KR100417980B1 - Hole structure for checking the inside of an airplane - Google Patents

Abstract

The present invention relates to a hole structure for the internal inspection of the aircraft, the hole structure for the internal inspection of the aircraft of the present invention, in a hole structure that can be equipped with a camera for the internal inspection of the aircraft, aircraft having a fuselage hole Fuselage; A skin coupled to cover the outer surface of the aircraft fuselage and having a skin hole communicating with the fuselage hole; A nut plate having a first nut hole communicating with the fuselage hole and the skin hole and coupled to an inner surface of the aircraft fuselage; A first bolt inserted together into the skin hole, the fuselage hole and the first nut hole, the end of which is coupled to the first nut hole, and has a second nut hole formed therein; It is preferable that a second bolt is inserted and coupled to the second nut hole formed in the first bolt, and according to the present invention having the above configuration, the internal inspection of the aircraft, in particular, the internal inspection of the aircraft fuselage and fuel tank. There is no need to install a separate inspection window on the aircraft, thereby reducing the time and process accordingly, improving work efficiency, and minimizing the structural change of the additional aircraft fuselage by installing the inspection window, thereby maintaining a solid aircraft. There is.

Description

HOLE STRUCTURE FOR CHECKING THE INSIDE OF AN AIRPLANE

The present invention relates to a hole structure installed for the internal inspection of the aircraft, and more particularly with the lens of the internal inspection camera in place of the conventional inspection window that is bolted for the internal inspection of the fuselage and fuel tank of the aircraft. The present invention relates to a hole structure for internal inspection of an aircraft consisting of a detachable bolt for inserting a cable. Generally, an inspection window of a predetermined size is installed in an aircraft for internal inspection of an aircraft fuselage and a fuel tank. This inspection window has a relatively large size and is bolted to the aircraft structure forming the skeleton of the aircraft for inspecting the state of its interior. FIGS. 1A and 1B show an example of the inspection window for the internal inspection of a conventional aircraft. . FIG. 1A is a plan view showing an inspection window installed in a predetermined portion of an aircraft structure for the internal inspection of a conventional aircraft, and FIG. 1B is a plan view showing a state in which the inspection window of FIG. 1A is removed. Inspection window 70 for the internal inspection of the aircraft includes a hole 72 formed on the edge of the inspection window. The bolt 80 is inserted into the hole 72. That is, the bolt 80 is coupled to the nut plate (not shown) fixed through the hole 72 and the bolt hole 14 of the aircraft structure 10 by rivets 90 inside the aircraft structure. As such, the inspection window for the internal inspection of the conventional aircraft is installed in the aircraft fuselage and the fuel tank so as to inspect the internal condition. However, the inspection window for the internal inspection of the conventional aircraft is bolted. It is structurally weak and takes a long time to remove and reattach the inspection window. In addition, the aircraft structure must be designed and manufactured to attach the inspection window to the aircraft structure. This has a problem that the complexity of the aircraft body itself causes a weight increase of the aircraft as opposed to the development of a light and durable aircraft structure.

Accordingly, the present invention has been derived to solve the above problems, the object of the present invention, there is no need to install a separate inspection window on the aircraft in the internal inspection of the aircraft, in particular the internal inspection of the aircraft fuselage and fuel tank accordingly It is to provide a hole structure for the internal inspection of the aircraft to maintain the aircraft in a solid state by minimizing the change of the structure of the additional aircraft fuselage according to the installation of the inspection window by improving the work efficiency by reducing the time and process.

Figure 1a is a plan view showing an example of the inspection window installed on the aircraft for the internal inspection of the conventional aircraft,

1B is a plan view illustrating a state in which the inspection window of FIG. 1A is removed;

2 is a plan view showing a hole structure installed in the aircraft for the internal inspection of the aircraft according to an embodiment of the present invention,

3 is a cross-sectional view showing a section cut along the line I-I of FIG.

FIG. 4 is a cross-sectional view illustrating a state in which a second bolt is removed from the hole structure of FIG. 3 and a cable with a camera lens attached thereto is inserted into the hole; FIG.

* Explanation of symbols for the main parts of the drawings * 10 ... Aircraft body 12 ... Body hole 20 ... Skin 22 ... Skin hole 30 ... Double bolt 32 ... First bolt 34 ... 2nd bolt 32a, 34a ... 1st and 2nd fastening groove 36 ... 2nd nut hole 40 ... nut plate 42; ... 1st nut hole 50a, 50b ... rivet

60 ... camera 62 ... cable

In order to achieve the above object, the hole structure for the internal inspection of the aircraft according to the present invention, the hole structure that can be equipped with a camera for the internal inspection of the aircraft, the aircraft body is formed with a fuselage hole; A skin coupled to cover the outer surface of the aircraft fuselage and having a skin hole communicating with the fuselage hole; A nut plate having a first nut hole communicating with the fuselage hole and the skin hole and coupled to an inner surface of the aircraft fuselage; A first bolt inserted together into the skin hole, the fuselage hole and the first nut hole, the end of which is coupled to the first nut hole, and has a second nut hole formed therein; It is preferable that a second bolt is inserted into and coupled to the second nut hole formed in the first bolt, and according to the present invention having the above-described configuration, the internal inspection of the aircraft, in particular, the internal inspection of the aircraft fuselage and fuel tank. Therefore, it is not necessary to install a separate inspection window on the aircraft, thereby reducing the time and process accordingly, improving work efficiency, and minimizing the structural change of the additional aircraft fuselage according to the installation of the inspection window, thereby maintaining a solid aircraft. Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the drawings. FIG. 2 is a plan view showing a hole structure installed in an aircraft for internal inspection of an aircraft according to an embodiment of the present invention, and FIG. 2 is a cross-sectional view taken along the line I-I of FIG. 2, and FIG. 4 shows a second bolt separated from the hole structure of FIG. 2 and 3, the hole structure for the internal inspection of the aircraft according to the embodiment of the present invention is formed in the aircraft fuselage 10. The skin 20 is coupled to surround the outer surface of the fuselage hole 12 and the aircraft fuselage 10, and has a skin hole 22 communicating with the fuselage hole 12. The fuselage of the aircraft fuselage 10 is provided. The first nut hole 42 communicating with the skin hole 22 formed in the hole 12 and the skin 20 is formed, and there is a nut plate 40 coupled to the inner surface of the aircraft fuselage 10. 12), the skin hole 22 and the first nut hole 42 are located on the same center line. Thus, the fuselage hole 12, the skin hole 22, and the first nut hole 42 located on the same center line are disposed. The first bolt 32 is inserted and fastened together. In detail, the first threaded portion 32b formed at the end of the first bolt 32 is connected to the nut plate 40. The first nut hole 42 formed in the inner circumferential surface thereof is fastened. A second nut hole 36 through which the inner circumferential surface of the first nut hole 42 is fastened is formed. And a second bolt 34 having a second threaded portion 34b formed on an outer circumferential surface thereof is inserted into the second nut hole 36. That is, the fuselage hole 12, the skin hole 22, and the first nut hole ( 42 is inserted into the form of the double bolt 30 consisting of the first bolt 32 and the second bolt 34. Further, the first bolt 32 and the second bolt (exposed to the skin 20 side) 34, the first and second fastening grooves 32a and 34a are formed so that the tools used to tighten or loosen them are in close contact. When the first fastening groove 23a and the second fastening groove 34a formed in the first bolt 32 and the second bolt 34 are matched with a predetermined tool and turned at the same time, the entire double bolt 30 is separated or engaged. do. If the second fastening groove 34a formed in the second bolt 34 is turned with a tool having a different size, the second bolt 34 is separated from the first bolt 32 and the first bolt 32 is removed. 2, the nut hole 36 is in an empty hollow state. Referring to FIG. 3, the embodiment of the present invention will be described in more detail. First, the aircraft fuselage 10 and the aircraft fuselage 10 forming the skeleton of the aircraft will be described. The fuselage hole 12 and the skin hole 22 are formed in arbitrary positions so that the double bolt 30 mentioned above may be inserted in the covering skin 20. Thereafter, the first nut hole 42 of the nut plate 40 is co-centered with the fuselage hole 12 and the skin hole 22 by using fixing means such as rivets 50a and 50b inside the aircraft fuselage 10. Next, the first bolt 32 with the second bolt 34 embedded therein is inserted through the fuselage hole 12 and the skin hole 22 to be formed of the nut plate 40. 1 and 2, the inserted first and second bolts 32 and 34 remain closed when the aircraft is in flight. As shown in FIG. Likewise, when the aircraft is in flight or in a hangar or the like, the second bolt 34 is fitted at the center of the first bolt 32 to seal the aircraft fuselage. Remove the 2 bolt 34 from the first bolt 32 and insert the cable 62 with the camera lens into the second nut hole 36. The inside of the aircraft can be inspected.

As described above, according to the present invention, in the internal inspection of the aircraft, in particular, the internal inspection of the aircraft fuselage and fuel tank, there is no need to install a separate inspection window on the aircraft, thereby reducing the time and process accordingly, thereby improving work efficiency. By minimizing the structural change of the additional aircraft fuselage due to the installation of the inspection window, the aircraft in a solid state is maintained.

Claims (1)

(Correction) In the hall structure which can attach a camera for the internal inspection of the aircraft, An aircraft body in which a fuselage hole is formed; A skin coupled to cover the outer surface of the aircraft fuselage and having a skin hole communicating with the fuselage hole; A nut plate having a first nut hole communicating with the fuselage hole and the skin hole and coupled to an inner surface of the aircraft fuselage; A first bolt inserted together into the skin hole, the fuselage hole and the first nut hole, the end of which is coupled to the first nut hole, and has a second nut hole formed therein; And a second bolt inserted into and coupled to the second nut hole formed in the first bolt.