Transport frame for assembled panels for aircraft wings

Abstract

The utility model relates to a kind of transport frame of aircraft wing with assembled plate parts, including rectangular bottom beam frame, bottom beam frame is by two groups of front, rear distribution horizontal bottom beam and the longitudinal bottom beam fixed between horizontal bottom beam, the lower end surface of bottom beam frame is respectively fixed with several transverse distribution load-bearing support, load-bearing support includes longitudinal joist, the left side of bottom beam frame is provided with several groups of longitudinal distribution load-bearing frame, load-bearing frame includes left and right two groups of bracket, bracket includes left vertical column fixed in joist and horizontal bottom beam, the upper end of left vertical column is fixed with longitudinal beam, longitudinal beam is fixedly connected with vertical longitudinal bracing plate by bolt assembly, load-bearing frame bracing plate is inserted and fixed with transverse profiling groove plate.This frame uses profiling support to support wing plate material, and only one side of wing plate material is installed and connected with limiting support, so that wing plate material is conveniently loaded and set in transport frame, and wing plate material can be effectively protected during transportation.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft component transport frames, and more specifically to a transport frame for assembled panels for aircraft wings. Background Technology

[0002] General aviation aircraft refers to all aircraft used for civil aviation activities other than scheduled passenger and cargo transport aircraft. Their operational scope covers industrial, agricultural, forestry, fishery, and construction operations, as well as non-public transport missions such as medical and health services, disaster relief, meteorological observation, marine monitoring, education and training, cultural and sports activities, and tourism. Existing general aviation aircraft have many components, and the production and assembly bases for these components are not located in the same place. Therefore, appropriate transport racks need to be designed for their transportation. For example, the upper part of a general aviation aircraft consists of two sets of wing panels, or already assembled wings. If conventional foam wooden frames are used for packaging, firstly, positioning and packaging are cumbersome, and secondly, the strength of the wooden frames is not very high, leading to breakage of wooden strips and damage to the frame during transportation. The wing panels are made of composite materials, which have high hardness but relatively low toughness. If the wooden frame is damaged, the wing panels are easily damaged as well. Therefore, an auxiliary transport fixture needs to be designed to facilitate wing positioning and installation while effectively providing protection. Utility Model Content

[0003] The purpose of this utility model is to address the shortcomings of existing technologies by providing a transport frame for assembled wing panels. It utilizes contoured supports to support the wing panels, and simultaneously uses limiting brackets to install and connect to one side of the wing panels, facilitating the loading and placement of the wing panels onto the transport frame. The transport frame can effectively protect the wing panels during transportation.

[0004] A transport frame for assembly panels for aircraft wings includes a rectangular bottom beam frame. The bottom beam frame consists of two sets of front and rear distributed transverse bottom beams and longitudinal bottom beams inserted and fixed between the transverse bottom beams. Several transversely distributed load-bearing supports are fixedly connected to the lower end face of the bottom beam frame. The load-bearing supports include longitudinal support beams. Several sets of longitudinally distributed load-bearing frames are arranged on the left side of the bottom beam frame. The load-bearing frames include left and right sets of brackets. Each bracket includes a left column fixedly connected to the support beam and the transverse bottom beam. A longitudinal support beam is fixedly connected to the upper end of the left column. A vertical longitudinal support plate is fixedly connected to the longitudinal support beam by bolt assembly. A transverse contoured groove plate is inserted and fixedly connected to the support plate of the load-bearing frame. The contoured groove plate includes a semi-wing-shaped glass fiber support groove plate. A foam buffer layer is fixedly connected to the inner surface of the glass fiber support groove plate.

[0005] A vertical support frame is fixed to the right side of the bottom beam frame. The support frame includes two right columns fixed to the horizontal bottom beam. Two sets of support beams are fixed to the upper part of the right columns, distributed vertically. Several sets of limiting brackets opposite to the contoured groove plate are fixed to the support beams. The limiting brackets include a fixing plate located on the upper side of the support beam and arranged vertically. The fixing plate has a longitudinal limiting slot formed therein. A limiting pin is inserted into the limiting slot, and the lower end of the limiting pin abuts against the support beam. Connecting columns are fixed to the front and rear ends of the fixing plate, and the lower ends of the connecting columns are fixed to the support beam.

[0006] Preferably, two sets of contoured groove plates are provided above the bottom beam frame, and the two sets of contoured groove plates are arranged in opposite directions;

[0007] The support frame is provided in two sets, and the limiting brackets on the upright frame are provided in four sets.

[0008] Preferably, the left and right wings of the aircraft are respectively placed in the two sets of contoured groove plates of the bottom beam frame. The side of the wing connected to the fuselage is provided with connecting lugs. The connecting lugs are inserted between the fixed plate and the support beam, and the limiting pin is inserted and fixed on the connecting lugs.

[0009] Preferably, the connecting posts on the front and rear sides of the fixing plate are studs, with nuts screwed onto the upper part of the studs, and the fixing plate is disposed between the nuts; the connecting lugs on the wing are clamped and fixed between the fixing plate and the support beam.

[0010] Preferably, the limiting pin is a cylindrical pin, and the diameter of the limiting pin is equal to the groove width of the upper limiting slot on the fixed plate.

[0011] Preferably, the limiting bracket on the upright is positioned above the contour groove plate.

[0012] The beneficial effects of this utility model are as follows:

[0013] This frame utilizes contoured supports to support the wing panels, while a limiting bracket is used to connect and install the wing panels on one side, facilitating the loading of the wing panels onto the transport frame. The transport frame effectively protects the wing panels during transportation. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 2 This is a front view schematic diagram of the loader wing of this utility model;

[0016] Figure 3 This is a schematic diagram of the internal contour groove plate of this utility model.

[0017] In the diagram: 1. Bottom beam frame; 11. Horizontal bottom beam; 12. Longitudinal bottom beam; 2. Bearing bracket; 21. Support beam; 22. Support leg; 3. Bearing frame; 31. Left column; 32. Longitudinal support beam; 33. Support plate; 4. Upright frame; 41. Right column; 42. Support beam; 5. Contour groove plate; 51. Fiberglass support groove plate; 52. Foam buffer layer; 6. Limiting bracket; 61. Fixing plate; 62. Fiberglass support groove plate; 63. Limiting pin; 7. Reinforcing plate; 8. Wing; 81. Connecting lug. Detailed Implementation

[0018] Example: See Figures 1 to 3 As shown, a transport frame for assembly panels for aircraft wings includes a rectangular bottom beam frame 1. The bottom beam frame 1 consists of two sets of front and rear distributed transverse bottom beams 11 and longitudinal bottom beams 12 inserted and fixed between the transverse bottom beams 11. Several transversely distributed load-bearing supports 2 are fixedly connected to the lower end face of the bottom beam frame 1. The load-bearing supports 2 include longitudinal support beams 21. Several sets of longitudinally distributed load-bearing frames 3 are provided on the left side of the bottom beam frame 1. The load-bearing frames 3 include left and right sets of brackets. The brackets include a left column 31 fixedly connected to the support beams 21 and the transverse bottom beams 11. A longitudinal support beam 32 is fixedly connected to the upper end of the left column 31. A vertical longitudinal support plate 33 is fixedly connected to the longitudinal support beam 32 by bolt assembly. A transverse contoured groove plate 5 is inserted and fixedly connected to the support plate 33 of the load-bearing frame 3. The contoured groove plate 5 includes a glass fiber support groove plate 51 in the shape of a semi-wing. A foam buffer layer 52 is fixedly connected to the inner surface of the glass fiber support groove plate 51.

[0019] A vertical support frame 4 is fixed to the right side of the bottom beam frame 1. The support frame 4 includes two right columns 41 fixed to the horizontal bottom beam 11. Two sets of vertically distributed support beams 42 are fixed to the upper part of the right columns 41. Several sets of limiting brackets 6 opposite to the contoured groove plate 5 are fixed to the support beams 42. The limiting brackets 6 include a fixing plate 61 located on the upper side of the support beam 42 and in a longitudinal direction. A longitudinal limiting slot 611 is formed on the fixing plate 61. A limiting pin 63 is inserted into the limiting slot 611. The lower end of the limiting pin 63 abuts against the support beam 42. Connecting columns 62 are fixed to the front and rear ends of the fixing plate 61, respectively. The lower end of the connecting column 62 is fixed to the support beam 42. The bottom beam frame 1, the load-bearing bracket 2, the load-bearing frame 3, and the support frame 4 are all made of steel.

[0020] Two sets of contoured groove plates 5 are provided above the bottom beam frame 1, and the two sets of contoured groove plates 5 are arranged in opposite directions; for example Figure 1 As shown, its contoured groove plate 5 consists of a first arc plate with a small radius and a second arc plate with a large radius, as well as a bottom transition plate connecting the two. Figure 1The first arc with a small radius on both sets of contouring plates 5 is set on the inner side, that is, the direction of the contouring plates 5 is set in opposite directions. This is mainly because the wings on both sides of the fuselage are symmetrical and opposite, so the contouring plates 5 need to be set according to the two sets of wings; the support plate 33 has a contouring slot 331 formed on it that is opposite to the contouring plate 5.

[0021] The support frame 3 has two sets, and the limiting bracket 6 on the upright frame 4 has four sets.

[0022] The two sets of contoured groove plates 5 of the bottom beam frame 1 respectively house the left and right wings 8 of the aircraft. The side of the wing 8 connected to the fuselage is provided with connecting lugs 81. The connecting lugs 81 are inserted between the fixed plate 61 and the support beam 42. The limiting pin 63 is inserted and fixed on the connecting lugs 81. The left and right movement of the wing 8 is restricted by the limiting bracket 6.

[0023] The connecting posts 62 on the front and rear sides of the fixing plate 61 are studs, and nuts are screwed onto the upper part of the studs. The fixing plate 61 is set between the nuts. The connecting lugs 81 on the wing 8 are clamped and fixed between the fixing plate 61 and the support beam 42.

[0024] The limiting pin 63 is a cylindrical pin, and the diameter of the limiting pin 63 is equal to the groove width of the upper limiting slot 611 of the fixing plate 61.

[0025] The limiting bracket 6 on the upright frame 4 is positioned above the contoured groove plate 5.

[0026] L-shaped supports 22 are fixed to the front and rear side walls of the support beam 21, respectively. The supports 22 have mounting holes 221 formed on them. The transport frame can be installed on the corresponding transport platform by bolts passing through the mounting holes 221 of the supports 22. At the same time, in order to improve the strength of the transport frame, several reinforcing plates 7 that are fixed to the bearing bracket 2 are fixed to the front and rear of the bottom beam frame 1, respectively.

[0027] Working principle: This structure is a transport frame for assembled panel components used in aircraft wings. The structure of its transport frame is as follows: Figure 1 As shown, the wing panels, including the assembled wing, such as... Figure 2 As shown, the wing 8 is installed on the transport frame. Based on the contoured groove plate 5, the wing 8 can be quickly positioned on the transport frame and then connected to the wing 8 through the limiting bracket 6, thus completing the installation connection of the wing 8. The transport frame can suspend the wing 8 inside it. The transport frame itself has high strength and can effectively protect the wing 8.

[0028] The embodiments described herein are illustrative and not intended to limit the scope of the invention. Any person skilled in the art can modify the embodiments without departing from the spirit and scope of the invention; therefore, the scope of protection of the invention should be as set forth in the claims.

Claims

1. A transport frame for assembled panels for aircraft wings, comprising a rectangular bottom beam frame (1), the bottom beam frame (1) consisting of two sets of front and rear distributed transverse bottom beams (11) and longitudinal bottom beams (12) inserted and fixed between the transverse bottom beams (11), and a plurality of transversely distributed load-bearing supports (2) fixedly connected to the lower end surface of the bottom beam frame (1), the load-bearing supports (2) comprising longitudinal support beams (21), characterized in that: On the left side of the bottom beam frame (1), there are several sets of longitudinally distributed support frames (3). The support frame (3) includes two sets of brackets, left and right. The bracket includes a left column (31) fixed to the support beam (21) and the horizontal bottom beam (11). The upper end of the left column (31) is fixed to a longitudinal support beam (32). The longitudinal support beam (32) is fixedly connected to a vertical longitudinal support plate (33) by bolt assembly. A transverse contoured groove plate (5) is inserted and fixedly connected to the support plate (33) of the support frame (3). The contoured groove plate (5) includes a glass fiber support groove plate (51) in the shape of a semi-wing. A foam buffer layer (52) is fixedly connected to the inner surface of the glass fiber support groove plate (51). A vertical support frame (4) is fixed to the right side of the bottom beam frame (1). The support frame (4) includes two right columns (41) fixed to the horizontal bottom beam (11). Two sets of support beams (42) are fixed to the upper part of the right columns (41) and are distributed vertically. Several sets of limiting brackets (6) opposite to the contoured groove plate (5) are fixed to the support beams (42). The limiting brackets (6) include a fixing plate (61) located on the upper side of the support beam (42) and is vertical. A vertical limiting slot (611) is formed on the fixing plate (61). A limiting pin (63) is inserted into the limiting slot (611). The lower end of the limiting pin (63) abuts against the support beam (42). Connecting columns (62) are fixed to the front and rear ends of the fixing plate (61). The lower end of the connecting column (62) is fixed to the support beam (42).

2. The transport frame for assembled panel components for aircraft wings according to claim 1, characterized in that: The bottom beam frame (1) is provided with two sets of contoured groove plates (5) above it, and the two sets of contoured groove plates (5) are set in opposite directions; The support frame (3) is provided in two sets, and the limiting bracket (6) on the upright frame (4) is provided in four sets.

3. A transport frame for panelized components of an aircraft wing as defined in claim 1, wherein: The two sets of contoured groove plates (5) of the bottom beam frame (1) respectively house the left and right wings (8) of the aircraft. The side of the wing (8) connected to the fuselage is provided with connecting lugs (81). The connecting lugs (81) are inserted between the fixing plate (61) and the support beam (42), and the limiting pin (63) is inserted and fixed on the connecting lugs (81).

4. A transport frame for panelized components of an aircraft wing as defined in claim 3, wherein: The connecting posts (62) on the front and rear sides of the fixing plate (61) are studs, and nuts are screwed onto the upper part of the studs. The fixing plate (61) is set between the nuts. The connecting lugs (81) on the wing (8) are clamped and fixed between the fixing plate (61) and the support beam (42).

5. The transport frame for assembled panel components for an aircraft wing according to claim 3, characterized in that: The limiting pin (63) is a cylindrical pin, and the diameter of the limiting pin (63) is equal to the groove width of the upper limiting slot (611) on the fixing plate (61).

6. The transport frame for assembled panel components for an aircraft wing according to claim 3, characterized in that: The limiting bracket (6) on the upright (4) is set above the contoured groove plate (5).

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