CN213689199U - Composite material part static force test tool - Google Patents
Composite material part static force test tool Download PDFInfo
- Publication number
- CN213689199U CN213689199U CN202022695269.XU CN202022695269U CN213689199U CN 213689199 U CN213689199 U CN 213689199U CN 202022695269 U CN202022695269 U CN 202022695269U CN 213689199 U CN213689199 U CN 213689199U
- Authority
- CN
- China
- Prior art keywords
- fixing
- composite material
- clamp plate
- universal joint
- test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a static force test tool for composite material parts, which comprises a fixing mechanism used for clamping and fixing the composite material parts; the universal joint is also included; the front end of the universal joint is connected with the fixing mechanism, and the rear end of the universal joint is a force application connecting end and is used for being connected with a force application mechanism. The fixing mechanism comprises an upper fixing clamp plate and a lower fixing clamp plate, and the upper fixing clamp plate and the lower fixing clamp plate are simultaneously provided with corresponding test material fixing holes for penetrating bolts. The utility model discloses an adjustment static test direction that this design can be nimble. The punching mode of the test clamping plate can ensure that the stress points of the composite material part are uniform. The data tested by the static test tool for the composite material part manufactured by the design is more real and effective.
Description
Technical Field
The utility model belongs to the technical field of the aircraft technique and specifically relates to a combined material part static test frock.
Background
In the field of aircrafts, composite static force tests are currently carried out by clamping composite blades through a clamp, and force is transmitted to the composite blades through the clamp after the test is started. The traditional splint punching mode is the mode of same pitch of holes and punches, can not effectual fixed combined material blade, and traditional application of force direction can only one direction can not multi-direction test static.
The utility model discloses it is not enough to have improved the aforesaid, can measure true effectual data.
Disclosure of Invention
The utility model aims at providing a combined material part static test frock to the defect that prior art exists, through the static test direction of regulation that this design can be nimble. The punching mode of the test clamping plate can ensure that the stress points of the composite material part are uniform. The data tested by the static test tool for the composite material part manufactured by the design is more real and effective.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a static test tool for composite material parts comprises a fixing mechanism, a static test mechanism and a static test mechanism, wherein the fixing mechanism is used for clamping and fixing the composite material parts;
the universal joint is also included;
the front end of the universal joint is connected with the fixing mechanism, and the rear end of the universal joint is a force application connecting end and is used for being connected with a force application mechanism.
Furthermore, the fixing mechanism comprises an upper fixing clamp plate and a lower fixing clamp plate, and the upper fixing clamp plate and the lower fixing clamp plate are simultaneously provided with corresponding test material fixing holes for penetrating bolts.
Furthermore, the front end of the universal joint is provided with a connecting block, the connecting block is provided with a connecting block fixing hole for connecting a fixing mechanism, the upper fixing clamp plate and the lower fixing clamp plate are provided with an edge fixing hole at the same time, and the connecting block fixing hole and the edge fixing hole are connected through penetrating fixing screws.
Furthermore, the force application connecting end at the rear end of the universal joint is a connecting column.
Further, the composite part is an aircraft propeller blade made of composite material.
Compared with the prior art, the utility model following beneficial effect has:
and (3) penetrating the propeller blade with the drilled hole position into the test material fixing hole by using a screw through the fixing clamping plate, fastening the screw, then penetrating the screw into the universal joint fixing hole, linking the universal joint, and fastening the screw. The other side fastens the propeller blades together by a propeller hub by screws. The assembled test material is mounted on a test frame, and then a force is applied to the stressed fixed point for testing.
The static test direction can be flexibly adjusted through the design. The punching mode of the test clamping plate can ensure that the stress points of the composite material part are uniform. The data tested by the static test tool for the composite material part manufactured by the design is more real and effective.
Drawings
Fig. 1 is a schematic structural view of the static force testing tool for composite material parts of the present invention;
FIG. 2 is a schematic view of a gimbal;
FIG. 3 is a schematic view of the structure of the fixing splint and the punching method.
In the figure: 1. propeller hub, 2 propeller blades, 3 fixed splint, 4 universal joints, 5 application of force spliced poles, 6 test material clamping fixed orifices, 7 connection fixed orifices.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides a technical solution:
a static test tool for composite material parts comprises a fixing mechanism, a static test mechanism and a static test mechanism, wherein the fixing mechanism is used for clamping and fixing the composite material parts;
also comprises a universal joint 4;
the front end of the universal joint is connected with the fixing mechanism, and the rear end of the universal joint is a force application connecting end and is used for being connected with a force application mechanism.
Furthermore, the fixing mechanism is a fixing splint, the fixing splint 3 comprises an upper fixing splint and a lower fixing splint, and the upper fixing splint and the lower fixing splint are simultaneously provided with corresponding test material clamping fixing holes 6 for penetrating bolts.
Furthermore, the front end of the universal joint is provided with a connecting block, the connecting block is provided with a connecting block fixing hole for connecting a fixing mechanism, the upper fixing clamp plate and the lower fixing clamp plate are provided with an edge fixing hole at the same time, and the connecting block fixing hole and the edge fixing hole are connected through penetrating fixing screws. The connecting block fixing hole and the edge fixing hole are collectively called as a connecting fixing hole 7
Furthermore, the force application connecting end at the rear end of the universal joint is a connecting column 5.
Further, the composite material part is an aircraft propeller blade 2 made of a composite material.
Referring to fig. 1 to 3, the test propeller blades are drilled in a staggered drilling manner of the test material fixing holes of the fixing splint. This way the tested propeller blades can be stressed evenly. And (3) penetrating the propeller blade with the drilled hole position into the test material fixing hole by using a screw through the fixing clamping plate, fastening the screw, then penetrating the screw into the universal joint fixing hole, linking the universal joint, and fastening the screw. The other side fastens the propeller blades together by a propeller hub by screws. The assembled test material is mounted on a test frame, and then a force is applied to the stressed fixed point for testing. Composite material parts in the name of the invention refer in the invention to propeller blades made of composite material.
The design can be real and effective, and the multidirectional static test of the composite material can be carried out according to the requirement.
All parts and parts which are not discussed in the present application and the connection mode of all parts and parts in the present application belong to the known technology in the technical field, and are not described again.
In the present application, the term "plurality" means two or more unless expressly defined otherwise. The terms "mounted," "connected," "fixed," and the like are to be construed broadly, and for example, "connected" may be a fixed connection, a removable connection, or an integral connection; "coupled" may be direct or indirect through an intermediary. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", "front", "back", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or unit indicated must have a specific direction, be constructed and operated in a specific orientation, and therefore, should not be construed as limiting the present invention.
In the description of the present specification, the description of the terms "one embodiment," "some embodiments," "specific embodiments," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A static test tool for composite material parts comprises a fixing mechanism, a static test mechanism and a static test mechanism, wherein the fixing mechanism is used for clamping and fixing the composite material parts;
the device is characterized by also comprising a universal joint;
the front end of the universal joint is connected with the fixing mechanism, and the rear end of the universal joint is a force application connecting end and is used for being connected with a force application mechanism.
2. The composite material part static force test tool according to claim 1, wherein the fixing mechanism comprises an upper fixing clamp plate and a lower fixing clamp plate, and the upper fixing clamp plate and the lower fixing clamp plate are simultaneously provided with corresponding test material fixing holes for penetrating bolts.
3. The composite material part static force test tool according to claim 2, wherein a connecting block is arranged at the front end of the universal joint, a connecting block fixing hole for connecting a fixing mechanism is formed in the connecting block, edge fixing holes are formed in the upper fixing clamp plate and the lower fixing clamp plate at the same time, and the connecting block fixing hole and the edge fixing hole are connected through penetrating fixing screws.
4. A composite material part static test tool according to claim 3, wherein the force application connection end at the rear end of the universal joint is a connection column.
5. A composite component static test fixture according to claim 2, 3 or 4, wherein the composite component is an aircraft propeller blade made of composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022695269.XU CN213689199U (en) | 2020-11-19 | 2020-11-19 | Composite material part static force test tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022695269.XU CN213689199U (en) | 2020-11-19 | 2020-11-19 | Composite material part static force test tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213689199U true CN213689199U (en) | 2021-07-13 |
Family
ID=76733976
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022695269.XU Active CN213689199U (en) | 2020-11-19 | 2020-11-19 | Composite material part static force test tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213689199U (en) |
-
2020
- 2020-11-19 CN CN202022695269.XU patent/CN213689199U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Heimbs et al. | Static and dynamic failure behaviour of bolted joints in carbon fibre composites | |
| US7975965B2 (en) | Wing tip joint in airfoils | |
| EP2362094B1 (en) | Method and device for attaching a reference marking to a rotor blade of a wind turbine | |
| US5753823A (en) | Rubber substrate shear lap-joint testing fixture | |
| CN213689199U (en) | Composite material part static force test tool | |
| CN112213189A (en) | Composite tension-shear test device | |
| CN111693371A (en) | Test fixture for testing tensile property of ceramic matrix composite | |
| US11260954B2 (en) | Apparatus for attaching aircraft wing structural components | |
| CN215155584U (en) | Quick assembly disassembly structure of unmanned aerial vehicle section | |
| CN207263432U (en) | The high-temperature high-frequency fatigue life test fixture of integral type blade of aviation engine | |
| CN105737790A (en) | Device for measuring test hole compression deformation | |
| CN114778049B (en) | Vibration testing device and vibration simulation method for airplane airfoil surface structure | |
| CN207318235U (en) | One kind is glued aluminium honeycomb sandwich construction front built-in fitting pull-off test fixture | |
| CN210451098U (en) | Device for drilling angle type splice plate | |
| CN111999172B (en) | Test fixture, device and method for rivet composite loading test | |
| CN211179280U (en) | Novel wedge cantilever beam loading device | |
| CN114216799A (en) | Composite material interlayer fracture toughness test clamp under low-speed impact and use method thereof | |
| CN208334057U (en) | A kind of longitudinal stretching shearing test clamp | |
| CN217638462U (en) | Overlap joint shear test frock | |
| CN216594492U (en) | Tensile destructiveness experiment clamp for automobile chassis spherical hinge | |
| CN220853942U (en) | Assembled cutting force measurement fixture | |
| CN219416642U (en) | Product clamp applied to vertical acceleration vibration test | |
| CN114735198B (en) | Propeller structure and rapid development and shaping method | |
| CN218907636U (en) | Helicopter booster fixture assembly | |
| CN208818101U (en) | Car steering tube column installation point verifying attachment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |