A device for lifting and positioning a large frame plate of an aircraft and a method of using the device

Abstract

The present invention belongs to the field of aviation assembly, and relates to a device for lifting and positioning a large frame plate of an aircraft and a method for using the device. The device comprises a column, a hand-cranked reducer, a screw assembly, a support and positioning assembly, and a double-slider linear guide; the hand-cranked reducer is fixed on the column, and can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio into the rotational motion in the vertical axis direction. The screw assembly connects the hand-cranked reducer with the support and positioning assembly, and can convert the rotational motion output by the hand-cranked reducer into the linear motion of the support and positioning assembly. The support and positioning assembly is connected to the column by a double-slider linear guide to ensure the accuracy of its own linear motion. By using this lifting and positioning device, the operator can quickly and manually lift the large frame plate of the aircraft over a long distance and stably, and position it at a specific position, which greatly reduces the difficulty of work, greatly improves work efficiency, and greatly reduces labor intensity.

Description

Technical Field

[0001] The invention belongs to the field of aviation assembly, and relates to a device for lifting and positioning a large frame plate of an aircraft and a use method thereof. Background Art

[0002] During the use of the large frame assembly tooling for aircraft, a lifting device is required to lift the large frame of the aircraft and to achieve the requirement of positioning it at a specific position. The lifting and positioning of large frame panels are difficult and demanding. The difficulty of lifting is reflected in the fact that large frame panels are not light in weight, and the lifting distance is long and the lifting process is stable, so it is difficult to achieve the lifting process of large frame panels; the demanding positioning is reflected in the fact that large frame panels are not light in weight and the lifting distance is long, so the lifting device is required to have good rigidity to achieve the positioning accuracy requirements, so the positioning requirements of large frame panels are relatively stringent.

[0003] Currently, the devices used to lift and position large aircraft frames are mostly single-guide rod or double-guide rod structures. The single-guide rod structure occupies a large space and is not easy to slide during use, while the double-guide rod does not slide smoothly and has poor positioning accuracy, which urgently needs to be improved. Summary of the invention

[0004] The purpose of the present invention is to propose a device for lifting and positioning a large aircraft frame and a method of using the device to solve the problem that the large aircraft frame requires a long lifting distance, a stable lifting process and high positioning accuracy.

[0005] The technical solution of the present invention is as follows:

[0006] The lifting and positioning of the large aircraft frame is achieved by a lifting and positioning device, so a lifting and positioning device is designed, which can achieve long-distance and stable lifting of the large aircraft frame and positioning at a specific position. A lifting and positioning device is placed on each side of the large aircraft frame, arranged under the large aircraft frame, and the two lifting and positioning devices are manually coordinated and adjusted to stably and effectively achieve the lifting and positioning of the upper large aircraft frame.

[0007] A device for lifting and positioning a large frame plate of an aircraft, comprising a column, a hand-cranked reducer, a lead screw assembly, a support positioning assembly and a double-slider linear guide;

[0008] The hand-crank reducer is fixed on the column, and can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio into the rotational motion in the vertical axis direction. The lead screw assembly connects the hand-crank reducer with the support and positioning assembly, and can convert the rotational motion output by the hand-crank reducer into the linear motion of the support and positioning assembly. The support and positioning assembly relies on the double-slider linear guide rail to connect with the column to ensure the accuracy of its own linear motion.

[0009] The pillars, such asFigure 2 As shown, it includes a bottom plate, a right side plate, a front plate, a left side plate, a connecting plate and a top plate.

[0010] The right side plate and the left side plate are vertically fixed on the upper surface of the bottom plate. The front plate is fixed between the right side plate and the left side plate, and the connecting plate is fixed on the upper surface of the middle position of the front plate. The top plate is welded to the top of the right side plate and the left side plate. The steel plates are connected by welding to provide physical support for the entire lifting and positioning device.

[0011] The hand-cranked reducer, such as Figure 3 As shown, it includes a handwheel, a worm gear reducer, a handwheel stopper and a stopper screw. The handwheel is fixed to the worm gear reducer through the handwheel stopper and the stopper screw, which can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio to the rotational motion in the vertical axis direction.

[0012] The screw assembly, such as Figure 4 As shown, it includes a bearing support, an end cover screw, a screw, a locking nut, a bearing end cover, a lower spacer, a plane bearing, an upper spacer, a deep groove ball bearing, a nut, a shaft end baffle and a baffle screw. The screw is mounted on the bearing support through two deep groove ball bearings and a plane bearing, and the lower end of the screw is locked by a locking nut. There are upper and lower spacers between the plane bearing and the upper deep groove ball bearing, and between the lower deep groove ball bearing and the locking nut, respectively, to ensure the smooth operation of each bearing. The bearing end cover is pressed on the outer ring of the lower deep groove ball bearing and is fixed to the bearing support by the end cover screw. The screw is connected to the nut by a thread, converting its own rotational motion into the linear motion of the nut. The shaft end baffle is fixed to the screw by the baffle screw, which can limit the nut in the axial direction.

[0013] The support and positioning assembly, such as Figure 5 As shown, it includes a gasket, a bracket screw, a cylindrical pin, a support plate, a bracket, a block nut, a block nut screw, and a threaded pin. The bracket is connected by the cylindrical pin, the bracket screw, the gasket and the support plate; the block nut is fixed to the bracket by the block nut screw; the threaded pin passes through the bracket and is connected to the block nut, which can position and clamp the large frame plate of the aircraft.

[0014] The double-slider linear guide rail, such as Figure 6 As shown, it includes a slider, a slider screw, a linear guide rail and a guide rail screw. The slider is fixed to the column by the slider screw, and the linear guide rail is connected to the support positioning assembly by the guide rail screw, so the slider is immovable relative to the fixed part such as the foundation, while the linear guide rail can move up and down in a vertical direction relative to the fixed part, so this is a reverse installation of the double slider linear guide rail, which ensures the accuracy of the linear motion of the support positioning assembly.

[0015] A method for using a device for lifting and positioning a large frame plate of an aircraft, the steps are as follows:

[0016] Step 1: If Figure 7 As shown, two lifting and positioning devices are arranged in left-right symmetrical positions under the large frame of the aircraft.

[0017] Step 2: The large frame of the aircraft needs to be connected to the two lifting positioning devices before lifting. The threaded pins in the support positioning assembly pass through the two positioning holes on the large frame of the aircraft and are fixed to the support positioning assembly, thereby limiting the five degrees of freedom of the large frame of the aircraft, leaving only the degree of freedom of movement in the normal direction of the large frame of the aircraft.

[0018] Step 3: When it is necessary to lift the large frame of the aircraft, shake the hand wheels in the hand-cranked reducers on the left and right sides at a constant speed at the same time, so that the support and positioning components on the left and right sides rise at a constant speed along the double-slider linear guide rails, lift the large frame of the aircraft up, and complete the lifting.

[0019] Step 4: When the large frame plate of the aircraft needs to be positioned, the nut in the screw assembly just moves to the upper limit position in contact with the shaft end baffle, completing the positioning of the large frame plate of the aircraft in the height direction. The reason why the large frame plate of the aircraft is exactly in the position to be positioned when the nut in the screw assembly moves to the upper limit position in contact with the shaft end baffle is that when installing the support positioning assembly, the position is positioned by relying on the laser tracker and the optical measuring ball, and then the nut in the screw assembly is rotated to the upper limit position in contact with the shaft end baffle, and then the nut in the screw assembly and the positioning hole connected to the support plate in the support positioning assembly are matched, and the two parts are connected with fasteners, so as to achieve that when the nut in the screw assembly moves to the upper limit position in contact with the shaft end baffle, the large frame plate of the aircraft is exactly in the position to be positioned.

[0020] Beneficial effects of the present invention:

[0021] By using this lifting and positioning device, operators can manually lift large aircraft frames quickly and stably over long distances and position them at specific positions, which greatly reduces the difficulty of work, improves work efficiency, and reduces labor intensity. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural diagram of the lifting and positioning device of the present invention;

[0023] Figure 2 It is a structural diagram of a column of the present invention;

[0024] Figure 3 It is a structural diagram of the hand-cranked reducer of the present invention;

[0025] Figure 4 It is a structural diagram of the lead screw assembly of the present invention;

[0026] Figure 5 is a structural diagram of the support and positioning assembly of the present invention;

[0027] Figure 6 It is a structural diagram of the double-slider linear guide of the present invention;

[0028] Figure 7 It is a schematic diagram of the overall use of the present invention.

[0029] In the figure: 1-lifting positioning device; 2-column; 3-hand-cranked reducer; 4-screw assembly; 5-support positioning assembly; 6-double-slider linear guide; 7-bottom plate; 8-right side plate; 9-front plate; 10-left side plate; 11-connecting plate; 12-top plate; 13-handwheel; 14-worm gear reducer; 15-handwheel stopper; 16-stopper screw; 17-bearing support; 18-end cover screw; 19-screw; 20-locking nut ; 21-bearing end cover; 22-lower spacer; 23-plane bearing; 24-upper spacer; 25-deep groove ball bearing; 26-nut; 27-shaft end baffle; 28-baffle screw; 29-gasket; 30-bracket screw; 31-cylindrical pin; 32-support plate; 33-bracket; 34-block nut; 35-block nut screw; 36-threaded pin; 37-slider; 38-slider screw; 39-linear guide; 40-guide screw. DETAILED DESCRIPTION

[0030] The technical solution of the present invention will be further described below in conjunction with specific embodiments and drawings.

[0031] Embodiment 1:

[0032] A device for lifting and positioning a large frame plate of an aircraft, comprising: a column 2, a hand-cranked reducer 3, a lead screw assembly 4, a support and positioning assembly 5 and a double-slider linear guide 6;

[0033] The hand-crank reducer 3 is fixed on the column 2, and can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio into the rotational motion in the vertical axis direction. The lead screw assembly 4 connects the hand-crank reducer 3 with the support and positioning assembly 5, and can convert the rotational motion output by the hand-crank reducer 3 into the linear motion of the support and positioning assembly 5. The support and positioning assembly 5 is connected to the column 2 by a double-slider linear guide 6 to ensure the accuracy of its own linear motion.

[0034] The column 2, such as Figure 2 As shown, it includes a bottom plate 7, a right side plate 8, a front plate 9, a left side plate 10, a connecting plate 11 and a top plate 12.

[0035] The right side plate 8 and the left side plate 10 are vertically fixed on the upper surface of the bottom plate 7. The front plate 9 is fixed between the right side plate 8 and the left side plate 10, and the connecting plate 11 is fixed on the upper surface of the middle position of the front plate 9. The top plate 12 is welded to the top of the right side plate 8 and the left side plate 10. The steel plates are connected by welding to provide physical support for the entire lifting and positioning device 1.

[0036] The hand-cranked reducer 3, as Figure 3 As shown, it includes a handwheel 13, a worm gear reducer 14, a handwheel stopper 15 and a stopper screw 16. The handwheel 13 is fixed to the worm gear reducer 14 through the handwheel stopper 15 and the stopper screw 16, which can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio to the rotational motion in the vertical axis direction.

[0037] The screw assembly 4, as Figure 4 As shown, it includes a bearing support 17, an end cover screw 18, a screw 19, a locking nut 20, a bearing end cover 21, a lower spacer 22, a plane bearing 23, an upper spacer 24, a deep groove ball bearing 25, a nut 26, a shaft end baffle 27 and a baffle screw 28. The screw 19 is mounted on the bearing support 17 through two deep groove ball bearings 25 and a plane bearing 23, and the lower end of the screw 19 is locked by the locking nut 20. There are upper spacers 24 and lower spacers 22 between the plane bearing 23 and the upper deep groove ball bearing 25, and between the lower deep groove ball bearing 25 and the locking nut 20, respectively, to ensure the smooth operation of each bearing. The bearing end cover 21 is pressed on the outer ring of the lower deep groove ball bearing 25 and fixed on the bearing support 17 by the end cover screw 18. The screw 19 is connected to the nut 26 through a thread, and its own rotational motion is converted into the linear motion of the nut 26. The shaft end baffle 27 is fixed to the screw rod 19 by a baffle screw 28, so as to limit the position of the nut 26 in the axial direction.

[0038] The support and positioning assembly 5, such as Figure 5 As shown, it includes a washer 29, a bracket screw 30, a cylindrical pin 31, a support plate 32, a bracket 33, a block nut 34, a block nut screw 35, and a threaded pin 36. The bracket 33 is connected by the cylindrical pin 31, the bracket screw 30, the washer 29 and the support plate 32; the block nut 34 is fixed to the bracket 33 by the block nut screw 35; the threaded pin 36 passes through the bracket 33 and is connected to the block nut 34, which can position and clamp the large frame plate of the aircraft.

[0039] The double-slider linear guide 6, as Figure 6As shown, it includes a slider 37, a slider screw 38, a linear guide 39 and a guide screw 40. The slider 37 is fixed to the column 2 by the slider screw 38, and the linear guide 39 is connected to the support positioning component 5 by the guide screw 40, so the slider 37 is immovable relative to the fixed part such as the foundation, while the linear guide 39 can perform vertical linear motion relative to the fixed part, so this belongs to the reverse installation of the double slider linear guide 6, which ensures the accuracy of the linear motion of the support positioning component 5.

[0040] Embodiment 2:

[0041] A method for using a device for lifting and positioning a large frame plate of an aircraft, the steps are as follows:

[0042] Step 1: If Figure 7 As shown, two lifting and positioning devices 1 are arranged at left-right symmetrical positions under the large frame of the aircraft.

[0043] Step 2: The large aircraft frame must be connected to the two lifting positioning devices 1 before lifting. The threaded pin 36 in the support positioning assembly 5 passes through the two positioning holes on the large aircraft frame and is fixed to the support positioning assembly 5, thereby limiting the five degrees of freedom of the large aircraft frame, leaving only the degree of freedom of movement in the normal direction of the large aircraft frame.

[0044] Step 3: When it is necessary to lift a large frame of an aircraft, the hand wheels 13 in the hand-cranked reducers 3 on both sides are shaken at a constant speed at the same time, so that the support and positioning components 5 on both sides rise at a constant speed along the double-slider linear guide rails 6, lifting the large frame of the aircraft to move up and complete the lifting.

[0045] Step 4: When the large frame plate of the aircraft needs to be positioned, the nut 26 in the screw assembly 4 just moves to the upper limit position in contact with the shaft end baffle 27, completing the positioning of the large frame plate of the aircraft in the height direction. The reason why the large frame plate of the aircraft is exactly in the position to be positioned when the nut 26 in the screw assembly 4 moves to the upper limit position in contact with the shaft end baffle 27 is that when the support positioning assembly 5 is installed, its position is positioned by relying on the laser tracker and the optical measuring ball, and then the nut 26 in the screw assembly 4 is rotated to the upper limit position in contact with the shaft end baffle 27, and then the nut 26 in the screw assembly 4 and the positioning hole connected to the support plate 32 in the support positioning assembly 5 are matched, and the two parts are connected with fasteners, so as to achieve that when the nut 26 in the screw assembly 4 moves to the upper limit position in contact with the shaft end baffle 27, the large frame plate of the aircraft is exactly in the position to be positioned.

Claims

1. A lifting and positioning device, characterized in that: Used for lifting and positioning a large frame plate of an aircraft, the lifting and positioning device (1) comprises a column (2), a hand-cranked reducer (3), a lead screw assembly (4), a supporting and positioning assembly (5) and a double-slider linear guide rail (6); The hand-cranked reducer (3) is fixed on the column (2) and can realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio into the rotational motion in the vertical axis direction; the lead screw assembly (4) connects the hand-cranked reducer (3) and the support and positioning assembly (5) and can convert the rotational motion output by the hand-cranked reducer (3) into the linear motion of the support and positioning assembly (5); the support and positioning assembly (5) is connected to the column (2) by a double-slider linear guide rail (6) to ensure the accuracy of its own linear motion; The hand-cranked reducer (3) comprises a hand wheel (13), a worm gear reducer (14), a hand wheel stop pad (15) and a stop pad screw (16); the hand wheel (13) is fixed to the worm gear reducer (14) via the hand wheel stop pad (15) and the stop pad screw (16), so as to realize the conversion of the hand-cranked rotational motion in the horizontal axis direction with a large reduction ratio into the rotational motion in the vertical axis direction; The screw assembly (4) comprises a bearing support (17), an end cover screw (18), a screw (19), a locking nut (20), a bearing end cover (21), a lower spacer (22), a plane bearing (23), an upper spacer (24), a deep groove ball bearing (25), a nut (26), an end baffle (27) and a baffle screw (28); the screw (19) is mounted on the bearing support (17) via two deep groove ball bearings (25) and a plane bearing (23), and the lower end of the screw (19) is locked via a locking nut (20); between the plane bearing (23) and the upper deep groove ball bearing, a locking nut (20) is provided. An upper spacer (24) and a lower spacer (22) are respectively arranged between the bearings (25) and between the lower deep groove ball bearing (25) and the locking nut (20) to ensure smooth operation of each bearing; the bearing end cover (21) is pressed on the outer ring of the lower deep groove ball bearing (25) and is fixed to the bearing support (17) by the end cover screw (18); the screw rod (19) is connected to the nut (26) by a thread to convert its own rotational motion into a linear motion of the nut (26); the shaft end baffle (27) is fixed to the screw rod (19) by the baffle screw (28) to achieve the limitation of the nut (26) in the axial direction; The double-slider linear guide (6) comprises a slider (37), a slider screw (38), a linear guide (39) and a guide screw (40); the slider (37) is fixed to the column (2) by the slider screw (38), and the linear guide (39) is connected to the support positioning assembly (5) by the guide screw (40), so the slider (37) is stationary relative to the fixed part of the foundation, while the linear guide (39) can perform vertical linear motion up and down relative to the fixed part, so this belongs to the reverse installation of the double-slider linear guide (6), which ensures the accuracy of the linear motion of the support positioning assembly (5).

2. A lifting and positioning device according to claim 1, characterized in that: The support positioning assembly (5) comprises a gasket (29), a bracket screw (30), a cylindrical pin (31), a support plate (32), a bracket (33), a block nut (34), a block nut screw (35), and a threaded pin (36); the bracket (33) is connected by the cylindrical pin (31), the bracket screw (30), the gasket (29) and the support plate (32); the block nut (34) is fixed to the bracket (33) by the block nut screw (35); the threaded pin (36) passes through the bracket (33) and is connected to the block nut (34), so as to position and clamp a large frame plate of an aircraft.

3. A lifting and positioning device according to claim 1 or 2, characterized in that: The column (2) includes a bottom plate (7), a right side plate (8), a front plate (9), a left side plate (10), a connecting plate (11) and a top plate (12); the right side plate (8) and the left side plate (10) are vertically fixed on the upper surface of the bottom plate (7); the front plate (9) is fixed between the right side plate (8) and the left side plate (10), and the connecting plate (11) is fixed on the upper surface of the middle position of the front plate (9); the top plate (12) is welded to the top of the right side plate (8) and the left side plate (10); the steel plates are connected by welding to provide physical support for the entire lifting and positioning device (1).

4. A method for using the lifting and positioning device according to any one of claims 1 to 3, characterized in that: Here are the steps: Step 1: Arrange two lifting and positioning devices (1) at left-right symmetrical positions under the large frame of the aircraft; Step 2: The large aircraft frame plate needs to be connected to the two lifting positioning devices (1) before lifting; the threaded pin (36) in the support positioning assembly (5) passes through the two positioning holes on the large aircraft frame plate and is fixed to the support positioning assembly (5), thereby limiting the five degrees of freedom of the large aircraft frame plate, leaving only the degree of freedom of movement in the normal direction of the large aircraft frame plate; Step 3: When it is necessary to lift the large frame of the aircraft, the hand wheels (13) in the hand-cranked reducers (3) on both sides are simultaneously shaken at a constant speed, so that the support and positioning components (5) on both sides are raised at a constant speed along the double-slider linear guide rails (6), and the large frame of the aircraft is lifted up to complete the lifting; Step 4: When the large frame plate of the aircraft needs to be positioned, the nut (26) in the screw assembly (4) is just moved to the upper limit position in contact with the shaft end baffle (27), thereby completing the positioning of the large frame plate of the aircraft in the height direction; the reason why the large frame plate of the aircraft is just in the position to be positioned when the nut (26) in the screw assembly (4) is moved to the upper limit position in contact with the shaft end baffle (27) is that when the support positioning assembly (5) is installed, its position is positioned by relying on a laser tracker and an optical measuring ball, and then the nut (26) in the screw assembly (4) is rotated to the upper limit position in contact with the shaft end baffle (27), and then the positioning hole connecting the nut (26) in the screw assembly (4) and the support plate (32) in the support positioning assembly (5) is matched, and the two parts are connected by fasteners, so that when the nut (26) in the screw assembly (4) is moved to the upper limit position in contact with the shaft end baffle (27), the large frame plate of the aircraft is just in the position to be positioned.

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