Spacecraft skin riveting device

Abstract

The utility model provides a device for riveting a spacecraft skin, and belongs to the technical field of spacecraft manufacturing. The device is flexible and stable in structure, has a bearing function, is good in adsorption effect, is convenient to use and operate, and improves the processing efficiency. A bracket of the device is slidably sleeved on a cross beam, two ends of the cross beam are respectively sleeved with hooking assemblies, two sliding rails are arranged in parallel, the two hooking assemblies are slidably hung on the two sliding rails, the cross beam is erected between the two sliding rails, the bracket is located in an area clamped by the two sliding rails, and the end parts of the upper end and the lower end of each sliding rail are respectively provided with a fixing assembly. The four fixing assemblies are all arranged on the outer wall of the spacecraft in an adsorption mode, and the working end of the riveting gun is supported and inserted into the supporting ring of the bracket. The device can share the weight of the riveting gun, the workload of an operator is relieved, the working efficiency is improved, all parts of the device can be detachably and fixedly installed, layout is flexible, adaptability is high, and use is convenient.

Description

TECHNICAL FIELD

[0001] The utility model belongs to spacecraft manufacturing technical field, especially relate to a spacecraft skin riveting device. BACKGROUND

[0002] In order to resist the huge pressure load of launching flight, the skin of spacecraft is fixed in the form of riveting, and in the implementation process of riveting procedure, the operator holds rivet gun and rivets one by one to the preset hole, and in the process of processing procedure, the operator needs to always hold the rivet gun, because the spacecraft is large in size, and the rivet applied specifically needs high strength, so the rivet applied specifically is generally large in size, and the volume and mass of rivet gun matched are also large, in the specific riveting procedure, the operator's overall labor intensity is great, and it is difficult to realize continuous operation, resulting in great processing difficulty and low processing efficiency. UTILITY MODEL CONTENTS

[0003] In order to solve the problems in the above background art, the utility model provides a spacecraft skin riveting device, which has flexible and stable structure, supporting function, good adsorption effect, convenient use and operation and improved processing efficiency.

[0004] The utility model solves technical scheme adopted by technical problems: a spacecraft skin riveting device, including sliding rail, crossbeam, bracket, hooking assembly and fixed assembly, the bracket is slidably sleeved on the crossbeam, the both ends of the crossbeam are respectively sleeved hooking assembly, two sliding rails are parallelly arranged, two hooking assemblies are slidably hung on two sliding rails, that is, the crossbeam is hung between two sliding rails, and the bracket is located in the region clamped by two sliding rails, the upper and lower ends of each sliding rail are detachably fixed with fixed assembly, four fixed assemblies are adsorbed on the outer wall of spacecraft, and the working end of rivet gun is supported and inserted into the supporting ring of the bracket.

[0005] The upper end of the bracket is provided with a sliding sleeve, and the supporting ring is fixedly arranged at the lower end of the sliding sleeve, and the axis of the sliding sleeve is perpendicular to the outer wall of the spacecraft, the sliding sleeve is sleeved on the crossbeam, a threaded hole one is formed in the sliding sleeve, and a jackscrew is screwed in the threaded hole one.

[0006] Each sliding rail comprises a plurality of series connection blocks, and the series connection blocks are sequentially hingedly connected end to end, and the longitudinal section of each series connection block is T-shaped, that is, the sliding rail is T-shaped rail, and the two hooking assemblies are buckled on the side walls of the two sliding rails away from each other.

[0007] Each of the hooking assemblies comprises a sleeve seat, two telescopic legs and two pulleys, a through hole is arranged on the sleeve seat in the transverse direction, the crossbeam is arranged in the through hole, two screw holes are arranged on the hole wall of the through hole, a top pin is screwed in the screw holes, the two telescopic legs are hingedly arranged on the end face of the sleeve seat close to the spacecraft, the two pulleys are rotatably arranged on the movable ends of the two telescopic legs, and the two pulleys are embedded in the groove surrounded by the sliding rail and the outer wall of the spacecraft.

[0008] The two telescopic legs are both hydraulic rods, the lengths of the two telescopic legs are adjustable, and the included angle between the two telescopic legs is adjustable, that is, the distance between the two pulleys is adjustable.

[0009] Each of the fixing assemblies comprises a positioning block, two air pumps and two silica gel suction cups, a T-shaped groove is formed on the positioning block and is matched with the sliding rail, the positioning block is sleeved on the sliding rail through the T-shaped groove, a screw hole three is formed in the positioning block and penetrates the T-shaped groove, a top pin is screwed in the screw hole three, the two air pumps are embedded on the end face of the spacecraft close to the positioning block, the two air pumps are located on the two sides of the T-shaped groove, and the silica gel suction cups are fixedly arranged on the air nozzles of the two air pumps.

[0010] The front ends of the upper and lower end faces of each of the stringing blocks are provided with slope surfaces, the two slope surfaces have the same inclination angle and intersect at the front ends to form a sharp corner, a pin hole one is arranged on the sharp corner in the transverse direction, a notch groove is arranged at the rear end of each of the stringing blocks, a pin hole two is arranged at the included angle of the notch groove in cooperation with the pin hole one, a pin shaft is arranged in cooperation between the pin hole one and the pin hole two, the upper inclined surface of the notch groove has the same inclination angle as the upper slope surface of the sharp corner, and the lower inclined surface of the notch groove has an inclination angle greater than that of the lower slope surface of the sharp corner, that is, a gap is formed between the lower inclined surface and the lower slope surface.

[0011] The device is provided with the sliding rail, the crossbeam and the bracket, the gravity required for lifting the rivet gun by the operator is shared, the work burden of the operator is reduced, and the work efficiency is indirectly improved; the sliding rail of the device is arranged in a detachable fixed mounting mode by the fixing assembly, the sliding rail is stable in installation and layout, position adjustment and change can be flexibly performed, and the device is convenient to use; the sliding rail of the device is formed by being hingedly connected by the plurality of stringing blocks, can be straightened and can be bent to be attached to the outer wall of the spacecraft, can be applied to the skin riveting processing of various spacecrafts, and has good adaptive performance. BRIEF DESCRIPTION OF DRAWINGS

[0012] In the drawings:

[0013] Figure 1 is a schematic diagram of overall application effects of the device;

[0014] Figure 2 is a schematic diagram of installation effects of the hooking assembly;

[0015] Figure 3 is Figure 2 is a partial enlarged view of A part in figure 1;

[0016] Figure 4 is a schematic diagram of the fixed assembly structure of the utility model;

[0017] Figure 5 is a schematic diagram of the straightening effect of the sliding rail of the utility model;

[0018] Figure 6 is a schematic diagram of the bending effect of the sliding rail of the utility model;

[0019] Figure 7 is a schematic diagram of the stringing block structure of the utility model Figure 1 (rear end structure schematic diagram);

[0020] Figure 8 is a schematic diagram of the stringing block structure of the utility model Figure 2 (front end structure schematic diagram);

[0021] In the figure: 1, sliding rail; 2, crossbeam; 3, bracket; 4, hooking assembly; 5, jackscrew; 6, fixed assembly; 7, spacecraft; 11, stringing block; 31, sliding sleeve; 32, supporting ring; 41, sleeving seat; 42, telescopic leg; 43, pulley; 61, positioning block; 62, air pump; 63, silica gel suction cup. DETAILED DESCRIPTION

[0022] The utility model will be further explained in detail in combination with the drawings. The drawings are all simplified schematic diagrams, and only illustrate the basic structure of the utility model in a schematic manner, so they only show the components related to the utility model.

[0023] A spacecraft skin riveting device, comprising sliding rails 1, crossbeams 2, brackets 3, hooking assemblies 4 and fixed assemblies 6, the bracket 3 is slidably sleeved on the crossbeam 2, the two ends of the crossbeam 2 are sleeved with hooking assemblies 4 respectively, the two sliding rails 1 are arranged in parallel, the two hooking assemblies 4 are slidably hung on the two sliding rails 1, that is, the crossbeam 2 is hung between the two sliding rails 1, and the bracket 3 is located in the region clamped by the two sliding rails 1, the upper and lower ends of each sliding rail 1 are detachably fixed with fixed assemblies 6, the four fixed assemblies 6 are all attached to the outer wall of the spacecraft 7, the working end of the rivet gun is inserted into the supporting ring 32 of the bracket 3, when the spacecraft 7 is riveted, the working end of the rivet gun is inserted into the supporting ring 32, according to the riveting position, the bracket 3 can be dragged to move to the corresponding position, and at the same time, the crossbeam 2 can slide freely along the sliding rail 1 by relying on the hooking assembly 4.

[0024] The bracket 3 upper end is provided with a sliding sleeve 31, and a supporting ring 32 is fixedly arranged at the lower end of the sliding sleeve 31. The axis of the sliding sleeve 31 is perpendicular to the outer wall of the spacecraft 7. The sliding sleeve 31 is sleeved on the cross beam 2. A threaded hole one penetrating the inner and outer walls of the sleeve is formed in the sliding sleeve 31. A jackscrew 5 is screwed in the threaded hole one. When the jackscrew 5 is screwed in the threaded hole one, the bracket 3 is locked in position on the cross beam 2. When the jackscrew 5 is unscrewed from the threaded hole one, the bracket 3 can slide freely along the cross beam 2. After the jackscrew 5 on the sliding sleeve 31 is screwed, the bracket 3 is locked in position on the cross beam 2. At this time, the rivet gun is moved to pull the cross beam 2 to adjust the sliding position along the sliding rail 1.

[0025] Each of the sliding rails 1 comprises a plurality of serially connected blocks 11. The plurality of serially connected blocks 11 are sequentially hingedly connected end to end. The longitudinal section of each of the serially connected blocks 11 is T-shaped, that is, the sliding rail 1 is a T-shaped rail. Two hooking assemblies 4 are respectively buckled at the side walls of the two sliding rails 1 away from each other.

[0026] Each of the hooking assemblies 4 comprises a sleeved seat 41, two telescopic legs 42 and two pulleys 43. A through hole is arranged on the sleeved seat 41 in the transverse direction. The cross beam 2 is sleeved in the through hole. A threaded hole two penetrating the hole wall is arranged on the hole wall of the through hole. A jackscrew 5 is screwed in the threaded hole two. When the jackscrew 5 is screwed in the threaded hole two, the sleeved seat 41 is locked in position on the cross beam 2. When the jackscrew 5 is unscrewed from the threaded hole two, the sleeved seat 41 can be adjusted in position on the cross beam 2. The two telescopic legs 42 are hingedly connected to the end face of the sleeved seat 41 close to the spacecraft 7. The two pulleys 43 are rotatably installed on the movable ends of the two telescopic legs 42. The two pulleys 43 are embedded in the groove surrounded by the sliding rail 1 and the outer wall of the spacecraft 7.

[0027] The two telescopic legs 42 are selected from hydraulic rods. The lengths of the two telescopic legs 42 are adjustable. The included angle between the two telescopic legs 42 is adjustable, that is, the distance between the two pulleys 43 is adjustable. The distance between the two pulleys 43 is adjusted to adapt to the bending degree of the sliding rail 1. At this time, the lengths of the telescopic legs 42 are adjusted to adapt.

[0028] Each of the pulleys 43 is made of rubber material. The rolling resistance is large, and the pulley 43 will not slide randomly. At the same time, the pulley 43 will not damage the skin of the spacecraft 7.

[0029] Each of the fixing assemblies 6 comprises a positioning block 61, two air pumps 62 and two silica gel suction cups 63, a T-shaped groove similar to the sliding rail 1 is formed on each positioning block 61, the positioning block 61 is sleeved on the sliding rail 1 through the T-shaped groove, three threaded holes penetrating through the T-shaped groove are formed on the positioning block 61, a jackscrew 5 is screwed in each threaded hole, the jackscrew 5 in the threaded hole can lock the position of the positioning block 61 on the sliding rail 1, and the sleeved seat 41 can be freely adjusted in position when the jackscrew 5 in the threaded hole is unscrewed; the positioning block 61 is embedded on the end face of the spacecraft 7 and two air pumps 62 are arranged on the two sides of the T-shaped groove, the silica gel suction cups 63 are fixedly arranged on the air nozzles of the two air pumps 62, the two silica gel suction cups 63 are tightly adsorbed on the outer wall of the spacecraft 7 when the air pump 62 is operated to perform air pumping, so that the fixing assembly 6 is stably adsorbed on the outer wall of the spacecraft 7, and the sliding rail 1 is stably fixed on the spacecraft 7.

[0030] The front end of each of the stringing blocks 11 is provided with a slope face, the two slope faces have the same inclination angle and intersect at the front end to form a sharp angle, a pin hole one is arranged at the sharp angle in the transverse direction, a notch groove is arranged at the rear end of each of the stringing blocks 11, a pin hole two is arranged at the intersection of the notch groove, a pin shaft is arranged in the matched pin hole one and the pin hole two, the upper inclined surface of the notch groove has the same inclination angle as the upper slope face of the sharp angle, and the lower inclined surface of the notch groove has an inclination angle greater than that of the lower slope face of the sharp angle, that is, a gap is formed between the lower inclined surface and the lower slope face, so that the bending function of the sliding rail 1 is realized.

[0031] Working principle: the two sliding rails 1 are arranged in parallel on the two sides of the position to be riveted by using the fixing assemblies 6, the jackscrews 5 on the fixing assemblies 6 are tightened to stably connect the fixing assemblies 6 and the sliding rails 1, the cross beam 2 with the bracket 3 is arranged between the two sliding rails 1 by using the two hooking assemblies 4, and the jackscrews 5 on the hooking assemblies 4 are tightened to stably arrange the cross beam 2 between the two sliding rails 1. When the plurality of fixing assemblies 6 are fixed in position, the plurality of air pumps 62 are operated, and the plurality of silica gel suction cups 63 are tightly adsorbed on the outer wall of the spacecraft 7, so that the detachable fixing and mounting of the sliding rail 1 are realized.

[0032] When the riveting process is performed, the front end of the rivet gun is inserted into the supporting ring 32, and the rivet holes to be riveted are arranged in the vertical direction, for example, the operator holds the handle of the rivet gun at one end to align the line of the rivet hole, and then tightens the jackscrew on the bracket 3 to keep the bracket 3 fixed on the cross beam 2, at this time, the rivet gun is moved from top to bottom or from bottom to top along the vertical direction, and the riveting of the rivet hole is completed one by one. Because the pulley 43 is made of rubber material, the pulley 43 has a certain friction with the sliding rail 1 and the skin, so the cross beam 2 will not slide arbitrarily under the influence of gravity, and the movement of the rivet gun can be moved by pulling the cross beam 2 through the bracket 3, the cross beam 2 and the bracket 3 share the weight of the rivet gun, thereby reducing the lifting burden of the operator and improving the processing efficiency. If the multiple rivet holes to be riveted are distributed horizontally, the sliding rail 1 can be arranged horizontally.

[0033] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can be variously changed and modified. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A device for riveting a spacecraft skin, characterized by: The utility model provides a kind of rivet gun's support device, including sliding rail (1), crossbeam (2), bracket (3), hook assembly (4) and fixed assembly (6), the bracket (3) slidingly covers in crossbeam (2), the both ends of crossbeam (2) are covered hook assembly (4) respectively, two sliding rail (1) are arranged in parallel, two hook assembly (4) slidingly hang in two sliding rail (1), that is, crossbeam (2) is hung between two sliding rail (1), and bracket (3) is located in the region of two sliding rail (1) clamping, the end of each sliding rail (1) can be detachably fixed and arranged fixed assembly (6) on upper and lower ends, four fixed assembly (6) are adsorbed and arranged on the outer wall of spacecraft (7), and the working end of rivet gun is supported and inserted in the support ring (32) of bracket (3).

2. A device for riveting a spacecraft skin as defined in claim 1, characterized in that: The upper end of the bracket (3) is provided with a sliding sleeve (31), and the support ring (32) is fixedly arranged at the lower end of the sliding sleeve (31). The axis of the sliding sleeve (31) is perpendicular to the outer wall of the spacecraft (7). The sliding sleeve (31) is sleeved on the crossbeam (2), and a threaded hole one penetrating the inner and outer walls of the sleeve is formed in the sliding sleeve (31). A jackscrew (5) is screwed into the threaded hole one.

3. A device for riveting a spacecraft skin as defined in claim 2, characterized in that: Each of the sliding rails (1) includes a plurality of serially connected blocks (11). The plurality of serially connected blocks (11) are sequentially hingedly connected end to end. The longitudinal section of each of the serially connected blocks (11) is T-shaped, i.e., the sliding rail (1) is T-shaped as a whole. The two hook assemblies (4) are respectively buckled at the side walls of the two sliding rails (1) away from each other.

4. A device for riveting a spacecraft skin as defined in claim 3, characterized in that: Each of the hook assemblies (4) includes a sleeved seat (41), two telescopic legs (42), and two pulleys (43). A through hole is formed in the sleeved seat (41) in the transverse direction. The crossbeam (2) is inserted into the through hole. Threaded holes two penetrating the hole walls are formed in the hole walls of the through hole. A jackscrew (5) is screwed into each of the threaded holes two. The two telescopic legs (42) are hingedly connected to the end face of the sleeved seat (41) close to the spacecraft (7). The two pulleys (43) are rotatably installed on the movable ends of the two telescopic legs (42). The two pulleys (43) are embedded in the grooves enclosed by the sliding rail (1) and the outer wall of the spacecraft (7).

5. A device for riveting a spacecraft skin as defined in claim 4, wherein: The two telescopic legs (42) are hydraulic rods. The lengths of the two telescopic legs (42) are adjustable. The included angle between the two telescopic legs (42) is adjustable, i.e., the distance between the two pulleys (43) is adjustable.

6. A device for riveting a spacecraft skin as defined in claim 4, wherein: Each of the fixed assemblies (6) includes a positioning block (61), two air pumps (62), and two silica gel suction cups (63). A T-shaped groove similar to the shape of the sliding rail (1) is formed in each of the positioning blocks (61). The positioning block (61) is sleeved on the sliding rail (1) through the T-shaped groove. Threaded holes three penetrating the T-shaped groove are formed in the positioning block (61). A jackscrew (5) is screwed into each of the threaded holes three. The positioning block (61) is embedded with the two air pumps (62) on the end face of the spacecraft (7). The two air pumps (62) are located on the two sides of the T-shaped groove. The silica gel suction cups (63) are fixedly arranged on the air nozzles of the two air pumps (62).

7. A device for riveting a spacecraft skin as claimed in claim 3 or claim 6, wherein: The front end of each said stringing block (11) is provided with a slope surface, the two slope surfaces have the same inclination angle and intersect at the front end to form a sharp angle, a pin hole one is arranged along the transverse direction at the sharp angle, the rear end of each said stringing block (11) is provided with a notched groove, a pin hole two is arranged at the included angle of the notched groove in cooperation with the pin hole one, a pin shaft is arranged between the cooperating pin hole one and pin hole two, the upper slope surface of the notched groove has the same inclination angle as the upper slope surface of the sharp angle, and the lower slope surface of the notched groove has an inclination angle greater than that of the lower slope surface of the sharp angle, that is, a gap is left between the lower slope surface and the lower slope surface.

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