CN214771758U - Electric brush mounting device of aircraft attack angle indicator - Google Patents
Electric brush mounting device of aircraft attack angle indicator Download PDFInfo
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- CN214771758U CN214771758U CN202023324352.2U CN202023324352U CN214771758U CN 214771758 U CN214771758 U CN 214771758U CN 202023324352 U CN202023324352 U CN 202023324352U CN 214771758 U CN214771758 U CN 214771758U
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- shaft bracket
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- clamping plate
- electric brush
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Abstract
The utility model discloses an angle indicator brush installation device is attacked to aircraft belongs to aviation repair technical field. The mounting device comprises a base and a shaft bracket, the shaft bracket is mounted at the edge of the base, and a first groove and a second groove are formed in the upper end face of the base; a semicircular through groove is formed in the upper end face of the shaft bracket. An upper clamping plate, a lower clamping plate, a potentiometer and a brush assembly of the aircraft angle of attack indicator are placed on the brush mounting device, wherein the lower clamping plate is attached to a second groove of the base, the upper clamping plate and the potentiometer are attached to a first groove of the base, and the brush assembly is placed on a shaft bracket and attached to a semicircular through groove 5 of the shaft bracket; and (4) the punch and the positioning pin are held by hands, and the punch and the positioning pin are hammered into the hole of the electric brush assembly and the hole of the shaft, so that the electric brush assembly is installed. The utility model discloses have higher practicality for current assembly method, simultaneously great improvement attack angle indicator brush installation effectiveness and quality, improve the security.
Description
Technical Field
The utility model belongs to the technical field of the aviation repair, concretely relates to brush installation device of angle indicator is attacked to aircraft.
Background
In the repairing process of the aircraft attack angle indicator, if the indicator has the conditions of large hysteresis error, large shaking amount of a pointer, loose shaft and the like, the electric brush assembly needs to be replaced, the appearance of some aircraft attack angle indicators is special and is limited by the appearance of some aircraft attack angle indicators, two persons need to be matched when the electric brushes are installed, one person fixes the positions of the electric brush assembly, the shaft and the positioning pin by hand, and the other person uses a punch to pound the positioning pin, and the method has the following defects: time and labor are wasted, and the working efficiency is low; the electric brush and the potentiometer are damaged due to unstable fixation of hands, so that economic loss is caused; the positioning pin is easy to injure people in the process of smashing the positioning pin.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides an angle indicator's brush installation device is attacked to aircraft can realize attacking the high efficiency of angle indicator's brush subassembly and safe installation.
The technical scheme of the utility model: an electric brush mounting device of an aircraft attack angle indicator comprises a base and a shaft bracket, wherein the shaft bracket is mounted at the edge of the base, and a first groove and a second groove are formed in the upper end surface of the base; wherein the width of the first groove is 8mm, and the width of the second groove is 2 mm; a semicircular through groove is formed in the upper end face of the shaft bracket.
Furthermore, the base is an anti-corrosion flat plate with a certain weight, and the whole device is supported and fixed.
Further, the distance between the first groove and the mounting position of the shaft bracket is 5 mm; the second groove is 20mm away from the mounting position of the shaft bracket.
Furthermore, the diameters of the first groove and the second groove are both 40 mm.
Furthermore, the semicircular through groove of the shaft bracket, the circle centers of the first groove and the second groove are positioned on the same horizontal straight line.
Furthermore, after the lower clamping plate of the aircraft attack angle indicator is arranged in the second groove, the upper clamping plate and the potentiometer are arranged in the first groove, and the electric brush assembly is just positioned in the semicircular through groove.
Has the advantages that:
the utility model discloses attack angle indicator axle, punch holder, lower plate, potentiometer, locating pin and brush subassembly with the aircraft and arrange its operation in, have higher practicality for current assembly method, simultaneously great improvement attack angle indicator brush installation effectiveness and quality, improve the security.
Drawings
Fig. 1 is a left side view of the overall structure of the present invention;
FIG. 2 is a front view of the overall structure of the present invention;
fig. 3 is a structural diagram of each component of the device of the present invention.
Wherein, 1-a base; 2-a shaft bracket.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings by way of examples.
As shown in fig. 1, 2 and 3, the electric brush mounting device of the aircraft attack angle indicator comprises a base 1 and a shaft bracket 2, wherein the shaft bracket 2 is fixedly arranged on the edge of the base 1; the implementation objects are an airplane attack angle indicator shaft, an upper clamping plate, a lower clamping plate, a potentiometer, a positioning pin and an electric brush assembly.
Wherein the base 1 is a stable anti-corrosion flat plate and is used for supporting and fixing the whole device; the edge of the upper end surface of the base is provided with a shaft bracket 2, the upper end surface of the base 1 is provided with two grooves, wherein a first groove with the width of 8mm and the diameter of 40mm is arranged at a position 5mm away from the mounting position of the shaft bracket 2; and a second groove with the width of 2mm and the diameter of 40mm is arranged at a position which is 20mm away from the installation position of the shaft bracket 2.
A semicircular through groove with the radius of 4mm is formed in the top end of the shaft bracket 2, and the top end of the shaft bracket and the circle centers of the first groove and the second groove of the base 1, which have the diameter of 40mm, are positioned on the same horizontal straight line.
When the device is used, an upper clamping plate, a lower clamping plate, a potentiometer and an electric brush assembly of the aircraft angle attack indicator are horizontally placed on an electric brush mounting device of the angle attack indicator by taking a shaft as a center, wherein the lower clamping plate is attached to a second groove of the base 1, the upper clamping plate and the potentiometer are attached to a first groove of the base 1, and the electric brush assembly is placed on the shaft bracket 2 and attached to a semicircular through groove of the shaft bracket 2; at the moment, the hole of the electric brush assembly is aligned upwards with the hole of the shaft, the punch and the positioning pin are held by hands, and the electric brush assembly is hammered into the hole of the electric brush assembly and the hole of the shaft, so that the electric brush assembly is installed.
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 (6)
1. An electric brush installation device of an aircraft attack angle indicator is characterized in that: the electric brush mounting device comprises a base and a shaft bracket, wherein the shaft bracket is mounted at the edge of the base, and a first groove and a second groove are formed in the upper end surface of the base; wherein the width of the first groove is 8mm, and the width of the second groove is 2 mm; a semicircular through groove is formed in the upper end face of the shaft bracket.
2. The brush mounting apparatus of claim 1, wherein: the base is made of a material with a certain weight and an anti-corrosion material.
3. The brush mounting apparatus of claim 1, wherein: the distance between the first groove and the mounting position of the shaft bracket is 5 mm; the second groove is 20mm away from the mounting position of the shaft bracket.
4. The brush mounting apparatus of claim 3, wherein: the diameters of the first groove and the second groove are both 40 mm.
5. The brush mounting apparatus of claim 1, wherein: the semi-circular through groove of the shaft bracket is positioned on the same horizontal straight line with the circle centers of the first groove and the second groove.
6. The brush mounting apparatus of claim 1, wherein: after the lower clamping plate of the aircraft attack angle indicator is arranged in the second groove, the upper clamping plate and the potentiometer are arranged in the first groove, the electric brush assembly is just positioned in the semicircular through groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023324352.2U CN214771758U (en) | 2020-12-31 | 2020-12-31 | Electric brush mounting device of aircraft attack angle indicator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023324352.2U CN214771758U (en) | 2020-12-31 | 2020-12-31 | Electric brush mounting device of aircraft attack angle indicator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214771758U true CN214771758U (en) | 2021-11-19 |
Family
ID=78743334
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023324352.2U Active CN214771758U (en) | 2020-12-31 | 2020-12-31 | Electric brush mounting device of aircraft attack angle indicator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214771758U (en) |
-
2020
- 2020-12-31 CN CN202023324352.2U patent/CN214771758U/en active Active
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