A fixed structure of a large elbow pipe of a T-tail aircraft

Abstract

The utility model discloses a kind of fixed structure of large elbow bend pipe in T-shaped tail wing aircraft fixed leading edge. Including bird-strike baffle, bird-strike baffle rear surface is connected with body along the longitudinal direction distribution 3 piece of baffle support rib, bird-strike baffle above the uppermost piece of baffle support rib, the bird-strike baffle at large elbow bend pipe through place is equipped with through hole, the orifice of through hole on bird-strike baffle front surface is equipped with U-shaped piece, two U-shaped arms of U-shaped piece are fixed by fastener with bird-strike baffle, the uppermost piece of baffle support rib leading edge jointly;Bird-strike baffle front surface between two U-shaped arms is also equipped with with bird-strike baffle, the uppermost piece of baffle support rib leading edge jointly fixed profilometry fixed component A, bird-strike baffle rear surface above U-shaped piece is also equipped with profilometry fixed component B, after large elbow bend pipe passes through through hole, corresponding profilometry fixed component A, B is fixed. The utility model can realize the efficient, reliable, light-weighted fixation of large elbow bend pipe, facilitate installation and maintenance.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural design technology, specifically relating to a fixed structure for a large bend tube at the fixed leading edge of a T-tail aircraft. Background Technology

[0002] In aircraft with a T-tail configuration, the fixed leading edge is located at the boundary between the vertical and horizontal stabilizers. A large amphibious aircraft requires piping to allow metal cables with tow cones to pass through. The piping needs to run along the mid-rear fuselage, the top of the rear fuselage tail section, the leading edge of the vertical box section, and down to the fin tip fairing of the vertical tail. The fixed leading edge, located between the leading edge of the vertical box section and the fin tip fairing, contains a large bend (approximately 150°). The overall piping layout is illustrated in the diagram. Figure 1 A vertical bird-strike shield is located inside the fixed leading edge. A through-hole is provided at the bend's path to facilitate its passage. This bend experiences significant external loads in both the radial and axial directions, therefore, it needs to be secured.

[0003] Traditional fixing methods have the following problems: 1) Poor stability: Bends, especially sharp bends, are prone to significant swaying and stress concentration at the bend point under long-term flight vibration, leading to reduced fatigue life. 2) Difficult installation and maintenance: The pipeline is located inside the fairing, and the traditional clamp + bracket fixing method requires a large installation space and disassemblies a large number of external fasteners for maintenance, which is time-consuming and labor-intensive. 3) Reliability risks: Vibration can easily cause traditional clamps to loosen, and friction and wear may occur between the pipeline and the bracket, posing a safety hazard in the long term. Utility Model Content

[0004] The purpose of this invention is to provide a fixing structure for a large bend in the leading edge of a T-tail aircraft. This invention enables efficient, reliable, and lightweight fixing of the large bend, and facilitates installation and maintenance.

[0005] The technical solution of this utility model is as follows: a fixing structure for a large bend tube at the fixed leading edge of a T-tail aircraft, including a bird strike shield. The rear wall of the bird strike shield is connected to the fuselage via three longitudinally distributed shield support ribs. A through hole is provided on the bird strike shield above the uppermost shield support rib, at the point where the large bend tube passes through. A U-shaped component is provided at the opening of the through hole on the front wall of the bird strike shield. The two U-shaped arms of the U-shaped component are fixed together with the bird strike shield and the leading edge of the uppermost shield support rib by fasteners. A contour-following fixing component A is also provided on the front wall of the bird strike shield between the two U-shaped arms, which is fixed together with the bird strike shield and the leading edge of the uppermost shield support rib. A contour-following fixing component B is also provided on the rear wall of the bird strike shield above the U-shaped component. After the large bend tube passes through the through hole, it is fixed by the contour-following fixing components A and B respectively.

[0006] In the aforementioned fixed structure of the large bend tube at the fixed leading edge of the T-tail aircraft, each U-shaped arm of the U-shaped component is provided with two connecting holes distributed along the arm length, and the connecting holes on the two U-shaped arms are arranged symmetrically.

[0007] In the aforementioned fixed structure of the large bend tube at the leading edge of the T-tail aircraft, the fasteners are MS20470 series rivets. After passing through the connecting hole, the fasteners are fixed together with the bird strike protection partition and the leading edge of the uppermost partition support rib.

[0008] In the aforementioned fixed structure for the large bend tube at the fixed leading edge of the T-tail aircraft, the contour fixing component A includes a contour slot bracket with an I-shaped structure. The contour slot bracket and the contour slot cover are connected to each other. The web of the contour slot bracket and the upper transverse plate are connected at the intersection by a concave lower contour flap. The contour slot cover has a convex upper contour flap in the middle. After the upper and lower contour flaps are engaged, they together wrap around the outer wall of the large bend tube.

[0009] In the aforementioned fixed structure of the large bend tube at the fixed leading edge of the T-tail aircraft, the arc length ratio of the lower and upper contoured lobes is 2:1.

[0010] In the aforementioned fixed structure of the large bend tube at the leading edge of the T-tail aircraft, the bottom of the bird strike shield is connected to the leading edge tip rib; the large bend tube passes through the leading edge tip rib and is fixed by the contour fixing component C fixed to the upper surface of the leading edge tip rib.

[0011] In the aforementioned fixed structure of the large bend tube at the fixed leading edge of the T-tail aircraft, the contour fixing components A, B, and C have the same structure.

[0012] In the aforementioned fixed structure of the large bend tube at the fixed leading edge of the T-tail aircraft, an annular washer is also provided between the lower and upper contoured petals and the large bend tube.

[0013] The technical effects of this utility model are: 1. Extremely high connection rigidity and stability: The contoured groove provides 2 / 3 wrap-around support for the bend, which greatly suppresses the vibration and displacement of the pipeline during flight, significantly reduces stress concentration, and improves fatigue life.

[0014] 2. Excellent vibration and wear resistance: The built-in elastic damping pad effectively isolates vibration, avoids hard contact and friction wear between the metal bend and the metal support, and improves system reliability.

[0015] 3. Efficient installation and maintenance: The installation mode uses detachable domestic bolts and nuts, which is simple to operate, convenient to purchase, and economical, greatly reducing maintenance time and costs.

[0016] 4. Significant lightweight advantage: The support structure can be used in narrower connection spaces, avoiding the design of large-size and heavy support structures, thus achieving overall weight reduction of the structure.

[0017] 5. Good versatility: The structural design can be adapted to meet the needs of different models, pipe diameters and bend angles, and has broad application prospects. Attached Figure Description

[0018] Figure 1 A schematic diagram of the laying of the tow cone pipeline channel.

[0019] Figure 2 This is a schematic diagram of the structure of this utility model.

[0020] Figure 3 This is a schematic diagram of the connection structure between the bend and the bird strike prevention partition.

[0021] Figure 4 This is a schematic diagram of a U-shaped component.

[0022] Figure 5 This is a schematic diagram of the contour-following fixing component.

[0023] Figure 6 This is a schematic diagram showing the connection between the bend and the leading edge rib. Detailed Implementation

[0024] To make the implementation process of this utility model clearer, the technical solutions of this utility model will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this utility model, and the parts not detailed are conventional techniques. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0025] Example 1. A fixing structure for a large bend in the leading edge of a T-tail aircraft, see [reference needed]. Figures 1-6The system includes a bird strike shield 1. The rear wall of the bird strike shield 1 is connected to the machine body via three longitudinally distributed shield support ribs 3. A through hole is provided on the bird strike shield 1 above the uppermost shield support rib 3, at the point where the large bend pipe 2 passes. A U-shaped component 4 is provided at the opening of the through hole on the front wall of the bird strike shield 1. The two U-shaped arms of the U-shaped component 4 are fixed to the bird strike shield 1 and the front edge of the uppermost shield support rib 3 by fasteners. A contour-following fixing component A5 is also provided on the front wall of the bird strike shield 1 between the two U-shaped arms, which is fixed together with the front edge of the bird strike shield 1 and the uppermost shield support rib 3. A contour-following fixing component B6 is also provided on the rear wall of the bird strike shield 1 above the U-shaped component 4. After the large bend pipe 2 passes through the through hole, it is fixed by contour-following fixing components A and B respectively. The U-shaped component with a flange is provided to enhance the rigidity of the bird strike shield after the through hole is opened.

[0026] Each U-shaped arm of the aforementioned U-shaped component 4 is provided with two connecting holes 7 distributed along the arm length, and the connecting holes 7 on the two U-shaped arms are arranged symmetrically.

[0027] The aforementioned fasteners are MS20470 series rivets. After passing through the connecting hole 7, the fasteners are fixed together with the bird strike protection partition 1 and the front edge of the uppermost partition support rib 3. The entire U-shaped piece and the partition are connected as a whole using MS20470 series rivets. For easy disassembly and without affecting the connection structure between the partition and the rib, symmetrical through holes are provided at the connection between the bird strike protection partition and the rib edge strip, two on each side, for a total of four.

[0028] The aforementioned contouring fixing component A5 includes a contouring slot bracket 8 with an I-shaped structure. The contouring slot bracket 8 and the contouring slot cover 9 are connected to each other. The web plate 81 of the contouring slot bracket 8 and the upper horizontal plate 82 are connected at the intersection by a concave lower contouring flap 83. The contouring slot cover 9 has a convex upper contouring flap 91 in the middle. After the upper and lower contouring flaps are engaged, they together wrap around the outer wall of the large bend tube 2. The inner contour surface formed by the engagement of the upper and lower contouring flaps completely fits the outer curved surface of the large bend tube.

[0029] To reduce weight and facilitate installation, contoured slot brackets and contoured slot covers are designed on both the front and rear sides of the bird strike protection partition. In front of the partition, the contoured slot bracket is arranged inside the U-shaped component. The position of the contoured fixing component matches the direction of the large bend in the pipe, and its inner contour surface conforms to the outer surface of the bend, providing precise radial and axial support for the bend.

[0030] The arc length ratio of the lower and upper contoured lobes mentioned above is 2:1. To facilitate installation and improve the rigidity of the connection with the bend, the ratio of the contoured slot bracket to the contoured slot cover to the outer diameter of the bend is 2:1, that is, 2 / 3 of the outer diameter depth is wrapped by the contoured slot bracket and 1 / 3 of the outer diameter depth is wrapped by the contoured slot cover.

[0031] The bottom of the aforementioned bird strike shield 1 is connected to the leading edge rib 10; the large bend tube 2 passes through the leading edge rib 10 and is fixed by the contour fixing component C11 fixed to the upper surface of the leading edge rib 10.

[0032] The aforementioned contouring fixing components A, B, and C have the same structure.

[0033] An annular washer 12 is also provided (bonded) between the aforementioned lower and upper contoured flaps and the large bend in the pipe 2. The annular washer 12 is an elastic damping pad made of ethylene propylene rubber of grade M049. To reduce vibration, reduce friction between the joint and the bend, and prevent misalignment with the bend's outer surface caused by potential deviations in the overall assembly of the bend, a universal annular washer is designed between the contoured slot bracket and the contoured slot cover. The washer is formed by laying a 1.5mm thick rubber plate in a circular shape according to the bend's shape to reduce installation and material costs.

[0034] The large bend is designed with straight pipes at the beginning and end for easy installation. It uses a straight pipe connector with a leading edge rib. The connector is similar to the contoured slot bracket and contoured slot cover at the bend, except for the difference in the height of the I-beam and the position of the base connection surface.

[0035] The large bend in the pipe has standard interfaces at both ends for connecting to the straight pipe section within the leading edge. Its bend angle can be any angle between 90° and 160°.

[0036] The contour-following fixing component is made of aerospace aluminum alloy material and is integrally formed by CNC machining or additive manufacturing, which ensures both strength and lightweight.

[0037] Preferably, the conformal fixing component is embedded with an elastic damping pad. This pad can effectively absorb vibration energy, prevent pipe wall wear, and allow the pipe to undergo slight deformation due to thermal expansion and contraction.

[0038] During installation, first secure the conformal slot bracket to the bird strike baffle and the baffle support ribs. Then carefully insert the large bend tube into the lower conformal flap 83. Finally, use the upper and lower conformal flaps to align and wrap around the bend tube, then fix the upper and lower conformal flaps to firmly secure the bend tube. Specifically, the connection method of the above-mentioned fixing structure includes the following steps: 1. Pre-installation bracket: Position and fix the conformal slot bracket to the bird strike prevention partition and partition support rib structure through the connection holes on its mounting base plate.

[0039] 2. Inserting the bend: Precisely insert the large bend into the contour slot of the bracket. At this time, the bend can achieve pre-positioning by its own weight and contouring.

[0040] 3. Tighten the contour slot cover: Operate the contour slot cover, insert the bolt, tighten the nut, and securely restrain the bent pipe in the contour slot to complete the installation.

[0041] 4. Connect the pipes: Connect the standard interfaces at both ends of the bend to the adjacent straight pipe sections.

[0042] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A fixing structure for a large bend in a tube located at the fixed leading edge of a T-tail aircraft, characterized in that, The system includes a bird strike shield (1). The rear wall of the bird strike shield (1) is connected to the machine body via three longitudinally distributed shield support ribs (3). A through hole is provided on the bird strike shield (1) above the uppermost shield support rib (3) at the passage of the large bend pipe (2). A U-shaped piece (4) is provided at the opening of the through hole on the front wall of the bird strike shield (1). The two U-shaped arms of the U-shaped piece (4) are fastened to the bird strike shield (1) and the uppermost shield. The front edge of the partition support rib (3) of the block is fixed together; the front wall of the bird strike prevention partition (1) between the two U-shaped arms is also provided with a contour fixing component A (5) which is fixed together with the front edge of the bird strike prevention partition (1) and the partition support rib (3) of the uppermost block; the rear wall of the bird strike prevention partition (1) above the U-shaped piece (4) is also provided with a contour fixing component B (6); after the large bend pipe (2) passes through the through hole, it is fixed by the contour fixing components A and B respectively.

2. The fixing structure for the large bend in the leading edge of a T-tail aircraft as described in claim 1, characterized in that, Each U-shaped arm of the U-shaped component (4) is provided with two connecting holes (7) distributed along the arm length, and the connecting holes (7) on the two U-shaped arms are arranged symmetrically.

3. The fixing structure for the large bend tube at the leading edge of a T-tail aircraft as described in claim 2, characterized in that, The fasteners are MS20470 series rivets. After passing through the connecting hole (7), the fasteners are fixed together with the front edge of the bird strike prevention partition (1) and the uppermost partition support rib (3).

4. The fixing structure for the large bend tube at the leading edge of a T-tail aircraft as described in claim 1, characterized in that, The contour fixing component A (5) includes a contour slot bracket (8) with an I-shaped structure. The contour slot bracket (8) and the contour slot cover (9) are connected to each other. The web plate (81) of the contour slot bracket (8) and the upper horizontal plate (82) are connected at the intersection by a concave lower contour flap (83). The contour slot cover (9) has a convex upper contour flap (91) in the middle. After the upper and lower contour flaps are engaged, they together wrap the outer wall of the large bend tube (2).

5. The fixing structure for the large bend tube at the fixed leading edge of a T-tail aircraft according to claim 4, characterized in that, The arc length ratio of the lower and upper contoured lobes is 2:

1.

6. The fixing structure for the large bend tube at the leading edge of a T-tail aircraft as described in claim 1, characterized in that, The bottom of the bird strike shield (1) is connected to the front edge rib (10); the large bend tube (2) passes through the front edge rib (10) and is fixed by the contour fixing component C (11) fixed to the upper surface of the front edge rib (10).

7. The fixing structure for the large bend tube at the leading edge of a T-tail aircraft as described in claim 1, characterized in that, The contour-fixing components A, B, and C have the same structure.

8. The fixing structure for the large bend in the leading edge of a T-tail aircraft as described in claim 4, characterized in that, An annular gasket (12) is also provided between the lower and upper contoured petals and the large bend tube (2).

Images