JPS6355017B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention involves holding a test material between a pair of frames attached to a column, and applying a tensile load, a compressive load, or a torsional load to the test material on one of the pair of frames. The present invention relates to an improvement of a material testing machine equipped with an actuator that applies a test load such as the above.

In conventional materials testing machines of this type, the column is permanently fixed to the base of the machine, and therefore the position of the actuator and the position of the test part are almost always set at fixed positions, and these positions cannot be changed. This was extremely inconvenient as it was not possible to change the position significantly depending on the exam situation. For example, a vertical test machine has a pair of frames attached to the support in an upper and lower arrangement by permanently fixing the support to the aircraft base in a vertical position, and an actuator is installed on either of the upper and lower frames. Then, when testing in a high temperature atmosphere, it is preferable to position the actuator at the bottom, and when testing in a low temperature atmosphere, it is preferable to position the actuator at the top. Although it is often required to selectively convert vertically in relation to position,
This is not possible, and therefore the testable range is limited to a narrow range, which is very inconvenient.

This invention was made with the aim of solving the above-mentioned conventional problems.

The present invention provides a material testing machine in which a test material is held between a pair of frames attached to a pair of supports, and one of the pair of frames is provided with an actuator that applies a test load to the test material. The center of the strut is supported on the fuselage bracket via a support shaft that intersects with the strut, and each of the struts is configured to be able to rotate 180 degrees around the support shaft with respect to the fuselage bracket, and both ends of each of the struts are are provided with legs for fixing to the fuselage bed, respectively, and are further provided with an operating mechanism for guiding the fuselage bracket so as to be movable up and down relative to the fuselage bed, and lifting the fuselage bracket between the fuselage bracket and the fuselage bed. It is characterized by:

Embodiments of the present invention will be described below with reference to the drawings.

The drawing shows an example of a vertical testing machine, in which a pair of left and right columns 1, which are vertical and parallel to each other,
1, a pair of upper and lower frames 2 and 3 are attached at intervals. Disc-like legs 1a, 1a and 1b, 1b of appropriate size are fixedly attached to the upper and lower ends of both supports 1, 1. The upper frame 2 of both frames is fixed to the columns 1, 1, while the lower frame 3 is movable along the columns 1, 1.

The upper frame 2 and the lower frame 3 have
Test material holders 2a and 3a consisting of grippers or platens facing each other are provided.
The test material 4 is held between the frames 2 and 3 by a and 3a. Then, the lower frame 3 is subjected to tests such as tensile load, compression load, torsional load, etc. by applying an axial pulling force, pushing force, or rotating force to the holder 3a, and applying a tensile load, compressive load, or torsional load to the held test material 4. An actuator 5 consisting of a hydraulic cylinder or the like for applying a load is provided. The lower frame 3 is configured as a crosshead that applies a test load to the test material 4, and the upper frame 2 is configured as a cross yoke that supports the reaction force of the load.

Between the legs 1b, 1b at the lower ends of both columns 1, 1 and the lower frame 3, the lower frame 3 is moved along both columns 1, 1, and the space between both frames 2, 3 is adjusted. Jacks 6, 6 are interposed for adjusting and setting the distance to a desired distance according to the dimensions of the test material 4. The lower frame 3 is provided with jacks 7, 7 for fixing it to both supports 1, 1 at a desired movement position by the jacks 6, 6.

Here, both the columns 1, 1 are connected to each other by means of support shafts 8, 8 which intersect the columns 1, 1 at right angles to the central part between the two frames 2, 3 in their lengths. It is supported by a pair of left and right fuselage brackets 9, 9 placed on both sides of the machine. In this way, both struts 1, 1 can be moved up and down with respect to the fuselage brackets 9, 9 around the support shafts 8, 8.
It can be rotated 180°. Both aircraft brackets 9,
9 is erected and fixed to the fuselage bed 10 installed on the floor, which constitutes a pedestal for the legs 1b, 1b at the lower end of both the supports 1, 1, or the legs 1a, 1a at the upper end. Then, the fixing bolts 11, 11 are used to fix the fuselage bed 10, so that the legs 1b, 1b at the lower end or the legs 1b, 1b at the upper end thereof The legs 1a, 1a can be selectively fixed.

Further, the support shaft 8 is provided with suitable operating means for reversing the support columns 1, 1. This operation means here includes a support shaft 8 fixed to the support column 1 that is rotatably supported by the fuselage bracket 9, and a worm wheel 12 fixedly attached to the support shaft 8 that is rotatably supported by the fuselage bracket 9. A worm 13 is engaged with the worm 13, and a rotating operation handle 14 is attached to the shaft of the worm 13. However, if the handle 14 is rotated, the worm 13
The support shaft 8 is rotated by the worm wheel 12, and thereby the support column 1 is rotated together with the support shaft 8, so that both support columns 1, 1 can be turned upside down about the support shafts 8, 8. . Note that such an operating means is provided as necessary, and instead of the above configuration, for example, the support shaft 8 may be rotated by a motor,
Other suitable configurations may be used.

Also, when inverting both the support columns 1, 1 around the support shafts 8, 8, the lower legs 1b, 1b or the upper leg 1
In order to allow the brackets 9, 1a to be laterally removed from the fuselage bed 10, both the fuselage brackets 9, 9 are configured to be extendable in the longitudinal direction. That is, both the fuselage brackets 9, 9 are connected to the support shaft 8 and the fuselage bed 10, respectively.
The upper part 9 is divided into an upper part 9a and a lower part 9b.
The structure is provided with an actuating means 15 consisting of a fluid pressure actuated cylinder or the like for moving the part a upwardly relative to the lower part 9b (see FIG. 2). Therefore, when the two struts 1, 1 are reversed about the support shafts 8, 8, the upper part 9a of the fuselage bracket 9 is moved by the actuating means 15 as shown by the imaginary lines in FIG.
By raising the legs relative to the lower part 9b, the entire struts 1, 1 are lifted upward together with the support shafts 8, 8, and the legs 1b, 1b or 1a, 1a are upwardly separated from the fuselage bed 10, and the separation distance is Side leg 1
b, 1b or 1a, 1a can be laterally removed from the fuselage bed 10 along an arcuate rotation locus L centered around the support shafts 8, 8. In addition, in order to separate the legs 1b, 1b or 1a, 1a from the fuselage bed 10, for example, the mutual contact surfaces of the legs 1b, 1b and 1a, 1a and the fuselage bed 10 must be aligned with the support shaft. The brackets 9, 9 may be formed into arcuate surfaces having centers 8, 8, and in this case, it is not necessary to configure the body brackets 9, 9 to be extendable as described above.

Thus, according to the material testing machine with the above configuration, the columns 1, 1 can be vertically reversed by 180 degrees with respect to the body brackets 9, 9 around the support shafts 8, 8.
By this reversal, it is possible to reverse the vertical positions of the upper frame 2 and the lower frame 3, and therefore the position of the actuator 5 can be changed to the position of the test material 4.
It is possible to change the position either below or above. Therefore, when a test is conducted in a high temperature atmosphere, the actuator 5 can be placed in a lower position to avoid the actuator 5 from being adversely affected by hot air, and when a test is conducted in a low temperature atmosphere, the actuator 5 can be positioned downward. By positioning the actuator 5 in the upper position, it is possible to avoid the adverse influence of cold air on the actuator 5, and in this way, it is possible to perform accurate tests in a state suitable for each test situation.

In the embodiment described above, the central part of the length of the column is supported by the spindle relative to the fuselage bracket, but the position where the column is supported by the spindle is as follows:
It may be placed at a position other than the center of the length of the support, and may be placed at any appropriate position. Furthermore, the support shaft may not intersect the support at a right angle, but may intersect obliquely at an appropriate angle. Furthermore, the present invention is applicable not only to vertical testing machines, but also to horizontal testing machines that are used with the support horizontally oriented, or testing machines that are used with the support slanted. It can be configured as a testing machine that allows the position of the actuator or the testing part to be changed significantly depending on the testing situation.

As explained above, according to the present invention, the pair of struts 1 are supported by the fuselage bracket 9a via the support shafts 8 intersecting with the support struts 1, and each strut 1 is rotated around the support shaft 8 with respect to the fuselage bracket 9a. It can be moved and rotated 180°. Further, according to the present invention, the legs 1a and 1b are provided at both ends of each support 1.
is provided. The legs 1a and 1b are the fuselage bed 10
It is for fixing to. Further, the fuselage bracket 9a is guided to be movable up and down relative to the fuselage bed 10, and an operating mechanism 15 is provided between the fuselage bracket 9a and the fuselage bed 10. When each support column 1 is reversed by 180 degrees, the operating mechanism 15 allows the Bracket 9a is lifted. Therefore, each post 1
is lifted together with the fuselage bracket 9a, and its leg 1a or 1b is lifted from the fuselage bed 10. Therefore, each support column 1 can be reversed without any problem without being hindered by the legs 1a, 1b. After the reversal, the fuselage bracket 9a can be lowered to its original height, and each strut 1 can be lowered together with the fuselage bracket 1a. Therefore, the legs 1a, 1b can come into contact with the fuselage bed 10, and the legs 1a, 1b can be fixed to the fuselage bed 10. As a result, for example, when testing the test material 4 in a high temperature atmosphere, the actuator 5 can be positioned below the test material 4 and protected from the high temperature atmosphere. On the other hand, when testing the test material 4 in a low temperature atmosphere, the actuator 5
can be placed above the test material 4 and protected from the low temperature atmosphere. Furthermore, the legs 1a and 1b of each support column 1 can be fixed to the fuselage bed 10, the test material 4 and the actuator 5 can be kept at a constant position, and the test material 4 can be tested accurately.

[Brief explanation of drawings]

FIG. 1 is a front view showing an embodiment of a testing machine according to the present invention, and FIG. 2 is a side view thereof. DESCRIPTION OF SYMBOLS 1... Strut, 2, 3... Frame, 4... Test material, 5... Actuator, 8... Support shaft, 9...
...Aircraft bracket, 10...Aircraft bed.

Claims (1)

[Claims] 1. A material testing machine in which a test material is held between a pair of frames attached to a pair of supports, and one of the pair of frames is provided with an actuator that applies a test load to the test material. , the center of each of the pillars is supported on the fuselage bracket via a support shaft that intersects with the support pillar, and each of the pillars is configured to be reversible by 180° around the support shaft with respect to the fuselage bracket; A leg portion for fixing to the fuselage bed is provided at each end of the support, and an operation for guiding the fuselage bracket so as to be movable up and down relative to the fuselage bed, and lifting the fuselage bracket between the fuselage bracket and the fuselage bed. A material testing machine characterized by being equipped with a mechanism.