Auxiliary device for disassembly and assembly of undercarriage

Abstract

The utility model relates to an undercarriage disassembly and assembly auxiliary device which comprises an I-shaped supporting seat, lockable casters are installed below the two ends of two transverse frames of the I-shaped supporting seat respectively, supporting rods are vertically installed above the two ends of the two transverse frames respectively, a guide rail is arranged on a bracket between the two transverse frames, and at least two sliding blocks are arranged on the guide rail. The sliding block is provided with a wheel axle vertex seat matched with two wheel axle vertexes of the undercarriage, when the undercarriage is placed on the auxiliary device, the undercarriage is supported on the two wheel axle vertex seats of the bracket through the two wheel axle vertexes of the undercarriage so as to be suspended, wheels of the undercarriage are distributed on the two sides of the bracket, and the whole undercarriage is located between the two transverse frames; the auxiliary device further comprises a fixing sleeve and a tightening belt, wherein the fixing sleeve is used for being arranged on the undercarriage inner cylinder in a sleeving mode, and the tightening belt is connected with the supporting rod and the fixing sleeve so as to tighten the undercarriage inner cylinder from different directions to keep the position of the undercarriage inner cylinder stable. By using the auxiliary device disclosed by the utility model, the disassembly and assembly operation of the undercarriage is safer, more efficient and more labor-saving.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft maintenance, concretely relates to a landing gear dismounting auxiliary device. BACKGROUND

[0002] The aircraft landing gear is a key time-life part, and its regular maintenance and replacement are indispensable links to ensure flight safety. However, in the current landing gear replacement process, there are many challenges and inconveniences.

[0003] The landing gear is a whole dismounting part, which is directly placed on the ground after being removed from the aircraft body. This not only increases the difficulty of dismounting the fine parts such as wheels and brakes, but also makes it extremely inconvenient to move due to ground friction. In the conventional operation, in order to push the landing gear out from under the large wing of the aircraft, it is often necessary to lay grease slides under the landing gear wheels to reduce friction, but this not only complicates the operation, but also makes it difficult to accurately control the direction and low in efficiency.

[0004] Especially troublesome is that when the wheels and brake systems of the landing gear need to be further removed, the traditional method needs to rely on CTI (hoisting and transporting equipment) for hoisting operation, so that the heavy landing gear is suspended in the air for subsequent disassembly. In this process, due to the lack of special fixing and supporting tools, the landing gear is prone to tilt and shift, not only threatening the safety of the operating personnel, but also greatly prolonging the operation time and increasing the labor intensity.

[0005] Specifically, the current method usually includes the following cumbersome steps:

[0006] Firstly, the side support, front and rear pivot pins, hydraulic pipeline and connecting wires connected with the landing gear need to be carefully disconnected to ensure that the landing gear can be safely separated from the aircraft;

[0007] Then, the CTI is used to slowly lift the landing gear away from the aircraft and place it on the ground;

[0008] Next, the grease slides are laid and the landing gear is pushed to the appropriate position by manpower, and then the CTI is used again to lift the landing gear for disassembly of the wheels and brake system;

[0009] Finally, the disassembled landing gear is placed on a special bracket for storage.

[0010] As can be seen from the above, during the entire disassembly process of the landing gear, multiple links are involved, including laying grease slides and pushing by manpower, multiple CTI hoisting, etc. Not only is it time-consuming and labor-intensive, but also there are safety hazards that cannot be ignored.

[0011] For example, the Boeing 767 model landing gear disassembly and replacement of the wheel, brake system and other components, according to the traditional approach, time-consuming as long as 192 working hours, that is, 8 days x 24 hours. This long operation cycle, not only affects the normal maintenance and operation of the aircraft, but also adversely affects the economic efficiency and service quality of the airline. Therefore, the development of a safe, efficient, and labor-saving landing gear disassembly operation scheme has become an important issue to be addressed in the current aviation maintenance field. Practical new type content

[0012] The utility model aims at providing a landing gear disassembly auxiliary device, which can make the landing gear disassembly operation more safe, efficient and labor-saving.

[0013] The utility model realizes its invention purpose through the following technical scheme: a landing gear disassembly auxiliary device, including the I-shaped support seat, the two ends of its two cross frames are respectively provided with lockable wheel feet, the upper parts are respectively provided with vertical support rods, the bracket between the two cross frames is provided with a guide rail, at least two sliding blocks are arranged on the guide rail, a wheel shaft vertex seat for cooperating with the two wheel shaft vertexes of the landing gear is arranged on the sliding block, when the landing gear is placed on the auxiliary device, it is suspended by being supported on the two wheel shaft vertex seats of the bracket through its two wheel shaft vertexes, its wheels are distributed on the two sides of the bracket, and the whole is located between the two cross frames;

[0014] The auxiliary device further comprises a fixing sleeve for sleeving on the inner cylinder of the landing gear, and a tightening belt connected with the support rod and the fixing sleeve so as to pull the inner cylinder of the landing gear from different directions to keep its position stable.

[0015] The support rod is hinged on the cross frame through a hinge shaft and can be folded on the cross frame, so as to be folded when the landing gear is placed on the auxiliary device, and unfolded after the landing gear is placed, which facilitates the placement operation of the landing gear.

[0016] The hinge of the support rod is formed with two groups of split holes, one of which is used for penetrating the hinge shaft, and the other is used for inserting a pin parallel to the hinge shaft to fix the support rod after the support rod is unfolded, so as to enhance the stability of the support rod in the unfolded state.

[0017] A lifting eye is fixed on the upper end of the support rod, which is used for facilitating the connection of the tightening belt and the support rod.

[0018] A trailer point is further arranged on the support seat for facilitating the towing of the auxiliary device.

[0019] As a preferred scheme, four sliding blocks are arranged on the guide rail, and auxiliary fixing rods for cooperating with the front and rear towing points of the landing gear to realize locking are arranged on the two sliding blocks on the outer side.

[0020] The fixed sleeve is a hoop with a plurality of hole positions distributed in the circumference.

[0021] The locking screw is arranged on the sliding block and used for locking the sliding block on the sliding rail.

[0022] The auxiliary fixing rod is a screw rod with a thread formed on the upper portion and two nuts sleeved, when the landing gear is placed on the auxiliary device, the screw rod is inserted into the hole position on the towing point of the landing gear, the lower nut is supported below the towing point, and the upper nut is locked with the towing point.

[0023] Except for individual models without the towing point, for most models, the fixing of the landing gear on the auxiliary device can be strengthened through the auxiliary fixing rod. However, the height of the towing point of each model is not the same, the locking of the towing point is realized through two movable nuts, and the design has good universality.

[0024] Beneficial effects:

[0025] 1) After the landing gear is disconnected from the main body of the aircraft, the landing gear is placed on the auxiliary device of the utility model through the CTI, the auxiliary device supports the landing gear through the cooperation of the wheel shaft top point seat and the landing gear wheel shaft top point, and the landing gear is pulled tightly from different directions through the cooperation of the supporting rod, the fixed sleeve, the tightening belt and the inner cylinder of the landing gear, so that stable bearing and flexible transfer of the landing gear can be realized. Moreover, the disassembly and assembly operation of the landing gear wheel and the brake system and the like can be directly performed on the auxiliary device of the utility model, which reduces the dependence on the CTI, is safer, more efficient and more labor-saving. In addition, after the auxiliary device is directly pushed to a suitable position, the wheel foot is locked, and stable storage of the landing gear can be realized. The utility model completely innovates the operation process of disassembly, transfer and storage of the landing gear in the traditional operation, and solves a major technical problem. The auxiliary device of the utility model can not only significantly reduce the double cost of human resources and material consumption, but also greatly shorten the operation cycle. For example, if the auxiliary device of the utility model is used for the displacement of the landing gear and the disassembly and assembly of the wheel and the brake system, the total time consumption is only 64 working hours, i.e. 4 persons x 16 hours, which is more than half of the time consumption of the traditional method.

[0026] 2) The auxiliary device of the utility model also has good universality: the structures of the wheel shaft top points of landing gears of various models are basically the same, and the spacing of the two wheel shaft top points may be slightly different. The auxiliary device of the utility model supports the landing gear through the cooperation of the spacing-adjustable two wheel shaft top point seats and the wheel shaft top points of the landing gear, so it has good universality and can basically be applied to the landing gears of all current models. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 It is a structure diagram of the auxiliary device of the utility model.

[0028] Figure 2 For Figure 1 the use of the auxiliary device is shown in the figure;

[0029] Figure 3 For Figure 1 the auxiliary device is shown in the figure; DETAILED DESCRIPTION

[0030] As Figures 1-3 shown, the embodiment of the auxiliary device includes an I-shaped support seat 1, the lower ends of the two crossbars of which are respectively provided with lockable wheels, and the upper ends of the crossbars are respectively provided with support rods 6 vertically installed thereon. The upper ends of the support rods 6 are further provided with lifting rings 4. The lifting rings 4 are used for the connection between the tightening belts 7 and the support rods 6, which will be mentioned later. The support rods 6 are hinged to the crossbars through hinge shafts 61 and can be folded on the crossbars, so as to be folded during the placement of the landing gear F and unfolded after the landing gear F is placed, thereby facilitating the placement operation of the landing gear F. In fact, the hinge shafts 61 of the support rods 6 are formed with two sets of opposite holes, one of which is used for penetrating the hinge shaft 61, and the other is used for inserting a pin 62 parallel to the hinge shaft 61 to fix the support rod 6 after the support rod 6 is unfolded, so as to enhance the stability of the support rod 6 in the unfolded state.

[0031] The two ends of the bracket between the two crossbars are respectively provided with a guide rail 11, and two sliding blocks 14 are arranged on each guide rail 11. The outer two sliding blocks 14 of the four sliding blocks 14 are provided with auxiliary fixing rods 3 used for cooperating with the front and rear towing points 18 of the landing gear F to realize locking. In the embodiment, the auxiliary fixing rod 3 is a screw rod 12 with a thread formed on the upper portion and sleeved with two nuts 13 and 10. As Figure 3 shown, when the landing gear F is placed on the auxiliary device, the screw rod 12 is inserted into the hole position of the towing point 18 of the landing gear F, and the lower nut 13 is supported below the towing point 18, and the upper nut 10 cooperates to lock the towing point 18 of the landing gear F. The screw rod 12 is also closely attached with a nylon protective sleeve, which prevents scratching of the hole position of the towing point 18 when in contact with the hole position.

[0032] Except for individual models without the design of the towing point 18, for most models, the fixation of the landing gear F on the auxiliary device can be enhanced through the auxiliary fixing rod 3. However, the heights of the towing points 18 of various models are not the same, and the locking of the towing points 18 is realized through the two movable nuts 13 and 10, which has better universality.

[0033] The inner two sliding blocks 14 are provided with wheel shaft vertex seats 2 used for cooperating with the wheel shaft vertexes 19 of the landing gear F. As Figure 2 , 3As shown, when the landing gear F is placed on the auxiliary device, it is suspended by the two wheel axle vertices 19 supported on the two wheel axle vertex seats 2 of the bracket, and the wheels of the landing gear F are distributed on both sides of the bracket and located between the two crossbars. The end of the wheel axle vertex 19 of the landing gear F is a semicircular protrusion, and a semicircular recess is formed on the corresponding wheel axle vertex seat 2 to accommodate it. After the two are connected, a good support relationship is formed.

[0034] The structure of the wheel axle vertices 19 of each model of landing gear F is basically the same, and the distance between the two wheel axle vertices 19 may be slightly different. In this embodiment, the auxiliary device supports the landing gear F through the cooperation of the two wheel axle vertex seats 2 with adjustable distance and the wheel axle vertices 19 of the landing gear F, so that the auxiliary device of this embodiment has good universality and can basically be applied to all current models.

[0035] As shown in the figure, Figure 1 A tow bar 5 is also provided on the crossbar to facilitate towing the auxiliary device.

[0036] As shown in the figure, Figure 3 Locking screws 15 and 16 are provided on the sliding block 14, the locking screw 15 is used to lock the sliding block 14 on the bottom surface of the sliding rail 11, and the locking screw 16 is used to lock the sliding block 14 on the side surface of the sliding rail 11.

[0037] As shown in the figure, Figure 2 The auxiliary device also includes a fixing sleeve 8 for sleeving on the inner cylinder 9 of the landing gear F, and a tightening belt 7 connecting the support rod 6 (the figure does not show the lifting ring 4 at the end position of the support rod 6) and the fixing sleeve 8 to pull the inner cylinder 9 of the landing gear F from different directions to keep its position stable. In this embodiment, the fixing sleeve 8 is a hoop with several hole positions distributed circumferentially, and the hole positions are arranged to facilitate the connection of the nylon tightening belt 7.

[0038] The process of using the auxiliary device of this embodiment to disassemble and assemble the landing gear F is as follows:

[0039] 1) The landing gear F is removed from the aircraft, and the landing gear F is lifted to a suitable height by the CTI. The auxiliary device is manually moved to the lower side of the landing gear F, the distance between the two wheel axle vertex seats 2 and the two auxiliary fixing rods 3 on the sliding rail 11 of the auxiliary device is adjusted, so that they are respectively aligned with the wheel axle vertices 19 and the front and rear towing points 18 of the landing gear F, and the landing gear F is slowly lowered to be supported on the auxiliary device.

[0040] 2) The front and rear towing points 18 of the landing gear F are locked by the nuts 13 and 10, and the locking screws 15 and 16 on the sliding block 14 are tightened.

[0041] 3) Four support rods 6 provided at the ends of the crossbar of the I-shaped support seat 1 are unfolded.

[0042] 4) Put the fixing sleeve 8 on the inner cylinder 9 of the landing gear F, pass the tightening belts 7 through the circumferential hole positions of the fixing sleeve 8, and then tighten the hanger rings 4 of the supporting rods 6 to make the four tightening belts 7 bear force uniformly.

[0043] 5) Artificially push the auxiliary device to make it come out from under the large wing of the airplane, lock the wheels and legs of the auxiliary device, and after fixing the auxiliary device, normal disassembly and assembly of the wheels and brake systems of the landing gear F can be carried out.

[0044] 6) Push the auxiliary device to a suitable position, lock the casters, and directly place the landing gear F on the auxiliary device for storage, which can greatly improve the flexibility of the landing gear F storage and transfer.

[0045] The auxiliary device of the utility model supports the landing gear through the cooperation of the wheel shaft vertex seat and the landing gear wheel shaft vertex, and tightens the landing gear from different directions through the cooperation of the supporting rod, the fixing sleeve, the tightening belt and the inner cylinder of the landing gear, which can realize stable bearing and flexible transfer of the landing gear. Using the auxiliary device of the utility model to support the disassembled landing gear not only supports the 360-degree rotation and displacement of the landing gear, but also has significantly better bearing capacity and stability than the current CTI suspension scheme, and directly carries out the disassembly and assembly of the wheels and brake systems of the landing gear, which can ensure the safety and efficiency of the operation process.

Claims

1. A landing gear dismounting assisting device, characterized by, The support seat comprises two horizontal frames, each of which is provided with a lockable wheel at its lower end and a support rod vertically installed at its upper end. A bracket is arranged between the two horizontal frames, and a guide rail is arranged on the bracket. At least two sliding blocks are arranged on the guide rail, and a wheel axle top point seat is arranged on each sliding block. When the landing gear is placed on the auxiliary device, the landing gear is supported by the two wheel axle top points and is suspended on the two wheel axle top point seats of the bracket, and the wheels are distributed on both sides of the bracket and are located between the two horizontal frames. The auxiliary device further comprises a fixing sleeve for sleeving on the inner cylinder of the landing gear, and a tightening belt for connecting the support rod and the fixing sleeve to tighten the inner cylinder of the landing gear from different directions to keep the position of the inner cylinder stable.

2. The supplementary device of claim 1, wherein, The support rod is hinged to the horizontal frame by a hinge shaft and can be folded on the horizontal frame.

3. The supplementary device of claim 2, wherein, Two groups of split holes are formed at the hinge of the support rod, one of which is used for penetrating the hinge shaft, and the other is used for inserting a pin parallel to the hinge shaft to fix the support rod after the support rod is unfolded.

4. The supplemental device of claim 1, wherein, A lifting ring is fixed to the upper end of the support rod.

5. The supplemental device of claim 1, wherein, A trailer point is further arranged on the support seat to facilitate dragging the auxiliary device.

6. The supplemental device of claim 1, wherein, The fixing sleeve is a hoop with a plurality of circumferentially distributed hole positions.

7. The supplemental device of claim 1, wherein, A locking screw is arranged on the sliding block to lock the sliding block on the guide rail.

8. The supplementary device according to any one of claims 1-7, characterized in that, Four sliding blocks are arranged on the guide rail, and auxiliary fixing rods are arranged on the two outer sliding blocks to cooperate with the towing points of the landing gear to achieve locking.

9. The supplemental device of claim 8, wherein, The auxiliary fixing rod is a screw rod with threads on its upper part and two nuts sleeved thereon. When the landing gear is placed on the auxiliary device, the screw rod is inserted into the hole position of the towing point of the landing gear, the lower nut is supported below the towing point, and the upper nut cooperates with the lower nut to lock the towing point.

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