CN109590921B - Satellite skin drilling and riveting tooling underframe assembly - Google Patents
Satellite skin drilling and riveting tooling underframe assembly Download PDFInfo
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- CN109590921B CN109590921B CN201811324948.7A CN201811324948A CN109590921B CN 109590921 B CN109590921 B CN 109590921B CN 201811324948 A CN201811324948 A CN 201811324948A CN 109590921 B CN109590921 B CN 109590921B
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- edge
- satellite
- hole
- outer edge
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H1/00—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
- B25H1/06—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby of trestle type
Abstract
The invention relates to a satellite skin drilling and riveting tooling underframe assembly which structurally comprises a large end frame fixing plate and a butt flange port, wherein eight brackets which are inclined inwards are uniformly arranged on the bottom surface of the large end frame fixing plate along the circumferential direction, the brackets are respectively connected with the middle points of eight sides of a regular octagonal frame, the joint of the regular octagonal frame and each bracket is respectively provided with a connecting rod towards the center of the regular octagonal frame, the intersection of the eight connecting rods is provided with a mounting plate, the bottom surface of the mounting plate is provided with the butt flange port, and the centers of the large end frame fixing plate, the regular octagonal frame, the mounting plate and the butt flange port are positioned on a straight line. The invention has the advantages that: simple structure is effective, has realized effectively fixing to the satellite skinning to the operation is riveted to the high-efficient brill of realization to the satellite skinning, can shorten the activity duration to about a week.
Description
Technical Field
The invention relates to a satellite skin drilling and riveting tooling underframe assembly.
Background
The satellite skin is one of the important structures of the satellite, and in the production and processing of the satellite, the surface of the satellite skin needs to be drilled and riveted to obtain a required hole.
In the prior art, manual drilling and riveting operation is generally adopted, corresponding drilling and riveting equipment is not provided, the production efficiency is low, one month of operation time is generally needed, and the increasing production requirements cannot be met.
Disclosure of Invention
The invention provides a drilling and riveting tooling underframe assembly for a satellite skin, which aims to overcome the defects in the prior art and realize effective fixation of the satellite skin so as to realize efficient drilling and riveting operation on the satellite skin.
The technical solution of the invention is as follows: the satellite skin drilling and riveting tooling underframe assembly structurally comprises a large end frame fixing plate and a butt flange port, wherein eight brackets which are inclined inwards are uniformly arranged on the bottom surface of the large end frame fixing plate along the circumferential direction, the brackets are respectively connected with the middle points of eight sides of a regular octagonal frame, a connecting rod is respectively arranged at the joint of the regular octagonal frame and each bracket towards the center of the regular octagonal frame, a mounting plate is arranged at the intersection of the eight connecting rods, the butt flange port is arranged on the bottom surface of the mounting plate, and the centers of the large end frame fixing plate, the regular octagonal frame, the mounting plate and the butt flange port are positioned on a straight line.
Preferably, the large end frame fixing plate comprises an inner edge and an outer edge, a step is arranged between the inner edge and the outer edge, a convex edge is arranged between the step and the outer edge, the heights of the inner edge, the convex edge, the step and the outer edge are sequentially reduced, and the inner edge, the step and the convex edge form a skin clamping groove in a surrounding mode.
Preferably, four quadrant lines are evenly carved on the outer edge along the circumferential direction, wherein two quadrant lines which are opposite are respectively provided with a quadrant line reference detection hole.
Preferably, the outer edge on evenly be equipped with two round pin holes along the circumference, evenly be equipped with a forced threaded bush mounting hole, a guiding hole, a forced threaded bush mounting hole, a guiding hole and a forced threaded bush mounting hole along last round pin hole to another round pin hole along the circumference in proper order on the outer edge, totally four guiding holes and six forced threaded bush mounting holes, the contained angle between adjacent round pin hole, guiding hole or the forced threaded bush mounting hole all is 30.
Preferably, twenty-four positioning connecting holes are uniformly formed in the inner edge along the circumferential direction.
Preferably, four target holes are uniformly arranged on the inner edge along the circumferential direction.
Preferably, the cross section of the convex edge is an isosceles trapezoid with a circular arc at a corner, the taper of the convex edge is in matched butt joint with the external upper frame, and the included angle of the outer edges of the waist of the isosceles trapezoid on the cross section of the convex edge is 105 degrees.
Preferably, the inner diameter of the inner edge is 2980mm, the height of the inner edge is 140mm, the outer diameter of the outer edge is 3600mm, the height of the outer edge is 59mm, the width of the step is 50mm, the height of the step is 86mm, and the height of the convex edge is 99 mm.
The invention has the advantages that: simple structure is effective, has realized effectively fixing to the satellite skinning to the operation is riveted to the high-efficient brill of realization to the satellite skinning, can shorten the activity duration to about a week.
Drawings
Fig. 1 is a schematic structural diagram of a satellite skin drilling and riveting tooling chassis assembly.
Fig. 2 is a top view of fig. 1.
Fig. 3 is a cross-sectional view of fig. 1.
Fig. 4 is a perspective view of fig. 1.
Fig. 5 is a schematic structural view of the large end frame fixing plate in fig. 1.
Fig. 6 is a top view of fig. 5.
Fig. 7 is a view from a-a of fig. 6.
Fig. 8 is a view from B-B of fig. 6 (positioning the connection hole).
In the figure, 1 is a large end frame fixing plate, 2 is a bracket, 3 is a regular octagonal frame, 4 is a connecting rod, 5 is a mounting plate, 6 is a butt flange port, 101 is an inner edge, 102 is an outer edge, 103 is a step, 104 is a convex edge, 105 is a quadrant line, 106 is a quadrant line reference detection hole, 107 is a pin hole, 108 is a guide hole, 109 is a press-in type threaded bushing mounting hole, 110 is a positioning connection hole, and 111 is a target hole.
Detailed Description
The present invention will be described in further detail with reference to examples and specific embodiments.
As shown in fig. 1-4, the satellite skin drilling and riveting tooling underframe assembly structurally comprises a large end frame fixing plate 1 and a butt flange port 6, wherein eight brackets 2 which are inclined inwards are uniformly arranged on the bottom surface of the large end frame fixing plate 1 along the circumferential direction, the brackets 2 are respectively connected with the middle points of eight sides of a regular octagonal frame 3, a connecting rod 4 is respectively arranged at the joint of the regular octagonal frame 3 and each bracket 2 towards the center of the regular octagonal frame 3, a mounting plate 5 is arranged at the joint of the eight connecting rods 4, the butt flange port 6 is arranged on the bottom surface of the mounting plate 5, and the centers of the large end frame fixing plate 1, the regular octagonal frame 3, the mounting plate 5 and the butt flange port 6 are positioned on a straight line.
As shown in fig. 5-8, the large end frame fixing plate 1 includes an inner edge 101 and an outer edge 102, a step 103 is provided between the inner edge 101 and the outer edge 102, a protruding edge 104 is provided between the step 103 and the outer edge 102, heights of the inner edge 101, the protruding edge 104, the step 103 and the outer edge 102 are sequentially reduced, and the inner edge 101, the step 103 and the protruding edge 104 form a skin slot.
Four quadrant lines 105 are evenly carved on the outer edge 102 along the circumferential direction, wherein two quadrant lines 105 which are opposite are respectively provided with a quadrant line reference detection hole 106.
The outer edge 102 is uniformly provided with two pin holes 107 along the circumferential direction, the outer edge is uniformly provided with a press-in type threaded bush mounting hole 109, a guide hole 108, a press-in type threaded bush mounting hole 109, a guide hole 108 and a press-in type threaded bush mounting hole 109 from one pin hole 107 to the other pin hole 107 along the circumferential direction, the total number of the four guide holes 108 and six press-in type threaded bush mounting holes 109 is four, and the included angle between every two adjacent pin holes 107, guide holes 108 or press-in type threaded bush mounting holes 109 is 30 degrees.
Twenty-four positioning connecting holes 110 are uniformly arranged on the inner edge 101 along the circumferential direction.
Four target holes 111 are uniformly arranged on the inner edge 101 along the circumferential direction.
The cross section of the convex edge 104 is an isosceles trapezoid with a circular arc at a corner, the taper of the convex edge 104 is in fit butt joint with the external upper frame, and the included angle of the outer edge 102 of the isosceles trapezoid on the cross section of the convex edge 104 is 105 degrees.
The inner diameter of the inner edge 101 is 2980mm, the height of the inner edge is 140mm, the outer diameter of the outer edge 102 is 3600mm, the height of the outer edge is 59mm, the width of the step 103 is 50mm, the height of the step 103 is 86mm, and the height of the convex edge 104 is 99 mm.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the inventive concept of the present invention, and these changes and modifications are all within the scope of the present invention.
Claims (8)
1. Satellite skin bores riveter dress underframe subassembly, its characteristic includes big end frame fixed plate (1) and docking flange mouth (6), wherein evenly be equipped with eight brackets (2) of leanin along the circumference on big end frame fixed plate (1) bottom surface, the mid point on eight limits of regular octagon frame (3) is connected respectively in bracket (2), regular octagon frame (3) and every bracket (2) junction are equipped with one connecting rod (4) to regular octagon frame (3) center respectively, mounting panel (5) are established to eight connecting rods (4) intersection, docking flange mouth (6) are established on mounting panel (5) bottom surface, the center of big end frame fixed plate (1), regular octagon frame (3), mounting panel (5) and docking flange mouth (6) is located a straight line.
2. The satellite skin drilling and riveting tooling underframe assembly as claimed in claim 1, wherein the large end frame fixing plate (1) comprises an inner edge (101) and an outer edge (102), a step (103) is arranged between the inner edge (101) and the outer edge (102), a convex edge (104) is arranged between the step (103) and the outer edge (102), the heights of the inner edge (101), the convex edge (104), the step (103) and the outer edge (102) are sequentially reduced, and a skin clamping groove is defined by the inner edge (101), the step (103) and the convex edge (104).
3. The satellite skinning drill-rivet tooling chassis assembly of claim 2, wherein four quadrant lines (105) are evenly carved on the outer rim (102) along the circumferential direction, wherein a quadrant line reference inspection hole (106) is respectively arranged at two opposite quadrant lines (105).
4. The satellite skin drilling and riveting tool chassis assembly as claimed in claim 2, wherein the outer edge (102) is uniformly provided with two pin holes (107) along the circumferential direction, the outer edge is uniformly provided with a press-in type threaded bushing mounting hole (109), a guide hole (108), a press-in type threaded bushing mounting hole (109), a guide hole (108) and a press-in type threaded bushing mounting hole (109) from one pin hole (107) to the other pin hole (107) along the circumferential direction, the total number of the guide holes (108) and the six press-in type threaded bushing mounting holes (109) are four, the included angle between the adjacent pin hole (107) and the guide hole (108), the included angle between the adjacent guide hole (108) and the press-in type threaded bushing mounting hole (109), and the included angle between the adjacent pin hole (107) and the press-in type threaded bushing mounting hole (109) are all 30 degrees.
5. The satellite skinning drill-rivet tooling chassis assembly of claim 2, wherein twenty-four locating attachment holes (110) are evenly circumferentially provided in the inner rim (101).
6. The satellite skinning drill-rivet tooling pedestal assembly of claim 2, wherein four target holes (111) are uniformly formed in the inner edge (101) along the circumferential direction.
7. The satellite skin drilling and riveting tool chassis assembly as claimed in claim 2, wherein the cross section of the convex edge (104) is in the shape of an isosceles trapezoid with a circular arc at a corner, the taper of the convex edge (104) is matched and butted with the external upper frame, and the included angle of the outer edges (102) of the isosceles trapezoid on the cross section of the convex edge (104) is 105 degrees.
8. The satellite skin drilling and riveting tool chassis assembly as claimed in claim 2, wherein the inner diameter of the inner edge (101) is 2980mm, the height of the inner edge is 140mm, the outer diameter of the outer edge (102) is 3600mm, the height of the outer edge is 59mm, the width of the step (103) is 50mm, the height of the step is 86mm, and the height of the convex edge (104) is 99 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811324948.7A CN109590921B (en) | 2018-11-08 | 2018-11-08 | Satellite skin drilling and riveting tooling underframe assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811324948.7A CN109590921B (en) | 2018-11-08 | 2018-11-08 | Satellite skin drilling and riveting tooling underframe assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109590921A CN109590921A (en) | 2019-04-09 |
| CN109590921B true CN109590921B (en) | 2020-10-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811324948.7A Active CN109590921B (en) | 2018-11-08 | 2018-11-08 | Satellite skin drilling and riveting tooling underframe assembly |
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Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6413022B1 (en) * | 2000-09-18 | 2002-07-02 | The Boeing Company | Vacuum clamp device |
| CN101975329B (en) * | 2010-10-27 | 2012-07-04 | 中国科学院西安光学精密机械研究所 | Supporting device with aluminum honeycomb interlayer and carbon fiber skin |
| CN102069457A (en) * | 2010-12-07 | 2011-05-25 | 成都飞机工业（集团）有限责任公司 | Self-centering positioning process equipment for fixing curved skin parts |
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2018
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| CN109590921A (en) | 2019-04-09 |
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Effective date of registration: 20220513 Address after: 100000 courtyard 1, Chaoyang Road, Chaoyang District, Beijing Patentee after: AVIC BEIJING AERONAUTICAL MANUFACTURING TECHNOLOGY Research Institute Address before: 214200 No.15, Huixing North Road, Zhuqiao Economic Development Zone, Yixing City, Wuxi City, Jiangsu Province Patentee before: YIXING RONGXING CASTING CO.,LTD. |
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