CN217370859U

CN217370859U - Modularized connecting tool for spacecraft

Info

Publication number: CN217370859U
Application number: CN202123303431.XU
Authority: CN
Inventors: 陈磊
Original assignee: Sky Sky Beijing Space Technology Co ltd
Current assignee: Sky Sky Beijing Space Technology Co ltd
Priority date: 2021-12-24
Filing date: 2021-12-24
Publication date: 2022-09-06
Anticipated expiration: 2031-12-24

Abstract

The application relates to the technical field of spacecraft propulsion, and discloses a modularized connecting tool for a spacecraft, which comprises fastening screws, an upper cover plate and a lower supporting plate. This frock is connected to modularization for spacecraft has the connection that is applicable to between the different propulsion products pipe class product, the dress card of having solved different external diameter work pieces is with the poor problem of back axiality, the dress card process is convenient, through the ladder semicircle of upper and lower structure, can quick integral fastening, the dress card process time of having saved, production efficiency has been improved, it has middle window to open in this application patent, can be better remain protective gas in the twinkling of an eye, solve the problem that protective gas can not fine protection welding seam, improve welding seam welding quality. After spot welding, the modularized tool is dismantled, and argon arc welding is used for circumferential welding, so that the welding seam can be ensured to be uniform and continuous.

Description

Modularized connecting tool for spacecraft

Technical Field

The application relates to the technical field of spacecraft propulsion, in particular to a modularized connecting tool for a spacecraft.

Background

When welding between the product among the propulsion module, its product stretches out the junction and be circular structure, need fix before welding, guarantee that the whole circle of welding seam can not change before the welding position, but during spot welding, the junction between the product can have the size nonconformity, can lead to follow-up welding to hardly guarantee the welding seam quality. If the welding method such as shielded gas arc welding is adopted, the welding gun has poor gas shielded molten pool effect due to the generation of a large heat source and low energy density, and welding seams are easy to oxidize after welding, so that the welding seam defects are caused for subsequent welding.

The existing modular tooling has the defects that due to the structure that two ends of a welding line are separated, the coaxiality requirement cannot be ensured after clamping, and the welding line can be greatly deviated particularly when the sizes of the welding lines on two sides are inconsistent. Meanwhile, effective weld joint protection is not formed during spot welding, the large-area color change condition is easy to occur around the welded weld joint after welding, the appearance quality of the weld joint and subsequent welding are affected to a great extent, and therefore the modularized connecting tool for the spacecraft is urgently needed.

SUMMERY OF THE UTILITY MODEL

To prior art's not enough, this application provides a frock is connected to modularization for spacecraft, possesses the easy, high advantage of axiality of dress card alignment when connecting between the different propulsion module formula products, has solved and has had difficult dress card alignment, the axiality is not high and welding seam oxidation problem when connecting between the different propulsion module formula products that mention in the above-mentioned background art.

In order to achieve the above purpose, the present application provides the following technical solutions: the utility model provides a frock is connected to modularization for spacecraft, includes fastening screw, upper cover plate, bottom plate, the fastening screw surface all with the inside and the inside swing joint of bottom plate of upper cover plate, upper cover plate bottom and bottom plate top swing joint, the upper cover plate passes through fastening screw fixed connection with the bottom plate.

Preferably, the number of the fastening screws is four, and the four fastening screws are symmetrically distributed on two sides of the upper cover plate.

Preferably, a module part product is arranged on one side of the upper cover plate, the upper cover plate is of a stepped structure, the upper end surfaces of the left side and the right side of the upper cover plate are platforms, the upper cover plate is internally provided with an unthreaded hole, the lower supporting plate is of a stepped structure, the left end and the right end of the lower supporting plate are semicircular, the lower supporting plate is internally provided with a threaded hole, and the inner side of the upper cover plate and the inner side of the lower supporting plate are respectively provided with a semi-unthreaded hole.

Preferably, its inboard structure of upper cover plate respectively has a big semicircle for both ends, and middle window is the little semicircle of ladder, big circle and ladder small circle and hole axiality among the stair structure of upper cover plate are < 0.10mm, its inboard structure of bottom plate respectively has a big semicircle for both ends, and middle window is the little semicircle of ladder, big circle and ladder small circle and hole axiality among the stair structure of bottom plate are < 0.10 mm.

Preferably, the inner side of the upper cover plate and the inner side of the lower supporting plate contain semi-smooth holes for placing module parts, the inner diameter of each semi-smooth hole and the outer diameter of a module part product are matched, and the matching tolerance is less than 0.04 mm.

Preferably, the end cover of the upper cover plate is provided with a middle window for inputting a welding heat source, and a certain storage space can be formed for welding protective gas, so that the oxidation of a welding seam area is avoided.

In summary, the present application includes at least one of the following benefits:

1. the pipe product clamping device has the advantages that the pipe product clamping device is suitable for connection of pipe products among different propulsion products, and the clamping problem of workpieces with different outer diameters is solved.

2. This application dress card process is convenient, and through the ladder semicircle of upper and lower structure, can quick integral fastening, saved dress card process time, improved production efficiency.

3. This application is through joining in marriage the car with the product external diameter, and it is high to realize dress card precision, is difficult for alignment welding seam and the low problem of axiality.

4. Open in this application and have middle window, can be better remain protective gas in the twinkling of an eye, solve the problem that protective gas can not fine protection welding seam, improve welding seam welding quality.

Drawings

FIG. 1 is a schematic structural diagram of the present application;

FIG. 2 is a partial cross-sectional view of the present application;

FIG. 3 is a schematic view of a weld stack assembly of the present application.

Wherein: 1. fastening screws; 2. an upper cover plate; 3. a lower supporting plate; 4. a modular part; 5. a light hole; 6. a threaded hole; 7. and (5) half of a light hole.

Detailed Description

The present application is described in further detail below with reference to figures 1-3.

The embodiment of the application discloses modularization connecting tool for a spacecraft. Referring to fig. 1, 2 and 3, a modularized connecting tool for a spacecraft comprises fastening screws 1, an upper cover plate 2 and a lower support plate 3, wherein the upper cover plate 2 is of a stepped structure, platforms are arranged at the left end and the right end, and four unthreaded holes 5 are formed, the coaxiality of a large circle, a stepped small circle and an inner hole in the stepped structure of the upper cover plate 2 is required to be less than 0.10mm, the lower support plate 3 is of a stepped structure, the left end and the right end are of a semicircular shape, four threaded holes 6 are formed, the inner side structure of the lower support plate is a large semicircle with each end, a middle window is a stepped small semicircle with a middle section also being a flat platform, a semi-unthreaded hole 7 for placing a module part is formed in the inner side, the inner diameter of the semi-unthreaded hole 7 is matched with the outer diameter of a module part product 4, the size is ensured to be consistent, the coaxiality of the large circle, the small circle and the inner hole in the stepped structure of the lower support plate 3 is required to be less than 0.10mm, the four fastening screws 1 respectively penetrate through the four unthreaded holes 5 of the upper cover plate 2, screw to in the 3 four screw holes 6 of bottom plate, when placing module part product 4, the position that needs the welding seam is at the middle window, then screw up fastening screw 1, the welding heat source can be through upper cover plate 2, the platform of 3 intermediate positions of bottom plate carries out the spot welding seam, the design has made special module spot welding frock and has solved difficult clamping and the poor problem of postweld axiality, and the frock material adopts red copper, stainless steel or titanium alloy, realize the purpose of fastening module part product 4 through four fastening screw 1 on every side, welder carries out spot welding through dress card frock platform department.

The implementation principle of the modularized connecting tool for the spacecraft in the embodiment of the application is as follows: when module part product 4 need be welded, when placing two module part products 4, the position that needs the welding seam is at middle window, then screws up four fastening screw 1, and the welding heat source can carry out the spot welding seam through the window of

upper cover plate

2, 3 intermediate positions of bottom plate, and spot welding clamping frock is demolishd to the spot welding back, and in advance before guaranteeing the axiality, argon arc welding is carried out very easily, and welding circumferential weld such as vacuum electron beam welding can guarantee the welding seam is even continuous.

Although embodiments of the present application have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the application, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a frock is connected to modularization for spacecraft, includes fastening screw (1), upper cover plate (2), bottom plate (3), its characterized in that: the outer surface of the fastening screw (1) is movably connected with the inside of the upper cover plate (2) and the inside of the lower support plate (3), the bottom of the upper cover plate (2) is movably connected with the top of the lower support plate (3), and the upper cover plate (2) is fixedly connected with the lower support plate (3) through the fastening screw (1).

2. The modular connecting tool for the spacecraft of claim 1, wherein: the number of the fastening screws (1) is four, and the four fastening screws (1) are symmetrically distributed on two sides of the upper cover plate (2).

3. The modular connecting tool for the spacecraft of claim 1, wherein: upper cover plate (2) one side is provided with module part product (4), upper cover plate (2) are stair structure, the up end on upper cover plate (2) left side and right side is the platform, unthreaded hole (5) have been seted up to upper cover plate (2) inside, bottom plate (3) are stair structure, both ends are semi-circular about bottom plate (3), threaded hole (6) have been seted up to bottom plate (3) inside, half unthreaded hole (7) have been seted up respectively to upper cover plate (2) inboard and bottom plate (3) inboard.

4. The modular connecting tool for the spacecraft of claim 3, wherein: its inboard structure of upper cover plate (2) respectively has a big semicircle for both ends, and middle window is the little semicircle of ladder, big circle and ladder small circle and hole axiality among the stair structure of upper cover plate (2) are < 0.10mm, its inboard structure of bottom plate (3) respectively has a big semicircle for both ends, and middle window is the little semicircle of ladder, big circle and ladder small circle and hole axiality among the stair structure of bottom plate (3) are < 0.10 mm.

5. The modular connecting tool for the spacecraft of claim 3, wherein: the inner side of the upper cover plate (2) and the inner side of the lower supporting plate (3) contain a half unthreaded hole (7) for placing module parts, the inner diameter of the half unthreaded hole (7) and the outer diameter of a module part product (4) are matched, and the matching tolerance is less than 0.04 mm.

6. The modular connecting tool for the spacecraft of claim 1, wherein: the end cover of the upper cover plate (2) is provided with a middle window for inputting a welding heat source, and a certain storage space can be formed for welding protective gas, so that the oxidation of a welding seam area is avoided.