Inner supporting and positioning device for aerospace craft equipment cabin machining

Abstract

The utility model discloses an inner supporting and positioning device for aerospace craft equipment cabin machining, and belongs to the technical field of aircrafts, a base is arranged below a first splicing block and a second splicing block, and the first splicing block and the second splicing block are placed above the base; a conical lifting cavity formed by mutual splicing is formed in the first splicing block and the second splicing block, a lifting cylinder matched with the lifting cavity is arranged in the middle of the base, and a to-be-machined equipment cabin is installed on the outer wall of the first splicing block and the outer wall of the second splicing block. A first sliding half cavity is formed in the middle of the first splicing block, a second sliding half cavity matched with the first splicing block is formed in the middle of the second splicing block, a threaded hole is formed in the top of the lifting cylinder, a lifting bolt is installed in the threaded hole in a threaded mode, and the lifting bolt penetrates through the first sliding half cavity and the second sliding half cavity above. Under the driving of the lifting bolt, the first splicing block and the second splicing block expand towards the two sides and clamp the equipment cabin, the structure is simple and easy to maintain, and the practicability of the device is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to an internal support positioning device for processing the equipment cabin of a space aircraft. Background Art

[0002] An aircraft is a device that flies within the atmosphere or in outer space (space). Aircraft are divided into three categories: aircraft, spacecraft, rockets, and missiles. Those that fly within the atmosphere are called aircraft, such as balloons, airships, airplanes, etc. They take off and fly relying on the static buoyancy of the air or the aerodynamic force generated by the relative motion of the air. Those that fly in space are called spacecraft, such as artificial earth satellites, manned spacecraft, space probes, space shuttles, etc. They obtain the necessary speed to enter space under the propulsion of a launch vehicle and then rely on inertia to perform orbital motions similar to celestial bodies.

[0003] The published patent No. CN212287536U discloses a positioning device for processing aircraft composite components, which includes a workbench. Both sides of the bottom end of the workbench are fixedly connected with side plates. The bottom ends of the two side plates are fixedly connected with feet. An adjusting mechanism is arranged between the two side plates. The adjusting mechanism is located below the workbench. The first clamping plate and the second clamping plate are symmetrically arranged on the adjusting mechanism. The workbench is provided with a first opening and a second opening. The first clamping plate and the second clamping plate respectively pass through the workbench through the first opening and the second opening. A placement groove is arranged on the workbench between the first clamping plate and the second clamping plate. The opposite sides of the upper ends of the first clamping plate and the second clamping plate are respectively fixedly connected with a first cross plate and a second cross plate. The first cross plate is inserted into the second cross plate. This utility model can extrude and clamp the four sides of the workpiece, so that the workpiece can be quickly positioned and fixed, ensuring the stability of the workpiece and thus ensuring the smooth progress of the processing process.

[0004] The applicability of the above-mentioned positioning device for processing is general. It is not convenient to perform internal clamping processing on cylindrical or conical workpieces, and the installation process is cumbersome, time-consuming and laborious. Therefore, an internal support positioning device for processing the equipment cabin of a space aircraft is designed here to solve the above problems. Content of the Utility Model

[0005] The purpose of the utility model is to provide an internal support positioning device for processing the equipment cabin of a space aircraft in order to solve the problems that the applicability of the traditional positioning device for processing is general, it is not convenient to perform internal clamping processing on cylindrical or conical workpieces, and the installation process is cumbersome, time-consuming and laborious.

[0006] To achieve the above object, the technical solution of the present utility model is: an internal support positioning device for processing the equipment cabin of a space vehicle, including a first splicing block and a second splicing block that cooperate with each other, and the first splicing block and the second splicing block form a conical cylinder structure; a base is arranged below the first splicing block and the second splicing block, and the first splicing block and the second splicing block are placed above the base; a lifting cavity in the shape of a cone formed by splicing with each other is opened inside the first splicing block and the second splicing block, a lifting cylinder matched with the lifting cavity is arranged in the middle of the base, and an equipment cabin to be processed is installed on the outer walls of the first splicing block and the second splicing block; a sliding half-cavity one is opened in the middle of the first splicing block, a sliding half-cavity two matched with it is opened in the middle of the second splicing block, a threaded hole is arranged at the top of the lifting cylinder, and a lifting bolt is installed in the threaded hole in a threaded manner, and the lifting bolt penetrates through the upper sliding half-cavity one and sliding half-cavity two.

[0007] As a further solution of the present utility model: a plurality of limiting arms are arranged on the inner wall of the top of the equipment cabin, and limiting grooves matched with them are opened at the tops of the first splicing block and the second splicing block.

[0008] As a further solution of the present invention: the width of the limiting groove is greater than the width of the limiting arm.

[0009] As a further solution of the present utility model: a support frame is fixedly arranged at the bottom of the base, and an anti-slip pad is further arranged at the bottom of the support frame.

[0010] As a further solution of the present utility model: a convex block is arranged at the bottom of the lifting cylinder, and a groove matched with it is opened at the top of the base.

[0011] As a further solution of the present utility model: a through first sliding groove is opened inside the first splicing block, a through second sliding groove is opened inside the second splicing block, and symmetric first sliding rod and second sliding rod are fixedly installed on the base in a threaded manner, the first sliding rod is located in the first sliding groove, and the second sliding rod is located in the second sliding groove.

[0012] As a further solution of the present utility model: the inner diameter of the first sliding groove is greater than the first sliding rod, and the inner diameter of the second sliding groove is greater than the second sliding rod.

[0013] The present utility model hereby provides an internal support positioning device for processing the equipment cabin of a space vehicle through improvement. Compared with the prior art, it has the following improvements and advantages:

[0014] The internal part of the equipment cabin can be positioned by the mutually cooperating first splicing block and second splicing block. Driven by the lifting bolts, the lifting cylinder moves upward and presses against the inner wall of the lifting cavity. At this time, the first splicing block and the second splicing block expand to both sides and clamp the equipment cabin. This structure is simple and easy to maintain, which further improves the practicality of the internal support positioning device for the equipment cabin processing of this aerospace vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present utility model will be further explained below in conjunction with the drawings and embodiments:

[0016] Figure 1 is a three-dimensional structure diagram of the structure of the present utility model;

[0017] Figure 2 is a three-dimensional structure diagram of the equipment cabin in the present utility model;

[0018] Figure 3 is a cross-sectional view of the present utility model;

[0019] Figure 4 is a three-dimensional structure diagram of the base in the present utility model;

[0020] Figure 5 is a three-dimensional structure diagram of the first splicing block and the second splicing block in the present utility model.

[0021] DESCRIPTION OF THE REFERENCE NUMERALS:

[0022] 1. First splicing block; 2. Second splicing block; 3. Equipment cabin; 4. Limiting arm; 5. Limiting groove; 6. First sliding half cavity; 7. Second sliding half cavity; 8. Lifting bolt; 9. Lifting cavity; 10. Base; 11. Support frame; 12. Groove; 13. Lifting cylinder; 14. Convex block; 15. Threaded hole; 16. First sliding groove; 17. Second sliding groove; 18. First sliding rod; 19. Second sliding rod. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] The following will be combined with the attached Figures 1 to 5 The present utility model will be described in detail. The technical solutions in the embodiments of the present utility model are clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0024] The present utility model provides an internal support positioning device for the equipment cabin processing of an aerospace vehicle through improvement, as Figures 1 - 5As shown in the figure, an internal support positioning device for processing the equipment cabin of a space vehicle includes a first splicing block 1 and a second splicing block 2 that cooperate with each other. The first splicing block 1 and the second splicing block 2 form a conical cylinder structure. Below the first splicing block 1 and the second splicing block 2, there is a base 10. The first splicing block 1 and the second splicing block 2 are placed above the base 10 and are in contact with it. Inside the first splicing block 1 and the second splicing block 2, there is a conical lifting cavity 9 formed by splicing with each other. In the middle of the base 10, there is a lifting cylinder 13 that cooperates with the lifting cavity 9. On the outer walls of the first splicing block 1 and the second splicing block 2, there is an equipment cabin 3 to be processed. In the middle of the first splicing block 1, there is a sliding half cavity 1 6, and in the middle of the second splicing block 2, there is a sliding half cavity 2 7 that cooperates with it. At the top of the lifting cylinder 13, there is a threaded hole 15, and a lifting bolt 8 is installed with internal threads in the threaded hole 15. The lifting bolt 8 passes through the upper sliding half cavity 1 6 and the sliding half cavity 2 7.

[0025] Through the mutually cooperating first splicing block 1 and second splicing block 2 of the present utility model, the inside of the equipment cabin 3 can be positioned. Driven by the lifting bolt 8, the lifting cylinder 13 moves upward and squeezes the inner wall of the lifting cavity 9. At this time, the first splicing block 1 and the second splicing block 2 expand to both sides and clamp the equipment cabin 3. This structure is simple and easy to maintain, which further improves the practicability of the internal support positioning device for processing the equipment cabin of the space vehicle.

[0026] When in use, first place the equipment cabin 3 on the outer walls of the first splicing block 1 and the second splicing block 2, and make the limiting arm 4 fall into the limiting groove 5. Then tighten the lifting bolt 8. Since the convex block 14 is limited by the groove 12, the lifting cylinder 13 will move upward relative to the lifting cavity 9. Under the extrusion of the lifting cylinder 13, the first splicing block 1 and the second splicing block 2 will expand to both sides, so as to abut against and clamp the inner wall of the equipment cabin 3.

[0027] Refer to the attached Figure 1 - attached Figure 3 , on the top inner wall of the equipment cabin 3, there are multiple groups of limiting arms 4, and on the tops of the first splicing block 1 and the second splicing block 2, there are limiting grooves 5 that cooperate with them.

[0028] In this embodiment: In order to limit the equipment cabin 3, make it installed on the outer walls of the first splicing block 1 and the second splicing block 2 and position it, the limiting arm 4 structure is designed.

[0029] Refer to the attached Figure 1 - attached Figure 3 , the width of the limiting groove 5 is greater than the width of the limiting arm 4.

[0030] In this embodiment, when the equipment compartment 3 is squeezed and positioned, the first assembly block 1 and the second assembly block 2 are squeezed to both sides, and the limiting groove 5 is displaced relative to the limiting arm 4, so that its width is greater than the limiting arm 4.

[0031] See attached Figure 1 and attached Figure 3 A support frame 11 is fixedly arranged at the bottom of the base 10, and an anti-slip pad is also arranged at the bottom of the support frame 11.

[0032] In this embodiment, in order to increase the friction force and thus further improve the stability, an anti-slip pad is designed.

[0033] See attached Figure 3 -Attached Figure 4 A protrusion 14 is provided at the bottom of the lifting cylinder 13, and a groove 12 cooperating therewith is provided at the top of the base 10.

[0034] In this embodiment, driven by the lifting bolt 8, the lifting cylinder 13 moves upward relative to the lifting chamber 9. In order to ensure that the lifting cylinder 13 does not rotate relative to the base 10 and thus cannot rise, a protrusion 14 structure is designed. During the entire clamping and loosening process, the protrusion 14 will not fall off the groove 12.

[0035] See attached Figure 3 -Attached Figure 4 A first sliding groove 16 is provided inside the first assembly block 1, a second sliding groove 17 is provided inside the second assembly block 2, and a symmetrical first sliding rod 18 and a second sliding rod 19 are fixedly installed with threads on the base 10. The first sliding rod 18 is located in the first sliding groove 16, and the second sliding rod 19 is located in the second sliding groove 17. The inner diameter of the first sliding groove 16 is larger than that of the first sliding rod 18, and the inner diameter of the second sliding groove 17 is larger than that of the second sliding rod 19.

[0036] In this embodiment: when the equipment compartment 3 is squeezed and positioned, the first splicing block 1 and the second splicing block 2 will be squeezed to both sides. At this time, the first splicing block 1 and the second splicing block 2 will be displaced relative to the first sliding bar 18 and the second sliding bar 19, so that their inner diameters are larger than the first sliding bar 18 and the second sliding bar 19.

[0037] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An internal support positioning device for processing aerospace equipment cabin, characterized in that: The invention comprises a first splicing block (1) and a second splicing block (2) which cooperate with each other, wherein the first splicing block (1) and the second splicing block (2) form a conical cylinder structure; a base (10) is arranged below the first splicing block (1) and the second splicing block (2), and the first splicing block (1) and the second splicing block (2) are placed above the base (10) and abut against it; a conical lifting cavity (9) formed by splicing each other is provided inside the first splicing block (1) and the second splicing block (2), and a lifting cavity (9) which is in contact with the lifting cavity (10) is arranged in the middle of the base (10). A lifting cylinder (13) matched with the cavity (9), the outer walls of the first splicing block (1) and the second splicing block (2) are installed with an equipment cabin (3) to be processed; the middle of the first splicing block (1) is provided with a sliding half-cavity (6), and the middle of the second splicing block (2) is provided with a sliding half-cavity (7) matched therewith, and the top of the lifting cylinder (13) is provided with a threaded hole (15), and the inner thread of the threaded hole (15) is installed with a lifting bolt (8), and the lifting bolt (8) passes through the upper sliding half-cavity (6) and the sliding half-cavity (7).

2. The inner support positioning device for aerospace equipment cabin processing according to claim 1, characterized in that: A plurality of groups of limiting arms (4) are arranged on the top inner wall of the equipment cabin (3), and limiting grooves (5) cooperating therewith are arranged on the tops of the first splicing block (1) and the second splicing block (2).

3. The inner support positioning device for processing aerospace equipment cabin according to claim 2, characterized in that: The width of the limiting groove (5) is greater than the width of the limiting arm (4).

4. The inner support positioning device for processing aerospace equipment cabin according to claim 1, characterized in that: A support frame (11) is fixedly arranged at the bottom of the base (10), and an anti-slip pad is also arranged at the bottom of the support frame (11).

5. The inner support positioning device for processing aerospace equipment cabin according to claim 1, characterized in that: The bottom of the lifting cylinder (13) is provided with a protrusion (14), and the top of the base (10) is provided with a groove (12) that cooperates with the protrusion (14).

6. The inner support positioning device for processing aerospace equipment cabin according to claim 1, characterized in that: A first sliding groove (16) is provided inside the first assembly block (1), a second sliding groove (17) is provided inside the second assembly block (2), and a symmetrical first sliding rod (18) and a second sliding rod (19) are fixedly mounted on the base (10) by threads, the first sliding rod (18) is located in the first sliding groove (16), and the second sliding rod (19) is located in the second sliding groove (17).

7. The inner support positioning device for processing aerospace equipment cabin according to claim 6, characterized in that: The inner diameter of the first sliding groove (16) is larger than the first sliding rod (18), and the inner diameter of the second sliding groove (17) is larger than the second sliding rod (19).

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