Porthole threading device for air inflation test of airplane passenger cabin

Abstract

The utility model belongs to the field of airplane structure strength tests, and particularly relates to an airplane passenger cabin inflation test porthole threading device which comprises a c-shaped ring and a sliding block, a wire inlet groove is formed in a fracture of the c-shaped ring, a center through hole forms a wire bunching hole, the thickness of the two sides of the wire inlet groove is reduced to form step faces, and through holes are formed in the step faces; the section of the sliding block is in a T shape, the sliding block comprises a transverse block on the top and a vertical block connected to one side of the transverse block, the vertical block is used for filling the wire inlet groove, the transverse block is in lap joint with the step face, a first through hole is formed in the transverse block, and a second through hole corresponding to the first through hole is formed in the step face. A bolt penetrates through the first through hole and the second through hole to fix the sliding block and the c-shaped ring.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing, and specifically relates to a wiring device for aircraft cabin inflation test window. Background Technology

[0002] In aircraft structural strength inflation tests, a large number of strain gauges often need to be attached, making the selection of the outlet position of the strain gauge wiring harness inside the aircraft crucial. To ensure the integrity of the aircraft structure, the selection is usually based on the principle of not damaging the aircraft structure; therefore, aircraft windows are the optimal choice.

[0003] Aircraft cabin inflation tests are often conducted in the middle to late stages of the overall model testing process. Strain gauges have already been installed inside the aircraft structure, and their adapter cables are connected to external measuring equipment via the aircraft windows. Since some defective strain gauges inevitably occur during the early stages of testing, and additional strain gauges may be needed to replace them or for testing purposes, the aircraft windows cannot be sealed with cables too early. This can only be done after all preparations are complete before the inflation test. This necessitates that the window cable threading device have an inlet to ensure that the cable threading is completed without cutting the strain gauge wiring, while also maintaining the aircraft's airtightness. Furthermore, the device must be simple in structure and easy to install. Utility Model Content

[0004] To address the aforementioned problems, this application provides a wiring device for an aircraft cabin inflation test window, comprising:

[0005] The C-shaped ring and the slider have a wire inlet groove formed at the break of the C-shaped ring, a wire bundle hole formed at the center through hole, and stepped surfaces formed by the reduction in thickness on both sides of the wire inlet groove, with through holes on the stepped surfaces.

[0006] The slider has a T-shaped cross section, which includes a horizontal block at the top and a vertical block connected to one side of the horizontal block. The vertical block is used to fill the inlet slot. The horizontal block overlaps the stepped surface. The horizontal block has a first through hole. The stepped surface has a second through hole corresponding to the first through hole. Bolts pass through the first through hole and the second through hole to fix the slider to the C-shaped ring.

[0007] Preferably, the threading device has an inner end face at one end where the slider block is located, and the inner end face has an annular protrusion inner ring surface, and the outer edge has an inner edge surface that is lower than the inner ring surface; the other end face of the threading device is an outer end face, and the outer end face has an annular protrusion outer ring surface, and the outer edge has an outer edge surface that is lower than the outer ring surface.

[0008] Preferably, the inner edge of the threading device is fitted to the frame of the porthole.

[0009] Preferably, the shape curvature of the threading device is the same as the curvature of the aircraft skin surface where it is located.

[0010] Preferably, the center through hole is an elliptical hole, and the inner diameter of the elliptical hole is determined by the number S of the wire bundle:

[0011] S = 4ab / 22;

[0012] a = b + 20;

[0013] where a is the major axis of the elliptical hole, and b is the minor axis of the elliptical hole.

[0014] Preferably, the height of the inner ring surface of the device is 15 mm higher than the inner edge surface of the device, and the thickness between the inner edge surface of the device and the outer edge surface of the device is 30 mm.

[0015] Preferably, the opening width d of the wire inlet groove is 15 mm, and the all edges of the slider and the c-shaped ring are chamfered with R0.5.

[0016] Preferably, the outer diameter of the outer ring surface of the device is 4 mm smaller than the diameter of the aircraft porthole, and the outer diameter of the c-shaped ring is 50 mm larger than the diameter of the aircraft porthole, which facilitates installation while ensuring the air tightness of the aircraft structure.

[0017] After the wire bundle hole of the threading device is completed, it is sealed by curing agent.

[0018] The advantages of the present application include that the threading device maintains closer contact with the aircraft porthole as the internal pressure of the aircraft increases during the test, thus having good air tightness, the present application is simple to install, easy to operate, has low processing requirements, and low cost. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is a perspective view of the outer end surface of the threading device of a preferred embodiment of the present application;

[0020] Figure 2 is a perspective view of the inner end surface of the threading device of a preferred embodiment of the present application;

[0021] Figure 3 is a front view of the outer end surface of the threading device of a preferred embodiment of the present application;

[0022] Figure 4 is a side view of the outer end surface of the threading device of a preferred embodiment of the present application. DETAILED DESCRIPTION

[0023] For the purpose, technical solutions and advantages of the present application, the technical solutions in the embodiments of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0024] The present application provides a large aircraft cabin inflation test porthole threading device, first constructs a porthole threading device that is adapted to the curvature of the aircraft skin surface, ensures the air tightness of the aircraft, and through the design of the wire inlet slot, the threading work can be completed without damaging the transmission cable, the structure is simple and easy to operate, and a new method is provided for the aircraft inflation test porthole threading. The present application provides an aircraft cabin inflation test porthole threading device, comprising:

[0025] The c-shaped ring and the sliding block 1-2 first determine the curvature of the aircraft skin surface, construct a porthole threading c-shaped ring that is adapted to the curvature of the aircraft skin surface, and the material is high-strength aluminum alloy LY12, which can ensure the strength and has a lighter weight;

[0026] The wire inlet slot 1-3 is formed at the break of the c-shaped ring, the center through hole forms a wire bundling hole, and the wire inlet slot 1-3 has a stepped surface formed by reducing the thickness on both sides; the stepped surface has a through hole 2-1;

[0027] The sliding block 1-2 has a T-shaped cross section, which includes a horizontal block at the top and a vertical block connected to one side of the horizontal block, the vertical block is used to fill the wire inlet slot 1-3, the horizontal block is lapped on the stepped surface, the horizontal block has a first through hole 1-1, the stepped surface has a second through hole 2-1 corresponding to the first through hole 1-1, and a bolt passes through the first through hole 1-1 and the second through hole 2-1 to fix the sliding block 1-2 and the c-shaped ring. The main body and the sliding block each have four first through holes 1-1 and second through holes 2-1, which are connected by four 304 stainless steel outer hexagonal bolts M10*80.

[0028] Preferably, the threading device has an inner end face at one end of the sliding block 1-2, the inner end face has a ring-shaped protruding device inner ring face 2-2, and the outer edge has a device inner edge face 2-3 with a height lower than the device inner ring face 2-2; the other end of the threading device is an outer end face, the outer end face has a ring-shaped protruding device outer ring face 1-4, and the outer edge has a device outer edge face 1-5 with a height lower than the device outer ring face 1-4.

[0029] In some optional embodiments, the device inner edge face 2-3 of the threading device is attached to the frame of the porthole.

[0030] In some optional embodiments, the shape of the threading device has the same curvature as the surface curvature of the aircraft skin at the location where the threading device is located.

[0031] In some optional embodiments, the center through hole is an elliptical hole, and the number of wire bundles S determines the inner diameter of the device elliptical hole: S = 4ab / 22, wherein the data acquisition wire model is ZR FEPVR-26#9P.

[0032] S = 4ab / 22;

[0033] a = b + 20;

[0034] Where a is the major axis of the elliptical hole, and b is the minor axis of the elliptical hole.

[0035] In some optional embodiments, the device inner ring face 2-2 is 15 mm higher than the device inner edge face 2-3, and the thickness between the device inner edge face 2-3 and the device outer edge face 1-5 is 30 mm.

[0036] In some optional embodiments, the opening width d of the wire inlet slot 1-3 is 15 mm, and the sliding block 1-2 and all the edges of the c-shaped ring are chamfered with R0.5.

[0037] In some optional embodiments, the outer diameter of the device outer ring face 1-4 is 4 mm smaller than the diameter of the aircraft porthole, and the outer diameter of the c-shaped ring is 50 mm larger than the diameter of the aircraft porthole, which facilitates installation while ensuring the air tightness of the aircraft structure.

[0038] After the completion of the wire bundle hole of the threading device, the wire bundle is sealed by a curing agent.

[0039] The specific installation steps of the porthole threading device are as follows:

[0040] a) The strain gauge wire bundle is threaded from the wire inlet slot of the porthole threading device into the passenger cabin of the aircraft body.

[0041] b) After threading is completed, the wire bundle is compressed by the sliding block, fixed by the hexagonal bolt, and then the gap between the wire bundles is treated by epoxy resin pouring, and the tapered wooden wedge is inserted into the middle of the wire bundle to further compress the gap between the wire bundles, and the curing time is 3-5 days under natural conditions.

[0042] c) The Gezhouba LDJ-281 adhesive is mixed with the curing agent at a weight ratio of 10:1, and is evenly applied to the outer edge surface of the device and the inner surface of the aircraft skin in contact therewith, so as to ensure good adhesion with the inner surface of the aircraft skin;

[0043] d) The wire harness is fixed on the outer surface of the aircraft, so as to keep the wire harness in a tensioned state; a bracket is arranged inside the aircraft, so as to keep the threading device in stable and close contact with the inner skin near the aircraft window;

[0044] e) After the structure is installed, the threading device and the contact area of the aircraft window, the main body and the bolt connection area of the sliding block are all coated with epoxy resin sealing treatment, and are cured for 2-3 days under natural conditions.

[0045] The advantages of the present application include that the threading device and the aircraft window maintain closer contact as the internal pressure of the aircraft increases during the test, thus having good air tightness, the present application is simple to install, convenient to operate, has low processing requirements and low cost.

[0046] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical scope disclosed in the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft cabin inflation test porthole threading device, comprising: The utility model relates to a kind of wire threading device, including: C-shaped ring and slider (1-2), the fracture of c-shaped ring forms incoming slot (1-3), central through-hole forms bundle hole, and the both sides of incoming slot (1-3) are formed step surface by reducing thickness; Slider (1-2) section is T-shaped, including the horizontal block of top and the vertical block connected to the side of the horizontal block, the vertical block is used to fill the incoming slot (1-3), the horizontal block is overlapped on the step surface, the horizontal block has first through-hole (1-1), the step surface has second through-hole (2-1) corresponding to first through-hole (1-1), and slider (1-2) is fixed with c-shaped ring by bolt passing through first through-hole (1-1) and second through-hole (2-1).

2. The aircraft cabin inflation test porthole threading device of claim 1, wherein, The end surface of the wire threading device where slider (1-2) horizontal block is located is inner end surface, and inner end surface has annular protruding device inner ring surface (2-2), and outer edge has device inner edge surface (2-3) with height lower than device inner ring surface (2-2);The other end surface of the wire threading device is outer end surface, and outer end surface has annular protruding device outer ring surface (1-4), and outer edge has device outer edge surface (1-5) with height lower than device outer ring surface (1-4).

3. The aircraft cabin inflation test porthole threading device of Claim 1, wherein, Device inner edge surface (2-3) of the wire threading device is attached to the frame of side window.

4. The aircraft cabin inflation test porthole threading device of Claim 1, wherein, The shape curvature of the wire threading device is same with the surface curvature of the position of aircraft skin.

5. The aircraft cabin inflation test porthole threading device of Claim 1, wherein, Central through-hole is oval hole, and the inner diameter of device oval hole is determined by the number S of wire bundle: S=4ab / 22; a=b+20; Wherein a is the long semi-axis of oval hole, and b is the short semi-axis of oval hole.

6. The aircraft cabin inflation test portress of claim 1, wherein, Device inner ring surface (2-2) is 15mm higher than device inner edge surface (2-3), and the thickness between device inner edge surface (2-3) and device outer edge surface (1-5) is 30mm.

7. The aircraft cabin inflation test portress of claim 1, wherein, Incoming slot (1-3) opening width d is 15mm, and all edges of slider (1-2) and c-shaped ring are chamfered with R0.

5.

8. The aircraft cabin inflation test portaway threader of Claim 1, wherein, Device outer ring surface (1-4) outer diameter is less than aircraft side window diameter 4mm, and the outer diameter of c-shaped ring is greater than aircraft side window diameter 50mm, to facilitate installation while ensuring the air tightness of aircraft structure.

9. The aircraft cabin inflation test portaway-wire device of Claim 1, wherein, After bundle hole wire bundle of the wire threading device is completed, it is sealed by curing agent.

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