Large aircraft structural member detection clamp

Abstract

The utility model relates to a large-scale aircraft structural member detection clamp, which comprises a clamping assembly, a motor, a support leg and a carrier table, and is characterized in that through the arrangement of the clamping assembly, if the outer side end surface of a structural member is a non-flat straight surface, the motor can be started, so that a clamping arm swings along with the turning and swinging of a deformation arm, and fastening blocks which are oppositely arranged can perform relative displacement conveniently; when attached to the outer side face of the structural part, the clamping plate is continuously subjected to outer-side tightening pressure, so that fastening effect force is conveniently generated on the structural part, if the outer side end face of the structural part is a flat and straight face, the first electric telescopic rod can be started to generate telescopic movement to drive the clamping plate to move, and after the clamping plate arranged on the opposite face relatively moves, the structural part is conveniently clamped; through cooperation of the hinge shaft, a person can adjust the height of the fastening plate according to the placement position and height of the structural member, so that the end face of one side of the fastening plate can always abut against the structural member, and the structural member placed on the carrying table can be clamped and fastened to be better detected.

Description

Technical Field

[0001] The utility model relates to the technical field of structural component detection, in particular to a large aircraft structural component detection fixture. Background Art

[0002] An airplane is a heavier-than-air aircraft with wings and one or more engines that can fly in the atmosphere by its own power. It can be divided into two categories according to its use: military aircraft and civilian aircraft. With the continuous development of aviation technology and the continuous improvement of aircraft performance, the aircraft manufacturing process is also constantly improving. Aircraft are made of multiple structural components. Before the aircraft is made, the structural parts need to be inspected, and usually a fixture is required to assist in preventing the structural parts from vibrating or falling during the inspection process.

[0003] When optimizing the existing large aircraft structural parts inspection fixtures, most of them are reflected in the convenience of loading and unloading structural parts on the fixture. For example, the Chinese utility model patent with application number CN202021657041.5 discloses "A kind of aircraft structural parts inspection fixture". In this device, a limiting block and an auxiliary block are connected to the side end of the inspection base, so that the tedious loading and unloading process of the structural parts is omitted when the structural parts are sent for inspection. The structural parts are directly fixed on the mobile fixture frame that can be used for inspection, making transportation and inspection easier to operate. At the same time, a plurality of mobile fixture frames with simple structures are provided, so that the structural parts sent for inspection will not pile up and occupy space and damage the structural parts themselves.

[0004] Although the above-mentioned large aircraft structural parts inspection fixture has certain advantages in terms of convenient operation, it still has certain disadvantages: the specifications of aircraft structural parts are diverse, and the clamping end of the fixture and the end face of the structural part that contacts and presses the structural part also need to adapt to the end face of the structural part to produce a greater tightening effect. The fixture in the prior art usually only has a single clamping surface, resulting in different structural parts that need to be clamped and tightened for inspection, and cannot be operated on the same fixture. Utility Model Content

[0005] 1. Technical issues to be solved

[0006] In order to solve the above technical problems, the utility model provides a large aircraft structural component detection fixture.

[0007] (II) Technical solution

[0008] Based on this, the utility model provides the following technical solutions: a large aircraft structural parts inspection fixture, comprising a clamping assembly, a motor, a support leg and a carrier, the support leg being embedded and connected below the carrier, the motor being installed at a lower outer side of the clamping assembly, and the clamping assembly being installed on the side of the carrier and being movably matched; the clamping assembly comprises a frame plate, a screw, an inner chamber, a restraining block, a moving block, a hinge column, a deformation arm and a clamping arm, the screw passing through the side end of the frame plate and rotatingly engaging, the inner chamber being located on the inner side of the frame plate, the restraining block being installed at the front end of the clamping arm, the moving block passing through and meshing with the screw, the side end of the moving block being hinged and movably matched with one end of the deformation arm, the other end of the deformation arm being hinged and matched with the hinge column, the hinge column being fixedly installed at a lower inner position of the inner chamber, and the rear end of the clamping arm being hinged and movably matched with the hinge column and the deformation arm.

[0009] Preferably, the inner chamber includes a guide rail, a mounting nail, a clamping plate and a first electric telescopic rod, the guide rail is installed at the top surface of the inner side of the inner chamber by the mounting nail, the rear end of the first electric telescopic rod is fixedly connected to the rear of the guide rail, and the front end of the first electric telescopic rod is connected to the upper end side of the clamping plate and movably matched.

[0010] Preferably, the clamping plate comprises an upper plate, a restraining plate and a hinge shaft, the upper end surface of the restraining plate is fixedly connected to the bottom of the upper plate, and the restraining plate penetrates and is hingedly matched with the hinge shaft.

[0011] Preferably, the loading platform includes a lifting platform, a fixed platform and a second electric telescopic rod, the lifting platform is located on the inner side of the fixed platform, the second electric telescopic rod is installed inside the fixed platform, and the upper end of the second electric telescopic rod is connected to the bottom of the lifting platform and movably cooperates.

[0012] Preferably, the frame plate is installed on the side of the carrier, and a motor is installed on the outer side of the side end surface of the frame plate. The screw is connected to the output end of the motor by passing through the frame plate and rotatably cooperates. The bottom gap of the restraining block moves on the upper end surface of the carrier, and one side of the frame plate is in an empty opening state. The restraining block has a cylindrical structure and is made of rubber material with good anti-slip properties. The clamping arms are provided at four places and are symmetrically arranged in pairs. The deformation arm deforms with the displacement of the moving block to assist in driving the clamping arm to move, so that the clamping arm can drive the restraining block to better produce a clamping effect force on the curved surface structure on the carrier during deformation.

[0013] Preferably, the mounting nails are embedded and connected to the wall surface of the frame plate, the guide rail gap is installed below the top wall surface of the frame plate, the first electric telescopic rod is telescopic, the clamping plate and the first electric telescopic rod are both provided with two places, and the oppositely arranged clamping plates are synchronously displaced under the telescopic cooperation of the first electric telescopic rod, so as to generate a clamping effect force on the planar structural member.

[0014] Preferably, the side end surface of the upper plate is connected to the front end of the first electric telescopic rod and movably cooperates with it. The restraining plate can be folded with the cooperation of the hinge shaft, and the thickness and height can be changed to facilitate the clamping of structural parts of different specifications.

[0015] Preferably, a frame plate is fixedly connected to the side end of the fixed platform, and the second electric telescopic rod is provided at four locations, which are respectively located at the four corners below the lifting platform. The lifting platform can be adjusted in height with the cooperation of the second electric telescopic rod, so as to facilitate the position change of the structural parts placed on the end surface of the lifting platform and better clamping.

[0016] (III) Beneficial effects

[0017] Compared with the prior art, the utility model provides a large aircraft structural parts inspection fixture, which has the following beneficial effects:

[0018] 1. In a large aircraft structural component inspection fixture, if the outer end face of the structural component is not a straight surface, the motor can be started to drive the screw to rotate, so that the movable block meshing with it can be displaced laterally, driving the position of one side end of the deformation arm to change, and the deformation arm to swing, so that the clamping arm swings with the deformation arm, so that the restraining blocks arranged opposite to each other can be relatively displaced. When the restraining blocks are attached to the outer side of the structural component, they are continuously subjected to tightening pressure from the outside, so as to produce a tightening effect on the structural component.

[0019] 2. This large aircraft structural component inspection fixture, if the outer end face of the structural component is a flat surface, can start the first electric telescopic rod to make it produce telescopic movement to drive the clamp plate to move, after the clamp plates arranged on the opposite sides are relatively displaced, it is convenient to clamp the structural component, and with the help of the hinged shaft, the personnel can adjust the height of the restraining plate according to the placement position and height of the structural component, so that one end face of it can always be pressed against the structural component, so that the structural components placed on the carrier can be clamped and tightened, so as to better carry out the inspection. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0021] Figure 2 It is a structural schematic diagram of the clamping assembly of the utility model;

[0022] Figure 3It is a structural schematic diagram of the inner chamber of the utility model;

[0023] Figure 4 It is a structural schematic diagram of the plywood of the utility model;

[0024] Figure 5 It is a structural schematic diagram of the component carrier of the utility model.

[0025] In the figure: clamping assembly-1, motor-2, supporting leg-3, loading platform-4, frame plate-11, screw-12, inner chamber-13, restraining block-14, moving block-15, hinged column-16, deformation arm-17, clamping arm-18, guide rail-131, mounting nail-132, clamping plate-133, first electric telescopic rod-134, upper plate-331, restraining plate-332, hinge shaft-333, lifting platform-41, fixed platform-42, second electric telescopic rod-43. DETAILED DESCRIPTION

[0026] 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.

[0027] See also Figure 1-2A large aircraft structural component inspection fixture includes a clamping assembly 1, a motor 2, a support leg 3 and a carrier 4, wherein the support leg 3 is embedded and connected below the carrier 4, the motor 2 is installed at the lower outer side of the clamping assembly 1, and the clamping assembly 1 is installed on the side of the carrier 4 and is movably matched; the clamping assembly 1 includes a frame plate 11, a screw rod 12, an inner chamber 13, a restraining block 14, a moving block 15, a hinge column 16, a deformation arm 17 and a clamping arm 18, the screw rod 12 passes through the side end of the frame plate 11 and is rotatably engaged, the inner chamber 13 is located on the inner side of the frame plate 11, the restraining block 14 is installed at the front end of the clamping arm 18, the moving block 15 passes through and meshes with the screw rod 12, the side end of the moving block 15 is hinged and movably matched with one end of the deformation arm 17, and the other end of the deformation arm 17 is hinged and matched with the hinge column 16, and the hinged The column 16 is fixedly installed at the lower position inside the inner chamber 13, the rear end of the clamping arm 18 is hinged and movably matched with the hinge column 16 and the deformation arm 17, the frame plate 11 is installed on the side of the carrier 4, and the motor 2 is installed on the outer side of the side end surface of the frame plate 11, the screw 12 is connected to the output end of the motor 2 by passing through the frame plate 11 and rotates together, the bottom gap of the restraining block 14 is movable on the upper end surface of the carrier 4, and one side of the frame plate 11 is in an empty opening state. The restraining block 14 is in a cylindrical structure and is made of rubber with good anti-slip properties. The clamping arm 18 is provided at four places and is symmetrically arranged in pairs. The deformation arm 17 is deformed with the displacement of the moving block 15, and assists in driving the clamping arm 18 to move, so that the clamping arm 18 can drive the restraining block 14 to better produce a clamping effect force on the curved surface structure on the carrier 4 during deformation.

[0028] See also Figure 3-4A large aircraft structural component inspection fixture, the inner chamber 13 includes a guide rail 131, a mounting nail 132, a clamping plate 133 and a first electric telescopic rod 134, the guide rail 131 is installed at the inner side top surface position of the inner chamber 13 through the mounting nail 132, the rear end of the first electric telescopic rod 134 is fixedly connected to the rear of the guide rail 131, the front end of the first electric telescopic rod 134 is connected to the upper end side of the clamping plate 133 and movably cooperates, the clamping plate 133 includes an upper plate 331, a restraining plate 332 and a hinge shaft 333, the upper end surface of the restraining plate 332 is fixedly connected to the bottom of the upper plate 331, the restraining plate 332 and the hinge shaft 333 are penetrated and hinged The mounting nails 132 are embedded and connected with the wall surface of the frame plate 11, and the guide rails 131 are installed in the gap below the top wall surface of the frame plate 11. The first electric telescopic rod 134 is retractable. The clamping plates 133 and the first electric telescopic rod 134 are each provided with two places. The oppositely arranged clamping plates 133 are synchronously displaced under the telescopic cooperation of the first electric telescopic rod 134, so as to produce a clamping effect force on the planar structural parts. The side end surface of the upper plate 331 is connected to the front end of the first electric telescopic rod 134 and is movably matched. The restraining plate 332 can be folded with the cooperation of the hinge shaft 333, and the thickness and height can be changed, so as to adapt to the clamping of structural parts of different specifications.

[0029] See also Figure 5 A large aircraft structural component inspection fixture, the component carrier 4 includes a lifting platform 41, a fixed platform 42 and a second electric telescopic rod 43. The lifting platform 41 is located on the inner side of the fixed platform 42, and the second electric telescopic rod 43 is installed inside the fixed platform 42. The upper end of the second electric telescopic rod 43 is connected to the bottom of the lifting platform 41 and movably cooperates. The side end of the fixed platform 42 is fixedly connected with a frame plate 11. The second electric telescopic rod 43 is provided with four locations, which are respectively located at the four corners below the lifting platform 41. The lifting platform 41 can be adjusted in height with the cooperation of the second electric telescopic rod 43, which is convenient for the position change of the structural parts placed on the end surface of the lifting platform 41 and is better clamped.

[0030] In summary, when in use, the aircraft structure to be inspected is placed on the carrier 4, and the personnel select a suitable clamping structure according to the shape and specifications of the structure. If the outer end face of the structure is a non-straight surface, the motor 2 can be started to drive the screw 12 to rotate, so that the movable block 15 meshing with it is laterally displaced, driving the position of one side end of the deformable arm 17 to change, and the deformable arm 17 is flipped and changed. The other side end of the deformable arm 17 is hinged to the clamping arm 18 through the hinge column 16, so that the clamping arm 18 swings with the deformation arm 17, so that the oppositely arranged restraining block 14 can be relatively displaced. The columnar shape of the restraining block 14 and its anti-slip properties, when it is attached to the outer side of the structure, is continuously subjected to the outer side The tightening pressure is convenient for the structure. The tightening effect force, if the outer end face of the structural part is a flat surface, the first electric telescopic rod 134 can be started to make it produce telescopic movement and drive the clamping plate 133 to move. After the clamping plates 133 arranged on the opposite surfaces are relatively displaced, the spacing can be flexibly changed, which is convenient for clamping the structural part, and 322 is coordinated by the hinge shaft 333. The personnel can adjust the height of the restraining plate 332 according to the placement position and height of the structural part, so that one end face of it can always be pressed against the structural part. If the structural part is placed on the lifting platform 41 and cannot reach the clamping of the restraining plate 332, the second electric telescopic rod 43 can also be started to make it telescopic and change to drive the lifting platform 41 to move up and down, so that the structural parts placed on the carrier 4 can be clamped and tightened, and better detection can be carried out.

[0031] The control method of the present invention is to control by manually starting and closing the switch. The wiring diagram of the power element and the provision of power supply are common knowledge in the field, and the present invention is mainly used to protect mechanical devices, so the present invention will not explain the control method and wiring arrangement in detail.

[0032] The control method of the present invention is automatic control through a controller. The control circuit of the controller can be realized by simple programming by technicians in this field. The provision of power is also common knowledge in this field. The present invention is mainly used to protect mechanical devices, so the present invention will no longer explain the control method and circuit connection in detail.

[0033] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A large aircraft structural parts inspection fixture, characterized by: The invention comprises a clamping assembly (1), a motor (2), a supporting leg (3) and a workpiece carrier (4), wherein the supporting leg (3) is embedded and connected below the workpiece carrier (4), the motor (2) is installed at a lower position outside the clamping assembly (1), and the clamping assembly (1) is installed on the side of the workpiece carrier (4) and is movably matched; The clamping assembly (1) comprises a frame plate (11), a screw rod (12), an inner chamber (13), a restraining block (14), a moving block (15), a hinge column (16), a deformable arm (17) and a clamping arm (18), wherein the screw rod (12) passes through the side end of the frame plate (11) and is rotatably engaged, the inner chamber (13) is located on the inner side of the frame plate (11), and the restraining block (14) is installed at the front end of the clamping arm (18). The movable block (15) penetrates and meshes with the screw rod (12); the side end of the movable block (15) is hinged and movably matched with one end of the deformable arm (17); the other end of the deformable arm (17) is hinged and movably matched with the hinge column (16); the hinge column (16) is fixedly installed at a lower position inside the inner chamber (13); the rear end of the clamping arm (18) is hinged and movably matched with the hinge column (16) and the deformable arm (17).

2. A large aircraft structural component inspection fixture according to claim 1, characterized in that: The inner chamber (13) comprises a guide rail (131), a mounting nail (132), a clamping plate (133) and a first electric telescopic rod (134); the guide rail (131) is mounted at the top end surface of the inner side of the inner chamber (13) through the mounting nail (132); the rear end of the first electric telescopic rod (134) is fixedly connected to the rear of the guide rail (131); the front end of the first electric telescopic rod (134) is connected to the upper end side surface of the clamping plate (133) and is movably matched.

3. A large aircraft structural component inspection fixture according to claim 2, characterized in that: The clamping plate (133) comprises an upper plate (331), a restraining plate (332) and a hinge shaft (333); the upper end surface of the restraining plate (332) is fixedly connected to the bottom of the upper plate (331); the restraining plate (332) and the hinge shaft (333) penetrate and are hingedly matched.

4. A large aircraft structural component inspection fixture according to claim 1, characterized in that: The loading platform (4) comprises a lifting platform (41), a fixed platform (42) and a second electric telescopic rod (43); the lifting platform (41) is located on the inner side of the fixed platform (42); the second electric telescopic rod (43) is installed inside the fixed platform (42); the upper end of the second electric telescopic rod (43) is connected to the bottom of the lifting platform (41) and is movably matched.

5. A large aircraft structural component inspection fixture according to claim 1, characterized in that: The frame plate (11) is installed on the side of the carrier (4), and a motor (2) is installed on the outer side of the side end surface of the frame plate (11). The screw rod (12) passes through the frame plate (11) and is connected to the output end of the motor (2) and rotates in coordination therewith. The bottom gap of the restraining block (14) moves on the upper end surface of the carrier (4).

6. A large aircraft structural component inspection fixture according to claim 2, characterized in that: The mounting nails (132) are embedded and fixedly connected with the wall surface of the frame plate (11), and the guide rails (131) are installed in a gap below the top wall surface of the frame plate (11).

7. A large aircraft structural component inspection fixture according to claim 3, characterized in that: The side end surface of the upper plate (331) is connected to the front end of the first electric telescopic rod (134) and is movably matched.

8. A large aircraft structural component inspection fixture according to claim 4, characterized in that: The side end of the fixing platform (42) is fixedly connected to a frame plate (11).

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