JP2005249614A - Load reduction system and model used for the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a technique which allows a test under a high Reynolds number state by increasing the internal pressure of a wind tunnel and prevents a model from receiving an unreasonable load through aerodynamic force acting on the model in the test, without upsizing the wind tunnel and the model. <P>SOLUTION: The aerodynamic load reduction mechanism includes means for generating a desired magnetic field in a testing area within the wind tunnel and uses a technique which distributes magnetic moments within the model in advance so that a model part (a wing), which receives a load through external force (aerodynamic force) and is likely to be deformed, is acted upon by magnetic force in the direction attaining a balance with the external force. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention is a technique for reducing a load applied by an external force acting on a structural model, particularly a technique suitable for reducing a model deformation caused by an aerodynamic load applied to a model in a wind tunnel test, and a device for preventing a model breakage and its use Regarding the model.

  Conventionally, in order to obtain the aerodynamic characteristics of an object with a model, it has been generally performed to support the model with a support member in the measurement section of the wind tunnel equipment, but the support member itself has an influence on the air flow on the model surface. As a result, the test results cannot be directly adopted as the aerodynamic characteristics of the model, and corrections accordingly must be made. Therefore, it has been proposed to support the model with a magnetic force which is a non-structural means in the wind tunnel test. Since the mechanical support member is not required by magnetically supporting the model, the aerodynamic influence on the model due to the presence of the support member can be eliminated. The magnetic support balance device, which is a means of magnetically supporting this model, has static or dynamic aerodynamic characteristics such as lift, drag, pitching (pitch) moment, etc. that the airflow flowing around the model acts on the model in the wind tunnel test. In order to generate a magnetic force that interacts with the magnet provided inside the model, it is a device that measures by replacing the magnitude of the current that flows through the coil provided on the wind tunnel side. (Refer to Patent Document 1 and Non-Patent Document 2) That is, the support mechanism detects that the model has changed from the initially set position / orientation with respect to the change in airflow, and the current flowing through the coil to maintain the initial state. This is a measurement by the so-called zero method in which the magnetic force is balanced by control. Know the aerodynamic characteristics acting on the model by measuring the coil current by investigating the relationship between the aerodynamic force and the magnitude of the coil current and preparing the correspondences such as maps, functions, and tables as data in advance. Can do.

  With reference to FIG.4 and FIG.5, the outline | summary of a magnetic support type wind tunnel and a magnetic support balance apparatus is demonstrated. FIG. 4 is a perspective view showing the basic configuration of the magnetic force support type wind tunnel and the magnetic force support balance device, and FIG. 5 is a conceptual diagram showing a power supply system and a measurement system used in the magnetic force support type wind tunnel and the magnetic force support balance device. The magnetic support balance device 20 shown in FIG. 4 is a device that supports the wind tunnel model 1 in the airflow with magnetic force, and can realize a wind tunnel test without support interference. The wind tunnel model 1 is equipped with a strong magnet body made of a magnetized material, a coil that continues to pass a current such as a superconducting coil, or a permanent magnet. The magnet body 1a of the wind tunnel model 1 receives a magnetic force due to a mutual magnetic action with an external magnetic field generated by energizing the coils 23 to 32 arranged around the measurement portion of the wind tunnel. Can be levitated and supported. The external magnetic field is composed of two magnetic circuits 21 and 22 each having a predetermined distance in the axial direction of the wind tunnel including coils 23 to 26 and coils 27 to 30 as magnetic support coils, and the two magnetic circuits arranged outside the two magnetic circuits 21 and 22. It is generated by air-core coils 31 and 32 which are also perpendicular to the circuits 21 and 22 and are also magnetic support coils. When the airflow direction in the wind tunnel is taken as the x-axis, the vertical direction in which gravity acts is the z-axis, and the y-axis is taken in the direction perpendicular to the x-axis and z-axis, the magnetic circuit 21 generates a z-axis direction magnetic field 1 A pair of coils 23 and 25 and a pair of coils 24 and 26 for generating a magnetic field in the y-axis direction, and a magnetic circuit 22 generates a magnetic field in the Y direction with a pair of coils 27 and 29 for generating a Z-direction magnetic field. It comprises a pair of coils 28 and 30 to be generated. By adjusting the current flowing in each coil of the magnetic circuits 21 and 22, the strength and direction of the magnetic field in the yz plane in the magnetic circuits 21 and 22 and the rate of change in the x-axis direction are continuously changed. Can be made. In addition, by adjusting the current flowing through the air-core coils 31 and 32, the rate of change of the strength of the magnetic field in the x-axis direction as viewed in the x-axis direction can be controlled, so that 5-axis control is possible. That is, the coils 23 to 30 of the magnetic circuits 21 and 22 function as a lift coil that applies a magnetic force that opposes the lift and pitching moment acting on the wind tunnel model 1, and the air-core coils 31 and 32 are provided on the wind tunnel model 1. It functions as a drag-resistance coil that provides a magnetic force against the working drag.

  In the wind tunnel, in addition to the wind tunnel model 1 and the coils 23 to 32, a power supply system that drives each coil, a measurement system that measures the position and posture of the wind tunnel model 1, and the position and posture of the wind tunnel model 1 are controlled. A control system is incorporated. As shown in FIG. 5, measurement data relating to the position / orientation of the wind tunnel model 1 detected by, for example, the camera 33 or the like in the measurement system is transmitted to the arithmetic control means 34 such as a personal computer. A current value to be passed through each coil necessary for maintaining the posture is calculated based on the relational data between the accumulated aerodynamic force and the magnitude of the coil current. After the calculation result is amplified by the current supply means 35, a controlled drive current is supplied to each of the coils 23-32.

In a magnetic support type wind tunnel device, as shown in FIG. 6, a straight rod-like strong permanent magnet 40 is usually used as a magnet body provided inside the model 1 to support the model 1 with magnetic force. In many cases, the longitudinal axis is arranged along the central axis of the model. The force that lifts the permanent magnet 40 vertically upward includes the magnetic moment held by the permanent magnet 40 and the magnet axial direction of the magnetic strength component directed vertically upward around the permanent magnet of the magnetic field generated by the magnetic circuits 21 and 22. It is represented by the product of That is, if x is the longitudinal axis of the permanent magnet 40 (usually coincides with the center axis of the model), Mx is the magnetic moment held by the permanent magnet 40, and Hz is the magnetic strength going vertically upward, The vertically upward magnetic force Fz trying to lift the magnet 40 is expressed by the following equation. The magnetic force Fz balances with the gravity mg acting on the model 1 so that the model 1 can be levitated in the airflow in the wind tunnel. The force equation is given by
Fz = Mx × (∂Hz / ∂x) = mg

When performing a test on an aircraft model or the like using such a magnetic support type wind tunnel and a magnetic support balance device, it may be required to obtain a high Reynolds number in the wind tunnel test. One way to deal with this is to increase the wind tunnel pressure. When the wind tunnel internal pressure is increased, the aerodynamic force applied to the model increases in proportion to the internal pressure, and there is a risk of deforming or damaging the model. Therefore, there is an upper limit for the wind tunnel internal pressure. In transonic wind tunnels, the limit is 5 bar, and in tests with a two-dimensional wing model between measurement walls, the risk of model damage increases at about 12 bar. In order to further increase the wind tunnel internal pressure and perform a test with a high Reynolds number, it is necessary to develop a method for reducing the aerodynamic load applied to the model. Another way to obtain a high Reynolds number is to increase the size of the model. However, increasing the size of the model requires a large wind tunnel facility that corresponds to the model, and the construction cost and maintenance of the wind tunnel facility. The cost will be enormous. Therefore, it is difficult to implement this method, and it is necessary to cope with the former method. To that end, it is strongly demanded to develop some method for reducing the aerodynamic load as described above.
JP 2003-344215 A "Wind Tunnel Model Magnetic Support Balance" Published on December 3, 2003 Hideo Sawada, Tetsuya Kunimasu: "Development of a 60cm magnetic support system for low-speed wind tunnels," Japan Aerospace Society Proceedings, Vol. 50, No. 580, May 2002, pp.188-195

  The problem to be solved by the present invention is that it is possible to test a high Reynolds number state by increasing the internal pressure of the wind tunnel without increasing the size of the wind tunnel and the model. The purpose is to present a technique for preventing the load.

The load reducing mechanism of the present invention is provided with means capable of generating a desired magnetic field in a test region such as in a wind tunnel, so that a magnetic force acts in advance in a direction that balances with a model portion that is easily loaded and deformed by an external force. The technique of distributing the magnetic moment in the model was adopted.
In aircraft models, magnetic moments are distributed over the wings, and in models where the model is stretched between the measurement walls (two-dimensional test) or in models where the model is installed on the wind tunnel wall, the wind tunnel test model is easily deformed by the aerodynamic force. The magnetic moment is distributed in advance in the model so that the magnetic force acts on the portion in the direction in which it is balanced.
The aerodynamic load reducing device according to the present invention calculates and outputs a coil that generates a magnetic field in a model installation region in a wind tunnel and a current value that generates a magnetic force necessary to cancel the distortion detection signal of the model. Calculation control means and means for amplifying the calculation value and supplying current to the magnetism generating coil are provided.
The aerodynamic load reducing device of the present invention uses a magnetic support balance device as a means for supporting the model, and superimposes the magnetic force for eliminating the overload on the model in addition to the original magnetic force for supporting the model. To act.
Furthermore, the present invention was applied to a stress test of a structure, and the load reducing mechanism was widely applied to the apparatus and model.

  The load reducing device of the present invention employs a technique in which a magnetic moment is distributed in advance in a model so that a magnetic force acts in a direction that balances with a portion of a model that is easily deformed by aerodynamic force in a wind tunnel test. As a result, a strong aerodynamic force was applied in a wind tunnel test with a high Reynolds number in which the wind tunnel internal pressure was high, and balance was applied with a reverse force so that overload would not be applied to parts that are easily deformed or damaged. Can prevent deformation and breakage of the model. Therefore, it was able to withstand the wind tunnel test under high pressure, and it was possible to perform a wind tunnel test with a high Reynolds number without increasing the size of the wind tunnel equipment or model.

Moreover, since the aerodynamic load reducing device of the present invention comprises a means for detecting distortion or stress of the model and a means for generating a magnetic force in a direction to suppress it when the model is subjected to a wind tunnel test. Since the magnetic force can be appropriately applied so as to cancel the load caused by the aerodynamic load, the model can be prevented from being deformed or damaged.
Furthermore, the aerodynamic load reducing device of the present invention adopting a configuration in which a magnetic support balance device is used as means for supporting the model and the magnetic force and the magnetic force for eliminating the overload on the model are applied in an overlapping manner. Even if a new wind tunnel facility is not prepared, it is sufficient to control the current value to the coil for generating the magnetic field so as to eliminate the overload and support of the model, and the conventional magnetic support type wind tunnel can be used as it is.

  The load reduction mechanism of the present invention is not limited to the wind tunnel test, and can be widely applied to the stress test of structures. Therefore, it can be applied to structure models such as airfoils, bridges, and towers equipped with high lift devices. When applied, the conventional load test could only measure the stress up to the point of failure when the model can withstand the load, but the stress measurement range can be greatly updated by balancing the external force with the magnetic force.

  The inventors of the present invention have been working on a magnetically supported wind tunnel, but when conducting a test with a high Reynolds number with a high pressure inside the wind tunnel, this technique is used to create an air rather than a model body part. If the magnetic moment is distributed so that the magnetic force acts on the most deformable part under the force, the magnetic force that supports the model is generated in the vicinity to suppress the deformation of the model, the model will be deformed or damaged. I came up with the idea that we should be able to prevent this. At the same time, not only wind tunnel test models floating in the air, such as aircraft, but also overload tests for structures such as wing types, bridges, towers and other easily deformable models equipped with high lift devices. In addition, the inventors have come up with the idea that this method can be widely used. In this case, an expensive model position / orientation sensor is not required, and the deformation of the model due to aerodynamic load can be suppressed by controlling the surrounding magnetic field using a signal from a sensor that measures model distortion, etc., provided outside the measurement unit. I also realized that I can do it. The magnetic field control device in this case can be greatly simplified as compared with the control device of the magnetic force support balance device.

  FIG. 1 shows a basic configuration of an aerodynamic load reducing device of the present invention. Reference numeral 2 denotes a magnetic field control coil or magnet for generating a magnetic field in the region where the test model 1 is installed, which is the same as that shown in FIG. In the wing of the model 1, magnetic lines of force are oriented in the x-axis direction, and the magnet 1a is elongated in the longitudinal direction of the wing. Reference numeral 4 denotes a strain sensor attached to a key point of the model 1 and detects the strain received by the model 1 by an external force (aerodynamic force). The detection signal of the strain sensor 4 is sent to the calculation control means 34, and the calculation control means 34 calculates a current value that generates a magnetic force sufficient to cancel the distortion applied to the model 1 in the magnetic field control coil or magnet 2. And the operation value signal is sent to the current supply means 35. The current supply means 35 amplifies the received calculation value signal and supplies a control current to the magnetic field control coil or magnet 2. When a control current is supplied from the current supply means 35 to the coil or magnet 2 for controlling the magnetic field, a new magnetic field is formed in the region where the test model 1 is installed, and the magnets 1a arranged in the model 1 are respectively connected. It receives the magnetic moment and acts to balance the external force (aerodynamic force) received by the model wing 1w to reduce the distortion of the wing 1w.

When a model 1 of an aircraft with a wing 1w attached to a fuselage 1b as shown in FIG. 2A is placed in a wind tunnel in a sting support and tested in a high Reynolds number state, the maximum stress generated at the root of the sting Is expressed by the following equation (1).
σ _max ∝ [λb ² / d ³ A] · f (M) · P ₀ · C _L (1)
Where λ is the distance between the representative force point position of the lift L and the sting root, A is the model aspect ratio, b is the blade span, d is the thickness dimension of the sting, P ₀ is the wind tunnel total pressure, and C _L is the lift coefficient. . When the test in the high Reynolds number state is performed, the structurally weak blade 1w portion is greatly bent as shown in FIG. The maximum stress applied to the wing root portion can be expressed in the same manner as the above equation (1). In this case, however, d is the thickness dimension of the blade, and λ is the distance between the representative power point position of the lift in the blade and the blade root position, which is approximately b / 4. The Reynolds number can be increased by increasing the wind tunnel working gas pressure and increasing the density, but the aerodynamic force applied to the model increases in proportion to the density, and if the wind tunnel pressure exceeds 5 bar, the model wing may be bent. Therefore, in the present invention, two sets of coils of 23, 25, 27, and 29 for generating an aircraft model in which magnets are arranged in the wing portion and a magnetic field in the z-axis direction arranged at predetermined intervals in the x-axis direction as shown in FIG. Alternatively, an aerodynamic load reducing device composed of a magnet is used to detect the aerodynamic strain received by the model 1 with a strain sensor 4 attached to a key point of the wing 1w, and a current corresponding to the distortion amount of the wing is supplied to the aerodynamic load reducing device. And the magnetic force was changed to balance the aerodynamic force and magnetic force applied to the model as shown in FIG. The magnetomotive force nJ at that time is as follows.
I _x · V · nJ / H ² ∝ q · b ² · C _L / A
nJ∝ [b ² H / AI _x V] · f (M) · H · P ₀ · C _L (2)
Here, I _x is the strength of magnetization in the air flow direction, V is the magnet volume in the model, H is the height of the measurement part, q is the dynamic pressure, n is the number of coil turns, J is the coil current, and the product nJ Becomes the magnetomotive force. Since the magnetomotive force nJ refers to the ability of the magnetic suspension balance device 20 capable of supporting a model 1 against the air force, this value is proportional to the product of the measurement section height H and the wind tunnel total pressure P _0.

On the other hand, the Reynolds number Re is expressed by the following equation.
Re = g (M) · T ₀ ^−1.4 · P ₀ · H (3)
Here, T ₀ is the wind tunnel temperature. It should be noted that if the Mach number and temperature are constant, both Re and magnetomotive force are proportional to P ₀ · H. As a result,
nJ = h (M) · Re · T ₀ ^1.4 (4)
The conclusion is reached that "if the wind tunnel Mach number, temperature, and Reynolds number are constant, the magnetomotive force necessary to support the magnetic force is also constant." On the other hand, from equation (1)
σ _max ∝F (M) · Re · T ₀ ^1.4 / H (5)
It becomes. In the case of the conventional sting support, it is disadvantageous to keep the Reynolds number constant and reduce the size, but in the case of a magnetic support balance device, the required magnetomotive force is constant, which is advantageous in increasing the Reynolds number. In the case of magnetic support, the magnetic force can be distributed to the blade portion in the same manner as the aerodynamic force to suppress the stress of the blade root, and the restriction of the wind tunnel pressure due to the model strength can be greatly reduced.
Note that this technique can be applied not only to the above-described high Reynolds number wind tunnel test that magnetically supports a small aircraft model, but also to a two-dimensional wing test in which both ends are fixed to the wind tunnel wall, and the reduction of the internal pressure limit can be measured. It is natural.

  1 shows an embodiment of the present invention. In the present invention, the magnetic lines of force are oriented in the x-axis direction and the shape of the magnet 1a is long in the longitudinal direction of the blade in the model 1, but in the small model, the magnet is disposed from the base of the blade to the tip. It is difficult, and there is a part that cannot be placed at the tip. In an actual aircraft, lift is generated only at the wing. Therefore, it is ideal if the model 1 can be supported by levitation using only the magnets disposed on the wing. The lacking part will be compensated with a magnet arranged on the body. The embodiment shown here is an aircraft model in which the ratio of the magnetic moment between the wing and the body is 1: 1. When this model was used to evaluate the possibility of a test with a high Reynolds number, it was found that the wind tunnel limit internal pressure could be increased to twice that of the prior art. Under the condition that it is not a model levitation of only the wing part, and the magnet arrangement is not over the entire wing part up to the tip of the wing part, a perfect aerodynamic balance was not realized but only reduced, but the wind tunnel limit internal pressure Can be said to be a major advancement that has renewed the limits of high Reynolds number experiments in small wind tunnel facilities.

  In the above description of the present specification, the technology for implementing the present invention in the high Reynolds number wind tunnel environment, which is the original object, has been described. However, the present invention is not limited to this, and the airfoil, bridge, tower mounted with a high lift device is not limited thereto. Even for such easily deformable models, this method can be widely used for overload tests on structures. That is, a load test is performed by placing a structure model in which a plurality of magnets and strain sensors are arranged at important points in a magnetic field generator similar to a magnetic force support balance device. The detection signal of this strain sensor is sent to the calculation control means, and the calculation control means determines a current value that generates a magnetic force sufficient to cancel the distortion received by the model in the magnetic field control coil or magnet, and passes through the current supply means. Thus, the control current is supplied to the magnetic field control coil or magnet. This current creates a new magnetic field in the area where the test model is placed, and the magnets arranged in the model 1 receive a magnetic moment and act to balance the external force received by the model. Reduce distortion. This prevents the destruction of the model, and can cope with an excessive load test.

It is a figure which shows the basic composition of the aerodynamic load reduction apparatus of this invention. It is a figure which compares and demonstrates a conventional apparatus and this invention. It is a figure explaining the mechanism of the magnetic field generation which acts on the magnet with a built-in model in the present invention. It is a figure which shows the outline | summary of the magnetic support balance apparatus used as the foundation of this invention. It is a conceptual diagram of a power supply system and a measurement system in the magnetic force support balance apparatus which is the basis of the present invention. It is sectional drawing which shows the wind tunnel model in the conventional magnetic support balance apparatus.

Explanation of symbols

1 Wind tunnel model 1a Magnet (built-in model)
1b fuselage 1w wing 2,21-32 coil or magnet for magnetic field control 4 strain sensor
20 Magnetic support balance 34 Calculation control means
35 Current supply means

Claims (7)

  A test model for a wind tunnel equipped with a magnetism generator on the wind tunnel side, and a magnetic moment is applied in advance in the model so that a magnetic force acts in a direction that balances with the aerodynamic force on a portion that is easily deformed by aerodynamic force. Distributed model.   The model according to claim 1, wherein the test model is a wing-type aircraft model, and the portion of the wind tunnel test model that is easily deformed by aerodynamic force is a wing.   The model according to claim 1, wherein the test model is a wind tunnel model in which a model is attached to a measurement unit wall.   A coil that generates a magnetic field in the model installation area in the wind tunnel, a calculation control means that calculates and outputs a current value that generates a magnetic force necessary to cancel the model distortion detection signal, and amplifies the calculation value And a means for supplying current to the magnetism generating coil.   The coil that generates a magnetic field in the model installation area in the wind tunnel uses a magnetic support balance device, and in addition to the original model support magnetic force, it acts to superimpose the magnetic force to eliminate overload on the model. The aerodynamic load reducing device according to claim 4.   A structural model for a stress test performed in a test area where a desired magnetic field is generated, and is preliminarily placed in the model so that a magnetic force acts on a portion that is easily deformed by an external force in a direction that balances the external force. A model in which magnetic moments are distributed.   A coil that generates a magnetic field in the model installation area, a calculation control means that calculates and outputs a current value that generates a magnetic force required to cancel the strain detection signal of the structure model, and amplifies the calculation value And a means for supplying an electric current to the magnetism generating coil.

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