CN219434569U - Safety strength test device for breakage of aircraft windshield - Google Patents
Safety strength test device for breakage of aircraft windshield Download PDFInfo
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- CN219434569U CN219434569U CN202320195663.8U CN202320195663U CN219434569U CN 219434569 U CN219434569 U CN 219434569U CN 202320195663 U CN202320195663 U CN 202320195663U CN 219434569 U CN219434569 U CN 219434569U
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Abstract
The utility model discloses an aircraft windshield breakage safety strength test device, which comprises a lower cavity, wherein the side surface of the lower cavity is provided with a pressurizing through hole; the upper sealing frame is arranged at the upper side edge of the lower cavity through a sealing component; the fixing clamp is used for clamping and fixing the test piece; an upper cavity protecting cover for covering the test piece; a breaking operation hammer for breaking the intermediate layer of the test piece; the deformation displacement sensor is arranged in the center of the upper side of the test piece; and the temperature sensor is arranged on the lower side of the test piece. According to the utility model, the middle layer of the aircraft windshield glass test piece is broken through the breakage operation hammer, meanwhile, the pressurization in the cabin of the aircraft during normal flight is simulated, the deformation condition of the test piece in the test process is finally detected by the deformation displacement sensor, the test data output to the computer is recorded, the breakage safety strength test is completed, the operation is easy, the higher control precision can be achieved, the pressurization is stable, the structure is simple, and the universality is realized.
Description
Technical Field
The utility model belongs to the technical field of glass breakage tests, and particularly relates to an aircraft windshield breakage safety strength test device.
Background
The method has important significance for the safety strength of the breakage of the windshield glass of the aircraft, namely the capability of keeping the rigidity of the whole structure of the windshield under the condition of pressurizing in a cabin after the multilayer glass of the windshield glass is broken and cracked. This requires the aircraft windshield to have high strength and resistance to pressure differentials. Therefore, the breaking safety strength of the aircraft windshield is a basic requirement of the safety service of the aircraft windshield.
The windshield glass needs to be designed according to safe breakage, and when any layer of the glass is damaged, the windshield glass must withstand the combined action of the maximum differential pressure load of the cabin and the influence of critical pneumatic pressure and temperature; it can be assumed that after a single break, which is easily found in the aircraft assembly, the cabin pressure difference drops from a maximum value according to the corresponding use limit, so that the aircraft can continue to fly safely at a certain cabin pressure level.
At present, no effective method for evaluating the breakage safety strength test of the windshield glass of the airplane exists in China, and no related testing equipment exists. The reason is mainly that the glass matched with the airplane is automatically researched and developed in China and just started, the test and detection experience is less, and related test equipment is not provided.
Therefore, development of a method and a device for testing the breakage safety strength of the aircraft windshield is urgently needed, basis and guidance are provided for material process selection and structure optimization design of the aircraft windshield, service reliability and the like, and the method and the device have important significance for guaranteeing the reliability and safety design of domestic aircraft.
Disclosure of Invention
In view of the above, the technical problem to be solved by the utility model is to provide an aircraft windshield breakage safety strength test device, which is used for avoiding the trouble that the prior aircraft windshield interlayer is broken and lacks a corresponding breakage safety strength test detection device.
In order to solve the technical problems, the utility model discloses an aircraft windshield breakage safety strength test device, which comprises:
the side surface of the lower cavity is provided with a pressurizing through hole;
the upper sealing frame is arranged at the upper side edge of the lower cavity through a sealing component;
the fixing clamp is arranged on the inner ring of the upper sealing frame in a surrounding mode and used for clamping and fixing the aircraft windshield glass test piece, wherein the edge wrapping of the end portion of the aircraft windshield glass test piece exposes a process hole;
the upper cavity protecting cover is arranged on the upper sealing frame, covers the aircraft windshield glass test piece and is reserved with a through hole corresponding to the process hole;
the broken operating hammer is used for guiding the process hole through the through hole and breaking the middle layer of the aircraft windshield glass test piece;
the deformation displacement sensor is arranged in the center of the upper side of the aircraft windshield glass test piece;
and the temperature sensor is arranged on the lower side of the aircraft windshield glass test piece.
According to an embodiment of the present utility model, the lower cavity and the upper cavity cover each have a sensor threading hole.
According to one embodiment of the utility model, the sealing assembly is provided as 0-shaped sealing rings with 2 channels of intervals, and the upper sealing frame and the lower cavity are fastened between the 0-shaped sealing rings through bolts.
According to an embodiment of the present utility model, the fixing jig includes:
the radian cushion block supports the lower side of the aircraft windshield glass test piece;
the side compression block is Z-shaped, one end of the side compression block is pressed against the upper side of the aircraft windshield glass test piece, and the other end of the side compression block is fixed on the upper sealing frame through bolts.
According to one embodiment of the utility model, the side compression block and the radian cushion block are arranged on a flexible buffer rubber pad which is abutted against an aircraft windshield glass test piece.
According to an embodiment of the present utility model, the pressurizing through hole is connected to the air compressor through a pipeline, and is provided with a pressure sensor.
According to one embodiment of the utility model, the breaking operation hammer is pushed by a cylinder to break the middle layer of the aircraft windshield test piece, cracks are formed, and at least 1 crack penetrates through the whole glass.
According to an embodiment of the present utility model, the upper cavity cover is made of transparent plexiglas.
Compared with the prior art, the utility model can obtain the following technical effects:
the device for testing the breakage safety strength of the aircraft windshield glass is provided for the aircraft glass, can simulate the environment state of the aircraft glass in the flight process, and provides a test basis for the design and optimization of the aircraft glass. The middle layer of the aircraft windshield glass test piece is broken through the broken operating hammer, meanwhile, the pressurization in the cabin of the normal flight opportunity of the aircraft is simulated, the deformation condition of the test piece in the test process is finally detected by the deformation displacement sensor, the test data output to the computer is recorded, the broken safety strength test is completed, the operation is easy, the higher control precision can be achieved, the pressurization is stable, the structure is simple, and the universality is realized.
Of course, it is not necessary for any one product embodying the utility model to achieve all of the technical effects described above at the same time.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and do not constitute a limitation on the utility model. In the drawings:
FIG. 1 is a schematic view of an aircraft windshield breakage safety strength test apparatus according to an embodiment of the present utility model.
Reference numerals
The device comprises a lower cavity 10, a pressurizing through hole 11, an upper sealing frame 20, a sealing assembly 30, a fixing clamp 40, an arc cushion block 41, a side pressure block 42, an aircraft windshield test piece 50, an upper cavity protective cover 60, a breakage operating hammer 70, a deformation displacement sensor 80 and a temperature sensor 90.
Detailed Description
The following detailed description of embodiments of the present utility model will be given with reference to the accompanying drawings and examples, by which the implementation process of how the present utility model can be applied to solve the technical problems and achieve the technical effects can be fully understood and implemented.
Referring to fig. 1, fig. 1 is a schematic diagram of an apparatus for testing breakage safety strength of an aircraft windshield according to an embodiment of the utility model.
As shown, an aircraft windshield breakage safety strength test apparatus comprising: a lower cavity 10, wherein a pressurizing through hole 11 is formed on the side surface of the lower cavity 10; the upper sealing frame 20 is arranged on the upper side edge of the lower cavity 10 through a sealing assembly 30; the fixing clamp 40 is arranged on the inner ring of the upper sealing frame 20 in a surrounding mode and is used for clamping and fixing the aircraft windshield glass test piece 50, wherein the edge wrapping of the end portion of the aircraft windshield glass test piece 50 exposes a process hole; the upper cavity protective cover 60 is arranged on the upper sealing frame 20, covers the aircraft windshield glass test piece 50 and is reserved with a through hole corresponding to the process hole; a breakage operating hammer 70, wherein the breakage operating hammer 70 guides the process hole from the through hole to break the middle layer of the aircraft windshield test piece 50; a deformation displacement sensor 80, the deformation displacement sensor 80 being provided in the center of the upper side of the aircraft windshield test piece 50; temperature sensor 90, temperature sensor 90 is disposed on the underside of aircraft windshield test piece 50.
In one embodiment of the present utility model, the testing device housing is composed of a lower cavity 10, an upper cavity protecting cover 60, and a glass clamping fixture, wherein the glass clamping fixture comprises an upper sealing frame 20 and a fixing clamp 40, the upper sealing frame 20 is sealed by a sealing assembly 20 and fixed by bolts, and the fixing clamp 40 is located between the upper cavity and the lower cavity. The upper cavity protecting cover 60 is a protecting cover, so that the personnel safety in the test process is ensured.
Specifically, the aircraft windshield test piece 50 is fixed at the edge by the fixing jig 40, and the process hole aligned with the breakage operating hammer 70 is exposed so that the breakage operating hammer 70 is knocked and broken to form a glass crack for test. In addition, the pressurizing through hole 11 on the side surface of the lower cavity 10 is used for improving the air pressure in the lower cavity 10, and it is to be understood that the lower cavity 10 is in a sealed state due to the fact that the upper side of the aircraft windshield glass test piece 50 is covered, and the high air pressure is introduced at the moment, so that the maximum pressure difference in the cabin can be simulated to complete a high-precision test. The temperature sensor 90 records the temperature of the environment at this time. The deformation displacement sensor 80 is disposed on the upper side of the aircraft windshield glass test piece 50, i.e. in the upper cavity, and detects the deformation condition of the test piece during the test process, and records the test data. Therefore, after the single-sided pressure bearing of the aircraft windshield glass test piece 50, the quality performance of the aircraft windshield glass test piece can be tested, whether the aircraft windshield glass test piece meets the specification of the corresponding product technical condition and the static pressure damage resistance strength test can be tested, and the accurate test of simulating the strength performance of the aircraft windshield glass in the working environment of different models can be realized by replacing the fixing clamp 40.
The lower cavity 10 and the upper cavity protecting cover 60 of the utility model are provided with sensor threading holes, and the sensor threading holes are sealed by sealing elements after threading, so that the accurate test is ensured.
In addition, the sealing component 40 is set to be a 0-shaped sealing ring with 2 intervals, so that the lower cavity 10 and the upper sealing frame 20 are convenient to form sealing, the upper sealing frame 20 and the lower cavity 10 are fastened through bolts between the 0-shaped sealing rings to complete fixation, and therefore the pressurizing work in the lower cavity 10 is ensured to be carried out safely, and the test is ensured to be accurate.
In a preferred embodiment, the fixing jig 40 includes: the arc cushion block 41 and the side compression block 42, wherein the arc cushion block 41 supports the lower side of the aircraft windshield test piece 50, and the arc fits the aircraft windshield test piece 50; the side compression block 42 is Z-shaped, one end of the side compression block is pressed against the upper side of the aircraft windshield glass test piece 50, the side compression block can be designed into a slope or radian, the lamination is enhanced, the other end of the side compression block is fixed on the upper sealing frame 20 through bolts, and the compression work is realized through the fastening bolts.
The aircraft glass is more in variety and most in curved surface modeling, in order to enable the device system to have universality and reduce manufacturing cost, the fixing clamp 40 is customized according to the glass with a specific model, and the fixing clamp 40 is designed to be a detachable replacement part arranged between an upper cavity and a lower cavity. The fixing jig 40 of the intermediate layer may be replaced only when other types of glass are to be tested.
Further, the side compression block 42 and the radian cushion block 41 are arranged on the flexible buffer rubber pad which abuts against the aircraft windshield glass test piece 50, so that flexible abutting and press-covering work is enhanced, and stability is enhanced.
The pressurizing through hole 11 is connected with the air compressor through a pipeline, and is provided with the pressure sensor, the pressure sensor converts a pressure signal into an A/D (analog-to-digital) signal, and the controller controls the work of the air compressor according to a given pressure threshold value, so that the lower surface of glass reaches the given air pressure, and the pressurizing through hole is simple in structure and convenient to use.
In addition, the breaking operation hammer 70 is pushed by the cylinder to break the middle layer of the aircraft windshield test piece 50 to form cracks, at least 1 crack penetrates through the whole glass, and the pressure difference between the inner surface and the outer surface of the windshield test piece 50 is required to reach the requirement and is kept for a certain time, so that test data are recorded.
Preferably, the upper cavity protecting cover 60 is made of transparent organic glass, so that the observation is convenient, the quality is light and thin, and the periphery can be fixed through fasteners, so that the safety is ensured.
In summary, the utility model provides a device for testing the breakage safety strength of the aircraft windshield glass, which can simulate the environment state of the aircraft glass in the flight process and provides a test basis for the design and optimization of the aircraft glass. The middle layer of the aircraft windshield glass test piece is broken through the broken operating hammer, meanwhile, the pressurization in the cabin of the normal flight opportunity of the aircraft is simulated, the deformation condition of the test piece in the test process is finally detected by the deformation displacement sensor, the test data output to the computer is recorded, the broken safety strength test is completed, the operation is easy, the higher control precision can be achieved, the pressurization is stable, the structure is simple, and the universality is realized.
While the foregoing description illustrates and describes the preferred embodiments of the present utility model, it is to be understood that the utility model is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the inventive concept as described herein, either as a result of the foregoing teachings or as a result of the knowledge or technology in the relevant art. And that modifications and variations which do not depart from the spirit and scope of the utility model are intended to be within the scope of the appended claims.
Claims (8)
1. An aircraft windshield breakage safety strength test device, characterized by comprising:
the side surface of the lower cavity is provided with a pressurizing through hole;
the upper sealing frame is arranged at the upper side edge of the lower cavity through a sealing component;
the fixing clamp is arranged on the inner ring of the upper sealing frame in a surrounding mode and used for clamping and fixing an aircraft windshield glass test piece, and the edge wrapping of the end portion of the aircraft windshield glass test piece exposes out of a process hole;
the upper cavity protection cover is arranged on the upper sealing frame, covers the aircraft windshield glass test piece and reserves a through hole corresponding to the process hole;
a breakage operating hammer guided to the process hole by the through hole for breaking the intermediate layer of the aircraft windshield test piece;
the deformation displacement sensor is arranged at the center of the upper side of the aircraft windshield glass test piece;
and the temperature sensor is arranged on the lower side of the aircraft windshield glass test piece.
2. The aircraft windshield breakage safety strength test device according to claim 1, wherein both of the lower cavity and the upper cavity boot have sensor threading holes.
3. The aircraft windshield breakage safety strength test device according to claim 1, wherein the seal assembly is provided as 2 spaced 0-seal rings, and the upper seal rim and the lower cavity are bolted between the 0-seal rings.
4. The aircraft windshield breakage safety strength test apparatus according to claim 1, wherein said fixing jig includes:
the radian cushion block supports the lower side of the aircraft windshield glass test piece;
the side compression block is Z-shaped, one end of the side compression block is pressed against the upper side of the aircraft windshield glass test piece, and the other end of the side compression block is fixed on the upper sealing frame through bolts.
5. The aircraft windshield breakage safety strength test device according to claim 4, wherein the side hold-down blocks and the arcuate pad surfaces are disposed on a flexible cushion pad that abuts the aircraft windshield test piece.
6. The apparatus according to claim 1, wherein the pressurizing through hole is connected to an air compressor through a pipe, and a pressure sensor is installed.
7. The apparatus of claim 1, wherein the breaking operating hammer is pushed by a cylinder to break the interlayer of the aircraft windshield test piece to form a crack, and at least 1 crack penetrates the entire glass.
8. The aircraft windshield breakage safety strength test device according to claim 1, wherein said upper cavity boot is provided as transparent plexiglass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320195663.8U CN219434569U (en) | 2023-02-06 | 2023-02-06 | Safety strength test device for breakage of aircraft windshield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320195663.8U CN219434569U (en) | 2023-02-06 | 2023-02-06 | Safety strength test device for breakage of aircraft windshield |
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| Publication Number | Publication Date |
|---|---|
| CN219434569U true CN219434569U (en) | 2023-07-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320195663.8U Active CN219434569U (en) | 2023-02-06 | 2023-02-06 | Safety strength test device for breakage of aircraft windshield |
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| CN (1) | CN219434569U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116858487A (en) * | 2023-09-05 | 2023-10-10 | 荣成康派斯新能源车辆股份有限公司 | Device and method for testing movement speed of windshield of motor home by air flow impact |
-
2023
- 2023-02-06 CN CN202320195663.8U patent/CN219434569U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116858487A (en) * | 2023-09-05 | 2023-10-10 | 荣成康派斯新能源车辆股份有限公司 | Device and method for testing movement speed of windshield of motor home by air flow impact |
| CN116858487B (en) * | 2023-09-05 | 2023-11-17 | 荣成康派斯新能源车辆股份有限公司 | Device and method for testing movement speed of windshield of motor home by air flow impact |
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