  This arrangement allows to distribute and reproduce high values of aerodynamic forces in the X direction without having to resort to using the single propeller of very large dimensions, since the larger the propeller, the greater its inertia to rotation and the worse the dynamic response, acceleration. and deceleration that allows5 10 15 20 25 30 reproduce aerodynamic forces that vary over time.  It also allows distributing and reproducing high values of aerodynamic forces in the X direction without having to resort to using a single propeller of very high turning speed.  These high speed rotation propellers have a bad dynamic response since they accumulate a large amount of kinetic energy, and they also have a bad dynamic response, taking longer to accelerate and decelerate to reproduce variable aerodynamic forces over time.  The propulsion units 24, 34 with their axes parallel to the X axis, are distributed in a YZ plane or one parallel to it, so that the scanning areas of all the propellers 25, 35 remain in the same plane.  This configuration allows reducing aerodynamic wake interference, which some propellers 25, 35 generate over others, facilitating the control of the device 20, 30 and its accuracy when reproducing loads.  In another order, and as seen in Figure 4, the consideration of a minimum of three propulsion units 44 with its axis parallel to the X axis pennite reproduce, not only a resulting thrust force according to the X direction, but two moments according to the y address and the Z address.  Since the propulsion units 44 are distributed in the YZ plane, and none of them coincide with the X axis, each of them generates a thrust force Fxi, a Myi moment and an Mzi moment, where: Fxi depends on the speed with which the engine 46 is governed.  Myi = Fxi.  dzi, where dzi is the distance between the axis of rotation of the propeller unit 45 and the coordinate axis Y.  Mzi = Fxi.  dxi, where dxi is the distance between the axis of rotation of the propeller unit 45 and the coordinate axis Z.  The joint action of the propulsion units 44 allows the device 40 to jointly generate a resulting thrust force and two moments according to the Y and Z direction.  5 10 15 20 25 3 Fx = L (FXi) i = l 3 3 My = L (MYi) = L (FXi.  dzi) i = l i = l 3 3 Mz = L (MZa = L (FXi 'dya i = l i = l This defines a determined system of three equations with three unknowns.  The parameters dzi and dyi are fixed values depending on the location of the propulsion units 44.  Thus, in order for the device 40 of the invention to reproduce a load Fx, My and Mz according to needs (variables), it is sufficient to excite each propulsion unit 44 to reproduce txi force Fxi (unknowns of the system of equations).  In the preferred embodiment, the device can integrate four propulsion units 44, distributed in the same YZ plane and with its parallel axis and not coincident with the X axis.  This configuration makes it possible to establish a system of three equations with four unknowns, which defines a system of infinite solutions.  From these infinite solutions a logic is established to select those in which the force of each propulsion unit Fxi of all the propulsion units 44 has the same meaning.  In this way it becomes possible to govern the device 40 so that the wake of all the propulsion units 44 has the same meaning and does not interfere with each other in a negative manner, increasing the precision of the reproduced forces.  In a preferred embodiment, the propulsion units 24, 34, 44 are distributed in forola such that the center of mass of the device 10, 20, 30, 40 is coincident with the X axis of the orthonormal coordinate system of the device 10, 20, 30  This distribution allows the trails of the different propulsion units 24, 34, 44 to be distributed as uniformly and symmetrically as possible to minimize5 10 15 20 25 unwanted interactions and interferences between them that disturb the precision of the forces to be reproduced.  In a preferred configuration, the device of the invention 10,20, 30, 40 incorporates an even number of propulsion units 24, 34, 44 with their axis of parallel rotation and not coincident with the Z axis of the orthon coordinate system of the device 10 , 20, 30,40, being distributed in the YZ plane of said orthon coordinate system of the device 10,20,30,40 or in a parallel plane and close to it.  By providing said propulsion units 24, 34, 44 their axis of rotation parallel to the Z axis, they generate reaction forces according to said direction.  On the other hand, since the propulsion units 24, 34, 44 are distributed on a YZ plane, said forces cannot generate moments on the Y and Z axes, since the distance of the vectors forces the Y axis is zero, and by therefore, the My moment generated, and the direction of the force is parallel to the Z axis, so that it cannot generate momentum on said axis.  However, said force Fz of the units described, can generate a torque with respect to the X axis of the OItonormal reference system of the device 10, 20, 30, 40, since they are not parallel to said X axis and do not cross it. .  The incorporation of at least two propulsion units 24, 34, 44 with their parallel axis and not coinciding with the Z axis makes it possible to establish the following system of equations: i ~ 2 Fz = L (FZi) i = li ~ 2 i ~ 2 Mx = L (MXi) = L (Fzi.  dYi) i = l i = l A system of two equations with at least two unknowns, which makes it possible to reproduce a resulting force according to the Z direction, and a moment according to the X direction.  This5 10 15 20 25 30 moment according to the X direction, or moment according to the direction of incidence of the wind, is of great importance and influence in the dynamic behavior of some bearing structures, as is the case of the turbines.  Specifically, the aerotubins are subjected to an aerodynamic moment or moment on an axis parallel to the direction of the incident wind and passing through the center of the rotor.  This moment has a significant weight in the dynamic behavior of the entire wind turbine bearing structure and, however, current solutions are not able to reproduce it.  With the arrangement described for the preferred embodiment, a moment Mx and a force Fz can be reproduced if necessary.  In a specific and preferred configuration of the invention, the propulsion urges 24, 34, 44 with their axis of rotation parallel to the Z axis are on both sides of the plane: xz of the orton0l111a1 coordinate system of the device 10, 20, 30, 40, And preferably, they are equidistant to said plane.  This arrangement is made to minimize the interference of the wake of the propulsion units 24, 34, 44 described and that, as far as possible, present a wake symmetry that may have a device 10, 20, 30, 40 more balanced capable of reproducing loads with greater precision.  Furthermore, also in a specific and preferred configuration of the invention, the propulsion units 24, 34, 44 with their axis of rotation parallel to the Z axis of the coordinate system, are aligned on the Y axis of the orthonormal coordinate system of the device 10 , 20, 30, 40 so that the interference of the wake of these units with the trails of other propulsion units 24, 34, 44, such as the propulsion units 24, 34, 44 with their axis of rotation parallel to the X axis of the ortononnal reference system, be minimal and symmetrical as far as possible, in order to minimize wake interference and reproduce loads as accurately as possible.  In this particular case in which the propulsion units 24, 34, 44 have their axis of rotation parallel to the Z axis, in a possible embodiment at least one propulsion unit 24, 34, 44 has an orientation such of the propulsion propeller 25, 35, 45 which generates a positively reactive reaction force of the Z axis of the normal orthographic coordinate system of the device, and in addition the at least one propulsion unit generates a negative negative reaction force of the Z axis of the orthonormal coordinate system of the device 10, 20, 30, 40.  In numerous application cases, such as in the simulation of aerodynamic loads incident on the rotor of an turbine, the force Fz that must be reproduced is of very small or zero value, while the value of the moment Mx has a high magnitude.  In that case, to achieve the condition: i ~ 2 Fz = ¿cFZa == ° i = l in addition to having at least one propulsion unit 24, 34, 44 on each side of the XZ plane, it is necessary that they develop forces in opposite directions so that the resultant of the forces contrasts themselves, while the moments of each of the forces generated by the different propulsion units 24, 34, 44 are solved.  So far, with a combination of the configurations described, the device of the invention 10, 20, 30, 40 allows to develop forces according to the direction of the X axis and moments according to the directions Y and Z, but also forces according to the direction Z and moments according to the X direction.  To complement the versatility of the device 10,20,30, and that it has the capacity to reproduce loads according to the Y direction, in a possible embodiment it is proposed to integrate at least one propulsion unit 24, 34, 44 with its axis of rotation parallel to the Y axis of the orthonormal coordinate system of the device 10,20, 30.  This configuration allows the reproduction of a force according to the Y direction.  If the drive shaft5 10 15 of propulsion 24, 34, 44 is parallel but not coincident with the Y axis, the force generated Fy, in addition to force, generates moments Mx and Mz as a function of the distance from the axis of the propulsion unit 24, 34, 44 to the respective axes.  In this preferred embodiment of the invention, the moments Mx and Mz generated by the propulsion units 24, 34, 44 with a rotation axis parallel to the Y axis, must be compensated by the remaining existing propulsion units 24, 34, 44 if its value does not correspond to the one that must be reproduced instantly.  To avoid the need for load compensation, in the preferred embodiment of the invention, the propulsion unit or units 24, 34, 44 with their axis of rotation parallel to the Y axis of the orthonolmal coordinate system, are located so that the axis of rotation coincides with the Y axis.  In this way, said propulsion units 24, 34, 44 with their axis of rotation parallel to the Y axis reproduce entirely Y component forces, and not moments that have to be compensated by the other propulsion units 24, 34, 44 to that the resulting forces and moments correspond to the desired one.   
    权利要求:
    Claims (16)
    [1]
    5 10 15 20 25 30 CLAIMS l. Device (10, 20, 30, 40) for reproducing and simulating aerodynamic and inertial loads and actions configured to be coupled to the test model of a bearing structure (11), such that said bearing structure (11) comprises a support (12) and a base structure (J 3), and thus study the dynamic response of the base structure (13) or the bearing structure (11) to the actions of wind and inertial forces, characterized in that it comprises: -at least two propulsion units (24, 34, 44) comprising in turn a propulsion propeller (25, 35, 45) and a motor (26, 36, 46), such that the propulsion propeller (25, 35, 45 ) is fixed to the rotor of the motor (26, 36, 46) and is driven by said motor (26, 36, 46); -a central frame (27, 37) configured to give physical support to the propulsion units (24, 34, 44) and allow the transmission of the reaction force generated by said propulsion units (24, 34, 44) to the model of the bearing structure (11) to be tested, comprising at least one arm (28, 38) and a central support (29, 39), such that each arm (28, 38) is attached to the central support (29, 39) , such that each propulsion unit (24, 34, 44) is attached to an arm (28, 38), with two or more propulsion units (24, 34, 44) being able to exist on the same arm (28, 38), and such that the central support (29, 39) and the arms (28, 38) form a structurally rigid assembly; -and an additional control system configured to individually govern the speed of each motor (26, 36, 46) AND its propulsion propeller (25, 35, 45) so that said control system governs the reaction that each propeller of propulsion (25, 35, 45) generates on the surrounding air mass and the force that it transmits to the central frame (27, 37), and through it, the force and moment that it transmits to the test model of the bearing structure (11 ); being the reference system of the device (10, 20, 30, 40) that which considers the X axis, an axis that, passing through the junction point of the central frame (27, 37) with the supporting structure (11), has a direction parallel to that of the prevailing wind whose5 10 15 20 25 30 actions are desired to reproduce; to the Z axis a vertical axis passing through the point of attachment of the central frame (27, 37) with the test bearing structure (11); and to the Y axis, a horizontal axis perpendicular simultaneously to the X and Z axes.
    [2]
    2. The device (10, 20, 30, 40) of claim 1, where the base structure (13) is a floating structure located in buoyancy and configured to study the dynamic interaction of the aerodynamic and inertial forces, with the hydrodynamic forces originated by the liquid flotation medium.
    [3]
    3. The device (10,20,30,40) of claim 1, wherein the base structure (13) is a structure fixed to the bottom of a liquid medium in a rigid or elastic way and configured to study the dynamic interaction of forces aerodynamic and inertial, with the hydrodynamic forces originated by the liquid medium in which it is partially submerged.
    [4]
    4. The device (10,20, 30, 40) of any of the preceding claims, wherein the control system is configured so that the force transmitted by the device to the support (12) is the force to which the rotor of a wind turbine.
    [5]
    5. The device (10,20,30,40) of any of the preceding claims, wherein the motors (26, 36, 46) are electric.
    [6]
    6. The device (10, 20, 30, 40) of any of the preceding claims, wherein the central support (29, 39) and the arms (28, 38) form a single piece that fully transmits the forces generated by the units propulsion (24, 34, 44).
    [7]
    The device (10, 20, 30, 40) of any of the previous claims, wherein at least one of the propulsion units (24, 34, 44) has its axis of rotation parallel to the X axis of the ortho coordinate system normal device (J 0, 20, 30, 40), said implementation being configured to reproduce at least W the force in the direction5 10 15 20 25 30 x.
    [8]
    The device (10, 20, 30, 40) of any of claims 6, wherein there are at least three propulsion units (24, 34, 44) AND where at least three propulsion units (24, 34, 44 ) have their axis of rotation parallel and not coincident to the X axis of the device's orthonomla1 coordinate system (10, 20, 30, 40) And they are distributed in the YZ plane of said device's orthonormal coordinate system (10, 20, 30 , 40) or in a 1m plane parallel and close to it, said implementation being configured to reproduce the thrust force in the X direction and moments in the directions along the Y and Z axes.
    [9]
    The device (10, 20, 30, 40) of the preceding claim, wherein the propulsion units (24, 34, 44) are four.
    [10]
    The device (10, 20, 30, 40) of any of the preceding claims, wherein the propulsion units (24, 34, 44) are distributed such that the center of mass of the device (10, 20, 30 , 40) is coincident with the X axis of the Oltonormal coordinate system of the device (10, 20, 30, 40).
    [11]
    The device (10, 20, 30, 40) of any of the preceding claims, wherein an even number of propulsion units (24, 34, 44) have their axis of rotation parallel and not coincident with the Z axis of the drive system. orthonormal coordinates of the device (JO, 20, 30, 40) and are distributed in the YZ plane of said oltononnal coordinate system of the device (10, 20, 30, 40) or in a plane parallel and close to it, said implementation being set to reproduce a moment in the X direction and 1st force in the Z direction.
    [12]
    The device (10, 20, 30, 40) of the preceding claim, wherein the propulsion units (24, 34, 44) are on both sides of the XZ plane of the orthonormal coordinate system of the device (10,20,30 , 40) And equidistant from said plane.5 10 15 20
    [13]
    The device (10, 20, 30, 40) of any one of claims JI to 12, wherein the propulsion units (24, 34, 44) are aligned on the Y axis of the orthonomlal coordinate system of the device (10, 20, 30, 40).
    [14]
    The device (10,20,30,40) of any of claims I1 to 13, wherein at least one propulsion unit (24, 34,44) has such an orientation of the propulsion propeller (25, 35, 45) that generates a reaction force in the positive direction of the Z axis of the device's orthonormal coordinate system (JO, 20, 30, 40), and where the at least one propulsion unit (24, 34, 44) generates a force reaction in the negative direction of the Z axis of the orthonnal coordinate system of the device (10, 20, 30, 40).
    [15]
    The device (10, 20, 30, 40) of any of the preceding claims, wherein at least one of the propulsion units (24, 34, 44) has its axis of rotation parallel to the Y axis of the ortononnal coordinate system of the device (10, 20, 30, 40), said implementation being configured to reproduce the force in the Y direction.
    [16]
    16. The device (10, 20, 30, 40) of the preceding claim wherein said at least one propulsion unit (24 34, 44) has its axis of rotation coincident with the Y axis of the orthonormal coordinate system of the device (10 , 20, 30, 40).
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    同族专利:
    公开号 | 公开日
    ES2632187B1|2018-06-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CN2926035Y|2006-03-10|2007-07-25|中国海洋石油总公司|Two-freedom wind-making system|
    KR20110007671A|2009-07-17|2011-01-25|태창엔이티 주식회사|A appratus for wind tunnel testing of wind power generator with large size blade|
    KR101684459B1|2016-04-06|2016-12-09|한국해양과학기술원|Wind load test equipment for wind turbines|
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