JP3809525B2 - Dynamic wind tunnel test equipment - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention is a dynamic wind tunnel test. Regarding equipment The wind test model can be simulated on a large scale without deviating from the wind tunnel measurement section even when the positional displacement due to rotational motion is large. age, A highly accurate position can be maintained and the number of test personnel can be reduced.
[0002]
[Prior art]
The conventional dynamic wind test model is a dynamic wind test model in which an aircraft model is placed in the space inside the wind tunnel measurement section with cables, etc., and floats in the space by the air current generated from the wind tunnel, creating a free flight state in the wind tunnel. Of 6 degrees of freedom exercise. FIG. Is an explanatory view showing the state of free flight of the dynamic wind test model, and the wind test model 50 is floating in the space of the measuring section in the wind tunnel by the air flow 60, and the pitch P and yaw Y around the center of gravity 51 of the airframe. A dynamic simulation test of an aircraft is performed by simulating a motion of six degrees of freedom in a roll R, a front-rear direction F, a left-right direction L, and a vertical direction U.
[0003]
The above six-degree-of-freedom motion simulation can be used for various aerodynamic performance tests of the aircraft body, but if the positional displacement accompanying the rotational motion is large, the model will deviate from the space in the narrow wind tunnel measurement section, There is a limit to the rotational motion simulation range. That is, the space of the measurement part of the wind tunnel is a space of 3.3 m × 3.3 m as an example, and the model flying in the space is about 1 m to 1.6 m in length and about 1 m in width and heavy. The length is about 17 kg, and the range of movement is naturally limited. It cannot handle a large amount of displacement, and damage occurs due to contact of the model with the wind tunnel structure.
[0004]
The above six-degree-of-freedom motion simulation can be used for various aerodynamic performance tests of the aircraft body, but it is necessary to control the behavior of the model in some way until the model control initial conditions (wind speed, thrust, etc.) are set. Yes, if the model behavior is restricted by attaching a cable, string, etc. to the model, it is necessary to loosen the cable, string, etc. at the time of transition to free flight. In this case, there is a high possibility that a large disturbance will enter. In addition, when actively controlling the flight, a complicated control system dedicated to takeoff must be considered separately, which is not possible with a simple method.
[0005]
In the dynamic wind tunnel test of aircraft models, various aerodynamic tests are conducted by placing a model in the wind tunnel and flowing an air flow. FIG. Is a perspective view of a dynamic wind tunnel test facility in the United States, and the wind test model 522 of the aircraft is free-flighted by receiving lift from the airflow 60 in the measurement section between the wind tunnel front part 520 and the wind tunnel rear part 521. is doing. One end of a cable 523 that transmits a control wire or a signal line from a sensor is connected to the model 522, and the other end of the cable 523 is connected to a computer 525. In addition, a safety cable 524 is connected to the model 522 so that it does not jump out of the wind tunnel even if the behavior of the model 522 becomes unstable.
[0006]
In the above-described wind tunnel test, many operators such as a safety cable operator 530, a wind tunnel operator 531, a pitch operation operator 532, a thrust operation operator 533, and a roll operation operator 534 are conducting tests.
[0007]
FIG. Is a perspective view of a conventional dynamic wind tunnel test facility, which is an example mainly conducted in Japan. In the figure, an aircraft wind test model 541 is held in a space portion by a cable in a wind tunnel 540 so as to receive an airflow 60. The front part of the model 541 is attached in the middle of the front cable 542, one end of the front cable 542 is fixed to a fixing part 544 in the wind tunnel, and the other end is fixed to the foundation via a pulley 543. Further, one end of the rear cable 545 is attached to the rear part of the model 541, and the other end of the rear cable 545 is fixed by applying an elastic force to the foundation via a pulley 546. Two TV cameras 548 a and 548 b are installed on the side of the wind tunnel of the model 541, and signals from the cameras are connected to the position measuring device 550 by electric wires 549. One end of a cable 547 made of an electric wire for controlling the attitude of the model or an electric wire connected to a sensor is connected to the model 541, and the other end of the cable 547 is connected to a computer 551 for control. In this example, the model 541 is supported by the cables 542 and 545 and the test is performed. However, a test is also performed in which the model 541 is supported by the vertical position holding device and the pitch posture can be changed.
[0008]
In the conventional dynamic wind tunnel test described above, FIG. In this example, a large number of test personnel are required, and skill is required for operation. In addition, human reaction speed is slow, models and wind tunnels become large-scale, and test reproducibility and test efficiency are poor. Also, FIG. In this example, since the model is supported by the cable, there is a problem that it is not possible to cope with forward / backward and left / right movement, and it becomes difficult to perform a high angle of attack test.
[0009]
[Problems to be solved by the invention]
As described above, in the wind tunnel test using the conventional dynamic wind test model of aircraft, if the amount of positional displacement due to rotational motion is large, the model will deviate from the narrow wind tunnel measurement section, and rotational motion with a large amount of positional displacement The simulation range was limited and large-scale exercise simulation was not possible. In addition, if the model deviates from the measuring unit, the expensive model may come into contact with the wind tunnel structure and be damaged, resulting in replacement of the model, which hinders efficient wind tunnel testing.
[0010]
In addition, as described above, the transition to a dynamic wind test free flight with a conventional aircraft model is constrained by a cable or a string, and the cable or string is loosened during the free flight transition to a free flight of the model. In such a method, there is a possibility that a large disturbance will be added to the behavior of the model when loosening the cable and string, and accurate test results in the early stage of model control cannot be obtained. There was a problem.
[0011]
In addition, as described above, in the conventional dynamic wind tunnel test, free flight is allowed. FIG. In this example, many people are required for the test, and the skill level of the personnel is also required. Also support the model with a cable FIG. In such a test facility, the model does not have freedom of movement, cannot move back and forth, and from side to side, cannot maintain a high angle of attack, and limits the application range of the test.
[0012]
Therefore, in the present invention, the wind test model is supported by using a gimbal mechanism that can rotate on three axes, and the model position is restrained to avoid the deviation of the model and greatly reduce the limitation of the rotational motion simulation range. An object of the present invention is to provide a dynamic wind tunnel testing apparatus that can perform the above-described problem.
[0013]
In addition, the present invention is configured to support the wind test model with a support rod to restrain the displacement in the lateral direction and to allow the wind test model to move up and down, and the lateral and longitudinal forces applied to the model are sensors. An object of the present invention is to provide a dynamic wind tunnel testing apparatus that can measure the model and estimate the translational motion of the model.
[0014]
Other objects and novel features of the present invention will be clarified in embodiments described later.
[0015]
[Means for Solving the Problems]
In order to solve the above-mentioned problems, the present invention provides the following (1) to (1) to (4) Provide the means.
[0016]
(1) A support rod that is erected from a lower support device installed below the wind tunnel measuring unit and that passes through the center of gravity of the wind test model so that the wind test model can move up and down, and is attached to the support rod A force measuring sensor for measuring the lateral and longitudinal force applied to the support rod, and a measuring device for taking in the measurement signal of the force measuring sensor and estimating the lateral and longitudinal force acting on the wind test model. A dynamic wind tunnel testing apparatus characterized by comprising:
[0017]
(2) Suspended from above the wind tunnel measuring unit, and a support rod that penetrates the center of gravity of the wind test model so that the wind test model can move up and down, and left and right attached to the support rod and applied to the support rod And a force measuring sensor for measuring the force in the front-rear direction, and a measuring device that takes in the measurement signal of the force measuring sensor and estimates the force in the left-right and front-rear directions acting on the wind test model. Dynamic wind tunnel testing device.
[0018]
(3) The support rod is provided with a rail in the longitudinal direction, and a guide groove that is slidably engaged with the rail is formed in the longitudinal direction around the hole through which the support rod of the wind test model passes. The dynamic wind tunnel testing apparatus according to (1) or (2), characterized in that:
[0019]
(4) A guide groove is formed in the support rod in the longitudinal direction, and a rail that slidably engages with the guide groove is formed in the longitudinal direction around the hole through which the support rod of the wind test model passes. The dynamic wind tunnel testing apparatus according to (1) or (2), wherein
[0020]
In (1) of the present invention, the wind test model has upper and lower support rods penetrating in the vertical direction, and the lateral position is constrained. The wind test model is easily moved in the vertical direction along the support rod by the air current, and at this time, even if the amount of displacement in the lateral direction increases, it does not deviate from the measurement section, and the test range is greatly limited. Alleviated. In addition, the force measurement sensor measures the lateral and longitudinal force applied to the support bar and outputs these measurement signals to the measurement device. In the measurement device, the lateral direction acting on the wind test model by these measurement signals, The force in the front-rear direction can be estimated. Therefore, in addition to simulating the vertical movement of the wind test model, it is possible to easily estimate the movement in the lateral direction and the longitudinal direction.
[0021]
(2) of the present invention is the same as the invention of (1) above except that the support rod is suspended from above and the tip penetrates the wind test model downward. In addition to the simulation of the vertical movement of the wind test model, the movement in the lateral direction and the front-rear direction can be easily estimated.
[0022]
In (3) of the present invention, the support rod is provided with a rail, the model side through hole is provided with a guide groove, and the rail and the guide groove are engaged with each other so as to be vertically slidable. ), A guide groove is formed in the support rod, and a rail is formed in the through hole. Therefore, the guide groove and the rail are engaged and slidable to form the above (1) or ( The vertical movement of the wind test model of the invention of 2) can be easily realized.
[0023]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, embodiments of the present invention will be specifically described with reference to the drawings.
[0024]
FIG. 1 is a configuration diagram of a three-degree-of-freedom motion simulation mechanism in a dynamic wind tunnel test apparatus as a first reference example that is the basis of the present invention. In the figure, reference numeral 50 denotes a wind test model, which is a reduced model of an aircraft as in the prior art. The wind test model 50 is disposed in the measurement unit 71 between the wind tunnel front part 70 and the wind tunnel rear part 72. As an example of the dimensions of the wind test model, the space part of the measuring unit 71 is 3.3 m × 3.3 m, the model 50 is 1.6 m long, 1.0 m wide, and weighs about 17 kg. .
[0025]
Reference numeral 1 denotes a gimbal mechanism which, as will be described later, has a structure capable of rotating with three degrees of freedom around three axes orthogonal to each other, and is attached so that the center of the three axes coincides with the center of gravity 51 of the wind test model 50. Has been placed. Reference numeral 2 denotes a support rod that supports the wind test model 50 via the gimbal mechanism 1, and the support rod 2 is supported by the base 61 by the lower support device 4 and stands vertically. Reference numeral 3 denotes a force measurement sensor (balance), which is attached in the middle of the support bar 2 and measures forces in the vertical direction, the front-rear direction, and the left-right direction applied to the support bar 2, respectively.
[0026]
In the three-degree-of-freedom motion simulation mechanism of the dynamic wind tunnel test apparatus having the above-described configuration, the airflow 60 from the windtunnel front part 70 flows toward the measurement unit 71, and the wind test model 50 is not shown in the drawing together with the lift force received by the airflow. A dynamic wind tunnel test is performed by rotating the roll R, the pitch P, and the yaw Y around the gimbal mechanism 1 by operating the control surface of the main wing and tail of the model. In this case, since the wind test model 50 is fixed to the foundation 61 by the support rod 2 via the lower support device 4, the wind test model 50 rotates only in the three axial directions around the gimbal mechanism 1 without moving. .
[0027]
Further, a force measuring sensor 3 is attached to the support bar 2, and this force measuring sensor 3 applies the forces in the vertical direction, the front-rear direction, and the left-right direction that the support bar 2 receives when the wind test model 50 rotates about three axes. Each can be measured and sent to a control device (not shown) to estimate the force received by the model at that time. The lower support device 4 that fixes and supports the support rod base is provided below the flow path of the air flow 60 formed by the wind tunnel front portion 70 and the wind tunnel rear portion 72 so as not to obstruct the air flow.
[0028]
FIG. 2 is an overall system configuration diagram using a three-degree-of-freedom motion simulation mechanism of the dynamic wind tunnel testing apparatus according to the first reference example. In the figure, the wind test model 50 is arranged in the measuring unit 71 as shown in FIG. 1 and supported by the base 61 via the lower support device 4 by the support rod 2. On the front and rear sides of the measuring unit 71, a gantry 40 is provided with a column erected from the foundation 61. On the gantry 40, a wiring / piping support base 41 provided with a connector 42 is attached. An umbilical cable 43 comprising wiring and piping to the wind test model 50 is connected to the connector 42. Reference numerals 44, 45, and 46 denote restraint cables, which are safety cables when the wind test model 50 is detached from the support rod 2, and are usually slack. A camera 47 measures the position of the wind test model 50 with two cameras.
[0029]
An air supply pipe 30 connected to the umbilical cable 43 is connected to the connector 42, and the air supply pipe 30 is connected to the high-pressure air source 34 through the control valve 31, the shut-off valve 32, and the air supply pipe 33. The connector 42 is connected to wiring from the control device 21 connected to the umbilical cable 43 as will be described later. Air from the air supply pipe 30 is ejected from the rear part of the wind test model 50 to obtain thrust, and an electric signal from the control device 21 controls a motor and an actuator in the wind test model 50.
[0030]
In the mechanism configured as described above, the flight control device 20 sends commands for various flight conditions of the wind test model 50 to the control device 21. The control device 21 sends a signal to the valve control device 23 based on a command from the flight control device 20, and the valve control device 23 controls the opening / closing of the shutoff valve 32 and the valve opening degree of the control valve 31 to set the flight conditions. The control device 21 sends a control signal through the connector 42 to control the motor and actuator inside the model, and the air and electric signals move the main wing and tail wing of the wind test model 50. The wing (that is, the control surface) is moved, and each rotation of the roll R, pitch P, and yaw Y of the wind test model 50 is controlled according to the flight conditions. In addition, the control device 21 receives the position signal of the wind test model 50 taken in by the two cameras 47 from the position measurement device 22 and sends it to the flight control device 20. Further, as described above, the control device 21 takes in a signal from the force measuring sensor 3, and this signal is a signal of force applied to the support rod 2 in the vertical, front-rear and left-right directions, and these signals are sent to the flight control device 20. send.
[0031]
FIG. 3 is a detailed view showing an example of the gimbal mechanism 1 used for the wind test model 50, wherein (a) is a side view and (b) is a front view. In both figures, 11 is a pitch axis, 12 is a roll axis, and 13 is a yaw axis. Reference numeral 14 denotes a bracket. A yaw shaft 13 is fixed to the lower surface, and the yaw shaft 13 is supported in a bearing 16 so as to be rotatable in the yaw direction. Reference numeral 15 denotes a shaft support portion, which rotatably holds the roll shaft 12, supports the roll shaft 12 so as to be rotatable in the roll direction R, and is rotatable in the pitch direction P around the pitch shaft 11 in the bracket 14. It is supported. The tip of the support bar 2 is fixed to the bearing 16 and supports the entire gimbal mechanism 1 via the yaw shaft 13. A model 50 is attached to the roll shaft 12.
[0032]
The gimbal mechanism 1 having the above configuration is incorporated into the center of gravity 51 of the wind test model 50, the center of gravity 51 is made to coincide with the center of the pitch axis 11 and the roll shaft 12, the wind test model 50 is supported by the support rod 2, and the dynamic wind tunnel test is performed. Since the wind test model 50 is fixed and supported in the measuring unit 71 by allowing movement in three degrees of freedom, the position of the wind test model 50 is restricted, and the deviation of the wind test model 50 from the measuring unit 71 is prevented. It is prevented and the restriction of the rotational motion simulation range is greatly relaxed.
[0033]
According to the first reference example described above, the wind test model 50 is supported by the gimbal mechanism 1 and the support rod 2, thereby preventing the wind test model 50 from departing from the measurement unit 71 and reducing the rotational motion simulation range. The restrictions are greatly relaxed. In addition, since force in the wind test model 50 is measured by the force measurement sensor 3 in the vertical direction, the front-rear direction, and the left-right direction, these are taken into the flight control unit 20 (see FIG. 2). Large-scale motion simulation that was impossible due to the deviation of the model from the wind tunnel measuring unit 71 becomes possible.
[0034]
FIG. 4 is a block diagram showing a three-degree-of-freedom motion simulation mechanism of a dynamic wind tunnel testing apparatus according to a second reference example of the present invention. In the first reference example, a second configuration is supported from a configuration in which a wind test model is supported from below. In the reference example, the wind test model is supported by being suspended from above.
[0035]
That is, in FIG. 4, the gimbal mechanism 1 is incorporated in the center of gravity 51 of the wind test model 50, and the gimbal mechanism 1 is supported by the support rod 82 as the upper fixed portion of the measurement unit space via the support rod support portion 84. It is attached to the gantry 40. That is, the wind test model 50 is configured to be suspended vertically from the upper portion of the gantry 40 by the support rod 82. Other configurations are the same as those of the first reference example described above, and the same or corresponding parts are denoted by the same reference numerals and description thereof is omitted. In the second reference example, the same function and effect as those of the first reference example can be obtained.
[0036]
In the second reference example, when the gimbal mechanism 1 shown in FIG. 3 is used, the wind test model 50 is suspended from the support rod 2 via the gimbal mechanism 1, so that the bearing shown in FIG. 16 and the yaw shaft 13 require a locking portion for preventing dropping, for example, a flange having a diameter larger than the shaft diameter is provided at the tip of the yaw shaft, and an enlarged groove portion is provided in the groove of the bearing 16, The yaw shaft may be rotatably engaged with the bearing.
[0037]
Further, the gimbal mechanism 1 shown in FIG. 3 described above is not limited to this structure, and any structure may be used as long as the structure can be rotated around three orthogonal axes. .
[0038]
FIG. 5 is a configuration diagram of the vertical motion simulation mechanism in the dynamic wind tunnel testing apparatus according to the first embodiment of the present invention. In the figure, a wind test model 50 is a reduced model of an aircraft as in the conventional case, and is arranged in a measurement unit 71 between a wind tunnel front part 70 and a wind tunnel rear part 72. As an example of the wind test model 50, the cavity of the measuring unit 71 is 3.3 m × 3.3 m, the model length is 1.6 m, the width (the length of the main wing) is 1.0 m, and the weight is 17 kg. It is a facility of degree.
[0039]
Reference numeral 101 denotes an interface part having a hole penetrating vertically, and the hole penetrating vertically is mounted so as to coincide with the center of gravity 51 of the wind test model 50 and penetrates a support rod as will be described later. Reference numeral 102 denotes a support rod through which the wind test model 50 passes through the interface unit 101 so as to be movable up and down. The support rod 102 is vertically fixed to the surface of the foundation 61 by the lower support device 4 and allows the wind test model 50 to move up and down but restrains the left and right and front and rear movements. Note that the interface unit 101 winds through a gimbal mechanism (substantially the same function as the gimbal mechanism 1 of the first reference example) that can rotate about the center of gravity 51 in the roll R, pitch P, and yaw Y directions. A trial model 50 is attached. Further, the lower support device 4 that fixes and supports the base portion of the support rod 102 is disposed below the flow path of the air flow 60 between the wind tunnel rear portion 70 and the front portion 71 so as not to obstruct the flow of the air flow.
[0040]
Reference numeral 3 denotes a force measurement sensor, which is attached in the middle of the support bar 102, measures the left and right forces before and after being applied to the support bar 102, and sends these signals to the measurement device 105. The measurement device 105 can estimate the longitudinal and lateral translational motions other than the vertical motion by estimating the longitudinal and lateral forces applied to the wind test model 50 from these measured values. The apparatus other than the mechanism for supporting the wind test model 50 is the same as the configuration of FIG. 2 shown in the first reference example.
[0041]
6A and 6B show the interface portion in the first embodiment, wherein FIG. 6A is a longitudinal sectional view thereof, and FIG. 6B is an AA sectional view of FIG. In the figure, the support rod 102 is formed with two rails 110a and 110b in the longitudinal direction. Further, the interface portion 101 is provided with a through hole 113 having a diameter slightly larger than the outer diameter of the support rod 102 so that the outer diameter of the support rod 102 can freely move up and down. Rails 110a and 110b of the support rod 102 are engaged with the through hole 113, and guide grooves 111a and 111b having a slightly larger shape than the rails 110a and 110b are formed in the longitudinal direction so that the support rod 102 can move up and down by sliding. Is formed.
[0042]
In the vertical motion simulation mechanism of the first embodiment having the above-described configuration, the airflow 60 from the wind tunnel front part 70 flows toward the measuring unit 71, and the wind test model 50 receives this airflow and has a lift depending on the state of the airflow. It occurs and moves up and down along the rails 110a and 110b of the support rod 102. The wind test model 50 is engaged with the rails 110a and 110b of the support rod 102 through guide grooves 111a and 111b, and the guide grooves 111a and 111b are grooves having a larger shape than the rails 110a and 110b. Thus, the vertical motion of the wind test model 50 can be easily simulated. Since the wind test model 50 is restrained in the lateral direction by the support rod 102, it does not deviate from the measuring unit 71, thereby greatly reducing the limitation of the test range.
[0043]
Further, the force in the lateral direction and the longitudinal direction applied to the support rod 102 are measured by the force measuring sensor 3, and these signals are input to the measuring device 105. Since the translational motion in the direction is estimated, the configuration of the first embodiment makes it easy to simulate the motion of the wind test model 50 in the vertical, horizontal, and longitudinal directions.
[0044]
FIG. 7 shows an interface part of a dynamic wind tunnel testing apparatus according to the second embodiment of the present invention, in which (a) is a longitudinal sectional view and (b) is a sectional view taken along line BB in (a). In the second embodiment, the rail of the support bar in the first embodiment is provided on the interface part, and the guide groove of the interface part is provided on the support bar. It is the same as that of the embodiment.
[0045]
That is, in FIG. 7, guide grooves 121 a and 121 b are formed in the support rod 102 in the longitudinal direction, and the interface portion 101 is provided with a through hole 123 that is slightly larger than the outer diameter of the support rod 102. The through holes 123 engage with the guide grooves 121a and 121b of the support rod 102 to form rails 120a and 120b having a shape slightly smaller than the groove shape of the guide grooves 121a and 121b. Even when the interface portion 101 having such a structure, the guide grooves 121a and 121b of the support rod 102, and the rails 120a and 120b are combined, the wind test model 50 can be easily moved up and down along the support rod 102. The same effect as the embodiment can be obtained.
[0046]
FIG. 8 is a configuration diagram of a dynamic wind tunnel testing apparatus according to the third embodiment of the present invention. In the third embodiment, the support rod is suspended from above, and the wind test model is suspended from above, from the method of supporting the lower portion of the support rod of the first embodiment shown in FIG. Is. Other configurations are the same as those of the first embodiment shown in FIG.
[0047]
That is, in FIG. 8, the support bar 132 is suspended vertically from the support bar support part 133, and the support bar support part 133 is supported and fixed to the gantry 40. The gantry 40 constitutes a gantry by standing pillars on both sides of the wind tunnel front part 70 and the wind tunnel rear part 72, and supports the support rod support part 133 on the upper side. The support bar 132 penetrates the wind test model 50 in the interface unit 101, and the wind test model 50 is inserted into the support bar 132 so as to be movable up and down in the interface unit 101 as in the third and second embodiments. Yes. A force measuring sensor 3 is attached to the support bar 132, and the lateral and front / rear direction forces applied to the support bar 132 are measured and input to the measuring device 105.
[0048]
According to the third embodiment having the above-described configuration, the support rod 132 is suspended from the upper mount 40, and the wind test model 50 is penetrated through the interface portion 101 at the tip so as to be movable up and down. Since the movement of the direction is constrained, the deviation of the wind test model 50 from the measurement unit 71 is prevented, the limitation of the test range is greatly relaxed, and the wind test model 50 is laterally measured by the measurement signal of the force measurement sensor 3. The translational motion in the front-rear direction can also be estimated, and the same effect as in the first and second embodiments can be obtained.
[0049]
Although the embodiments of the present invention have been described above, it will be obvious to those skilled in the art that the present invention is not limited thereto and various modifications and changes can be made within the scope of the claims. .
[0050]
【The invention's effect】
The dynamic wind tunnel test apparatus of (1) of the present invention is erected from a lower support device installed below the wind tunnel measuring section, and the center of gravity of the wind test model is adjusted so that the wind test model can move up and down. A support rod that penetrates, a force measurement sensor that is attached to the support rod and measures force in the left and right and front and rear directions applied to the support rod, and a right and left and front and rear that act on the wind test model by taking measurement signals of the force measurement sensor And a measuring device for estimating the directional force.
[0051]
With such a configuration, even if the amount of displacement in the lateral direction increases, the measurement range does not deviate from the measurement unit, and the limitation of the test range is greatly relaxed. In addition, the force measurement sensor measures the lateral and longitudinal force applied to the support bar and outputs these measurement signals to the measurement device. In the measurement device, the lateral direction acting on the wind test model by these measurement signals, The force in the front-rear direction can be estimated. Therefore, in addition to simulating the vertical movement of the wind test model, it is possible to easily estimate the movement in the lateral direction and the longitudinal direction.
[0052]
The dynamic wind tunnel test apparatus of (2) of the present invention is the same as the invention of (1) above except that the support rod is suspended from above and the tip penetrates the wind test model downward. In addition to the same action and effect as the invention of (1) above, in addition to simulating the vertical movement of the wind test model, the movement in the lateral direction and the front-rear direction can be easily estimated.
[0053]
In the dynamic wind tunnel testing apparatus according to (3) of the present invention, a rail is provided on the support rod, a guide groove is provided on the through hole on the model side, and the rail and the guide groove are engaged to be slidable up and down. In the dynamic wind tunnel testing apparatus of (4) of the present invention, since the guide groove is formed on the support rod and the rail is formed on the through hole, the guide groove and the rail can be engaged and slidable. By adopting the configuration, the vertical movement of the wind test model of the invention of the above (1) or (2) can be easily realized.
[Brief description of the drawings]
FIG. 1 is a configuration diagram of a simulation mechanism, which is a dynamic wind tunnel testing apparatus according to a first reference example of the present invention.
FIG. 2 is an overall system configuration diagram of a wind tunnel test using a simulation mechanism according to a first reference example of the present invention.
3A and 3B show a gimbal mechanism applied to a simulation mechanism according to a first reference example of the present invention, where FIG. 3A is a side view and FIG. 3B is a front view.
FIG. 4 is a configuration diagram of a dynamic wind tunnel testing apparatus according to a second reference example of the present invention.
FIG. 5 is a configuration diagram of the dynamic wind tunnel testing apparatus according to the first embodiment of the present invention.
6A and 6B show an interface part of the dynamic wind tunnel testing apparatus according to the first embodiment of the present invention, where FIG. 6A is a longitudinal sectional view, and FIG. 6B is a sectional view taken along line AA in FIG.
FIGS. 7A and 7B show an interface part of a dynamic wind test model vertical motion simulation mechanism in a dynamic wind tunnel testing apparatus according to a second embodiment of the present invention, wherein FIG. 7A is a longitudinal sectional view, and FIG. It is a BB sectional view in).
FIG. 8 is a configuration diagram of a dynamic wind test model vertical motion simulation mechanism, which is a dynamic wind tunnel testing apparatus according to a third embodiment of the present invention.
FIG. 9 is a perspective view showing an example of a conventional wind tunnel test facility.
FIG. 10 is a perspective view showing another example of a conventional wind tunnel test facility.
FIG. 11 is a general explanatory diagram of a 6-DOF motion simulation of an aircraft dynamic wind test model.
[Explanation of symbols]
1 Gimbal mechanism
2,82,102,132 Support rod
3 Force measurement sensor
4 Lower support device
11 Pitch axis
12 Roll axis
13 Yaw axis
14 Bracket
15 shaft support
16 Bearing
20 Flight controller
21 Control device
22 Position measuring device
23 Valve control device
30, 33 Air supply pipe
31 Control valve
32 Shut-off valve
34 High-pressure air source
40 frame
41 Support for wiring and piping
42 Connector
43 Umbilical cable
44, 45, 46 Restraint cable
47 Camera
50 wind test model
51 Center of gravity
60 Airflow
61 Basics
70,520 Wind tunnel front
71 Measuring unit
72,521 Wind tunnel rear
84 Support rod support
101 Interface section
105 Measuring device
110a, 110b, 120a, 120b rail
111a, 111b, 121a, 121b Guide groove
113,123 Through hole
133 Support rod support part
523 cable
524 safety cable
525 computer
530 Safety cable operator
531 Wind Tunnel Operator
532 pitch operator
533 thrust operator
534 Roll operation operator
540 wind tunnel
542 Front cable
543,546 pulley
544 Fixed part in wind tunnel
545 Rear cable
547 cable
548a, 548b TV camera
549 electric wire
550 Position measuring device
551 computer

Claims (4)

  A support rod that is erected from a lower support device installed below the wind tunnel measurement unit and that passes through the center of gravity of the wind tunnel model so that the wind tunnel model can move up and down, and is attached to the support rod and attached to the support rod A force measurement sensor that measures the applied force in the left and right and front and rear directions, and a measurement device that takes in a measurement signal of the force measurement sensor and estimates the left and right and front and rear force acting on the wind test model. Dynamic wind tunnel testing equipment.   A support rod that is suspended from above the wind tunnel measurement unit and penetrates the center of gravity of the wind test model so that the wind test model can move up and down, and the left and right and front and rear directions attached to the support rod and applied to the support rod A dynamic wind tunnel comprising: a force measurement sensor for measuring the force of the power; and a measuring device for taking in a measurement signal of the force measurement sensor and estimating a left-right and front-rear force acting on the wind test model Test equipment.   The support rod is provided with a rail in the longitudinal direction, and a guide groove that is slidably engaged with the rail is formed in the longitudinal direction around the hole through which the support rod of the wind test model passes. The dynamic wind tunnel testing apparatus according to claim 1 or 2, characterized in that:   A guide groove is formed in the support rod in the longitudinal direction, and a rail that slidably engages with the guide groove is provided in the longitudinal direction around the hole through which the support rod of the wind test model passes. The dynamic wind tunnel testing apparatus according to claim 1 or 2.

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