CN106240842B - A kind of asymmetric fuselage bulkhead four-point bending test method and device - Google Patents
A kind of asymmetric fuselage bulkhead four-point bending test method and device Download PDFInfo
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- CN106240842B CN106240842B CN201610541264.7A CN201610541264A CN106240842B CN 106240842 B CN106240842 B CN 106240842B CN 201610541264 A CN201610541264 A CN 201610541264A CN 106240842 B CN106240842 B CN 106240842B
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- 238000013001 point bending Methods 0.000 title claims abstract description 41
- 238000010998 test method Methods 0.000 title claims abstract description 21
- 238000012360 testing method Methods 0.000 claims abstract description 90
- 238000000429 assembly Methods 0.000 claims abstract description 35
- 230000000712 assembly Effects 0.000 claims abstract description 35
- 238000005452 bending Methods 0.000 claims abstract description 15
- 238000005192 partition Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 abstract 1
- 238000005259 measurement Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 2
- 238000009661 fatigue test Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
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Abstract
The invention discloses a kind of asymmetric fuselage bulkhead four-point bending test method and devices.The asymmetric fuselage bulkhead four-point bending test method includes the following steps: step 1: adding test block for asymmetric fuselage bulkhead to be measured；Step 2: to increase separately a load head assembly on two opposite weighted platforms of experiment loading unit, the load head assembly can adapt to the bending deformation that fuselage bulkhead is occurred, remain that loading force is vertical with bulkhead flat segments (similarly hereinafter)；Step 3: asymmetric fuselage bulkhead to be measured being arranged between two load head assemblies, and carries out four-point bending test.The cross section flexual center that asymmetric fuselage bulkhead four-point bending test method in the present invention makes the load pressure heart of the asymmetric fuselage bulkhead in load test pass through the asymmetric fuselage bulkhead, the bending deformation for adjusting asymmetric fuselage bulkhead to be measured by way of deforming when loading head assembly in stress in load, achievees the purpose that the asymmetric eccentric structure of measurement.
Description
Technical Field
The invention relates to the technical field of static force/fatigue test of airplane structures, in particular to a four-point bending test method and a four-point bending test device for an asymmetric fuselage bulkhead.
Background
In the static force/fatigue test of an airplane structure, a test piece for four-point bending is generally of a symmetrical structure, and because the cross section profile loaded by a fuselage bulkhead is of an asymmetrical eccentric structure, eccentric moment can be generated when ballast is directly applied to a testing machine, so that the posture of the test piece is inclined. This eccentric moment will be transmitted to the testing machine through the anchor clamps, results in the bending of the testing machine chuck, and along with the increase of ballast, this moment also can grow, is the trend of dispersing to probably lead to the test piece experimental data set failure mode inaccurate.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide an asymmetric fuselage bulkhead four-point bend test method that overcomes or at least alleviates at least one of the above-mentioned deficiencies of the prior art.
In order to achieve the aim, the invention provides a four-point bending test method for an asymmetric fuselage bulkhead, which comprises the following steps: step 1: adding a test block to the asymmetric fuselage bulkhead to be tested, so that a loading pressure center of the asymmetric fuselage bulkhead during loading test passes through a cross section bending center of the asymmetric fuselage bulkhead; step 2: respectively adding a loading head assembly on two opposite loading platforms of a test loading device, wherein the loading head assembly can adapt to bending deformation of a machine body bulkhead and always keep a loading force vertical to a straight section of the bulkhead; and step 3: and arranging the asymmetric fuselage bulkhead to be tested between the two loading head assemblies, and performing a four-point bending test.
Preferably, the asymmetric fuselage bulkhead four-point bending test method further comprises: pre-step 1: and calculating the bending center of the cross section of the asymmetric fuselage bulkhead to be detected.
The invention also provides a four-point bending test device for the asymmetric fuselage bulkhead, which is used for installing the asymmetric fuselage bulkhead to be tested to a test loading device and carrying out the four-point bending test method for the asymmetric fuselage bulkhead as described above, wherein the test loading device is used for applying load to the asymmetric fuselage bulkhead to be tested, and each asymmetric fuselage bulkhead is provided with two bulkhead loading sections; it is characterized in that the asymmetric fuselage bulkhead four-point bending test device comprises: the test block assemblies are divided into two groups, one group of test block assemblies are arranged on one bulkhead loading section of the asymmetric fuselage bulkhead to be tested, and the other group of test block assemblies are arranged on the other bulkhead loading section; the loading head assemblies are four in number, wherein every two loading head assemblies are used for one bulkhead loading section, so that the four loading head assemblies are divided into a first loading group and a second loading group; one loading head assembly in the first loading group is arranged on one surface of one loading platform of the test loading device; the other loading head assembly is arranged on one surface of the other loading platform, and the two loading head assemblies are oppositely arranged so as to form a loading space which is used for clamping one partition frame loading section; one loading head assembly in the second loading group is arranged on one surface of one loading platform of the test loading device; the other loading head assembly is arranged on one surface of the other loading platform, and the two loading head assemblies are oppositely arranged so as to form a loading space which is used for clamping the other bulkhead loading section; the test block assembly is used for following the bending deformation of the fuselage bulkhead, and always keeping the loading force vertical to the straight section of the bulkhead, so that the constant bending moment applied in the four-point bending test is ensured to be unchanged; the loading head assembly is used for moving along with the asymmetric fuselage bulkhead when the asymmetric fuselage bulkhead deforms under load, and all the loading head assemblies are matched, so that the direction of the force applied to the asymmetric fuselage bulkhead by the test loading device in the loading process is always perpendicular to the asymmetric fuselage bulkhead.
Preferably, the test block assembly comprises a plurality of test blocks, and each test block is detachably connected with the bulkhead loading section.
Preferably, the test block is bolted to the bulkhead loading section.
Preferably, each of said loading head assemblies comprises: the bracket is connected with the loading platform; the first loading head is arranged on the bracket, and the surface of the first loading head, which is far away from the bracket, is a concave surface; a second loading head, one surface of which is a concave surface and the other surface of which is a flat surface, wherein the flat surface is in contact with the bulkhead loading section, the concave surface of the second loading head is opposite to the concave surface of the first loading head, and a receiving space is formed between the concave surface of the first loading head and the concave surface of the second loading head; and the cylinder is arranged in the accommodating space and can rotate in the accommodating space.
Preferably, the area of the surface of the bracket carrying the first loading head is larger than the area of the surface of the first loading head in contact with the bracket.
The four-point bending test method of the asymmetric fuselage bulkhead in the invention enables the loading pressure center of the asymmetric fuselage bulkhead during loading test to pass through the cross section bending center of the asymmetric fuselage bulkhead, and adjusts the bending deformation of the asymmetric fuselage bulkhead to be tested in a way that the loading head assembly deforms when stressed during loading, thereby achieving the purpose of measuring the asymmetric eccentric structure.
Drawings
Fig. 1 is a schematic flow chart of an asymmetric fuselage bulkhead four-point bending test method according to an embodiment of the invention.
Fig. 2 is a schematic structural diagram of an asymmetric fuselage bulkhead four-point bending test apparatus according to an embodiment of the invention.
Reference numerals
| 1 | Test loading device | 31 | Support frame |
| 2 | Asymmetric fuselage bulkhead | 32 | First loading head |
| 3 | Loading head assembly | 33 | Second loading head |
| 11 | Loading platform | 34 | Cylinder |
| 4 | Test block |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
Fig. 1 is a schematic flow chart of an asymmetric fuselage bulkhead four-point bending test method according to an embodiment of the invention. Fig. 2 is a schematic structural diagram of an asymmetric fuselage bulkhead four-point bending test apparatus according to an embodiment of the invention.
The asymmetric fuselage bulkhead four-point bending test method shown in FIG. 1 comprises the following steps: step 1: adding a test block to the asymmetric fuselage bulkhead to be tested, so that a loading pressure center of the asymmetric fuselage bulkhead during loading test passes through a cross section bending center of the asymmetric fuselage bulkhead; step 2: respectively adding a loading head assembly on two opposite loading platforms of a test loading device, wherein the loading head assembly can adapt to bending deformation of a machine body bulkhead and always keep a loading force vertical to a straight section of the bulkhead; and step 3: and arranging the asymmetric fuselage bulkhead to be tested between the two loading head assemblies, and performing a four-point bending test.
The four-point bending test method of the asymmetric fuselage bulkhead in the invention enables the loading pressure center of the asymmetric fuselage bulkhead during loading test to pass through the cross section bending center of the asymmetric fuselage bulkhead, and adjusts the bending deformation of the asymmetric fuselage bulkhead to be tested in a way that the loading head assembly deforms when stressed during loading, thereby achieving the purpose of measuring the asymmetric eccentric structure.
It can be understood that the asymmetric fuselage bulkhead four-point bending test method further comprises the following steps of 1: and obtaining the cross section bending center of the asymmetric fuselage bulkhead to be measured. The cross-sectional centroid can be calculated from the cross-sectional geometry or can be known in advance.
The invention also provides a four-point bending test device for the asymmetric fuselage bulkhead, which is used for installing the asymmetric fuselage bulkhead to be tested to the test loading device and carrying out the four-point bending test method for the asymmetric fuselage bulkhead as described above, wherein the test loading device 1 is used for applying load to the asymmetric fuselage bulkhead 2 to be tested, and each asymmetric fuselage bulkhead 2 is provided with two bulkhead loading sections.
The asymmetric fuselage bulkhead four-point bending test device shown in fig. 2 comprises test block assemblies and a loading head assembly 3, wherein the test block assemblies are divided into two groups, one group of test block assemblies is arranged on one bulkhead loading section of the asymmetric fuselage bulkhead 2 to be tested, and the other group of test block assemblies is arranged on the other bulkhead loading section; the number of the loading head assemblies 3 is four, wherein every two loading head assemblies 3 are used for one bulkhead loading section, so that the four loading head assemblies are divided into a first loading group and a second loading group; one loading head assembly 3 in the first loading group is arranged on one surface of one loading platform 11 of the test loading device 1; the other loading head assembly 3 is arranged on one surface of the other loading platform 11, and the two loading head assemblies 3 are oppositely arranged, so that a loading space is formed and is used for clamping a partition frame loading section; one loading head assembly 3 in the second loading group is arranged on one surface of one loading platform 11 of the test loading device; the other loading head assembly 3 is arranged on one surface of the other loading platform 11, and the two loading head assemblies 3 are oppositely arranged, so that a loading space is formed and is used for clamping the other bulkhead loading section; the test block assembly is used for following the bending deformation of the machine body bulkhead frame and always keeping the loading force vertical to the straight section of the bulkhead frame, so that the constant bending moment applied in the four-point bending test is ensured to be unchanged; the loading head assembly is used for moving along with the asymmetric fuselage bulkhead when the asymmetric fuselage bulkhead deforms under load, and all the loading head assemblies are matched, so that the direction of the force applied to the asymmetric fuselage bulkhead by the test loading device in the loading process is always perpendicular to the asymmetric fuselage bulkhead.
The asymmetric fuselage bulkhead four-point bending test device adopts the test block assembly to enable the loading pressure center of the asymmetric fuselage bulkhead during loading test to pass through the cross section bending center of the asymmetric fuselage bulkhead, and adjusts the bending deformation of the asymmetric fuselage bulkhead to be tested in a mode that the loading head assembly deforms when stressed during loading, so that the purpose of measuring the asymmetric eccentric structure is achieved.
It will be appreciated that the test block assembly comprises a plurality of test blocks 4, each test block 4 being removably connected to the bulkhead loading section. It will be appreciated that the number of test blocks depends on the shape of the asymmetric fuselage formers. For example, in the embodiment shown in fig. 2, 3 test blocks are provided on each bulkhead loading section of the asymmetric fuselage bulkhead.
It can be understood that the asymmetric fuselage bulkhead four-point bending test device is convenient to recycle by being connected in a detachable mode.
Advantageously, the test block 4 is bolted to the bulkhead loading section. The bolt connection is the simplest connection mode, and excessive interference on the shape and the structure of the device is not needed, so that the situations of centroid shift and the like of the to-be-tested asymmetric fuselage bulkhead caused by the increase of the connection mode can be prevented.
Referring to fig. 2, in the present embodiment, each loading head assembly includes a bracket 31, a first loading head 32, a second loading head 33, and a column 34, and the bracket 31 is connected to the loading platform 11; the first loading head 32 is arranged on the bracket 31, and the surface of the first loading head 32 far away from the bracket is a concave surface; one surface of the second loading head 33 is a concave surface, the other surface is a plane, the plane is in contact with the bulkhead loading section, the concave surface of the second loading head 33 is opposite to the concave surface of the first loading head, and an accommodating space is formed between the concave surface of the first loading head and the concave surface of the second loading head; the cylinder 34 is disposed in the accommodating space and can rotate in the accommodating space. It will be appreciated that in this manner, when a force is transmitted to the second loading head, the second loading head changes the direction of the force by moving due to its smooth contact with the cylinder, thereby achieving the purpose of the present application.
Advantageously, the area of the face of the carriage 31 carrying the first loading head is greater than the area of the face of the first loading head in contact with the carriage. With the adoption of the structure, the first loading head can be arranged on the bracket more stably.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. The asymmetric fuselage bulkhead four-point bending test method is characterized by comprising the following steps of:
step 1: adding a test block to the asymmetric fuselage bulkhead to be tested, so that a loading pressure center of the asymmetric fuselage bulkhead during loading test passes through a cross section bending center of the asymmetric fuselage bulkhead; the test block is arranged on one bulkhead loading section and the other bulkhead loading section of the asymmetric fuselage bulkhead (2) to be tested;
step 2: respectively adding a loading head assembly on two opposite loading platforms of a test loading device, wherein the loading head assemblies can adapt to bending deformation of a machine body bulkhead and always keep loading force vertical to a straight section of the bulkhead; the number of the loading head assemblies (3) is four, wherein every two loading head assemblies (3) are used for one bulkhead loading section, so that the four loading head assemblies are divided into a first loading group and a second loading group;
one loading head assembly (3) in the first loading group is arranged on one surface of one loading platform (11) of the test loading device (1); the other loading head component (3) is arranged on one surface of the other loading platform (11), and the two loading head components (3) are oppositely arranged, so that a loading space is formed and is used for clamping a bulkhead loading section;
one loading head assembly (3) in the second loading group is arranged on one surface of one loading platform (11) of the test loading device; the other loading head component (3) is arranged on one surface of the other loading platform (11), and the two loading head components (3) are oppositely arranged, so that a loading space is formed and is used for clamping the other bulkhead loading section;
and step 3: and arranging the asymmetric fuselage bulkhead to be tested between the two loading head assemblies, and performing a four-point bending test.
2. The asymmetric fuselage bulkhead four-point bend test method of claim 1, wherein the asymmetric fuselage bulkhead four-point bend test method further comprises:
pre-step 1: and calculating the bending center of the cross section of the asymmetric fuselage bulkhead to be detected.
3. An asymmetric fuselage bulkhead four-point bending test device for mounting an asymmetric fuselage bulkhead to be tested to a test loading device and performing the asymmetric fuselage bulkhead four-point bending test method according to claim 1 or 2, the test loading device (1) being configured to apply a load to the asymmetric fuselage bulkhead (2) to be tested, each asymmetric fuselage bulkhead (2) having two bulkhead loading sections; it is characterized in that the asymmetric fuselage bulkhead four-point bending test device comprises:
the test block assemblies are divided into two groups, one group of test block assemblies are arranged on one partition frame loading section of the asymmetric fuselage partition frame (2) to be tested, and the other group of test block assemblies are arranged on the other partition frame loading section;
the number of the loading head assemblies (3) is four, wherein every two loading head assemblies (3) are used for one bulkhead loading section, so that the four loading head assemblies are divided into a first loading group and a second loading group;
one loading head assembly (3) in the first loading group is arranged on one surface of one loading platform (11) of the test loading device (1); the other loading head component (3) is arranged on one surface of the other loading platform (11), and the two loading head components (3) are oppositely arranged, so that a loading space is formed and is used for clamping a bulkhead loading section;
one loading head assembly (3) in the second loading group is arranged on one surface of one loading platform (11) of the test loading device; the other loading head component (3) is arranged on one surface of the other loading platform (11), and the two loading head components (3) are oppositely arranged, so that a loading space is formed and is used for clamping the other bulkhead loading section; wherein,
the test block assembly is used for keeping the loading force vertical to the straight section of the bulkhead all the time along with the bending deformation of the bulkhead of the machine body, so that the constant bending moment applied in the four-point bending test is ensured to be unchanged;
the loading head assembly is used for moving along with the asymmetric fuselage bulkhead when the asymmetric fuselage bulkhead deforms under load, and all the loading head assemblies are matched, so that the direction of the force applied to the asymmetric fuselage bulkhead by the test loading device in the loading process is always perpendicular to the asymmetric fuselage bulkhead.
4. An asymmetric fuselage bulkhead four-point bending test apparatus according to claim 3, wherein the test block assembly comprises a plurality of test blocks (4), each test block (4) being detachably connected to the bulkhead loading section.
5. The asymmetric fuselage bulkhead four-point bending test apparatus of claim 4, wherein the test block (4) is bolted to the bulkhead loading section.
6. The asymmetric fuselage bulkhead four-point bending test apparatus of claim 5, wherein each said load head assembly comprises:
a bracket (31), the bracket (31) being connected to the loading platform (11);
a first loading head (32), wherein the first loading head (32) is arranged on the bracket (31), and the surface of the first loading head (32) far away from the bracket is a concave surface;
a second loading head (33), one face of the second loading head (33) being a concave face and the other face being a flat face, the flat face being in contact with the bulkhead loading section, the concave face of the second loading head (33) being opposite to the concave face of the first loading head, and a receiving space being formed between the concave face of the first loading head and the concave face of the second loading head;
a cylinder (34), the cylinder (34) being disposed within the receiving space and being rotatable within the receiving space.
7. The asymmetric fuselage bulkhead four-point bending test apparatus according to claim 6, wherein the area of the face of the bracket (31) bearing the first loading head is greater than the area of the face of the first loading head in contact with the bracket.
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| CN201610541264.7A CN106240842B (en) | 2016-07-11 | 2016-07-11 | A kind of asymmetric fuselage bulkhead four-point bending test method and device |
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| CN108334653B (en) * | 2017-10-20 | 2019-09-17 | 北京空天技术研究所 | A kind of Static Analysis Model of Micro-machined modification method, update the system and Static Strength Analysis method |
| CN109357851B (en) * | 2018-10-17 | 2020-08-11 | 中国飞机强度研究所 | Four-point bending test loading method for curved frame structure of machine body |
| CN116660055B (en) * | 2023-06-02 | 2023-11-03 | 南京航空航天大学 | Four-point bending loading test device suitable for main cargo compartment door lock hook structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| PT103034A (en) * | 2003-10-28 | 2005-04-29 | Univ Do Minho | UNIVERSAL MACHINE FOR MULTIAXIAL TESTS |
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| EP2407767A4 (en) * | 2009-03-10 | 2014-05-21 | Mitsubishi Materials Corp | Biaxial tensile testing machine |
| CN102288483A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket |
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