Main landing gear assembly tool

Abstract

The utility model discloses a main landing gear assembly tool, and relates to the field of aircrafts. The main landing gear assembly tool comprises a supporting mechanism, a lifting mechanism, a guide plate and at least two positioning pin shafts. The lifting mechanism is arranged at one end of the supporting mechanism away from the ground; the guide plate is arranged at the end, away from the supporting mechanism, of the lifting mechanism and provided with a plurality of mounting holes corresponding to assembly hole positions of the machine body. And the at least two positioning pin shafts are detachably connected to the mounting holes of the guide plate, correspond to the diagonal hole positions of the main undercarriage and are coaxial with the assembly hole positions of the fuselage. Therefore, according to the main undercarriage assembly tool, rapid and accurate assembly of the main undercarriage and the fuselage is achieved through the steps of accurate alignment, stable lifting, efficient assembly, reliable fixing and the like, the assembly efficiency and quality are improved through the tool, and the risk and cost in the assembly process are reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an assembly tool for a main landing gear. BACKGROUND

[0002] In the manufacturing process of a small fixed-wing aircraft, the precise assembly of the main landing gear is a crucial link, which is directly related to the take-off and landing stability, flight safety and durability of the overall structure of the aircraft. The traditional assembly method of the main landing gear mainly relies on manual operation, especially for the main landing gear with a weight of about 60-80 kg, the assembly process is particularly heavy and complex.

[0003] The existing assembly operation of the main landing gear usually includes multiple steps such as lifting, lifting, aligning, and bolt positioning. These steps not only require a large amount of manpower, such as four to five operators to complete together, but also require the main landing gear to be in a lifted state for a long time during the assembly process, which undoubtedly increases the physical burden of the operators. In addition, during the entire assembly process, the main landing gear is always in a state of leaving the ground, which requires the operators to continuously maintain high attention and physical input. Once the coaxiality of the assembly hole is reached, the operator needs to quickly perform the bolt fastening operation to ensure the firmness of the assembly. This process not only takes time and effort, but also puts a high demand on the physical and endurance of the operators. SUMMARY

[0004] The embodiment of the present application provides an assembly tool for a main landing gear, which solves the technical problems of complex operation and large manpower demand in the prior art.

[0005] The embodiment of the present application provides an assembly tool for a main landing gear, which solves the technical problems of complex operation and large manpower demand in the prior art.

[0006] A support mechanism;

[0007] A lifting mechanism is arranged at one end of the support mechanism away from the ground;

[0008] A guide plate is arranged at one end of the lifting mechanism away from the support mechanism, and a plurality of mounting holes corresponding to the assembly hole of the fuselage are arranged on the guide plate;

[0009] At least two positioning pins are detachably connected to the mounting holes of the guide plate, and correspond to the assembly hole of the main landing gear plate spring, and are coaxial with the assembly hole of the fuselage.

[0010] In one possible implementation, the lifting mechanism includes a lead screw device and a hand wheel; both ends of the lead screw device are connected to one end of the support mechanism away from the ground and the guide plate, respectively; the hand wheel is connected to one end of the lead screw device, and is used to drive the lifting movement of the lead screw device.

[0011] In a possible implementation, the lifting mechanism further comprises a base plate; the base plate is arranged between the support mechanism and the screw rod device.

[0012] In a possible implementation, the support mechanism comprises a top plate and a plurality of support pieces; a top portion of the top plate is connected to an end of the lifting mechanism away from the guide plate; the plurality of support pieces are arranged along a periphery of a bottom portion of the top plate.

[0013] In a possible implementation, the support mechanism further comprises a plurality of support beams; two ends of each of the plurality of support beams are connected to two adjacent support pieces, respectively.

[0014] In a possible implementation, the support mechanism further comprises a plurality of bottom plates; the plurality of bottom plates are arranged at an end of each of the support pieces away from the top plate.

[0015] In a possible implementation, the support mechanism further comprises a plurality of long cross beams; each of the plurality of support pieces is arranged obliquely; two ends of each of the plurality of long cross beams are connected to two adjacent support pieces and are located below the support beam.

[0016] In a possible implementation, the main landing gear assembly tool further comprises a plurality of universal wheels; the plurality of universal wheels are arranged at an end of the support mechanism away from the lifting mechanism.

[0017] In a possible implementation, one end of the positioning pin shaft is externally threaded, and the other end is in the shape of a cylinder.

[0018] In a possible implementation, the lifting mechanism comprises a hydraulic device; two ends of the hydraulic device are connected to the guide plate and an end of the support mechanism away from the ground, respectively.

[0019] The one or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0020] The main landing gear assembly tool provided in the embodiments of the present application comprises a support mechanism, a lifting mechanism, a guide plate and at least two positioning pin shafts. The working process is as follows: first, the two positioning pin shafts are installed on the guide plate, and then the two diagonal assembly hole positions at the main landing gear plate spring are accurately aligned and then inserted into the two positioning pin shafts. This step realizes the preliminary connection of the main landing gear and the guide plate and provides a basis for subsequent assembly.

[0021] Subsequently, the entire main landing gear assembly tool is moved to the designated assembly station. At the assembly station, the operator adjusts the position of the main landing gear assembly tool to preliminarily align the positioning pin shafts with the assembly holes of the fuselage and ensure their coaxiality, which ensures the accurate alignment of the main landing gear and the fuselage during assembly and reduces assembly errors caused by misalignment.

[0022] Next, the guide plate and the main landing gear thereon are smoothly lifted by operating the lifting mechanism. As the guide plate is lifted, the main landing gear also rises until the two positioning pin shafts are completely inserted into the corresponding assembly holes of the fuselage. At the same time, the upper end surface of the leaf spring of the main landing gear is in close contact with the mounting surface of the fuselage, ensuring the stability and safety of the main landing gear during lifting.

[0023] At this time, the operator stops the lifting operation and inserts assembly bolts into the mounting holes of the guide plate where the positioning pin shafts are not installed. These assembly bolts are aligned with the corresponding assembly holes of the fuselage, and nuts are installed below the assembly bolts, thereby completing the preliminary fixation of the diagonal assembly holes of the main landing gear leaf spring to the assembly holes of the fuselage.

[0024] After completing the preliminary fixation, the operator can easily separate the positioning pin shafts from the guide plate and remove them from the interior of the fuselage, while withdrawing the remaining part of the main landing gear assembly tool from below the fuselage. This step simplifies the assembly process, improves assembly efficiency, and provides great convenience for subsequent assembly work.

[0025] Finally, the operator inserts assembly bolts through the assembly holes of the main landing gear leaf spring that have not yet been assembled, and installs nuts below the assembly bolts. By tightening the nuts, the main landing gear is fixed to the fuselage, thereby completing the assembly of the entire main landing gear.

[0026] Therefore, by precise alignment, smooth lifting, efficient assembly, and reliable fixation, the application realizes the rapid and accurate assembly of the main landing gear and the fuselage. This tool not only improves assembly efficiency and quality, but also reduces the risk and cost of the assembly process. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the description of the embodiments of the present application. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0028] Fig. 1 The structural schematic diagram of the main landing gear assembly tool provided in the embodiments of the present application is shown in the figure.

[0029] Fig. 2A schematic diagram illustrating the use of the main landing gear assembly tooling provided in this application embodiment;

[0030] Fig. 3 This is a schematic diagram of the main landing gear assembly fixture and main landing gear assembly hole positions provided in the embodiments of this application.

[0031] Icons: 1-Support mechanism; 11-Top plate; 12-Support component; 13-Support beam; 14-Base plate; 15-Long crossbeam; 2-Lifting mechanism; 21-Screw assembly; 22-Handwheel; 23-Plate; 3-Guide plate; 4-Positioning pin; 5-Wheel caster; 6-Main landing gear. Detailed Implementation

[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0033] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0034] This application provides a main landing gear assembly fixture, such as... Figs. 1 to 3 As shown. The main landing gear assembly fixture includes a support mechanism 1, a lifting mechanism 2, a guide plate 3, and at least two locating pins 4. The lifting mechanism 2 is located at the end of the support mechanism 1 away from the ground. The guide plate 3 is located at the end of the lifting mechanism 2 away from the support mechanism 1, and has multiple mounting holes corresponding to the mounting holes on the fuselage. At least two locating pins 4 are detachably connected to the mounting holes on the guide plate 3, and correspond to the mounting holes on the leaf springs of the main landing gear 6, and are coaxial with the mounting holes on the fuselage.

[0035] Specifically, the mounting holes of the present application are provided with four, and the corresponding assembly hole positions of the fuselage and the assembly hole positions at the leaf spring of the main landing gear 6 are respectively provided with four.

[0036] It should be noted that the main landing gear assembly tool working process is as follows: first, install two positioning pin shafts 4 on the guide plate 3, and accurately pass the two diagonal assembly hole positions at the leaf spring of the main landing gear 6 into the two positioning pin shafts 4 after accurate alignment, which realizes the preliminary connection of the main landing gear 6 and the guide plate 3, and provides a basis for subsequent assembly.

[0037] Subsequently, the entire main landing gear assembly tool is moved to the designated assembly station. At the assembly station, the operator preliminarily aligns the positioning pin shaft 4 with the assembly hole position of the fuselage by adjusting the position of the main landing gear assembly tool, and ensures that they are coaxial, which ensures the accurate alignment of the main landing gear 6 and the fuselage during assembly, and reduces the assembly error caused by misalignment.

[0038] Then, by operating the lifting mechanism 2, the guide plate 3 and the main landing gear 6 thereon are smoothly lifted. As the guide plate 3 is lifted, the main landing gear 6 also rises until the two positioning pin shafts 4 are completely inserted into the corresponding assembly hole positions of the fuselage. At the same time, the upper end surface of the leaf spring of the main landing gear 6 is in close contact with the mounting surface of the fuselage, ensuring the stability and safety of the main landing gear 6 during lifting.

[0039] At this time, the operator stops the lifting operation and inserts assembly bolts into the mounting holes of the guide plate 3 where the positioning pin shafts 4 are not installed. Align these assembly bolts with the corresponding assembly hole positions on the fuselage, and screw nuts under the assembly bolts, thereby preliminarily fixing the diagonal assembly hole positions at the leaf spring of the main landing gear 6 and the assembly hole positions of the fuselage.

[0040] After preliminary fixation, the operator can easily separate the positioning pin shaft 4 from the guide plate 3 and take it out from the inside of the fuselage, while withdrawing the remaining part of the main landing gear assembly tool from below the fuselage, which simplifies the assembly process, improves the assembly efficiency, and provides great convenience for subsequent assembly work.

[0041] Finally, the operator inserts the assembly bolt through the assembly hole position of the main landing gear 6 leaf spring that has not been assembled, and screws the nut under the assembly bolt. By tightening the nut, the main landing gear 6 is fixed on the fuselage, thereby completing the assembly of the entire main landing gear 6.

[0042] Therefore, through the steps of accurate alignment, smooth lifting, efficient assembly and reliable fixation, the present application realizes the rapid and accurate assembly of the main landing gear 6 and the fuselage, which not only improves the assembly efficiency and quality, but also reduces the risk and cost in the assembly process.

[0043] Specifically, when the main landing gear 6 completes two diagonal assembly hole positions, the installed assembly bolt functions as the positioning pin shaft 4, plays a positioning role, that is, can ensure the coaxiality of the other two assembly hole positions of the main landing gear 6, and completes the assembly at one time without secondary hole alignment.

[0044] In the embodiment of the present application, the lifting mechanism 2 comprises a screw rod device 21 and a hand wheel 22. Two ends of the screw rod device 21 are connected to one end of the support mechanism 1 away from the ground and the guide plate 3 respectively. The hand wheel 22 is connected to one end of the screw rod device 21 and is used to drive the lifting movement of the screw rod device 21.

[0045] In the embodiment of the present application, the lifting mechanism 2 further comprises a pad plate 23. The pad plate 23 is arranged between the support mechanism 1 and the screw rod device 21.

[0046] It should be noted that the pad plate 23 increases the stroke of the screw rod device, thereby improving the adjustment range of the tooling. The increase in the adjustment range enables the tooling to meet the assembly requirements of the fuselage and the main landing gear 6 located at different heights. The screw rod device is simple to operate and only needs to be rotated by the hand wheel 22 to realize the lifting operation of the main landing gear 6, which is convenient and labor-saving.

[0047] In the embodiment of the present application, the support mechanism 1 comprises a top plate 11 and a plurality of support pieces 12. The top of the top plate 11 is connected to one end of the lifting mechanism 2 away from the guide plate 3. The plurality of support pieces 12 are arranged along the circumference of the bottom of the top plate 11.

[0048] In the embodiment of the present application, the support mechanism 1 further comprises a plurality of support beams 13. Two ends of the plurality of support beams 13 are connected to adjacent two support pieces 12 respectively.

[0049] In the embodiment of the present application, the support mechanism 1 further comprises a plurality of bottom plates 14. The plurality of bottom plates 14 are arranged at one end of the corresponding support pieces 12 away from the top plate 11.

[0050] It should be noted that the existence of the plurality of bottom plates 14 increases the contact area of the support mechanism 1 with the ground, improves the overall anti-overturning capability, and ensures that the support mechanism 1 can remain stable when bearing heavy load or performing complex assembly operations.

[0051] In the embodiment of the present application, the support mechanism 1 further comprises a plurality of long cross beams 15. The plurality of support pieces 12 are all arranged obliquely. Two ends of the plurality of long cross beams 15 are connected to adjacent two support pieces 12 respectively and are located below the support beams 13.

[0052] It should be noted that the oblique arrangement of the plurality of support pieces 12 and the connection of the long cross beams 15 below the support beams 13 not only optimize the mechanical structure of the support mechanism 1, but also improve the anti-rollover and anti-twist capabilities.

[0053] Specifically, the long beam 15, the bottom plate 14, the top plate 11 and the support 12 of the application are all made of Q235 stainless steel with a size of 30mm*30mm profile, which has a strength meeting the use requirements and a low material cost.

[0054] In the embodiment of the application, the main landing gear assembly tooling further comprises a plurality of universal wheels 5. The plurality of universal wheels 5 are arranged at an end of the support mechanism 1 away from the lifting mechanism 2.

[0055] It should be noted that the universal wheels 5 can help to transfer the main landing gear 6 to the corresponding assembly station quickly and easily.

[0056] When assembling, the operator first rotates the hand wheel 22 to start the screw rod device to lift the guide plate 3. With the rising of the guide plate 3, the main landing gear 6 is also lifted. When the positioning pin shaft 4 accurately enters the assembly hole of the fuselage, the operator locks the universal wheel 5 to ensure the stability and safety of the entire assembly process.

[0057] In the embodiment of the application, one end of the positioning pin shaft 4 is externally threaded, and the other end is in the shape of a cylinder.

[0058] It should be noted that the cylindrical shape cooperates with the assembly hole of the fuselage in the form of a pin shaft. The guide plate 3 is provided with an internally threaded mounting hole matched with the externally threaded positioning pin shaft 4. When the positioning pin shaft 4 completes its positioning and guiding functions, it can be easily separated from the guide plate 3, so as not to affect the subsequent assembly process of the main landing gear 6. In addition, the spacing of the mounting holes on the guide plate 3 is determined according to the spacing requirements of the assembly hole of the main landing gear 6 and the assembly hole of the fuselage. Therefore, when the positioning pin shaft 4 cooperates with the assembly hole of the fuselage, the coaxiality between the guide plate 3, the main landing gear 6 and the assembly hole of the fuselage can be ensured.

[0059] Of course, the positioning pin shaft 4 of the application can also be designed in the shape of a cylinder at both ends, one end of which cooperates with the mounting hole of the guide plate 3 in the form of a pin shaft. At this time, the separation function of the positioning pin shaft 4 from the guide plate 3 can be realized by using a punch to knock the positioning pin shaft 4.

[0060] In the embodiment of the application, the lifting mechanism 2 comprises a hydraulic device. The two ends of the hydraulic device are respectively connected to the guide plate 3 and the end of the support mechanism 1 away from the ground.

[0061] It should be noted that the lifting mechanism 2 of the application is not limited to a hydraulic device, and it can also use a pneumatic device or an electric device to realize the lifting function.

[0062] Further, the main landing gear assembly tool of the present application can position, lift and align the main landing gear 6 with the assembly hole of the fuselage, thereby completing the assembly of the main landing gear 6. The support mechanism 1 can stably support and quickly transfer the main landing gear 6; the guide plate 3 positions the main landing gear 6 with the positioning pin shaft 4, the lifting mechanism 2 lifts the main landing gear 6, aligns the positioning pin shaft 4 with the assembly hole of the fuselage, and plays a directional guiding role, after the assembly of the two assembly bolts is completed, the positioning pin shaft 4 is separated from the guide plate 3 and taken out from above the fuselage, and at the same time the remaining part of the main landing gear assembly tool is withdrawn from below the fuselage, thereby completing the whole-process assembly operation of the main landing gear 6.

[0063] The various embodiments in the specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to each other, and each embodiment focuses on the difference from other embodiments.

[0064] The above examples are only used to illustrate the technical solutions of the present application, and are not limited to the present application; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that the technical solutions recorded in the foregoing examples can still be modified, or some or all of the technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. A main landing gear assembly fixture, characterized by, The utility model relates to a kind of aircraft main landing gear positioning device, including: Support mechanism (1); Lifting mechanism (2) is set to the end of the support mechanism (1) away from ground; Guide plate (3) is set to the end of the lifting mechanism (2) away from the support mechanism (1), and is provided with multiple installation holes corresponding with the assembly hole position of fuselage; At least two positioning pin shafts (4) are detachably connected to the installation hole of the guide plate (3), and correspond with the assembly hole position at the leaf spring of main landing gear (6), and are coaxial with the assembly hole position of fuselage.

2. The main landing gear assembly tooling fixture of Claim 1, wherein, The lifting mechanism (2) includes screw rod device (21) and hand wheel (22); Two ends of the screw rod device (21) are connected to the end of the support mechanism (1) away from ground and the guide plate (3) respectively; The hand wheel (22) is connected to one end of the screw rod device (21), for driving the lifting movement of the screw rod device (21).

3. The main landing gear assembly tooling fixture of Claim 2, wherein, The lifting mechanism (2) further includes backing plate (23); The backing plate (23) is arranged between the support mechanism (1) and the screw rod device (21).

4. The main landing gear assembly tooling fixture of Claim 1, wherein, The support mechanism (1) includes top plate (11) and multiple support pieces (12); The top of the top plate (11) is connected to the end of the lifting mechanism (2) away from the guide plate (3); Multiple support pieces (12) are arranged along the circumference of the bottom of the top plate (11).

5. The main landing gear assembly tooling fixture of Claim 4, wherein, The support mechanism (1) further includes multiple support beams (13); Two ends of multiple support beams (13) are connected to adjacent two support pieces (12) respectively.

6. The main landing gear assembly tooling fixture of Claim 4, wherein, The support mechanism (1) further includes multiple bottom plates (14); Multiple bottom plates (14) are arranged at the end of corresponding support pieces (12) away from the top plate (11).

7. The main landing gear assembly tooling fixture of Claim 5, wherein, The support mechanism (1) further includes multiple long cross beams (15); Multiple support pieces (12) are all arranged obliquely; Two ends of multiple long cross beams (15) are connected to adjacent two support pieces (12) respectively, and are located below the support beam (13).

8. The main landing gear assembly tooling fixture of Claim 1, wherein, Further including multiple universal wheels (5); Multiple universal wheels (5) are arranged at the end of the support mechanism (1) away from the lifting mechanism (2).

9. The main landing gear assembly tooling fixture of Claim 1, wherein, One end of the positioning pin shaft (4) is external thread, and the other end is cylindrical shape.

10. The main landing gear assembly tooling fixture of Claim 1, wherein, The lifting mechanism (2) includes hydraulic device; Two ends of the hydraulic device are connected to the guide plate (3) and the end of the support mechanism (1) away from ground respectively.

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