Method for dismounting an aircraft skin

Abstract

The application discloses a kind of dismounting methods of aircraft skin, including cutting old aircraft skin;Old aircraft skin is connected with skin lifting appliance;Old aircraft skin is transferred to material placement area;According to the connecting hole size of connecting seat on skin lifting appliance, corresponding lifting hole is drilled on new aircraft skin;New aircraft skin is connected with the connecting seat on skin lifting appliance;New aircraft skin is lifted to the old aircraft skin cutting position on aircraft fuselage;Mark the processing position that needs to be trimmed, punched on new aircraft skin;New aircraft skin is lifted to material processing area, skin storage rack is placed in material processing area, and new aircraft skin is supported on skin storage rack;Adjust the angle of aircraft skin supported by skin support, process new aircraft skin;The application can replace manpower with machinery to lift and store aircraft skin, facilitate staff to transfer, process and install aircraft skin, reduce labor intensity, improve work efficiency and safety.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft maintenance, in particular to a dismounting method of aircraft skin. BACKGROUND

[0002] When the aircraft maintenance personnel replace the aircraft skin, they need to dismount the skin for trimming and drilling and other processing operations, and need to dismount and install several times on the aircraft body for comparison and shaping. After the processing work is completed, the aircraft skin is installed on the aircraft. The existing dismounting method of the engine has high labor intensity, low efficiency, and high risk of scratching the aircraft skin. The specific steps are as follows:

[0003] S1. The worker gets on the scaffold platform 1;

[0004] S2. After the old aircraft skin 2 is separated from the aircraft body after cutting and pulling out the nails, the old aircraft skin is manually moved from the scaffold platform to the ground;

[0005] S3. After the new aircraft skin is manually moved from the ground to the scaffold platform, the new aircraft skin is covered on the aircraft body, and the positions needing drilling and trimming are marked on the new skin with a marker pen;

[0006] S4. The new aircraft skin is manually moved from the scaffold platform to the ground workbench 3;

[0007] S5. Some construction workers need to crouch to drill the skin upward, and other construction workers need to trim and assemble the reinforcing rib around the skin for processing;

[0008] S6. After the new aircraft skin is manually moved from the ground workbench to the scaffold platform, it is manually covered on the aircraft body, and then rivets are installed. SUMMARY

[0009] The technical problem to be solved by the present application is to provide a dismounting method of aircraft skin, which optimizes the process flow, thereby reducing the labor intensity and the risk of scratching the skin during moving, and improving the work efficiency.

[0010] To solve the above technical problems, the present application adopts the following technical solutions:

[0011] A dismounting method of aircraft skin, comprising the following steps:

[0012] S1. The worker cuts the old aircraft skin that needs to be replaced;

[0013] S2. After cutting, the rivets on the old aircraft skin are pulled out, and the old aircraft skin is separated from the aircraft body;

[0014] S3, use the crane to hoist the skin hoist to above the old aircraft skin, and connect the old aircraft skin with the skin hoist;

[0015] S4, the crane rises, drives the skin hoist to hoist the old aircraft skin, the skin hoist includes a lifting rod, and a plurality of lifting rings and a plurality of lifting point units sleeved on the lifting rod, the lifting ring is connected with the crane lifting belt, the lifting point unit includes a lifting point ring, a lifting belt, a tension meter and a connecting seat connected in turn from top to bottom, the old aircraft skin is connected with the connecting seat on the skin hoist by using the rivet hole on the old aircraft skin and the screw rod;

[0016] S5, the old aircraft skin is transferred to the material placing area, and the old aircraft skin is disconnected from the skin hoist and unloaded on the ground in the material placing area;

[0017] S6, according to the size of the connecting hole of the connecting seat on the skin hoist, a corresponding lifting hole is drilled on the new aircraft skin;

[0018] S7, the new aircraft skin is connected with the connecting seat on the skin hoist by using the lifting hole on the new aircraft skin and the screw rod;

[0019] S8, the new aircraft skin is hoisted to the old aircraft skin cutting position on the aircraft fuselage;

[0020] S9, the new aircraft skin is covered on the aircraft fuselage, the new aircraft skin is disconnected from the skin hoist, and the processing position of the new aircraft skin that needs to be trimmed and punched is marked;

[0021] S10, the new aircraft skin is connected with the connecting seat on the skin hoist again, the new aircraft skin is hoisted to the material processing area, the skin storage rack is placed in the material processing area, the skin storage rack includes a storage rack base and a skin support arranged on the storage rack base, a support rod assembly is arranged on the top of the storage rack base and can be adjusted in angle, the support rod assembly is connected with the back side of the skin support, the skin support is supported on the storage rack base through the support rod assembly, and the new aircraft skin is disconnected from the skin hoist and supported on the skin support;

[0022] S11, the support angle of the skin support for the aircraft skin is adjusted by rotating the support rod assembly, so that the new aircraft skin is processed, and the processing items include drilling, shaping and installing reinforcing ribs;

[0023] S12, after the processing items are completed, the new aircraft skin is connected with the skin hoist again and hoisted to the old aircraft skin cutting position on the aircraft fuselage;

[0024] S13, the new aircraft skin is disconnected from the skin hoist, covered on the aircraft fuselage, and fixed by installing rivets, and the installation of the new aircraft skin is completed.

[0025] On the basis of the above technical solutions, the application can be improved as follows:

[0026] Further, in step S3, the sling is provided with an adjusting buckle for adjusting the length of the sling, and the suspender is further provided with a limiting block for limiting the moving position of the upper sling ring and the suspension point unit.

[0027] Further, the upper sling ring comprises a sling ring frame, an inner sling ring, an outer sling ring and a connecting screw rod, the inner sling ring is sleeved on the suspender, the outer sling ring is used for being connected with the sling of the crane, the inner sling ring is located in the sling ring frame, the connecting screw rod passes through the sling ring frame and the inner sling ring, the inner sling ring is installed on the sling ring frame, and the outer sling ring is installed at the top end of the sling ring frame.

[0028] Further, the connecting seat comprises a connecting rod and a U-shaped seat fixedly connected with the connecting rod, a connecting hole is formed in the bottom surface of the U-shaped seat, and a screw rod is installed through the connecting hole to connect the aircraft skin.

[0029] Further, in step S10, the supporting rod assembly comprises a long supporting rod and a short supporting rod hingedly connected at the top of the storage rack base, and a connecting rod fixedly arranged at the back side of the skin bracket, the upper end of the connecting rod is hingedly connected with the free end of the long supporting rod through a first rotating shaft, the lower end of the connecting rod is hingedly connected with the free end of the short supporting rod through a second rotating shaft, and a rotatable connecting rod mechanism is formed; wherein the length of the long supporting rod is smaller than that of the short supporting rod, and the length of the connecting rod is smaller than that of the long supporting rod and the short supporting rod; a telescopic push rod is connected between the short supporting rod and the storage rack base, the fixed end of the push rod is hingedly connected with the top of the storage rack base, and the extending end of the push rod is hingedly connected on the short supporting rod.

[0030] Further, the skin bracket comprises three horizontal rods parallel to the length direction of the storage rack base, and a plurality of arc-shaped rods connected between the horizontal rods, and the horizontal rods and the arc-shaped rods are arranged in a crisscross manner to form a hollow arc-shaped frame structure.

[0031] Further, the horizontal rod located at the bottom side of the skin bracket is in abutting cooperation with the bottom edge of the aircraft skin, the horizontal rod is provided with a plurality of bayonets, the bottom end of the arc-shaped rod is provided with a plurality of pin holes matched with the bayonets, the bayonets are inserted into the pin holes to fix the arc-shaped rod and the horizontal rod, and the pin holes are provided with two groups of bayonets with different heights.

[0032] Further, the upper part and the lower part of each arc-shaped rod are provided with self-locking joints, the self-locking joint is composed of two mutually hinged sleeves, a ratchet wheel is arranged in the hinge part of the sleeve, and the arc-shaped rod is inserted into the sleeve.

[0033] Further, an upwardly inclined limiting rod is further arranged at the top of the storage rack base, the limiting rod is located at one side of the long supporting rod and opposite to the arc-shaped rod, and a supporting clamp corresponding to the cross-sectional profile of the arc-shaped rod is arranged at the top of the limiting rod.

[0034] Further, a universal wheel is installed at the right angle of the bottom of the storage rack base.

[0035] Compared with the prior art, the present application has the following advantages:

[0036] (1) In the aircraft skin dismounting method of the present application, the aircraft skin is hoisted and stored by using the skin hoist and the skin storage rack, so that the work personnel can transfer, process and install the aircraft skin, reduce labor intensity, and improve work efficiency and safety;

[0037] (2) In the present application, the relative positions between the hoisting points can be adjusted according to the actual situation by using the aircraft skin hoist, which is suitable for hoisting work of different parts of various models and skins of different models, and has good practicability;

[0038] (3) In the present application, the aircraft skin storage state can be adjusted in a rotating manner according to the actual situation by using the aircraft storage rack, so that the aircraft skin can be stored and processed at different angles, which is convenient for the work personnel to work, and the original standing, kneeling and squatting operation is changed to the present standing and sitting operation, which greatly improves the comfort and efficiency of the operation. BRIEF DESCRIPTION OF DRAWINGS

[0039] The present application will be further described in detail below in combination with the drawings and specific embodiments

[0040] Figure 1 is a schematic diagram of the existing aircraft skin dismounting method;

[0041] Figure 2 is a schematic diagram of the existing aircraft skin processing method;

[0042] Figure 3 is a use state diagram of the aircraft skin hoist of the present application;

[0043] Figure 4 is a front view of the use state of the aircraft skin hoist of the present application;

[0044] Figure 5 is Figure 4 is a partial enlarged view of A;

[0045] Figure 6 is a structural schematic diagram of the upper hoisting ring in the aircraft skin hoist of the present application;

[0046] Figure 7 is a perspective view of the connecting seat in the aircraft skin hoist of the present application;

[0047] Figure 8 is a top view of the connecting seat in the aircraft skin hoist of the present application;

[0048] Figure 9The structure schematic view of the aircraft skin storage rack of the present application;

[0049] Figure 10 The structure schematic view of the aircraft skin storage rack of the present application; Figure 9 The local enlarged view of B in the above figure;

[0050] Figure 11 The structure schematic view of the connecting structure of the cross bar and the arc-shaped bar on the bottom side of the skin rack of the present application.

[0051] The marks on the drawings: 1-scaffold platform, 2-aircraft skin, 3-ground workbench, 101-derrick, 102-hoisting point ring, 103-upper hoisting belt ring, 103a-hoisting belt ring frame, 103b-inner hoisting belt ring, 103c-outer hoisting belt ring, 103d-connecting screw rod, 104-hoisting belt, 105-adjusting buckle, 106-tension meter, 107-connecting seat, 107a-connecting rod, 107b-U-shaped seat, 107c-connecting hole, 108-limiting block, 201-storage rack base, 202-skin rack, 202a-cross bar, 202b-arc-shaped bar, 203-long support rod, 204-short support rod, 205-connecting rod, 206-first rotating shaft, 207-second rotating shaft, 208-push rod, 209-pin hole, 210-latch, 211-self-locking joint, 212-limiting rod, 213-castor. DETAILED DESCRIPTION

[0052] The specific embodiments of the present application are further described below in conjunction with the drawings, and the description of the embodiments is used to help understand the present application, but does not constitute a limitation of the present application. In addition, the technical features involved in the various embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0053] Referring to Figures 3 to 11 , the present application relates to a dismounting method of an aircraft skin, comprising the following steps:

[0054] S1, the worker gets on the scaffold platform and cuts the old aircraft skin which needs to be replaced;

[0055] S2, after cutting, the rivets on the old aircraft skin are pulled out, and the old aircraft skin is separated from the aircraft body;

[0056] S3, the skin hoist is hoisted to above the old aircraft skin by using the crane, and the old aircraft skin is connected with the skin hoist;

[0057] S4, the crane is lifted, drive the skin hoist to lift the old aircraft skin, the skin hoist includes a boom 101, and a plurality of upper lifting rings 103 and a plurality of lifting point units are sleeved on the boom 101, the upper lifting ring 103 is connected with the crane lifting belt 104, the lifting point unit includes a lifting point ring 102, a lifting belt 104, a tension meter 106 and a connecting seat 107 connected in turn from top to bottom, the old aircraft skin is connected with the connecting seat 107 on the skin hoist by using the rivet hole on the old aircraft skin and the screw rod;

[0058] S5, the old aircraft skin is transferred to the material placing area, and the old aircraft skin is disconnected from the skin hoist and unloaded on the ground in the material placing area;

[0059] S6, according to the size of the connecting hole 107c of the connecting seat 107 on the skin hoist, a corresponding lifting hole is drilled on the new aircraft skin;

[0060] S7, the new aircraft skin is connected with the connecting seat 107 on the skin hoist by using the lifting hole on the new aircraft skin and the screw rod;

[0061] S8, the new aircraft skin is hoisted to the old aircraft skin cutting position on the aircraft fuselage;

[0062] S9, the new aircraft skin is covered on the aircraft fuselage, the new aircraft skin is disconnected from the skin hoist, and the processing position of the new aircraft skin which needs to be trimmed and punched is marked;

[0063] S10, the new aircraft skin is connected with the connecting seat 107 on the skin hoist again, and the new aircraft skin is hoisted to the material processing area, the skin storage rack is placed in the material processing area, the skin storage rack includes a storage rack base 201 and a skin cradle 202 arranged on the storage rack base 201, a support rod assembly which can be adjusted in angle by rotating up and down is arranged on the top of the storage rack base 201, the support rod assembly is connected with the back side of the skin cradle 202, the skin cradle 202 is supported on the storage rack base 201 through the support rod assembly, and the new aircraft skin is disconnected from the skin hoist and supported on the skin cradle 202;

[0064] S11, the support angle of the skin cradle 202 for the aircraft skin is adjusted by rotating the support rod assembly, so that the new aircraft skin is processed, and the processing items include drilling, shaping and installing reinforcing ribs;

[0065] S12, after the processing items in S11 are completed, the new aircraft skin is connected with the skin hoist again and hoisted to the old aircraft skin cutting position on the aircraft fuselage;

[0066] S13, the new aircraft skin is disconnected from the skin hoist, covered on the aircraft fuselage, installed with rivets for fixation, and the installation work of the new aircraft skin is completed.

[0067] The aircraft skin dismounting method of the present application uses the skin lifting device and the skin storage rack to mechanically instead of manually lift and store the aircraft skin, which facilitates the work staff to transfer, process and install the aircraft skin, reduces labor intensity, and improves work efficiency and safety.

[0068] In step S3, the tension meter 106 is used to monitor the force of each lifting point in real time; the lifting belt 104 is provided with an adjusting buckle 105 for adjusting the length of the lifting belt 104; and the lifting rod 101 is further provided with a limiting block 111 for limiting the movement of the upper lifting belt ring 103 and the lifting point unit.

[0069] In the embodiment, the upper lifting belt ring 103 includes a lifting belt ring frame 103a, an inner lifting belt ring 103b, an outer lifting belt ring 103c and a connecting screw rod 103d, the inner lifting belt ring 103b is sleeved on the lifting rod 101, the outer lifting belt ring 103c is used to be connected with the crane lifting belt 104, the lifting belt ring frame 103a is a square frame, the inner lifting belt ring 103b is a circular ring, the inner lifting belt ring 103b is located in the lifting belt ring frame 103a, the connecting screw rod 103d passes through the lifting belt ring frame 103a and the inner lifting belt ring 103b, and the inner lifting belt ring 103b is installed on the lifting belt ring frame 103a, the outer lifting belt ring 103c is a triangle, and the outer lifting belt ring 103c is installed at the top end of the lifting belt ring frame 103a, when the tension direction changes during the lifting of the skin lifting device, the inner lifting belt ring 103b can change the corresponding angle with the force.

[0070] In the embodiment, the connecting seat 107 includes a connecting rod 107a and a U-shaped seat 107b fixedly connected with the connecting rod 107a, three connecting holes 107c are formed in the bottom surface of the U-shaped seat 107b, a screw rod is installed through the connecting holes 107c to connect the aircraft skin, and the three connecting holes 107c can ensure that the connecting seat 107 is stably connected with the aircraft skin.

[0071] In step S10, the support rod assembly includes a long support rod 203 and a short support rod 204 hinged at the top of the storage rack base 201, and a connecting rod 205 fixedly arranged at the back side of the skin bracket 202, the upper end of the connecting rod 205 is hinged with the free end of the long support rod 203 through a first rotating shaft 206, and the lower end of the connecting rod 205 is hinged with the free end of the short support rod 204 through a second rotating shaft 207, forming a rotatable connecting rod mechanism; wherein the length of the long support rod 203 is less than the length of the short support rod 204, and the length of the connecting rod 205 is less than the length of the long support rod 203 and the short support rod 204; the short support rod 204 is a driving rod, and a telescopic push rod 208 is connected between the short support rod 204 and the storage rack base 201, the fixed end of the push rod 208 is hinged with the top of the storage rack base 201, and the extending end of the push rod 208 is hinged on the short support rod 204; the push rod 208 is an existing manual telescopic rod, which has a hand wheel for adjusting the telescopic length, by rotating the hand wheel, the manual telescopic rod is telescoped to drive the short support rod 204 to rotate, and the connecting rod 205 is driven to rotate around the first rotating shaft 206 to change the supporting angle of the skin bracket 202 to the aircraft skin.

[0072] When the connecting rod 205 is rotated to be parallel to the storage rack base 201, the skin bracket 202 can support the aircraft skin to be laid down; when the connecting rod 205 is rotated to be perpendicular to the storage rack base 201, the skin bracket 202 can support the aircraft skin to be stored vertically, and in the vertical storage state, the workers can process the aircraft skin at the front and rear parts at the same time, such as punching, trimming and other processing, which changes the original standing, kneeling and squatting operation to the present standing and sitting operation, and improves the operation efficiency.

[0073] In the embodiment, the skin bracket 202 includes three horizontal rods 202a parallel to the length direction of the storage rack base 201, and a plurality of arc-shaped rods 202b connected between the horizontal rods 202a, the horizontal rods 202a and the arc-shaped rods 202b are arranged in a crisscross manner to form a hollow arc-shaped frame structure, so as to facilitate the workers to pass through the skin bracket 202 to process the aircraft skin and reduce the obstruction.

[0074] When the skin bracket 202 stores the aircraft skin in an inclined or vertical manner, the horizontal rod 202a located at the bottom side of the skin bracket 202 is in abutting cooperation with the bottom edge of the aircraft skin, the horizontal rod 202a is inserted with a bolt 210, the bottom end of the arc-shaped rod 202b is provided with a pin hole 209 matched with the bolt 210, the bolt 210 is inserted into the pin hole 209 to fix the arc-shaped rod 202b and the horizontal rod 202a; the pin hole 209 is provided with two groups of different heights, according to actual needs, the bolt 210 is correspondingly inserted into the pin hole 209 of the corresponding height to change the width of the skin bracket 202, and adapt to the storage needs of aircraft skins of different specifications.

[0075] The upper part and the lower part of each arc-shaped rod 202b in the embodiment are provided with self-locking joints 211, the degree of opening and closing of the self-locking joints 211 is adjusted to adjust the arc of the arc-shaped rod 202b, so that the arc of the whole skin bracket 202 is adjusted to meet the storage requirements of different aircraft skins; the self-locking joint 211 is composed of two mutually hinged sleeves, a ratchet (not shown in the figure) is arranged in the hinge of the sleeve, and the arc-shaped rod 202b is inserted into the sleeve.

[0076] In the embodiment, an upwardly inclined limiting rod 212 is further arranged on the top of the storage rack base 201, the limiting rod 212 is located on one side of the long supporting rod 203 and opposite to the arc-shaped rod 202b, and a supporting clamp corresponding to the cross-sectional profile of the arc-shaped rod 202b is arranged on the top of the limiting rod 212; when the skin bracket 202 is rotated to the upside-down storage of the aircraft skin, the supporting clamp on the top of the limiting rod 212 cooperates with the arc-shaped rod 202b, the limiting rod 212 can support the skin bracket 202 upward to limit the rotation of the skin bracket 202, prevent the aircraft skin from sliding due to the too large rotation angle, increase the supporting strength and improve the stability, and the rotation angle of the skin bracket 202 is 0°-90°.

[0077] In the embodiment, universal wheels 213 are installed at the right angles of the bottom of the storage rack base 201, so that the aircraft skin storage rack is moved by the staff to transfer and carry the aircraft skin, and the loading and unloading operation of the aircraft skin during the transfer is reduced.

[0078] The above embodiments of the application are not a limitation on the protection scope of the application, the embodiments of the application are not limited to this, and any other forms of modification, replacement or change of the above structure of the application according to the above content of the application, the ordinary technical knowledge and common means in the art, without departing from the above basic technical idea of the application, should fall within the protection scope of the application.

Claims

1. A method of disassembling an aircraft skin, characterized in that, The method comprises the following steps: S1, a worker cuts the old aircraft skin that needs to be replaced; S2, after cutting, the rivets on the old aircraft skin are pulled out, and the old aircraft skin is separated from the aircraft body; S3, a crane is used to hoist a skin hoist to above the old aircraft skin, and the old aircraft skin is connected with the skin hoist; S4, the crane is raised to hoist the old aircraft skin with the skin hoist, the skin hoist comprises a hoisting rod and a plurality of hoisting rings and a plurality of hoisting point units sleeved on the hoisting rod, the hoisting rings are connected with the crane hoisting belt, the hoisting point units comprise a hoisting point ring, a hoisting belt, a tension gauge and a connecting seat connected in sequence from top to bottom, the rivet holes on the old aircraft skin are used to connect the old aircraft skin with the connecting seat on the skin hoist by means of a screw rod; S5, the old aircraft skin is transferred to a material placing area, the old aircraft skin is disconnected from the skin hoist, and is unloaded on the ground in the material placing area; S6, according to the size of the connecting hole of the connecting seat on the skin hoist, a corresponding hoisting hole is drilled on the new aircraft skin; S7, the hoisting hole on the new aircraft skin is used to connect the new aircraft skin with the connecting seat on the skin hoist by means of a screw rod; S8, the new aircraft skin is hoisted to the position where the old aircraft skin is cut on the aircraft body; S9, the new aircraft skin is covered on the aircraft body, the new aircraft skin is disconnected from the skin hoist, and the processing position that needs to be trimmed and punched is marked on the new aircraft skin; S10, the new aircraft skin is connected with the connecting seat on the skin hoist again by means of a screw rod, the new aircraft skin is hoisted to a material processing area, a skin storage rack is placed in the material processing area, the skin storage rack comprises a storage rack base and a skin support arranged on the storage rack base, a support rod assembly that can be adjusted in an up-down direction to adjust the supporting angle is arranged on the top of the storage rack base, the support rod assembly is connected with the back side of the skin support, the skin support is supported on the storage rack base through the support rod assembly, the new aircraft skin is disconnected from the skin hoist and is supported on the skin support; S11, the supporting angle of the skin support for the aircraft skin is adjusted by rotating the support rod assembly, so that the new aircraft skin is processed, and the processing items include drilling, shaping and installing reinforcing ribs; S12, after the processing items in step S11 are completed, the new aircraft skin is connected with the skin hoist again and is hoisted to the position where the old aircraft skin is cut on the aircraft body; S13, the new aircraft skin is disconnected from the skin hoist, is covered on the aircraft body, and is fixed by installing rivets, and the installation of the new aircraft skin is completed.

2. The method of claim 1, wherein, In step S4, the hoisting belt is provided with an adjusting buckle for adjusting the length of the hoisting belt, and the hoisting rod is further provided with a limiting block for limiting the moving position of the hoisting ring and the hoisting point unit.

3. The method of claim 2, wherein, The hoisting ring comprises a hoisting ring frame, an inner hoisting ring, an outer hoisting ring and a connecting screw rod, the inner hoisting ring is sleeved on the hoisting rod, the outer hoisting ring is used to be connected with the crane hoisting belt, the inner hoisting ring is arranged in the hoisting ring frame, the connecting screw rod passes through the hoisting ring frame and the inner hoisting ring, the inner hoisting ring is arranged on the hoisting ring frame, and the outer hoisting ring is arranged at the top end of the hoisting ring frame.

4. The method of claim 3, wherein, The connecting seat comprises a connecting rod and a U-shaped seat fixedly connected with the connecting rod, a connecting hole is formed in the bottom surface of the U-shaped seat, and a screw rod is arranged in the connecting hole to connect the aircraft skin.

5. The method of claim 1, wherein, In step S10, the support rod assembly includes a long support rod and a short support rod hinged on the top of the storage rack base, and a connecting rod fixedly arranged on the back side of the skin bracket, the upper end of the connecting rod is hinged with the free end of the long support rod through a first rotating shaft, and the lower end of the connecting rod is hinged with the free end of the short support rod through a second rotating shaft, forming a rotatable connecting rod mechanism; wherein the length of the long support rod is less than the length of the short support rod, and the length of the connecting rod is less than the length of the long support rod and the short support rod; a telescopic push rod is connected between the short support rod and the storage rack base, the fixed end of the push rod is hinged with the top of the storage rack base, and the extending end of the push rod is hinged on the short support rod.

6. The method of claim 5, wherein, The skin bracket includes three crossbars parallel to the length direction of the storage rack base, and a plurality of arc-shaped rods connected between the crossbars, the crossbars and the arc-shaped rods are arranged in a crisscross manner to form a hollow arc-shaped frame structure.

7. The method of claim 6, wherein, The crossbar located on the bottom side of the skin bracket is in abutting engagement with the bottom edge of the aircraft skin, the crossbar is inserted with a bolt, the bottom end of the arc-shaped rod is provided with a bolt hole matched with the bolt, the bolt is inserted into the bolt hole to fix the arc-shaped rod and the crossbar, and the bolt hole is provided with two groups of different heights.

8. The method of claim 7, wherein, The upper part and the lower part of each arc-shaped rod are provided with self-locking joints, the self-locking joint is composed of two mutually hinged sleeves, a ratchet is arranged in the hinge of the sleeve, and the arc-shaped rod is inserted into the sleeve.

9. The method of claim 8, wherein, An upwardly inclined limiting rod is further arranged on the top of the storage rack base, the limiting rod is located on one side of the long support rod and opposite to the arc-shaped rod, and a supporting clamp corresponding to the cross-sectional profile of the arc-shaped rod is arranged on the top of the limiting rod.

10. The method of claim 6, wherein, A universal wheel is installed at the right angle of the bottom of the storage rack base.

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