Auxiliary assembling device for aircraft parts

Abstract

The utility model relates to the technical field of aircraft manufacturing, in particular to an aircraft component auxiliary assembling device which comprises a bottom plate, and an electric hydraulic rod is fixedly installed on the top of the bottom plate. The electric hydraulic rod is started to drive the base and the connecting base to vertically move, the connecting base drives the top plate and the supporting plate to move, and therefore the supporting height of the aircraft component is adjusted, the first motor is started to drive the rotating shaft to rotate, the rotating shaft drives the connecting base to rotate, and the connecting base drives the top plate and the supporting plate to rotate, and therefore the aircraft component is driven to flexibly turn over. A second motor is started to drive a screw rod to rotate, the screw rod drives a sliding block to horizontally slide under limiting of a mounting groove, the sliding block drives a hinge rod to rotate around a hinge point and push a supporting plate, and therefore the supporting plate rotates around the hinge point, the vertical angle of the aircraft component is adjusted according to needs, and the assembling efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing, in particular to an auxiliary assembly device for aircraft parts. Background Art

[0002] During the manufacturing process of an aircraft, the assembly of components and large parts of the aircraft (such as the fuselage and wings) requires the assistance of assembly tooling; in other words, the components and large parts of the aircraft are assembled on assembly tooling.

[0003] To this end, someone proposed an aircraft assembly jig and recorded it in Chinese patent documents [Application No.: 201210116659.4; Application Publication No.: CN102632383A]. Although this solution solves the technical problem of thermal expansion difference between steel and aluminum materials of large-size jigs, there are still the following practical problems in the actual assembly production process: 1. The assembly jig is not easy to lay flat and stable, which affects the subsequent assembly efficiency and assembly accuracy; 2. After the assembly is completed, multiple people must cooperate when taking out the workpiece, which can easily cause scratches on the surface of the workpiece. Utility Model Content

[0004] The purpose of the utility model is to provide an auxiliary assembly device for aircraft components to solve the problems raised in the above background technology.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] An aircraft component auxiliary assembly device, comprising: a bottom plate, an electric hydraulic rod is fixedly installed on the top of the bottom plate, a base is fixedly installed on the piston end of the electric hydraulic rod, a first adjustment mechanism is arranged on the base, a top plate is arranged on the first adjustment mechanism, a support plate is hinged on the top of the top plate, and a second adjustment mechanism is arranged between the top plate and the support plate;

[0007] The first adjustment mechanism comprises: a rotating shaft, the rotating shaft is rotatably connected to the inner cavity of the base, the outer wall of the rotating shaft is fixedly sleeved with a connecting seat, and the top of the connecting seat is fixedly connected to the bottom of the top plate, the front side of the base is fixedly installed with a motor 1, and the front end of the rotating shaft passes through the base and is fixedly connected to the output end of the motor 1;

[0008] The second adjusting mechanism comprises: a mounting groove, wherein the mounting groove is arranged at the top of the top plate, the inner wall of the mounting groove is connected with a screw rod by a bearing rotation, the outer wall of the screw rod is connected with a slider by a thread, the top of the slider is hinged with a hinge rod, and the other end of the hinge rod is hinged with the bottom of the support plate, a second motor is fixedly installed on the front of the top plate, the front end of the screw rod penetrates the top plate and is fixedly connected with the output end of the second motor, the base and the connecting seat are driven to move vertically by starting the electric hydraulic rod, and the connecting seat drives the top plate and the support plate to move, so as to adjust the support height of the aircraft component, the rotating shaft is driven to rotate by starting the first motor, the rotating shaft drives the connecting seat to rotate, and the connecting seat drives the top plate and the support plate to rotate, so as to drive the aircraft component to flip flexibly, the screw rod is driven to rotate by starting the second motor, the screw rod drives the slider to slide horizontally under the limit of the mounting groove, the slider drives the hinge rod to rotate around the hinge point and push the support plate, so that the support plate rotates around the hinge point, so as to adjust the vertical angle of the aircraft component according to the needs, thereby improving the assembly efficiency.

[0009] Preferably, a clamping mechanism is provided on the support plate, and the clamping mechanism comprises: a fixing plate, the fixing plate is fixedly connected to the top of the support plate, an electric telescopic rod is fixedly installed on the left side of the fixing plate, and a clamping plate is fixedly installed on the piston end of the electric telescopic rod, and the clamping plate is driven to move by starting the electric telescopic rod, so that the two clamping plates move relative to each other to clamp and fix the aircraft components, thereby improving the support stability of the aircraft components.

[0010] Preferably, the clamping plate is arranged in a "U" shape, and a rubber pad is bonded to the inner cavity of the clamping plate. The rubber pad is arranged on the clamping plate to protect the aircraft components and avoid scratches on the surface of the workpiece.

[0011] Preferably, there are two groups of the clamping mechanisms, and the two groups of the clamping mechanisms are arranged opposite to each other on the top of the support plate.

[0012] Preferably, the slider is slidably connected to the inner wall of the mounting groove, and the slider is limited by the mounting groove, so that the rotational movement of the slider is converted into horizontal movement.

[0013] Preferably, universal wheels are provided on the base plate, and there are four universal wheels, which are respectively fixedly mounted at the four bottom corners of the base plate. The universal wheels facilitate movement of the device and improve flexibility.

[0014] Compared with the prior art, the beneficial effects of the utility model are:

[0015] 1. Start the electric hydraulic rod to drive the base and the connecting seat to move vertically, and the connecting seat drives the top plate and the support plate to move, so as to adjust the support height of the aircraft parts. Start the motor 1 to drive the rotating shaft to rotate, the rotating shaft drives the connecting seat to rotate, and the connecting seat drives the top plate and the support plate to rotate, so as to drive the aircraft parts to flip flexibly. Start the motor 2 to drive the screw to rotate, and the screw drives the slider to slide horizontally under the limit of the installation groove. The slider drives the hinge rod to rotate around the hinge point and push the support plate, so that the support plate rotates around the hinge point, so as to adjust the vertical angle of the aircraft parts according to needs, thereby improving the assembly efficiency.

[0016] 2. By starting the electric telescopic rod to drive the clamping plate to move, the two clamping plates can move relative to each other to clamp and fix the aircraft parts, thereby improving the support stability of the aircraft parts. At the same time, rubber pads are set on the clamping plates to protect the aircraft parts and avoid scratches on the workpiece surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0018] Figure 2 It is a left view of the utility model;

[0019] Figure 3 It is a left side cross-sectional view of the top plate in the utility model;

[0020] Figure 4 It is a top view of the utility model.

[0021] In the figure: 1. bottom plate; 2. electric hydraulic rod; 3. base; 4. first adjusting mechanism; 41. rotating shaft; 42. connecting seat; 43. motor 1; 5. top plate; 6. supporting plate; 7. second adjusting mechanism; 71. mounting groove; 72. screw rod; 73. slider; 74. hinge rod; 75. motor 2; 8. clamping mechanism; 81. fixing plate; 82. electric telescopic rod; 83. clamping plate; 84. rubber pad; 9. universal wheel. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] like Figure 1-4As shown, an auxiliary assembly device for aircraft parts includes: a bottom plate 1, an electric hydraulic rod 2 is fixedly installed on the top of the bottom plate 1, a base 3 is fixedly installed on the piston end of the electric hydraulic rod 2, a first adjustment mechanism 4 is arranged on the base 3, a top plate 5 is arranged on the first adjustment mechanism 4, a support plate 6 is hinged on the top of the top plate 5, and a second adjustment mechanism 7 is arranged between the top plate 5 and the support plate 6; the first adjustment mechanism 4 includes: a rotating shaft 41, the rotating shaft 41 is rotatably connected to the inner cavity of the base 3, a connecting seat 42 is fixedly sleeved on the outer wall of the rotating shaft 41, and the top of the connecting seat 42 is fixedly connected to the bottom of the top plate 5, A motor 43 is fixedly installed on the front side of the base 3, and the front end of the rotating shaft 41 passes through the base 3 and is fixedly connected to the output end of the motor 43; the second adjusting mechanism 7 includes: a mounting groove 71, the mounting groove 71 is opened on the top of the top plate 5, the inner wall of the mounting groove 71 is rotatably connected to the screw 72 through a bearing, the outer wall of the screw 72 is threadedly connected to a slider 73, the top of the slider 73 is hinged with a hinge rod 74, and the other end of the hinge rod 74 is hinged to the bottom of the support plate 6, and a motor 2 75 is fixedly installed on the front side of the top plate 5, and the front end of the screw 72 passes through the top plate 5 and is fixedly connected to the output end of the motor 2 75.

[0024] Specifically, the slider 73 is slidably connected to the inner wall of the installation groove 71, and the slider 73 is limited by the installation groove 71, so that the rotational movement of the slider 73 is converted into horizontal movement, and the base 3 and the connecting seat 42 are driven to move vertically by starting the electric hydraulic rod 2, and the connecting seat 42 drives the top plate 5 and the support plate 6 to move, so as to adjust the support height of the aircraft component, and the rotating shaft 41 is driven to rotate by starting the motor 1 43, and the rotating shaft 41 drives the connecting seat 42 to rotate, and the connecting seat 42 drives the top plate 5 and the support plate 6 to rotate, so as to drive the aircraft component to flip flexibly. By starting the second motor 75 to drive the screw rod 72 to rotate, the screw rod 72 drives the slider 73 to slide horizontally under the limit of the installation groove 71, and the slider 73 drives the hinge rod 74 to rotate around the hinge point and push the support plate 6, so that the support plate 6 rotates around the hinge point, so as to adjust the vertical angle of the aircraft parts as needed, thereby improving the assembly efficiency; universal wheels 9 are arranged on the base plate 1, and the number of universal wheels 9 is four, and the four universal wheels 9 are respectively fixedly mounted at the bottom four corners of the base plate 1. The universal wheels 9 are arranged to facilitate the movement of the device and improve the flexibility.

[0025] like Figure 1-4 As shown, a clamping mechanism 8 is provided on the support plate 6, and the clamping mechanism 8 includes: a fixed plate 81, the fixed plate 81 is fixedly connected to the top of the support plate 6, an electric telescopic rod 82 is fixedly installed on the left side of the fixed plate 81, and a clamping plate 83 is fixedly installed on the piston end of the electric telescopic rod 82, the clamping plate 83 is arranged in a "U" shape, and a rubber pad 84 is bonded to the inner cavity of the clamping plate 83.

[0026] Specifically, there are two groups of clamping mechanisms 8, which are relatively arranged on the top of the support plate 6. By starting the electric telescopic rod 82 to drive the clamping plate 83 to move, the two clamping plates 83 are relatively moved to clamp and fix the aircraft components, thereby improving the support stability of the aircraft components. At the same time, rubber pads 84 are arranged on the clamping plates 83 to protect the aircraft components and avoid scratches on the surface of the workpiece.

[0027] Furthermore, the electrical equipment in this embodiment is connected to a control switch, and the above electrical control technologies are all existing technologies, which are not the main innovation of this application and are not described in detail here.

[0028] The working principle of the utility model is as follows: when in use, the aircraft component is placed on the support plate 6, and the clamping plate 83 is driven to move by starting the electric telescopic rod 82, so that the two clamping plates 83 move relative to each other to clamp and fix the aircraft component, and the base 3 and the connecting seat 42 are driven to move vertically by starting the electric hydraulic rod 2, and the connecting seat 42 drives the top plate 5 and the support plate 6 to move, so as to adjust the support height of the aircraft component, and the rotating shaft 41 is driven to rotate by starting the motor 1 43, and the rotating shaft 41 drives the connecting seat 42 to rotate, and the connecting seat 42 drives the top plate 5 and the support plate 6 to rotate, so as to drive the aircraft component to flip flexibly, and the screw rod 72 is driven to rotate by starting the motor 2 75, and the screw 72 drives the slider 73 to slide horizontally under the limit of the installation groove 71, and the slider 73 drives the hinge rod 74 to rotate around the hinge point and push the support plate 6, so that the support plate 6 rotates around the hinge point, so as to adjust the vertical angle of the aircraft component according to needs, thereby improving the assembly efficiency.

[0029] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the utility model and are not used to limit the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection of the utility model is defined by the attached claims and their equivalents.

Claims

1. An aircraft component auxiliary assembly device, characterized in that: include: A bottom plate (1), an electric hydraulic rod (2) is fixedly mounted on the top of the bottom plate (1), a base (3) is fixedly mounted on the piston end of the electric hydraulic rod (2), a first adjustment mechanism (4) is arranged on the base (3), a top plate (5) is arranged on the first adjustment mechanism (4), a support plate (6) is hingedly connected to the top of the top plate (5), and a second adjustment mechanism (7) is arranged between the top plate (5) and the support plate (6); The first adjustment mechanism (4) comprises: a rotating shaft (41), the rotating shaft (41) being rotatably connected to the inner cavity of the base (3), a connecting seat (42) being fixedly sleeved on the outer wall of the rotating shaft (41), and the top of the connecting seat (42) being fixedly connected to the bottom of the top plate (5), a motor 1 (43) being fixedly mounted on the front side of the base (3), and a front end of the rotating shaft (41) passing through the base (3) and being fixedly connected to the output end of the motor 1 (43); The second adjustment mechanism (7) comprises: a mounting groove (71), the mounting groove (71) being opened at the top of the top plate (5), the inner wall of the mounting groove (71) being rotatably connected to a screw rod (72) via a bearing, the outer wall of the screw rod (72) being threadedly connected to a slider (73), the top of the slider (73) being hinged to a hinge rod (74), and the other end of the hinge rod (74) being hinged to the bottom of the support plate (6), a second motor (75) being fixedly mounted on the front surface of the top plate (5), and a front end of the screw rod (72) penetrating the top plate (5) and being fixedly connected to an output end of the second motor (75).

2. The aircraft component auxiliary assembly device according to claim 1, characterized in that: A clamping mechanism (8) is provided on the support plate (6), and the clamping mechanism (8) comprises: a fixing plate (81), the fixing plate (81) being fixedly connected to the top of the support plate (6), an electric telescopic rod (82) being fixedly mounted on the left side of the fixing plate (81), and a clamping plate (83) being fixedly mounted on the piston end of the electric telescopic rod (82).

3. The aircraft component auxiliary assembly device according to claim 2, characterized in that: The clamping plate (83) is arranged in a "U" shape, and a rubber pad (84) is bonded to the inner cavity of the clamping plate (83).

4. The aircraft component auxiliary assembly device according to claim 2, characterized in that: There are two groups of the clamping mechanisms (8), and the two groups of the clamping mechanisms (8) are arranged opposite to each other on the top of the support plate (6).

5. The aircraft component auxiliary assembly device according to claim 1, characterized in that: The sliding block (73) is slidably connected to the inner wall of the mounting groove (71).

6. The aircraft component auxiliary assembly device according to claim 1, characterized in that: Universal wheels (9) are arranged on the bottom plate (1), and there are four universal wheels (9). The four universal wheels (9) are respectively fixedly mounted at the four bottom corners of the bottom plate (1).

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