CN211919017U - Static discharger of airplane - Google Patents
Static discharger of airplane Download PDFInfo
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- CN211919017U CN211919017U CN201922418202.9U CN201922418202U CN211919017U CN 211919017 U CN211919017 U CN 211919017U CN 201922418202 U CN201922418202 U CN 201922418202U CN 211919017 U CN211919017 U CN 211919017U
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Abstract
The invention belongs to the field of airplane static protection, and relates to an airplane static discharger, which comprises: the tail end of the discharge rod (1) is provided with a boss (3) which can be connected with the base (2), the base (2) is fixed at the tip of the airplane in a riveting mode, and deposited static electricity is discharged; the base (2) is provided with a cross groove (4), and the boss (3) is inserted in the cross groove (4). When the electrostatic discharger is used, the discharger is provided with the cross groove, the discharge rod is provided with the cross boss, so that the electrostatic discharger can be adjusted according to the structural condition of the trailing edge of the wing, the electrostatic discharger is installed, particularly the base can be effectively contacted with the trailing edge aiming at the trailing edge of the flat structure, and the point discharge efficiency is improved. Compared with the traditional bonding type static discharger, the structure is simple, the installation is convenient, and the practical value is very high.
Description
Technical Field
The invention belongs to the field of electrostatic protection of airplanes.
Background
At present, the trailing edge of a common airplane wing mainly has an arc structure (figure 1) and a flat structure (figure 2), and because the two structures both belong to edge tip structures on the airplane, deposited static electricity generated by friction of an airplane body in airplane flight can be gathered towards the tip part of the trailing edge, a static electricity discharger is installed, the effective contact between the static electricity discharger and the airplane body is guaranteed, the static electricity can be effectively discharged, and the flight safety is protected.
With respect to the wing structure of fig. 1, the conventional electrostatic discharger is installed (fig. 3) to effectively discharge static electricity. In the wing structure in fig. 2, after the conventional electrostatic discharger is installed (fig. 4), it can be known from the figure that a large gap is formed at the position due to the presence of a break angle of the wing, so that the electrostatic discharger cannot be completely attached to the rear edge of the wing, and the electrostatic discharge is insufficient in practical use, which may affect the flight safety.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides an aircraft electrostatic discharger, which aims to solve the problem of electrostatic discharge at the trailing edge of a flat wing.
Technical scheme
An aircraft static discharger comprising: the tail end of the discharge rod 1 is provided with a boss 3 which is connected with the base 2, the base 2 is fixed at the tip of the airplane in a riveting mode, and deposited static electricity is discharged; the base 2 is provided with a cross groove 4, and the boss 3 is inserted in the cross groove 4.
The boss 3 is a cross boss.
The boss 3 is transversely or longitudinally inserted into the cross-shaped groove 4.
The cross-shaped groove 4 and the boss 3 are connected through the matching of conductive adhesive.
The base 2 is provided with a rivet hole, and installation and reinforcement are carried out through a riveting mode.
After the boss 3 of the discharge rod 1 is coated with conductive adhesive, the conductive adhesive is inserted into the groove 4 of the discharger base 2, and after the conductive adhesive is solidified, the base is fixed on the rear edge of the airplane in a riveting mode; the static electricity generated by the airplane during the flight is discharged after passing through the base 2 and the discharge rod 1.
Advantageous effects
According to the invention, by designing the electrostatic discharger with the cross groove base and the discharge rod with the cross boss, and selecting a proper discharger installation direction according to the specific situation of the trailing edge of the wing in the installation process, the problem of poor electrostatic discharge effect when the electrostatic discharger on the airplane is used on the flat wing can be solved.
Drawings
FIG. 1 is a view of the trailing edge structure of a cambered airfoil.
FIG. 2 is a view of the trailing edge of a flat wing.
Fig. 3 is a diagram of a conventional electrostatic discharger installation for the wing structure of fig. 1.
Fig. 4 is a diagram of a conventional electrostatic discharger installation for the wing structure of fig. 2.
Fig. 5 is a side view of the electrostatic discharger of the present invention.
Fig. 6 is a side view of the discharge rod of the present invention.
Fig. 7 is a top view of the arrester base of the present invention.
Fig. 8 is a top view of the electrostatic discharger of the present invention.
Detailed Description
The electrostatic discharger of the present invention comprises two parts: 1. a static discharger base; 2. and a static discharger discharge rod. The electrostatic discharger discharge rod is fixed in the groove of the discharger base through the boss part.
The invention mainly designs a cross boss at the tail end of a discharge rod in the design of the electrostatic discharger, and a cross groove is formed in a base. During use, firstly, a proper discharger base placing method is selected according to the specific situation of the trailing edge of the wing during installation, the discharge rod boss is coated with conductive adhesive and then fixed on the static discharger base, and after the discharge rod is completely fixed, the base is fixed on the trailing edge part of the wing in a riveting mode, so that the static electricity discharge requirement is met.
As shown in fig. 4 to 8, the electrostatic discharger of the present invention includes a discharge rod 1, and the discharge rod 1 is connected to a discharger base 2 by a conductive paste.
The discharger base 2 is made of plastic material added with conductive material, and the surface of the discharger base is coated with a conductive layer.
The discharge rod 1 is provided with a cross boss 3, so that the installation mode can be adjusted to meet the requirements of different directions.
The discharger base 2 is provided with a cross groove 4 which plays a role of fixing the discharge rod.
The discharger base 2 is provided with a first rivet hole 5, a second rivet hole 6, a third rivet hole 7 and a fourth rivet hole 8, and the effect of fixing the electrostatic discharger is achieved.
The using method of the invention is as follows:
longitudinal or transverse pedestal mounting is selected according to the form of the trailing edge of the wing. After the boss 3 of the discharge rod 1 is coated with conductive adhesive, the conductive adhesive is inserted into the groove 4 of the discharger base 2, and after the conductive adhesive is solidified, the base is fixed on the rear edge of the airplane in a riveting mode. The static deposition generated by the airplane in flight can realize discharge after passing through the base 2 and the discharge rod 1.
When the electrostatic discharger is used, the discharger is provided with the cross groove, the discharge rod is provided with the cross boss, so that the electrostatic discharger can be adjusted according to the structural condition of the trailing edge of the wing, the electrostatic discharger is installed, particularly the base can be effectively contacted with the trailing edge aiming at the trailing edge of the flat structure, and the point discharge efficiency is improved. Compared with the traditional bonding type static discharger, the structure is simple, the installation is convenient, and the practical value is very high.
Claims (6)
1. An aircraft static discharger, comprising: the tail end of the discharge rod (1) is provided with a boss (3) which is connected with the base (2), the base (2) is fixed at the tip of the airplane in a riveting mode, and deposited static electricity is discharged; the base (2) is provided with a cross groove (4), and the boss (3) is inserted in the cross groove (4).
2. An aircraft static discharger according to claim 1 wherein,
the boss (3) is a cross boss.
3. An aircraft static discharger according to claim 2 wherein,
the boss (3) is transversely or longitudinally inserted into the cross groove (4).
4. An aircraft static discharger according to claim 3 wherein,
the cross-shaped groove (4) and the boss (3) are connected in a matching way through conductive adhesive.
5. An aircraft static discharger according to claim 4 wherein,
the base (2) is provided with a rivet hole, and the installation and the reinforcement are carried out through a riveting mode.
6. An aircraft static discharger according to claim 5 wherein,
after a boss (3) of the discharge rod (1) is coated with conductive adhesive, the conductive adhesive is inserted into a groove (4) of a discharger base (2), and after the conductive adhesive is solidified, the base is fixed on the rear edge of the airplane in a riveting mode; the static deposition generated by the airplane in flight is discharged after passing through the base (2) and the discharge rod (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922418202.9U CN211919017U (en) | 2019-12-27 | 2019-12-27 | Static discharger of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922418202.9U CN211919017U (en) | 2019-12-27 | 2019-12-27 | Static discharger of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211919017U true CN211919017U (en) | 2020-11-13 |
Family
ID=73326757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922418202.9U Active CN211919017U (en) | 2019-12-27 | 2019-12-27 | Static discharger of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211919017U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671037A (en) * | 2022-05-30 | 2022-06-28 | 合肥航太电物理技术有限公司 | Electrostatic discharge brush and arrangement method |
-
2019
- 2019-12-27 CN CN201922418202.9U patent/CN211919017U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671037A (en) * | 2022-05-30 | 2022-06-28 | 合肥航太电物理技术有限公司 | Electrostatic discharge brush and arrangement method |
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