JP2016161436A - Loading test method and loading device of structure - Google Patents

Abstract

PROBLEM TO BE SOLVED: To easily adjust the position of a suspended spindle while the load of the spindle is charged on a structure, in a loading test of the structure.SOLUTION: A loading device 10 charges a load of a spindle 12 suspended using a wire 11 on each of a plurality of loading places P in a body of an aircraft. The loading device includes the spindle 12, the wire 11, and a winding machine 20 capable of vertically adjusting the position of the spindle 12. By adjusting the position of the spindle 12 by winding the wire 11 with the winding machine 20 while the spindle 12 is connected to the wire 11, the spindle 12 can be prevented from interfering with a peripheral member such as a floor 14. Therefore, the strength test can be performed smoothly.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a loading test for a large structure such as an aircraft.

In an aircraft strength test, a predetermined load based on an analysis of an aerodynamic load or the like is applied to the aircraft after canceling its own weight.
In order to distribute the weight of the aircraft, multiple points such as several tens to 100 are selected on the aircraft. The weight of the fuselage connected to the wires attached to each of the multiple points is applied upward by a pulley installed in the frame to cancel the weight of the aircraft.

When the weight of the aircraft is canceled and a load is applied to the aircraft by a hydraulic actuator or the like, the aircraft may be deformed, and accordingly, the weight may be displaced downward to reach the floor.
FIG. 15A shows a state in which the weight of the body 1 is canceled by applying the load of the weight 12 upward by the pulley 13, and FIG. 15B shows that the load is further applied to the body 1. 12 shows a state where the floor 12 has arrived on the floor 14.
In order for the weight 12 to function, the length of the wire 11 that suspends the weight 12 is shortened when the weight 12 is or is about to reach the floor 14 (FIG. 15C). Position adjustment work is required.
Here, if the pulley 13 is installed at a sufficiently high position so that the weight 12 does not reach the floor 14 even if the airframe 1 is displaced, it is not necessary to adjust the position of the weight 12. However, a larger frame capable of installing the pulley 13 at a high position is required.

Since the size of the frame is limited from the viewpoint of the test site space and cost, adjustment work of the weight position is assumed during the strength test.
The following issues exist regarding the work.
(1) Once the weight is removed from the wire to adjust the position of the weight (FIG. 15C), the test is interrupted until the weight is returned.
(2) It takes time to adjust the position of the weight including removal and attachment of the weight.
(3) If you remove multiple weights that need to be adjusted at the same time and try to adjust the positions of those weights in parallel, the weights of those weights will be released at the same time, so the balance of the aircraft can be maintained. There is a risk of disappearing. For this reason, a plurality of weights are removed one by one in order and the positions thereof are adjusted, and the work takes time.

The problems described above also apply to structures other than aircraft.
Moreover, the said subject applies to the whole test loaded on a structure with the load of the suspended weight irrespective of use of a pulley.

  The present invention relates to a loading test of a structure, and an object thereof is to easily adjust the position of the weight while applying the load of the suspended weight to the structure.

A loading device according to the present invention is a loading device that applies a load of a weight suspended using a linear member to each of a plurality of loading points of a structure, and the position of the weight, the linear member, and the weight And an adjustment section that can adjust the height in the vertical direction (vertical direction).
“Adjusting the position of the weight in the vertical direction” as described above is different from moving the weight in the vertical direction as the structure is displaced by the application of a load. While the weight follows the displacement, the vertical position of the weight is positively adjusted.

  The loading device of the present invention can be provided with a fixed pulley that is installed above the loading location and on which a linear member is wound. In this case, the structure can be lifted by applying a weight load upward to the structure by the fixed pulley.

  In the loading device of the present invention, it is preferable that the adjustment unit includes a coupling unit coupled to the weight and a drum around which the linear member is wound by being given torque.

  The loading device of the present invention includes a moving pulley that receives a weight below the fixed pulley, and the adjusting unit is installed on a member that is above the moving pulley and that is responsible for the reaction force of the force acting on the adjusting unit. And a drum around which the linear member is wound by applying torque, and the linear member is preferably wound around the drum of the adjusting unit via the fixed pulley and the movable pulley.

  In the above configuration, the member responsible for the reaction force is a frame on which work associated with the test using the loading device is performed, and the adjustment unit installed in the frame is preferably collected in a predetermined region of the frame.

  In the loading device of the present invention, it is preferable that the adjustment unit includes a first screw that is connected to the linear member and hangs down, and a second screw that is connected to the weight and engages with the first screw.

  In the loading device of the present invention, the weight has a plurality of pieces as adjustment parts arranged in the direction around the axis of the linear member, and the plurality of pieces are suspended along the axial direction of the linear member; It is preferable that the posture can be reversed in the up and down direction from the suspended state to the state where the linear member extends from the radial direction to the standing direction along the axial direction.

In the loading device of the present invention, the weight has a plurality of pieces arranged in the direction around the axis of the linear member, and a plurality of pieces that are opposed to each other in the diameter direction of the linear member are assembled into a set. It is preferable that the pieces can be slid along the linear member for each set.
The fact that the pieces are "facing in the diameter direction of the linear member" includes that the pieces are positioned point-symmetrically.

  The loading apparatus of the present invention can be preferably applied to the test of an aircraft that is a structure.

  The loading test method of the present invention is a test method in which a load of a weight suspended using a linear member is applied to each of a plurality of loading points by the above-described loading device, and the vertical position of the weight is determined. By adjusting with an adjustment part, the interference to the surrounding member is avoided.

  In the loading test method of the present invention, while applying a load of a weight suspended by using a linear member hung on a fixed pulley installed above the loading location to each of a plurality of loading locations, A predetermined load can be applied.

  In the loading test method of the present invention, a test for applying a predetermined load to a structure is performed while changing the load conditions while canceling the weight of the structure by lifting the structure by a weight load using a fixed pulley. A plurality of test cases with different load conditions due to the load test information processing device equipped with an arithmetic unit, in which the weight of the structure is canceled by applying lifting loads by weights and fixed pulleys to each of the plurality of loading points. Obtaining a position adjustment amount from each initial position of each of the plurality of weights, and applying a marking indicating the position adjustment amount of each of the plurality of weights to the linear member or adjustment unit for hanging the corresponding weights; It is preferable to perform.

  In the loading test method described above, in the step of obtaining the weight position adjustment amount, the estimated structure displacement amount obtained by estimating the displacement amount generated in the structure and the displacement amount of the structure at each of the plurality of loading points are calculated. Using the estimated load location displacement amount obtained by estimation and the estimated weight displacement amount obtained by estimating the displacement amount of the weight corresponding to each of the plurality of load locations, the weight position adjustment amount is obtained. Is preferred.

  In the loading test method of the present invention, the load condition of the test for applying a predetermined load to the structure is changed while canceling the weight of the structure by lifting the structure by the weight load using a fixed pulley. The weight of the structure is canceled by applying a lifting load by a weight and a fixed pulley to each of the plurality of loading points, and the number of weight adjustment operations is adjusted by a loading test information processing device equipped with an arithmetic unit. From the viewpoint of relatively reducing, it is preferable to perform a step of determining the order in which a plurality of test cases having different load conditions are performed, and to execute the test cases according to the order.

  According to the loading device of the present invention and the loading test method using the loading device, the weight can interfere with surrounding members such as the floor by adjusting the position of the weight while the weight is connected to the linear member by the adjusting unit. Since it can be avoided, the strength test of the structure can be carried out smoothly while ensuring the safety of the operator.

It is a schematic diagram which shows the loading apparatus used for the strength test of the aircraft which concerns on 1st Embodiment. (A) is a side view of the weight with which the loading apparatus shown in FIG. 1 was equipped. (B) is a top view which shows the steel plate of a weight. (A) is a figure which shows that a weight falls with the upward bending deformation of a main wing. (B) is a figure which shows the state in which the pulley was installed in the higher position. (A) And (b) is a schematic diagram which concerns on the 1st modification of the adjustment part of the position of a weight. (A) And (b) is a schematic diagram which concerns on the 1st modification of the adjustment part of the position of a weight. (A)-(c) is a schematic diagram which concerns on the 2nd modification of the adjustment part of the position of a weight. (C) is the VIc-VIc sectional view taken on the line (a) and (b). (A)-(d) is a schematic diagram which concerns on the 3rd modification of the adjustment part of the position of a weight. (B) is a cross-sectional view of the weight piece. (D) is the VIId-VIId sectional view taken on the line of (a) and (c). (A) And (b) is a schematic diagram which concerns on the 4th modification of the adjustment part of the position of a weight. It is a schematic diagram which shows the loading apparatus which concerns on 2nd Embodiment. It is a schematic diagram which shows that the adjustment part is collected in the predetermined area | region of a frame. It is a figure which shows the procedure of the strength test method which concerns on 3rd Embodiment. It is a figure which shows the procedure of the strength test method which concerns on 4th Embodiment. It is a schematic diagram which shows the state which marked the position adjustment amount of the weight in the strength test which concerns on 4th Embodiment. It is a figure which shows the procedure of the strength test method which concerns on 5th Embodiment. It is a schematic diagram for demonstrating the position adjustment operation | work of the conventional weight.

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.
[First Embodiment]
In the present embodiment, an aircraft strength test will be taken as an example, and a multipoint loading test method of the present invention and a loading apparatus used for the test will be described.
In an aircraft strength test (loading test), the weight of the aircraft is canceled (self-weight correction), and then a load based on an aerodynamic load analysis is applied to the aircraft.
When lifting the airframe to cancel the weight of the airframe, the loading device 10 shown in FIG. 1 is used.
For example, a load is applied by the loading device 10 to each of the loading places P of about several tens to 100 selected on the airframe.
The loading device 10 corresponding to each of a large number of loading points P acts upward on the loading point P by using the pulley 13 on which the wire 11 is hung around the load 12 suspended by the wire 11. By doing so, the dead weight distributed to the loading point P is canceled.

The loading device 10 shown in FIG. 1 loads on a loading point P selected at the wing tip of the main wing 1A of the aircraft.
Due to the bending moment due to the weight of the main wing 1A, the wing tip is displaced downward with respect to the joint of the main wing 1A to the fuselage, but the position of the wing tip is displaced upward by the self-weight cancellation by the loading device 10.
The loading device 10 includes a weight 12, a wire 11 that suspends the weight 12, a pulley 13 around which the wire 11 is wound, and an adjustment unit that can adjust the position of the weight 12 in the vertical direction by winding the wire 11. The winder 20 is provided. The weight 12 is suspended so as to fit between the floor 14 (or the ground) of the test site and the pulley 13.
Each of the pulleys 13 provided in each of the loading devices 10 individually corresponding to a large number of loading points P is installed on a frame 15 in which columns and beams are assembled.

The weight 12 has a weight corresponding to its own weight distributed to the loading point P.
The weight 12 of this embodiment is provided with the laminated body 16 of the steel plate 161, and the cover 17 which covers the laminated body 16, as shown to Fig.2 (a), and is exhibiting the column-shaped external appearance.
The laminated body 16 has a plurality of steel plates 161 and a holder 18 that holds the steel plates 161 in a stacked state.
As shown in FIG. 2B, a slot 163 is formed from one place on the circumference of a steel plate 161 having a circular outer shape to the center of the plane.
The holder 18 includes a disc-shaped bottom plate 181 and a holding rod 182 standing up from the bottom plate 181.
The holding rod 182 passes through each slot 163 of the steel plates 161 to be laminated.

A necessary number of steel plates 161 are supported on the bottom plate 181 according to the weight distributed to the loading location P, and the steel plates 161, the holder 18, and the cover 17 are handled integrally by covering the steel plates 161 with the cover 17. be able to.
The weight 12 is not limited to the above configuration, and can be configured in an appropriate form.

The wire 11 is pulled out from the winder 20, and is attached to a loading point P located on the upper skin of the main wing 1A via a fixture (not shown) as shown in FIG. The wire 11 extends upward from the loading point P and is wound around the pulley 13.
Although not shown in detail, the pulley 13 is a fixed pulley including a rotatable rope and a support portion that rotatably supports the rope and is fixed to the frame 15.
The pulley 13 is located above the loading location P, and the weight of the weight 12 acts upward on the loading location P by the pulley 13 so that part of the weight of the main wing 1A is canceled. At this time, the frame 15 takes charge of the reaction force acting on the pulley 13. The pulley 13 can also be installed on a member that can take a reaction force other than the frame 15.

  The vertical position of the loading location P moves as the displacement of the main wing 1A changes, but the pulley 13 is located above the position of the loading location P when it moves most upward through the strength test. Therefore, an upward load can be reliably applied to the loading point P.

  Another pulley that is wound around the same wire 11 may be interposed between the pulley 13 and the weight 12.

Now, when performing an aircraft strength test, the load of the weight 12 connected to the wire 11 attached to each of a number of loading points P set on the fuselage including the main wing 1A is directed upward via the pulley 13. By acting, the entire weight of the aircraft is canceled. A predetermined load based on the analysis is applied to an appropriate position of the airframe using a loading means such as a single or a plurality of hydraulic actuators 19 (FIG. 3A) while canceling its own weight.
The strength test performed in the present embodiment includes a plurality of test cases with different load conditions, and various load conditions including the position where the load is applied by the hydraulic actuator 19 and the magnitude of the load are provided for each test case. It has been established.
Based on the test case, for example, a load simulating an aerodynamic load that causes upward bending deformation is applied to the main wing 1A. As shown in FIG. 3A, when the main wing 1A is bent upward, the weight 12 is displaced downward.

In the course of such a strength test, it is assumed that the weight 12 reaches the floor 14 due to the displacement of the airframe. When the weight 12 arrives at the floor 14, the load of the weight 12 is supported by the floor 14 (see FIG. 15B), so that the own weight distributed to the loading location P is not canceled by the load of the weight 12.
Therefore, it is preferable to adjust the vertical position of the weight 12 so that the weight 12 does not reach the floor 14, but once the weight 12 is removed from the wire 11 in order to adjust the position of the weight 12 (FIG. 15C). )), Cancellation of its own weight by the weight 12 does not work.

Based on the above, the loading device 10 of the present embodiment uses the winder 20 (FIG. 1) as an adjustment unit that can adjust the position of the weight 12 in the vertical direction while applying the load of the weight 12 to the loading point P. I have.
A weight 12 is suspended by a wire 11 that can be wound by a winder 20.
By winding the wire 11 with the winder 20 corresponding to each of the loading points P and keeping the weight 12 above the floor 14, a load is applied to the airframe by a hydraulic actuator or the like while canceling the weight of the entire airframe. Since it can be input, a predetermined strength test can be performed.
The winder 20 can also be used when the weight 12 is lowered to the floor 14 after the test.

Due to the displacement of the airframe during the strength test, there is a possibility that the weight 12 may interfere with the frame 15 and other equipment arranged at the test site in addition to the floor 14. In contrast to the example shown in FIG. 3A, if the weight 12 is displaced upward because the main wing 1 </ b> A is bent downward, the weight 12 may interfere with the pulley 13.
Even in such a case, by lifting and lowering the weight 12 by the winder 20, it is possible to avoid the load of the weight 12 being supported on the frame 15 or the like and to maintain the state in which the weight is canceled.

The winding machine 20 includes a casing 21 coupled to the holding rod 182 of the weight 12, a drum 22 around which the wire 11 is wound by being pivotally supported by the casing 21 and the wire 22 being wound around the drum 22. A handle 23 that can be rotated to wind up, a speed reduction mechanism (not shown) that decelerates and transmits the rotating force of the handle 23 to the drum 22, and a winding (not shown) such as a ratchet or a one-way clutch that restricts reverse rotation of the drum 22. And a return regulating section.
In addition, the winder 20 includes a braking mechanism that brakes the rotation of the drum 22 when the wire 11 is rewound, and the wire 11 is pulled out from the drum 22 without attaching the weight 12 and attached to the loading point P or attached to the pulley 13. A switching unit 24 that switches the operation of the winder 20 between a state in which the drum 22 idles with respect to the restriction mechanism / braking mechanism and a state in which the wire 11 is wound around the drum 22 when being wound is provided.
As the configuration of the winder 20, a known configuration can be adopted as appropriate.

When the handle 23 is rotated, torque corresponding to the reduction ratio of the speed reduction mechanism is applied to the drum 22, so that the wire 11 suspending the weight 12 can be wound around the drum 22. Since the winder 20 and the weight 12 are displaced upward by the length of the wire 11 wound up, the position of the weight 12 can be adjusted without removing the weight 12.
In the present embodiment in which the wire 11 is wound while the weight 12 remains attached to the winder 20, it is not necessary to remove and attach the weight 12.
In addition, the position of the weight 12 can be easily adjusted by a simple operation of turning the handle 23 and winding the wire 11.

  As described above, the winder 20 provided in the loading device 10 allows the weight 12 to be positioned around the floor 14 or the like while the load of the weight 12 is applied to the loading point P without removing the weight 12. It can adjust so that it may not interfere with a member. Therefore, the strength test of the aircraft can proceed smoothly while keeping the aircraft in a state where its own weight is canceled.

Moreover, since the winding machine 20 is provided, the weight 12 can be separated from the floor 14 as necessary, so that as shown in FIG. It is not necessary to install the pulley 13 at a higher position in preparation for when the weight 12 is lowered.
As shown in FIG. 3B, if the pulley 13 is installed at a sufficiently high position, a sufficient distance D is secured between the weight 12 and the floor 14 with respect to the amount of displacement of the airframe during the strength test. However, the frame 15 increases in size as the pulley 13 is higher in position. Moreover, if the bell which becomes a heavy article of about 500 kg at the maximum is located above, it cannot be said that it is preferable in terms of safety as a place where people work.
According to the present embodiment, since the position of the weight 12 can be adjusted in a timely manner, an increase in the size of the frame 15 can be avoided, so that an aircraft strength test can be performed even if there is a space limitation at the test site. In addition, the cost of the strength test can be reduced. Also, safety can be secured.

In this embodiment, the position of the weight 12 can be adjusted without removing the weight 12, and therefore, the effect is particularly great in smoothly proceeding with a test for applying loads to a large number of loading points P. This will be described below.
Based on the load condition of a certain test case, if the wire 11 is pulled out from the winder 20 by an appropriate length and set in the pulley 13 or the loading point P, the load is applied when moving to another test case. It is possible that a plurality of weights 12 are likely to reach the floor 14 by changing the conditions.
At this time, once the weight 12 is removed for adjustment work such as shortening the wire 11, the load acting on the machine body is removed by the amount of the weight 12.

Therefore, if the plurality of weights 12 that do not have the winder 20 and need to be adjusted with respect to the floor 14 are removed at the same time and the wires 11 corresponding to the respective weights 12 are shortened, the plurality of weights 12 As a result of the simultaneous removal of the load, the aircraft may lose balance.
If the plurality of weights 12 are removed at the same time as described above, the balance of the machine body may be lost. Therefore, it is assumed that the adjustment work is performed by removing the weights 12 one by one in order. In that case, neither the removal / attachment of the weights 12 nor the adjustment work of the wires 11 to which the weights 12 are connected can be performed in parallel between the plurality of weights 12, so that the position adjustment work of each weight 12 is completed. It takes time.

  On the other hand, in the present embodiment, since the position of the weight 12 can be adjusted by the winder 20 without removing the weight 12, there is no fear that the weight of the weight 12 is lost and the balance of the body is lost, and the position of each of the plurality of weights 12 is determined. While confirming, the position adjustment work can proceed in parallel between the weights 12. For this reason, the work for adjusting the position of the weight 12 can be completed quickly, which can contribute to shortening the test time. The greater the number of weights 12 to be adjusted, the higher the time reduction effect.

In the present embodiment, a power source such as an electric motor that applies torque to the drum 22 of the winder 20 may be introduced.
As the winder 20, various known cargo handling machines can be used. Examples thereof include a winch, a hoist, and a lever block (registered trademark).
Further, instead of the wire 11 connected to the weight 12, an appropriate linear member such as a rope or string can be used.

Hereinafter, an example of an adjustment unit that can be replaced with the winder 20 of the first embodiment will be described.
<First Modification>
In order to adjust the position of the weight 12, as shown in FIGS. 4A and 4B, an adjustment unit 30 having a screw can be used.
The adjustment unit 30 includes a female screw 31 provided on the shaft portion of the weight 12 and a male screw 32 that engages with the inner side of the female screw 31 from above.

The female screw 31 extends on the axis of the weight 12 and is fixed to the bottom plate 181 and the top plate 183 of the weight 12. The female screw 31 may penetrate the bottom plate 181 and protrude downward from the bottom plate 181. The female screw 31 may penetrate the top plate 183 and protrude upward from the top plate 183.
The female screw 31 can also be embedded in the shaft portion of the holding rod 182 (FIG. 2A) that collects the stacked steel plates 161.

The male screw 32 is connected to the wire 11 having a predetermined length via a bracket (not shown) and hangs down.
When the male screw 32 and the female screw 31 are rotated relative to each other using a tool or the like in a state where the male screw 32 is received from above, the male screw 32 is screwed downward into the female screw 31. It is. Accordingly, the female screw 31 and the weight 12 are displaced upward with respect to the male screw 32.
When the male screw 32 and the female screw 31 are relatively rotated in opposite directions, the male screw 32 comes out upward from the inside of the female screw 31. Accordingly, the female screw 31 and the weight 12 are displaced downward with respect to the male screw 32.
Therefore, by rotating the male screw 32 and the female screw 31 relative to each other in an appropriate direction, the vertical position of the weight 12 can be adjusted so as not to interfere with surrounding members such as the floor 14.

A female screw 31 and a male screw 32 of a length necessary for adjusting the position of the weight 12 during the strength test are prepared. Then, the test is performed with the male screw 32 screwed up to an appropriate depth inside the female screw 31.
As shown in FIG. 4, when the strength test is performed with about half of the male screw 32 exposed from the upper end of the female screw 31, the weight 12 can be displaced upward and downward with a sufficient amount of displacement. .
If the female screw 31 extends from the upper end to the lower end of the weight 12, the position of the weight 12 can be adjusted by the maximum dimension (height) of the weight 12 in the vertical direction.

  In order to keep the weight 12 at the adjusted position, it is preferable that the adjustment unit 30 is provided with an anti-rotation member (such as a nut) that restricts or suppresses relative rotation between the female screw 31 and the male screw 32.

  In the configuration shown in FIG. 4, the female screw 31 is located inside the weight 12, and the position of the weight 12 can be adjusted by engaging the female screw 31 and the male screw 32 inside the weight 12. . Therefore, as shown in FIG. 5 (a), a space is secured between the weight 12 and the floor 14 as compared with the case where the female screw 31 and the male screw 32 positioned outside the weight 12 are engaged. While the height from the floor 14 to the pulley 13 is suppressed, the frame 15 can be downsized.

  The configuration shown in FIG. 5A is different from the configuration (FIG. 3B) in which the position of the weight 12 can be adjusted and the adjustment unit that can adjust the position of the weight 12 is not provided. The height from the floor 14 to the pulley 13 can be suppressed to the extent that it is not necessary to ensure a sufficient distance between the floor 12 and the floor 14. Therefore, the configuration shown in FIG.

As long as the position of the weight 12 can be adjusted by engaging the screw directly or indirectly connected to the wire 11 and the screw directly or indirectly connected to the weight 12, the weight 12 using the screw is used. The position adjusting unit 30 can be appropriately configured.
For example, as shown in FIG. 5B, the adjustment unit 30 is configured so that a male screw 32 provided on the shaft portion of the weight 12 engages with a female screw 31 that is connected to the wire 11 and hangs down. May be.

<Second Modification>
In the configuration shown in FIG. 6A, the weight 42 itself also serves as the adjustment unit 40 for the position of the weight 42.
The weight 42 is divided into a plurality of pieces 43. These pieces 43 are suspended by a chain 45 or the like on a disc 44 supported by a wire 11 having a predetermined length. The pieces 43 are arranged point-symmetrically in the direction around the axis of the wire 11 in a state where the pieces 43 hang downward from the disk 44.
The plurality of pieces 43 included in the weight 42 stand up along the axial direction of the wire 11 as shown in FIG. 6A and stand up along the axial direction of the wire 11 as shown in FIG. 6B. In this state, the posture is inverted in the vertical direction while being connected to the wire 11, thereby functioning as the adjustment unit 40 for the position of the weight 42.

In the example shown in FIG. 6C, there are a total of eight pieces 43 of the weight 42, which are formed in the same cross-sectional rhombus shape.
These pieces 43 are arranged in the direction around the axis of the wire 11 and function as one weight 42 in either a suspended state (FIG. 6A) or an upright state (FIG. 6B). The eight pieces 43 are composed of four sets of pieces 43 positioned point-symmetrically with respect to the axis of the weight 42.
The number and the cross-sectional shape of the pieces 43 are not limited to the example shown here, and can be determined as appropriate.
Each piece 43 is formed by a plurality of plates having the same cross section (here, rhombus) gathered in the axial direction of the weight 42, and one piece can be obtained by passing a wire, a rod, or the like through a hole 43A formed in these plates. Are grouped together. A necessary load can be obtained by increasing or decreasing the number of plates constituting each piece 43.

  In the state where the piece 43 is suspended, the weight 42 is in the position shown in FIG. 6A, and the distance from the floor 14 to the weight 42 is D1. When the lower end side of each piece 43 is lifted from that state, the piece 43 is expanded outward in the radial direction of the wire 11 as shown by a two-dot chain line. (FIG. 6B). Then, the position of the weight 42 rises, and the distance from the floor 14 to the weight 42 is expanded to D2.

  In order to hold the standing piece 43 as shown in FIG. 6B, an engaging portion 46 that can be engaged with the wire 11 is provided at the upper end of each piece 43 when standing (the lower end when drooping). ing. An engaged portion for engaging the engaging portion 46 can also be provided on the wire 11.

<Third Modification>
Also in the configuration shown in FIG. 7A, the weight 47 itself also serves as the adjustment unit 40 for the position of the weight 47.
The weight 47 is divided into a plurality of pieces 43.
As shown in FIG. 7 (d), the weight 47 has four sets (A 1, A 2, A 3, A 4) of pieces 43 positioned symmetrically with respect to the axis of the weight 47.
Then, the upper ends of the pieces 43 forming the same set are assembled through the support member 48. The support member 48 holds pieces 43 of the same set in a point-symmetrical position, and is prepared individually for the sets A1 to A4. Each of the pieces 43 hangs down below the support member 48 because the support members 48 are supported by the wires 11.

As shown in FIG. 7A, the wire 11 having a predetermined length includes a lower stopper 491 provided at a position determined on the wire 11 and a position determined on the wire 11 as well. And an upper stopper 492 provided at the top. Here, the positions where the four support members 48 are restricted by the stoppers 491 and 492 are indicated by black circles in FIGS. It is also possible to provide stoppers 491 and 492 that collectively restrict the positions of the support members 48.
The lower stopper 491 restricts the downward movement of the support member 48. Further, the upper stopper 492 restricts the movement of the support member 48 further upward. The support member 48 can slide along the wire 11 between the lower stopper 491 and the upper stopper 492. The support member 48 slid downward is held by the lower stopper 491. The support member 48 slid upward is held by the upper stopper 492.

By sliding the support member 48, the piece 43 can be slid along the wire 11 for each group. The pieces 43 in a point-symmetrical position can be stably slid.
As shown in FIG. 7B, the piece 43 and the piece 43 forming the group A1 are slid until the support member 48 reaches the upper stopper 492. Similarly, the pieces 43 and 43 forming the set A2, the pieces 43 and 43 forming the set A3, and the pieces 43 and 43 forming the set A4 are sequentially slid until the upper stopper 492 is reached.
As a result, the weight 47 located below as shown in FIG. 7A rises to a position above it as shown in FIG. 7C. Accordingly, the distance D1 from the floor 14 to the weight 47 is increased to the distance D2.

  Instead of providing the lower stopper 491 and the upper stopper 492 on the wire 11, a holder that can be held at an appropriate position of the wire 11 can be provided on the support member 48. Then, since the support member 48 slid along the wire 11 is held at an appropriate position of the wire 11 by the holder, the position of the weight 47 can be adjusted steplessly.

<Fourth Modification>
A weight 50 shown in FIG. 8A includes a weight body 51 and a bag body 52 disposed around the wire 11 inside the weight body 51.
The weight main body 51 includes a first portion 511 supported by the wire 11 and a substantially cylindrical second portion 512 surrounding the first portion 511. The wire 11 passes through the second portion 512. The bag body 52 is disposed between the first portion 511 and the second portion 512.

  The bag body 52 can contain compressed air. When the compressed air is not put in the bag body 52, the second portion 512 is supported on the upper end of the first portion 511 as shown in FIG. The second portion 512 extends downward from the first portion 511.

When compressed air is introduced into the bag body 52 from a valve (not shown), the bag body 52 swells in a cylindrical shape and increases in height as shown in FIG. Due to the bag body 52, the second portion 512 is pushed upward along the wire 11.
The vertical position of the weight body 51 can be adjusted by increasing / decreasing the bulk of the bag body 52 when the compressed air is inserted into or removed from the bag body 52 through the valve.
Compressed air can be supplied into the bag body 52 from a compressed air source provided at the test site.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIGS.
In the following, the description will be focused on matters that are different from the first embodiment. The same components as those described in the first embodiment are denoted by the same reference numerals.
As shown in FIG. 9, the loading device 60 of the second embodiment receives the weight 11, the weight 12, the pulley 13, which is a fixed pulley, and the weight 12 below the pulley 13, and the wire 11 is wound around. And a winder 20 capable of winding the wire 11.

In the present embodiment, the casing of the winder 20 is not coupled to the weight 12 and is installed on the frame 15. A force corresponding to half of the load of the weight 12 acts on the winder 20. The frame 15 is responsible for the reaction force of the force acting on the winder 20.
Since half of the load of the weight 12 is supported by the frame 15, in order to apply the same load to the loading point P as in the first embodiment, the weight 12 having a weight twice that of the first embodiment is used.

  The wire 11 is wound around the drum of the winder 20 from the loading point P via the pulley 13 and the movable pulley 61. The weight 12 is supported by the movable pulley 61 in the middle of the wire 11.

By using the movable pulley 61 that receives the weight 12 in the middle of the wire 11, the winder 20 can be disposed at a position separated from the weight 12. Therefore, as shown in FIG. 10, the winders 20 corresponding to the wires 11 connected to each of the plurality of loading points P scattered in various parts of the airframe (here, the main wing 1 </ b> A) are gathered in a predetermined region in the frame 15. Are arranged.
Another pulley can be interposed in the section where the wire 11 is routed from the movable pulley 61 to the winder 20.

If the winder 20 is operated near the weight 12, an operator needs to move from the weight 12 to another weight 12 when adjusting the positions of the plurality of weights 12.
On the other hand, when the winder 20 is gathered in a predetermined region of the frame 15 that is distant from the position of the weight 12 as in this embodiment, the position adjustment of the plurality of weights 12 is efficiently performed on the spot. Can be done automatically.

  Further, since the movable pulley 61 receives the weight 12, the displacement amount of the weight 12 is halved with respect to the displacement amount of the airframe, so the distance that the weight 12 approaches toward the floor 14 during the strength test. The (displacement amount) is also halved. . Therefore, the strength test can proceed smoothly, and the height of the frame 15 can be suppressed.

[Third Embodiment]
Next, a third embodiment of the present invention will be described with reference to FIG.
In the third embodiment, when performing the strength test, the weight of the airframe is canceled by lifting the airframe with the weight 12 and the pulley 13, and the position adjustment amount from the position (initial position) of each weight 12 at that time is obtained. Keep it.
The dead weight of the airframe can be canceled by the loading device 10 and the loading device 60 described above.

The position adjustment amount from the initial position of each of the plurality of weights 12 is calculated by a loading test information processing apparatus including an arithmetic unit.
FIG. 11 shows a processing procedure executed by the loading test information processing apparatus.
The processing procedure includes a step S10 for estimating a displacement amount generated in the entire body, and a step S20 for calculating a position adjustment amount from the initial position of each weight 12 based on the estimated body displacement amount.

  Aircraft displacement amount estimation step S10 estimates the airframe displacement amount that occurs in each part of the airframe due to the cancellation of its own weight by weight 12, and estimates the airframe displacement amount that occurs in each part of the airframe by lifting the entire body whose weight has been corrected. Step S12, Step S13 for estimating the amount of airframe displacement that occurs in each part of the airframe by applying the load specified by the test case with the hydraulic actuator 19, etc., and the amount of airframe displacement estimated in Steps S11 to S13, respectively. Step S14 for estimating the estimated total body displacement amount (estimated structure displacement amount).

  In the weight position adjustment amount calculation step S20, a step S21 for estimating a body displacement amount (a loading load location displacement amount) at each loading location P based on the total body displacement amount, and a loading location P based on the loading load location displacement amount, respectively. Step S22 for estimating the displacement amount (estimated weight displacement amount) of each weight 12 corresponding to the above, Step S23 for calculating the position of each weight 12 that does not interfere with surrounding members such as the floor 14, and the calculated position of no interference Step S24 for calculating a position adjustment amount from the initial position of each weight 12 in the range.

  By performing steps S10 and S20 described above, the position adjustment amount from the initial position of each weight 12 is calculated. By adjusting the position adjustment amount, the position of the weight is adjusted by using any one of the adjustment units described in the first embodiment and the first to fourth modifications and the second embodiment described above, You can do a test.

[Fourth Embodiment]
Next, a fourth embodiment of the present invention will be described with reference to FIG.
In the fourth embodiment, the position adjustment work from the initial position of each weight 12 is obtained for each test case by the same method as in the third embodiment, thereby reducing the position adjustment work of the weight 12.

FIG. 12 shows a processing procedure (steps S10 and S20) executed by the loading test information processing apparatus.
By performing Step S10 and Step S20 for each test case, the position adjustment amount from the initial position of each weight 12 is calculated for each test case.
By grasping these position adjustment amounts during the strength test, the operation of appropriately adjusting the position of each weight 12 according to the test case can be smoothly performed.

In the strength test, in addition to obtaining in advance the position adjustment amount from the initial position of each weight 12 for each test case, a marking indicating the position adjustment amount of each weight 12 is used as a wire to suspend the corresponding weight 12 If it is applied to 11 etc., the workability of the position adjustment of the weight 12 is further improved.
In that case, following step S10 and step S20, step S30 which marks the wire 11 etc. which suspends each weight 12 is performed.
For example, when the loading device 10 (FIG. 1) including the winder 20 is used, as shown in FIG. 13, markings M1, M2, and M3 indicating the amount of position adjustment based on the initial position H0 of the weight 12 are used. Is applied to the wire 11. The markings M1, M2, and M3 individually correspond to test cases.
In carrying out each test case, the position of the weight 12 can be easily adjusted by winding the wire 11 to the corresponding marking position.

  The marking can be applied to an appropriate target according to the configuration of the adjustment unit that can adjust the position of the weight. For example, it is possible to mark the male screw 32 of the adjustment unit 30 described in the first modification of the first embodiment.

[Fifth Embodiment]
Next, a fifth embodiment of the present invention will be described with reference to FIG.
In the fifth embodiment, as in the fourth embodiment, the position adjustment amount from the initial position of each weight 12 is obtained for each test case.
In addition, in the fifth embodiment, step S40 for determining the order of the plurality of test cases based on the obtained position adjustment amounts of the respective weights 12 is performed by the loading test information processing apparatus. Thereby, the position adjustment work of the weight 12 is further reduced.

In step S40, a plurality of test cases that can set the same position on the same weight 12 is obtained based on the range of positions that do not interfere with surrounding members calculated in step S23, and these test cases are continuously executed. Determine the order in which test cases will be conducted. The execution order of the test cases is preferably determined from the viewpoint of relatively reducing the number of times of adjusting the position of the weight 12.
For the test cases that are subsequently performed, a common position adjustment amount is set as the position adjustment amount from the initial position of the weight 12. Step S24 for calculating the position adjustment amount from the initial position of the weight 12 and step S40 may be integrated.
When the test cases are performed according to the order determined in step S40, the position adjustment of the weight 12 is not necessary because the position adjustment of the weight 12 for which a common position adjustment amount is set among the plurality of test cases to be subsequently performed is not necessary. The number of operations to be performed can be reduced.

  In the present embodiment, as described in the fourth embodiment, it is also preferable to apply markings indicating the weight position adjustment amount to the wire 11 or the like.

In addition to the above, as long as the gist of the present invention is not deviated, the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.
The loading device according to the present invention does not necessarily include the pulley 13 that causes the load of the weight 12 to act upward on the structure. As long as the loading device that does not include the pulley 13 and applies the load of the weight 12 suspended by using the wire 11 to the structure as it is is provided with an adjustment unit that can adjust the vertical position of the weight. Are included in the present invention.

The present invention can be widely applied to strength tests of structures other than aircraft.
The loading device described in each of the above embodiments can be used not only for a multi-point loading test but also for a test in which a load of the weight 12 is applied to a single loading point P set on a structure.

1A Main Wing 10 Loading Device 11 Wire (Linear Member)
12 weight 13 pulley (fixed pulley)
14 Floor (surrounding members)
15 Frame 16 Laminate 17 Cover 18 Holder 19 Hydraulic Actuator 20 Winder (Adjustment Unit)
21 Casing (joint part, installation part)
22 Drum 23 Handle 24 Switching unit 30 Adjusting unit 31 Female screw (first screw)
32 Male screw (2nd screw)
40 Adjustment part 42 Weight 43 Piece 44 Disc 45 Rope 46 Engagement part 47 Weight 48 Support member 50 Weight 51 Weight body 52 Bag body 60 Loading device 61 Moving pulley 161 Steel plate 163 Slot 181 Bottom plate 182 Holding rod 183 Top plate 491 Lower side Stopper 492 Upper stopper 511 First portion 512 Second portion A1 to A4 Set D Distance D1 Distance D2 Distance H0 Initial position M1, M2, M3 Marking P Loading location S10 Machine body displacement amount estimation step S20 Weight position adjustment amount calculation step

Claims (14)

A loading device that applies a load of a weight suspended using a linear member to each of a plurality of loading points of a structure,
The weight;
The linear member;
An adjustment unit capable of adjusting the position of the weight in the vertical direction,
A loading device characterized by that. It has a fixed pulley that is installed above the above-mentioned load location and on which the linear member is hung.
The loading device according to claim 1. The adjustment unit is
A coupling portion coupled to the weight;
A drum around which the linear member is wound when torque is applied,
The loading apparatus according to claim 1 or 2, wherein A moving pulley that receives the weight below the fixed pulley;
The adjustment unit is
An installation part installed on a member that is responsible for the reaction force of the force acting on the adjustment part above the movable pulley;
A drum around which the linear member is wound when torque is applied;
The linear member is
Via the fixed pulley and the moving pulley, wound around the drum of the adjustment unit,
The loading device according to claim 2. The member responsible for the reaction force is
It is a frame where work associated with the test using the loading device described above is performed,
The adjusting unit installed in the frame is
Collected in a predetermined area of the frame,
The loading apparatus according to claim 4. The adjustment unit is
A first screw connected to the linear member and hanging down;
A second screw connected to the weight and engaged with the first screw;
The loading apparatus according to claim 1 or 2, wherein The weight is
Arranged in the direction around the axis of the linear member, having a plurality of pieces as the adjustment unit,
The plurality of pieces are
A state of hanging along the axial direction of the linear member;
From the suspended state to the state of standing up along the axial direction through a state of expanding to the outside in the radial direction of the linear member,
It is possible to flip the posture up and down,
The loading apparatus according to claim 1 or 2, wherein The weight is
It has a plurality of pieces arranged in the direction around the axis of the linear member,
Among the plurality of pieces, those facing each other in the diameter direction of the linear member are assembled and assembled.
For each group,
The piece is slidable along the linear member;
The loading apparatus according to claim 1 or 2, wherein Used for testing the aircraft as the structure,
The loading device according to any one of claims 1 to 8. With the loading device according to any one of claims 1 to 9,
A test method of applying a load of the weight suspended by using the linear member to each of a plurality of the above-described load locations,
Adjusting the vertical position of the weight by the adjustment unit so as to avoid the weight from interfering with surrounding members;
A loading test method characterized by that. A predetermined load is applied to the structure while applying a load of the weight suspended by using the linear member hung around a fixed pulley installed above the load point to each of the plurality of load points described above. Add
The loading test method according to claim 10. In performing a test to apply a predetermined load to the structure while changing the load condition while canceling the weight of the structure by lifting the structure by the load of the weight using the fixed pulley,
A state in which the weight of the structure is canceled by applying a lifting load by the weight and the fixed pulley to each of the plurality of load points described above,
Obtaining a position adjustment amount from the initial position of each of the plurality of weights for each of a plurality of test cases with different load conditions by a load test information processing apparatus provided with an arithmetic device;
Applying the marking indicating the position adjustment amount of each of the plurality of weights to the linear member or the adjustment unit that suspends the corresponding weight.
The loading test method according to claim 11, wherein: In the step of obtaining the position adjustment amount of the weight,
An estimated structure displacement obtained by estimating a displacement generated in the structure;
The amount of displacement of the apparent load point obtained by estimating the amount of displacement of the structure at each of the plurality of load points,
Using the estimated weight displacement amount obtained by estimating the displacement amount of the weight respectively corresponding to a plurality of the above-mentioned load locations,
Obtaining the position adjustment amount of the weight;
The loading test method according to claim 12, wherein: In performing a test to apply a predetermined load to the structure while changing the load condition while canceling the weight of the structure by lifting the structure by the load of the weight using the fixed pulley,
A state in which the weight of the structure is canceled by applying a lifting load by the weight and the fixed pulley to each of the plurality of load points described above,
From the viewpoint of relatively reducing the number of operations for adjusting the position of the weight by the information processing apparatus for loading test provided with an arithmetic device, performing a step of determining the order in which a plurality of test cases with different load conditions are performed,
Performing the test cases according to the sequence;
The loading test method according to claim 11, wherein:

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