CN212044471U - High-efficient frock that decomposes of aircraft DC generator end shield - Google Patents
High-efficient frock that decomposes of aircraft DC generator end shield Download PDFInfo
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- CN212044471U CN212044471U CN201922457574.2U CN201922457574U CN212044471U CN 212044471 U CN212044471 U CN 212044471U CN 201922457574 U CN201922457574 U CN 201922457574U CN 212044471 U CN212044471 U CN 212044471U
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- current generator
- rod
- direct current
- ejector rod
- supporting block
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Abstract
The utility model discloses a high-efficient frock that decomposes of aircraft DC generator end shield, include: the device comprises an acting rod, a supporting block, a top rod and more than two fixed grippers; the acting rod is fixed at one end of the ejector rod, and the acting rod and the ejector rod form a T-shaped structure; the other end of the ejector rod penetrates through the supporting block and is in threaded fit with the supporting block; pin hole ends of more than two fixed grippers are respectively connected with pin holes at two ends of the supporting block through pin shafts, and the fixed grippers are locked by a locking mechanism around the rotation of the pin shafts; the connecting hook ends of the more than two fixed grippers respectively abut against the lower surface of the direct current generator end cover, and the lower surface is the end surface of the end face of the direct current generator end cover opposite to the direct current generator shell; the ejector rod penetrates through the tail end of the supporting block and is opposite to the output shaft of the direct-current generator; the utility model discloses can realize high-efficient, the safe decomposition of aircraft DC generator end shield and DC generator casing junction.
Description
Technical Field
The utility model belongs to the technical field of the aviation is repaired and is put, concretely relates to high-efficient frock that decomposes of aircraft DC generator end shield.
Background
The aircraft dc generator requires disassembly of its end shield and dc generator housing for repair. The existing decomposition tool is a hammer and a cutter release tool, the hammer is used for knocking different parts of an end cover, so that a gap is formed between the end cover and a direct current generator shell, the cutter release tool is inserted into the gap, and the end cover is prized forcibly to be separated from the direct current generator shell, so that the purpose of decomposition is achieved. The disadvantages of this decomposition process are: firstly, the outer surface of the end cover is damaged or deformed due to knocking of the hammer, so that the external dimension of the end cover is changed, and the phenomenon of incomplete assembly can occur during repair and assembly; secondly, when the end cover and the direct current generator shell are pried by the unclamping tool, the end cover and the direct current generator shell are mechanically damaged, and when the end cover or the direct current generator shell is seriously damaged, the end cover or the direct current generator shell is scrapped, so that the repair cost is increased; thirdly, the end shield and the direct current generator shell are inconvenient to separate through manual operation, the workload is large, and the working efficiency is low. At present, no relevant disassembling tool is available, and the end shield can be quickly and effectively separated from the direct-current generator shell.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides an aircraft direct current generator end shield high efficiency decomposes frock can realize high efficiency, the safe decomposition of aircraft direct current generator end shield and direct current generator casing junction.
The utility model discloses a realize through following technical scheme:
the utility model provides an aircraft DC generator end shield high efficiency decomposes frock, includes: the device comprises an acting rod, a supporting block, a top rod and more than two fixed grippers;
the peripheral device includes: the device comprises a direct current generator shell, a direct current generator output shaft and a direct current generator end cover, wherein the direct current generator end cover is an object to be decomposed;
the ejector rod is provided with an external thread;
the middle part of the supporting block is provided with an internal thread, and the two ends of the supporting block are provided with pin holes;
a pin hole is processed at one end of the fixed gripper, and a connecting hook is arranged at the other end of the fixed gripper;
the overall connection relationship is as follows: the acting rod is fixed at one end of the ejector rod, and the acting rod and the ejector rod form a T-shaped structure;
the other end of the ejector rod penetrates through the supporting block and is in threaded fit with the supporting block;
pin hole ends of more than two fixed grippers are respectively connected with pin holes at two ends of the supporting block through pin shafts, and the fixed grippers are locked by a locking mechanism around the rotation of the pin shafts;
the connecting hook ends of the more than two fixed grippers respectively abut against the lower surface of the direct current generator end cover, and the lower surface is the end surface of the end face of the direct current generator end cover opposite to the direct current generator shell; the ejector pin passes through the tail end of the supporting block and is opposite to the output shaft of the direct-current generator.
Furthermore, the middle part of the acting rod is provided with an external thread;
one end of the ejector rod is provided with a threaded hole along the radial direction of the ejector rod;
the acting rod penetrates through a threaded hole of the ejector rod, and the acting rod and the ejector rod are in threaded fit.
Furthermore, the tail end of the ejector rod opposite to the output shaft of the direct current generator is processed into a tip.
Furthermore, the fixed tongs are V-shaped rods, and the angle of the tip end of each V-shaped rod is an obtuse angle and is in circular arc transition.
Further, the locking mechanism is a positioning pin or a locking nut.
Has the advantages that: the utility model realizes the separation of the end cover of the DC generator and the shell of the DC generator only by rotating the action rod and controlling the advance and retreat of the ejector rod, simplifies the manual operation, reduces the damage influence of human factors in the decomposition process of the end cover of the DC generator, and improves the production quality; and simultaneously, the utility model discloses still significantly reduced work load, improved work efficiency, the decomposition of specially adapted DC generator end shield.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a front view of the overall structure and the object to be decomposed;
the device comprises a direct current generator, a motor shell 1, a fixed gripper 2, a direct current generator end cover 3, a direct current generator shaft 4, a push rod 5, a support block 6 and a force applying rod 7.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings by way of examples.
The embodiment provides an aircraft direct current generator end shield high efficiency decomposes frock, refers to fig. 1-2, includes: the device comprises an acting rod 7, a supporting block 6, a top rod 5 and two fixed grippers 2;
the peripheral device includes: the device comprises a direct current generator shell 1, a direct current generator output shaft 4 and a direct current generator end cover 3, wherein the direct current generator end cover 3 is an object to be decomposed;
the middle part of the acting rod 7 is provided with an external thread;
the ejector rod 5 is provided with an external thread, one end of the ejector rod is provided with a threaded hole along the radial direction of the ejector rod, and the other end of the ejector rod is provided with a tip;
the middle part of the supporting block 6 is provided with an internal thread, and the two ends of the supporting block are provided with pin holes;
the fixed gripper 2 is a V-shaped rod, a pin hole is machined in one end of the fixed gripper, a connecting hook is arranged at the other end of the fixed gripper, and the angle of the tip end of the V-shaped rod is an obtuse angle and is in circular arc transition;
the overall connection relationship is as follows: the acting force rod 7 penetrates through a threaded hole of the ejector rod 5, an external thread in the middle of the acting force rod 7 is in threaded fit with the threaded hole of the ejector rod 5, and the acting force rod 7 and the ejector rod 5 form a T-shaped structure;
the tip of the ejector rod 5 penetrates through the supporting block 6 and is in threaded fit with the supporting block 6;
pin hole ends of the two fixed grippers 2 are respectively connected with pin holes at two ends of the supporting block 6 through pin shafts, and are locked through a locking mechanism, so that the fixed grippers 2 are prevented from rotating around the pin shafts; the locking mechanism is a positioning pin or a locking nut;
the connecting hook ends of the two fixed grippers 2 respectively abut against the lower surface of the direct current generator end cover 3, and the lower surface is the end surface of the end of the direct current generator end cover 3 opposite to the direct current generator shell 1; the tip of the mandril 5 is opposite to the output shaft 4 of the DC generator.
When the disassembly operation is carried out, one hand of an operator fixes the supporting block 6, the other hand pulls the acting rod 7 to rotate around the axis of the ejector rod 5, so that the ejector rod 5 is driven to rotate around the axis of the ejector rod 5, and the ejector rod 5 and the supporting block 6 are subjected to relative displacement along the axial direction of the ejector rod 5 due to the threaded fit of the ejector rod 5 and the supporting block 6, so that the linear motion of the ejector rod 5 along the axial direction is realized; when the tip of the ejector rod 5 is abutted against the output shaft 4 of the direct current generator, the action force rod 7 is continuously pulled, so that the ejector rod 5 continuously extends, and further the direct current generator shell 1 and the direct current generator output shaft 4 which are integrally and fixedly connected are pushed to move towards the direction far away from the end cover 3 of the direct current generator until the shell of the direct current generator shell 1 is separated from the end cover 3 of the direct current generator, and the decomposition of the end cover 3 of the direct current generator is realized.
In summary, the above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. 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. The utility model provides an aircraft DC generator end shield high efficiency decomposes frock which characterized in that includes: the device comprises an acting rod (7), a supporting block (6), a top rod (5) and more than two fixed grippers (2);
the peripheral device includes: the device comprises a direct current generator shell (1), a direct current generator output shaft (4) and a direct current generator end cover (3), wherein the direct current generator end cover (3) is an object to be decomposed;
an external thread is processed on the ejector rod (5);
the middle part of the supporting block (6) is provided with an internal thread, and the two ends of the supporting block are provided with pin holes;
a pin hole is machined in one end of the fixed gripper (2), and a connecting hook is arranged at the other end of the fixed gripper;
the overall connection relationship is as follows: the acting force rod (7) is fixed at one end of the ejector rod (5), and the acting force rod (7) and the ejector rod (5) form a T-shaped structure;
the other end of the ejector rod (5) penetrates through the supporting block (6) and is in threaded fit with the supporting block (6);
pin hole ends of more than two fixed grippers (2) are respectively connected with pin holes at two ends of the supporting block (6) through pin shafts, and the fixed grippers (2) are locked by a locking mechanism around the rotation of the pin shafts;
the connecting hook ends of more than two fixed grippers (2) respectively abut against the lower surface of the direct current generator end cover (3), and the lower surface is the end surface of the end of the direct current generator end cover (3) opposite to the direct current generator shell (1); the ejector rod (5) penetrates through the tail end of the supporting block (6) and is opposite to the output shaft (4) of the direct-current generator.
2. The efficient disassembly tool for the end shield of the airplane direct-current generator as claimed in claim 1, wherein the middle part of the acting rod (7) is provided with an external thread;
one end of the ejector rod (5) is provided with a threaded hole along the radial direction of the ejector rod;
the acting force rod (7) penetrates through a threaded hole of the ejector rod (5), and the acting force rod and the ejector rod are in threaded fit.
3. The efficient disassembling tool for the end shield of the airplane direct-current generator according to claim 1, wherein the tail end of the ejector rod (5) opposite to the output shaft (4) of the direct-current generator is processed into a tip.
4. The efficient disassembling tool for the end shield of the airplane direct current generator as claimed in claim 1, wherein the fixing hand grip (2) is a V-shaped rod, and the angle of the tip end of the V-shaped rod is an obtuse angle and is in a circular arc transition.
5. The efficient disassembling tool for the end shield of the airplane direct-current generator according to claim 1, wherein the locking mechanism is a positioning pin or a locking nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922457574.2U CN212044471U (en) | 2019-12-31 | 2019-12-31 | High-efficient frock that decomposes of aircraft DC generator end shield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922457574.2U CN212044471U (en) | 2019-12-31 | 2019-12-31 | High-efficient frock that decomposes of aircraft DC generator end shield |
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| Publication Number | Publication Date |
|---|---|
| CN212044471U true CN212044471U (en) | 2020-12-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922457574.2U Active CN212044471U (en) | 2019-12-31 | 2019-12-31 | High-efficient frock that decomposes of aircraft DC generator end shield |
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| CN (1) | CN212044471U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111015588A (en) * | 2019-12-31 | 2020-04-17 | 大连长丰实业总公司 | High-efficient frock that decomposes of aircraft DC generator end shield |
| CN113079722A (en) * | 2021-04-02 | 2021-07-09 | 常州大学 | Soil loosening manipulator for cultivation robot |
-
2019
- 2019-12-31 CN CN201922457574.2U patent/CN212044471U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111015588A (en) * | 2019-12-31 | 2020-04-17 | 大连长丰实业总公司 | High-efficient frock that decomposes of aircraft DC generator end shield |
| CN113079722A (en) * | 2021-04-02 | 2021-07-09 | 常州大学 | Soil loosening manipulator for cultivation robot |
| CN113079722B (en) * | 2021-04-02 | 2022-02-11 | 常州大学 | Soil loosening manipulator for cultivation robot |
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