A portable aircraft access ladder

Abstract

This utility model provides a portable aircraft maintenance ladder, relating to the field of aircraft maintenance technology. It includes a top fixing mechanism, multiple main columns, and a base. The top fixing mechanism comprises a top body, two fixing hooks, and a bottom connector I. The main columns include a main column body, a footboard, top connector I, and bottom connector II. The base includes top connector II and a base plate. When adjacent main columns are spliced ​​together, the bottom connector II of the upper main column engages with the top connector I of the lower main column; the bottom connector I engages with the top connector I of the uppermost main column; and the top connector II engages with the bottom connector II of the lowermost main column. This utility model solves the problems of limited applicability, difficult installation and storage, and large space occupation of traditional aircraft maintenance ladders, effectively improving the efficiency and safety of engineers during aircraft maintenance.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, and in particular to a portable aircraft maintenance ladder. Background Technology

[0002] As a product of modern industry, airplanes play a vital role in both passenger transport and national defense. However, the high-altitude environment in which aircraft operate necessitates frequent maintenance; otherwise, safety cannot be guaranteed, potentially leading to significant losses. Furthermore, the sheer size of aircraft makes the maintenance of some critical components extremely difficult. Traditional aircraft maintenance ladders often have the following shortcomings: 1. Fixed structure, limited application scenarios: Traditional aircraft maintenance ladders are generally designed based on the aircraft structure. Due to the different shapes of different aircraft, aircraft maintenance ladders often cannot be used interchangeably. This requires a variety of different models of maintenance ladders to complete the maintenance of different aircraft.

[0003] 2. Large size: Traditional aircraft maintenance ladders are generally not foldable or can only be partially folded, which often requires more space and manpower for storage. Their large size also makes transportation more inconvenient.

[0004] 3. Difficult installation and deployment: Traditional aircraft maintenance ladders are too large to be easily installed near aircraft. Utility Model Content

[0005] To address the aforementioned technical problems of traditional aircraft maintenance ladders, such as limited application scenarios, large size, and difficult installation, a portable aircraft maintenance ladder is provided. The technical means employed in this invention are as follows: A portable aircraft maintenance ladder includes a top fixing mechanism, a multi-section main column and a base connected together, wherein the top fixing mechanism is installed and connected to the top of the uppermost main column and the base is installed and connected to the bottom of the lowermost main column. The top fixing mechanism includes a top body, two fixing hooks, and a bottom connector I. The two fixing hooks are respectively connected to the upper sides of the top body and have folding and unfolding functions; the bottom connector I is located at the bottom of the top body. The main column includes a main column body, two pedals, a top connector I, and a bottom connector II. The two pedals are rotatably connected to both sides of the main column body and have folding and unfolding functions. The top connector I and the bottom connector II are respectively located at the top and bottom of the main column body. The base includes a top connector II and a bottom plate. The top connector II is rotatably connected to the upper surface of the bottom plate, and a shock-absorbing pad II is fixedly connected to the bottom surface of the bottom plate. When splicing and connecting two adjacent main columns, the bottom connector II of the upper main column is connected to the top connector I of the lower main column, the bottom connector I is connected to the top connector I of the uppermost main column, and the top connector II is connected to the bottom connector II of the lowermost main column.

[0006] Furthermore, the fixing hook is connected to the top body by bolts. The fixing hook has a hook-shaped structure, and shock-absorbing pads I are provided on the inner and outer surfaces and head of the fixing hook away from the top body.

[0007] Furthermore, the bottom connector I is a protruding structure I provided at the bottom of the top main body, and the top connector I is a groove structure I opened at the top of the main column. The outer wall of the protruding structure I is provided with an external thread I, and the inner wall of the groove structure I is provided with an internal thread I. The external thread I is engaged with the internal thread I of the top connector I of the uppermost main column.

[0008] Furthermore, the bottom connector II is a raised structure II provided at the bottom of the main column body, and the outer wall of the raised structure II is provided with an external thread II, which is engaged with the internal thread I of the top connector I of the adjacent main column.

[0009] Furthermore, the top connector II has a groove structure II on its top, and the inner wall of the groove structure II has an internal thread II, which is engaged with the external thread II of the bottom connector II of the bottom main column.

[0010] Furthermore, the pedal and the main column body are rotatably connected via a hinge seat and hinge shaft I.

[0011] Furthermore, the bottom of the top connector II is rotatably connected to the base plate via hinge shaft II and hinge seat.

[0012] Furthermore, the base plate has a square plate structure with a flat bottom surface.

[0013] Furthermore, one side of the main column body has a vertical plane, and the vertical planes of the main column bodies of the multi-section main columns are located on the same plane.

[0014] Furthermore, a vertical mounting groove is formed on the other side of the main column body opposite to the vertical plane. A support frame is installed in the vertical mounting groove. The support frame includes a first bracket and a second bracket with folding and unfolding functions. The top end of the first bracket is rotatably connected to the top of the vertical mounting groove, and the bottom end is suspended. A shock-absorbing pad III is provided at the bottom end of the first bracket. The top end of the second bracket is connected to the first bracket, and the bottom end is rotatably connected to the bottom of the vertical mounting groove.

[0015] Compared with the prior art, the present invention has the following advantages: 1. The portable aircraft maintenance ladder provided by this utility model has connectors with uniform thread size for the main column, base and top fixing mechanism. The main columns can be connected in any number to obtain the aircraft maintenance ladder of the required height.

[0016] 2. The portable aircraft maintenance ladder provided by this utility model has a top fixing mechanism that can contact the aircraft via a fixing hook and is equipped with shock-absorbing pads. It can be applied to various different aircraft shapes and structures, increasing the reusability of the maintenance ladder.

[0017] 3. The portable aircraft maintenance ladder provided by this utility model has a step connected to the main column via a hinge shaft and a hinge seat, which can be folded or unfolded, reducing the space occupied compared to traditional maintenance ladders.

[0018] 4. The portable aircraft maintenance ladder provided by this utility model has a top connector I and a bottom connector II at the connection between two adjacent main columns. The two main columns can be assembled or disassembled with simple operation, which greatly improves the efficiency of engineers.

[0019] 5. The portable aircraft maintenance ladder provided by this utility model has a top connector II on the base and a bottom plate that are hinged together, which can meet the different tilt angle requirements when the ladder is used.

[0020] Based on the above reasons, this utility model can be widely promoted in fields such as aircraft maintenance. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a schematic diagram of the main column of this utility model; Figure 3 This is a schematic diagram showing the unfolded main column pedal and support frame of this utility model; Figure 4 This is a schematic diagram of the top fixing mechanism of this utility model; Figure 5 This is a structural schematic diagram of the base of this utility model.

[0023] In the diagram: 1. Top fixing mechanism; 2. First main column; 3. Second main column; 4. Third main column; 5. Base; 1.1 Top body; 1.2 Fixing hook; 1.3 Shock-absorbing pad I; 1.4 Bolt; 1.5 Bottom connector I; 1.6 External thread I; 2.1 Main column body; 2.2 Pedal; 2.3 Top connector I; 2.4 Hinge seat; 2.5 Hinge shaft I; 2.6 Bottom connector II; 2.7 First bracket; 2.8 Second bracket; 2.9 Shock-absorbing pad III; 2.10 Internal thread I; 2.11 External thread II; 5.1 Top connector II; 5.2 Hinge shaft II; 5.3 Base plate; 5.4 Internal thread II. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0025] Example 1 Traditional aircraft maintenance ladders are each designed for a specific aircraft type, cannot be folded for storage, occupy a large space, and are difficult to install. Therefore, this invention provides an aircraft maintenance ladder that can be quickly assembled and disassembled, allows folding, and is applicable to multiple aircraft types. This facilitates the storage of maintenance ladders in hangars and streamlines the aircraft maintenance process for engineers.

[0026] This utility model discloses a portable aircraft maintenance ladder, which includes a top fixing mechanism 1, a multi-section main column and a base 5 connected together. The top fixing mechanism 1 is installed and connected to the top of the uppermost main column, and the base 5 is installed and connected to the bottom of the lowermost main column. The top fixing mechanism 1 includes a top body 1.1, two fixing hooks 1.2 and a bottom connector I 1.5. The two fixing hooks 1.2 are respectively connected to the upper two sides of the top body 1.1 and have folding and unfolding functions; the bottom connector I 1.5 is located at the bottom of the top body 1.1. The main column includes a main column body 2.1, two pedals 2.2, a top connector I 2.3, and a bottom connector II 2.6. The two pedals 2.2 are rotatably connected to both sides of the main column body 2.1 and have folding and unfolding functions. The top connector I 2.3 and the bottom connector II 2.6 are respectively located at the top and bottom of the main column body 2.1. The base 5 includes a top connector II 5.1 and a base plate 5.3. The top connector II 5.1 is rotatably connected to the upper surface of the base plate 5.3, and the bottom surface of the base plate 5.3 is fixedly connected to a shock-absorbing pad II. When splicing and connecting two adjacent main columns, the bottom connector II2.6 of the upper main column is connected to the top connector I2.3 of the lower main column, the bottom connector I1.5 is connected to the top connector I2.3 of the uppermost main column, and the top connector II5.1 is connected to the bottom connector II2.6 of the lowermost main column.

[0027] This utility model relates to the field of special aircraft maintenance. It features multiple footboards hinged to a main column. Connectors are located at the top and bottom of the main column, enabling the connection of multiple main column sections, the main column to the base, and the main column to the top fixing mechanism. The hinged connection between the footboards and the main column allows for folding or unfolding. The top fixing mechanism can be hooked to aircraft components via fixing hooks, while the base, in conjunction with shock-absorbing pads, further enhances stability. This utility model solves the problems of existing aircraft maintenance ladders, such as non-adjustable dimensions, inconvenience in storage and transportation (during storage, each main column section can be separated, and the main column, top fixing mechanism, and base can be separated for multi-part storage), and low versatility. It effectively improves the efficiency and safety of engineers during aircraft maintenance.

[0028] This invention is applicable to various types of aircraft, including civil airliners, military fighter jets, and transport aircraft.

[0029] Example 2 This utility model discloses a portable aircraft maintenance ladder, which is a new type of aircraft maintenance ladder that can be flexibly and quickly assembled, used for aircraft maintenance, foldable, and applicable to a variety of aircraft. It solves the problems of traditional aircraft maintenance ladders having a small application range, difficult installation and storage, and large space occupation. It includes: a top fixing mechanism 1, a multi-section main column and a base 5 that are spliced ​​and connected. The top fixing mechanism 1 is installed and connected to the top of the uppermost main column, and the base 5 is installed and connected to the bottom of the lowermost main column.

[0030] In this invention, the multi-section main columns have the same structure, and the ladder length can be freely adjusted by changing the number of main columns. Different numbers of main columns can be assembled according to the aircraft size to obtain the required aircraft maintenance ladder, thus adapting to the maintenance of different aircraft. In this embodiment, as shown... Figure 1 As shown, taking three main pillars as an example, three main pillar sections are drawn, namely the first main pillar 2, the second main pillar 3, and the third main pillar 4. The number of main pillars is variable and is not limited to three sections.

[0031] The top fixing mechanism 1 includes a top body 1.1, two fixing hooks 1.2, and a bottom connector I 1.5. The two fixing hooks 1.2 are respectively connected to the upper two sides of the top body 1.1 and have folding and unfolding functions. The bottom connector I 1.5 is set at the bottom of the top body 1.1. One end of the fixing hook 1.2 is connected to the top body 1.1 by bolts 1.4 and ear plates. An L-shaped groove can be opened on each side of the top body 1.1. The ear plates are welded to the horizontal plane of the L-shaped grooves. The bolts 1.4 pass through the ear plates and fixing hooks 1.2 in sequence and are screwed into the top body 1.1. The fixing hook 1.2 has an approximately U-shaped hook structure. Shock-absorbing pads I 1.3 are provided on the inner and outer surfaces and head of the fixing hook 1.2 on the side away from the top main body 1.1. The shock-absorbing pads I 1.3 are made of existing nitrile rubber composite material. The shock-absorbing pads I 1.3 are used to attach to the load-bearing parts of the aircraft during use. When fixing the shock-absorbing pads I 1.3, both sides of the pads can be folded up, and then the folded parts are fixed to the fixing hook 1.2 with screws. This way, the screws will not contact the aircraft fuselage and will not cause damage to the aircraft fuselage. Additionally, shock-absorbing pads I 1.3 are also provided on the outer surface of the fixing hook 1.2, which can wrap the front side of the fixing hook 1.2 with shock-absorbing pads I 1.3 to prevent scratches to the aircraft fuselage due to improper installation. Figure 3 As shown, the fixing hook 1.2 can be composed of three integrally connected rods, namely the first rod, the second rod, and the third rod connected in sequence. The end of the first rod away from the second rod is connected to the top body 1.1 by bolt 1.4. Shock-absorbing pads I 1.3 are set on the inner and outer surfaces of the second and third rods, and shock-absorbing pads I 1.3 are also set on the head of the third rod away from the second rod. In use, loosen bolt 1.4, open the fixing hook 1.2, adjust it to the required angle, and then tighten bolt 1.4 for use. When not in use, bolt 1.4 can be loosened, the fixing hook 1.2 can be folded up and stored, and then bolt 1.4 can be tightened to make the top fixing mechanism smaller and easier to store. Bolt 1.4 can be a bolt of existing structural form of grade 8.8 or above, which can withstand shear force of more than 2 tons, far exceeding the weight of the ladder and the user, and can withstand a large torque when locked, meeting the usage requirements. After the fixing hook 1.2 is folded up and stored, its first rod can be rotated to be parallel to the horizontal plane of the L-shaped groove of the top body 1.1. The fixing hook 1.2 can be hung on the aircraft, thereby fixing the ladder to the aircraft. The fixing hook 1.2 enables the ladder to be fixed to the aircraft fuselage. At the same time, the shock-absorbing pad I 1.3 can increase the friction between the fuselage and the ladder, and also prevent the ladder from damaging the aircraft fuselage, so that the ladder can be attached to different aircraft.

[0032] The main column comprises a main column body 2.1, two pedals 2.2, a top connector I 2.3, and a bottom connector II 2.6. The two pedals 2.2 are symmetrically rotatably connected to the left and right sides of the main column body 2.1, and have folding and unfolding functions. The lower end of the pedal 2.2 is rotatably connected to the main column body 2.1 via three hinge seats 2.4 and hinge shaft I 2.5. The hinge shaft I 2.5 passes through both the lower end of the pedal 2.2 and the three hinge seats 2.4, which are spaced apart. The pedals 2.2 are folded or unfolded via the hinge seats 2.4 and hinge shaft I 2.5. The pedals 2.2 are unfolded when in use and folded when stored. The top connector I 2.3 and the bottom connector II 2.6 are respectively located at the top and bottom of the main column body 2.1. The multiple sections of the main column are detachable (or flexibly assembled), allowing the long ladder to be divided into multiple smaller sections for easy storage and transportation. In this embodiment, the main column has a columnar structure. The main column body 2.1 has two arc-shaped side surfaces, and the two side steps 2.2 are installed on these two side surfaces. The side steps 2.2 can be unfolded. Vertical receiving grooves can be opened on the outer walls of the two side surfaces of the main column body 2.1. The lower end of the step 2.2 is hinged to the bottom end of the receiving groove. When stored, the step 2.2 is folded into the receiving groove. The outer surface of the folded step 2.2 is on the same cylindrical surface as the arc-shaped outer surface of the main column body 2.1, thus reducing the size and space occupied. The upper surface of the unfolded step 2.2 is flat, and the lower surface is arc-shaped. The unfolded step 2.2 is perpendicular to the main column body 2.1, and the bottom end of the receiving groove can limit and support the unfolded step 2.2. Multiple main column sections are spliced ​​together to form the ladder body. One side of the main column body 2.1 has a vertical plane. After the multiple main column sections are spliced ​​together, the vertical planes of the main column body 2.1 of the multiple main column sections are on the same plane. When there is no suitable position on the aircraft for the fixing hook 1.2 to hook onto, the vertical plane of the main column body 2.1 can be directly contacted with the outer wall of the aircraft for use. The vertical plane of the main column body 2.1 of the multi-section main column is opposite to the folding direction of the fixing hook 1.2. This ensures that when the vertical plane of the main column body 2.1 is against the aircraft, the fixing hook 1.2 faces outwards away from the fuselage, thus not interfering with the ladder's use. Simultaneously, the fixing hook 1.2 can be locked at a suitable angle using bolts 1.4, so that when the user climbs to the top of the ladder, the fixing hook 1.2 will not affect the user's work. Bolts 1.4 can also be loosened to temporarily remove the fixing hook 1.2, which can then be reassembled after the user finishes their work. A vertical mounting groove can be opened on the opposite side of each main column body 2.1 opposite to the vertical plane. An adjustable support frame is installed in this groove, with the support frame located on the same side as the fixing hook 1.2. Figure 2 and Figure 3In the center, two pedals 2.2 are respectively arranged on the left and right sides of the main column body 2.1, while the support frame and vertical plane are respectively arranged on the front and rear sides of the main column body 2.1. The support frame includes a first bracket 2.7 and a second bracket 2.8 with folding and unfolding functions. When there are support parts on the machine body, the support frame can extend after unfolding to provide support, tilting and supporting the support parts on the machine body. The top of the first bracket 2.7 is rotatably connected to the top of the vertical mounting slot, and the bottom is suspended. The bottom of the first bracket 2.7 is provided with a shock-absorbing pad III 2.9, which contacts the support parts on the machine body. The shock-absorbing pad III 2.9 is made of existing nitrile rubber composite material. The top of the second bracket 2.8 is connected to the first bracket 2.7, and the bottom is rotatably connected to the bottom of the vertical mounting slot. When using the fixing hook 1.2 to connect to the machine body, and there are support parts on the machine body, such as Figure 3 As shown, the first bracket 2.7 and the second bracket 2.8 on the corresponding main column body 2.1 can be unfolded for use. The first bracket 2.7 has multiple symmetrically arranged oblique holes on both sides, with two symmetrical oblique holes forming a group. The second bracket 2.8 has short shafts on both sides of its top, which are inserted into a group of oblique holes. Depending on the support location on different machine bodies, a corresponding support frame on the main column body 2.1 will be used for support, and the required support angle of the first bracket 2.7 will vary. The angle of the first bracket 2.7 can be adjusted by adjusting the short shaft of the second bracket 2.8 and its connection to the required group of oblique holes. Simultaneously, the second bracket 2.8 also provides support and fixation for the first bracket 2.7. When there are no support locations on the machine body, such as... Figure 2 As shown, both the first bracket 2.7 and the second bracket 2.8 are folded into the mounting groove. Grooves are opened on both sides of the top inner side of the first bracket 2.7. After the second bracket 2.8 is folded, the short axes on both sides of the second bracket 2.8 are located in the grooves, and the grooves can restrict the movement of the second bracket 2.8.

[0033] The base 5 includes a top connector II 5.1 and a base plate 5.3. The top connector II 5.1 is rotatably connected to the upper surface of the base plate 5.3. A shock-absorbing pad II (not shown in the figure) is fixedly connected to the bottom surface of the base plate 5.3. The shock-absorbing pad II is made of existing nitrile rubber composite material, providing excellent grip. The entire bottom surface of the base plate 5.3 can be covered with the shock-absorbing pad II. The bottom of the top connector II 5.1 is rotatably connected to the base plate 5.3 via a hinge shaft II 5.2 and hinge seats. Two hinge seats are welded to the upper surface of the base plate 5.3, and the hinge shaft II 5.2 passes through the top connector II 5.1 and the two hinge seats. Through the hinge between the top connector II 5.1 and the base plate 5.3, the ladder can maintain frictional contact with the ground at different tilt angles when used on different aircraft. When the ladder hooks onto the aircraft fuselage or rests against the aircraft, the rotation between the top connector II 5.1 and the base plate 5.3 ensures that the base plate 5.3 maintains frictional contact with the ground at different tilt angles. The base plate 5.3 has a square plate structure with a flat bottom surface. The dimensions of the base plate 5.3 can be larger than the outer diameter of the main column.

[0034] Any two main columns can be spliced ​​together. When two adjacent main columns are spliced ​​together, the bottom connector II2.6 of the upper main column is connected to the top connector I2.3 of the lower main column, the bottom connector I1.5 is connected to the top connector I2.3 of the uppermost main column, and the top connector II5.1 is connected to the bottom connector II2.6 of the lowermost main column.

[0035] The bottom connector I1.5 is a cylindrical protrusion I set at the bottom of the top main body 1.1 (the protrusion I can be integrally formed with the top main body 1.1). The top connector I2.3 is a cylindrical groove structure I opened at the top of the main column body 2.1. The outer wall of the protrusion I is provided with an external thread I1.6, and the inner wall of the groove structure I is provided with an internal thread I2.10. The external thread I1.6 is connected to the internal thread I2.10 of the top connector I2.3 of the uppermost main column.

[0036] Bottom connector Ⅱ2.6 is a cylindrical protrusion structure Ⅱ set at the bottom of the main column body 2.1 (the protrusion structure Ⅱ can be integrally formed with the main column body 2.1). The outer wall of the protrusion structure Ⅱ is provided with external thread Ⅱ2.11, which is connected to the internal thread Ⅰ2.10 of the top connector Ⅰ2.3 of the adjacent main column.

[0037] The top connector Ⅱ5.1 has a cylindrical groove structure Ⅱ on its top. The inner wall of the groove structure Ⅱ has an internal thread Ⅱ5.4. The internal thread Ⅱ5.4 is engaged with the external thread Ⅱ2.11 of the bottom connector Ⅱ2.6 of the bottom main column.

[0038] How to use this utility model: In the initial state, the pedals on the main column are all folded, and the fixing hooks are in the folded state with the smallest volume. After receiving this utility model product, the user first calculates the required number of main columns based on the altitude of the target aircraft to be inspected. Then, the corresponding number of main columns are spliced ​​together. The spliced ​​multi-section main columns are then assembled with the top fixing mechanism and the base. Next, the folded footplates on each main column are opened. When there is a suitable hook position on the aircraft, the fixing hook is opened. The ladder is then placed on the aircraft via the fixing hook or rested against the aircraft via the vertical plane of the main column body. When the footplates on the multi-section main columns are unfolded, they are arranged in a row; that is, multiple footplates on the left are in the same row, and multiple footplates on the right are in the same row. The fixing hook on the left is located above the left row of footplates, and the fixing hook on the right is located above the right row of footplates.

[0039] After use, when storing the ladder, first remove it from the aircraft, fold the steps of each main column, remove the top fixing mechanism and base, disassemble each section of the main column, and fold the fixing hooks. Finally, store it in its smallest possible size.

[0040] When in use, for example, when inspecting a civil aircraft engine, the fixing hook can be attached to a suitable part of the wing, and the base plate will make frictional contact with the ground through the shock-absorbing pad II. For example, when inspecting an aircraft window, the fixing hook can be attached to the fuselage, and the base plate will make frictional contact with the ground through the shock-absorbing pad II.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A portable aircraft access ladder characterized by, It includes a top fixing mechanism (1), a multi-section main column and a base (5) that are spliced ​​together. The top fixing mechanism (1) is installed and connected to the top of the uppermost main column, and the base (5) is installed and connected to the bottom of the lowermost main column. The top fixing mechanism (1) includes a top body (1.1), two fixing hooks (1.2) and a bottom connector I (1.5). The two fixing hooks (1.2) are respectively connected to the upper sides of the top body (1.1) and have folding and unfolding functions. The bottom connector I (1.5) is located at the bottom of the top body (1.1). The main column includes a main column body (2.1), two pedals (2.2), a top connector I (2.3), and a bottom connector II (2.6). The two pedals (2.2) are rotatably connected to both sides of the main column body (2.1) and have folding and unfolding functions. The top connector I (2.3) and the bottom connector II (2.6) are respectively located at the top and bottom of the main column body (2.1). The base (5) includes a top connector II (5.1) and a base plate (5.3). The top connector II (5.1) is rotatably connected to the upper surface of the base plate (5.3), and a shock-absorbing pad II is fixedly connected to the bottom surface of the base plate (5.3). When splicing and connecting two adjacent main columns, the bottom connector II (2.6) of the upper main column is connected to the top connector I (2.3) of the lower main column, the bottom connector I (1.5) is connected to the top connector I (2.3) of the uppermost main column, and the top connector II (5.1) is connected to the bottom connector II (2.6) of the lowermost main column.

2. The portable aircraft access ladder of Claim 1, wherein, The fixing hook (1.2) is connected to the top body (1.1) by bolts (1.4). The fixing hook (1.2) has a hook-shaped structure. The inner and outer surfaces and the head of the fixing hook (1.2) away from the top body (1.1) are provided with shock-absorbing pads I (1.3).

3. The portable aircraft access ladder of Claim 1, wherein, The bottom connector I (1.5) is a raised structure I provided at the bottom of the top body (1.1), and the top connector I (2.3) is a groove structure I opened at the top of the main column body (2.1). The outer wall of the raised structure I is provided with an external thread I (1.6), and the inner wall of the groove structure I is provided with an internal thread I (2.10). The external thread I (1.6) is connected to the internal thread I (2.10) of the top connector I (2.3) of the uppermost main column.

4. The portable aircraft access ladder of Claim 3, wherein, The bottom connector II (2.6) is a raised structure II provided at the bottom of the main column body (2.1). The outer wall of the raised structure II is provided with an external thread II (2.11). The external thread II (2.11) is connected to the internal thread I (2.10) of the top connector I (2.3) of the adjacent main column.

5. The portable aircraft access ladder of Claim 4, wherein, The top connector II (5.1) has a groove structure II on its top, and the inner wall of the groove structure II has an internal thread II (5.4). The internal thread II (5.4) is connected to the external thread II (2.11) of the bottom connector II (2.6) of the bottom main column.

6. The portable aircraft access ladder of Claim 1, wherein, The pedal (2.2) and the main column body (2.1) are rotatably connected by a hinge seat (2.4) and a hinge shaft I (2.5).

7. The portable aircraft access ladder of Claim 1, wherein, The bottom of the top connector II (5.1) is rotatably connected to the base plate (5.3) via the hinge shaft II (5.2) and the hinge seat.

8. The portable aircraft access ladder of Claim 1, wherein, The base plate (5.3) has a square plate structure and a flat bottom surface.

9. The portable aircraft access ladder of Claim 1, wherein, One side of the main column body (2.1) has a vertical plane, and the vertical planes of the main column body (2.1) of the multi-section main columns are located on the same plane.

10. The portable aircraft access ladder of Claim 9, wherein, A vertical mounting groove is provided on the side opposite to the vertical plane of the main column body (2.1). A support frame is installed in the vertical mounting groove. The support frame includes a first bracket (2.7) and a second bracket (2.8) with folding and unfolding functions. The top of the first bracket (2.7) is rotatably connected to the top of the vertical mounting groove, and the bottom is suspended. A shock-absorbing pad III (2.9) is provided at the bottom of the first bracket (2.7). The top of the second bracket (2.8) is connected to the first bracket (2.7), and the bottom is rotatably connected to the bottom of the vertical mounting groove.

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