CN221248465U

CN221248465U - Tool plate for rocket engine

Info

Publication number: CN221248465U
Application number: CN202322512048.8U
Authority: CN
Inventors: 荆智; 刘俊杰
Original assignee: Beijing Institute Of Aeronautical Science And Technology Development
Current assignee: Beijing Institute Of Aeronautical Science And Technology Development
Priority date: 2023-09-15
Filing date: 2023-09-15
Publication date: 2024-07-02
Anticipated expiration: 2033-09-15

Abstract

The utility model discloses a tooling plate for a rocket engine, which comprises: a plurality of arc plates, wherein the thickness of the arc plates is the same, and the adjacent arc plates are connected with each other to form a circular ring; a plurality of first through holes are formed in the arc plate along the thickness direction of the arc plate, and the first through holes are distributed along the circumference of the arc plate. The tooling plate can accurately position the size and the position of the mounting hole and is convenient to use.

Description

Tool plate for rocket engine

Technical Field

The utility model relates to a rocket engine, in particular to a tooling plate for the rocket engine.

Background

The rocket engine comprises a plurality of parts, and manufacturers of the parts are different, so that the parts are reworked or scrapped due to the fact that the assembly holes are more or less deviated in the assembly process of the parts of the rocket engine.

Disclosure of utility model

In view of the above-mentioned drawbacks or shortcomings of the prior art, it is desirable to provide a tooling plate for rocket engines that is capable of accurately positioning the assembly holes and that is convenient to use.

The utility model provides a tooling plate for a rocket engine, which comprises:

a plurality of arc plates, wherein the thickness of the arc plates is the same, and adjacent arc plates are connected with each other to form a circular ring;

The arc plate is provided with a plurality of first through holes along the thickness direction of the arc plate, and the first through holes are distributed along the circumference of the arc plate.

Optionally, the arc plate has an upper surface and a lower surface, the upper surface of one end of the arc plate extends along the central line direction to form an upper connection surface, and the lower surface of the other end of the arc plate extends along the central line direction to form a lower connection surface; the sum of the thickness of the upper connecting surface and the thickness of the lower connecting surface is equal to the thickness of the arc plate.

Further, a plurality of assembly holes are formed in the upper connecting surface or the lower connecting surface, and a second through hole is formed in the lower connecting surface or the upper connecting surface corresponding to the assembly holes.

Further, the assembly hole is a counter bore.

Further, a first positioning pin hole is arranged between two adjacent assembly holes, and the first positioning pin hole penetrates through the upper connecting surface or the lower connecting surface.

Optionally, second positioning pin holes are formed in the arc plate along the thickness direction, and the second positioning pin holes are distributed along the circumferential direction of the arc plate and located between adjacent first through holes.

Optionally, the arc plate is made of stainless steel.

Optionally, the radius of the inner arc edge of the arc plate is 1700mm, and the radius of the outer arc edge of the arc plate is 1800mm.

Optionally, the diameter of the first through holes is 21mm, and the radius of the connecting line of the circle centers of the plurality of first through holes is 1750mm.

Compared with the prior art, the utility model has the beneficial effects that:

The tooling plate for the rocket engine comprises: the arc plates are connected with each other at two ends of two adjacent arc plates, the thickness of each arc plate is the same, and the arc plates are spliced into a circular shape finally.

A plurality of first through holes are formed in the arc plate, the first through holes are formed in the direction of the thickness of the arc plate, the axis of the first through holes is perpendicular to the horizontal plane of the arc plate, and the first through holes are distributed in a plurality of positions along the circumference of the arc plate and used for positioning the matched assembly holes of all parts of the rocket engine. The tooling plate can accurately position the size and the position of the mounting hole and is convenient to use.

It should be understood that the description in this summary is not intended to limit the critical or essential features of the embodiments of the utility model, nor is it intended to limit the scope of the utility model. Other features of the present utility model will become apparent from the description that follows.

Drawings

Other features, objects and advantages of the present utility model will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the accompanying drawings in which:

FIG. 1 is a schematic top view of a tooling plate;

FIG. 2 is a schematic view of A-A in cross-section.

FIG. 3 is a partial enlarged view at B;

FIG. 4 is a schematic top view of an arc plate and a connecting plate;

Fig. 5 is a schematic view of the bottom view structure of the arc plate and the connecting plate.

Reference numerals in the drawings: 1. an arc plate; 2. a first through hole; 3. a fitting hole; 4. a second through hole;

11. An upper surface; 12. a lower surface; 13. a first positioning pin hole; 14. a second dowel hole;

111. An upper connection surface;

121. And a lower connection surface.

Detailed Description

The utility model is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be noted that, for convenience of description, only the portions related to the utility model are shown in the drawings.

It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other. The utility model will be described in detail below with reference to the drawings in connection with embodiments.

Referring to fig. 1, the present utility model provides a tooling plate for a rocket engine, comprising: the arc plates 1 have the same thickness, and adjacent arc plates 1 are connected with each other to form a circular ring;

A plurality of first through holes 2 are arranged on the arc plate 1 along the thickness direction thereof, and the plurality of first through holes 2 are distributed along the circumferential direction of the arc plate 1 and are used for positioning the positions of the mounting holes matched with all parts of the rocket engine. The tooling plate can accurately position the size and the position of the mounting hole and is convenient to use.

The rocket engine is assembled from a plurality of parts because, for two mutually assembled parts, before each part mounting hole is machined, it is necessary to ensure that the two mutually assembled part mounting holes correspond to each other. First, a plurality of arc plates 1 constituting a circular ring shape are placed on a processing plane of one of two fitting parts, the position of the first through hole 2 is aligned with a position where the part needs to be bored (a boring position, that is, a mounting hole position of two mutually fitted parts of a rocket engine), and then the mounting hole is processed by a punching die or machining or the like. After the installation hole is machined, the arc plate 1 is taken down, then a plurality of arc plates 1 forming a circular ring shape are placed on a machining plane of the other of the two assembly parts, the position of the first through hole 2 is aligned with the position of the part to be perforated (the perforation position is the installation hole position of the two mutually assembled parts of the rocket engine), and then the installation hole is machined through a stamping die or machining mode. Finally, the parts with the two mounting holes matched with each other are obtained.

As shown in fig. 2 and 3, as an alternative embodiment, the arc plate 1 has an upper surface 11 and a lower surface 12, the upper surface 11 of one end of the arc plate 1 extends in the direction of the center line thereof to form an upper connection surface 111, and the lower surface 12 of the other end of the arc plate 1 extends in the direction of the center line thereof to form a lower connection surface 121; the sum of the thickness of the upper connection face 111 and the thickness of the lower connection face 121 is equal to the thickness of the arc plate 1.

One of them, a plurality of assembly holes 3 (the assembly holes 3 are counter bores) are arranged on the upper connecting surface 111, and a second through hole 4 is arranged on the lower connecting surface 121 corresponding to the assembly holes 3; wherein a first positioning pin hole 13 is provided between two adjacent assembly holes 3. Firstly, a locating pin penetrates through a first locating pin hole 13, an upper connecting surface 111 and a lower connecting surface 121 are pre-fixed, then countersunk screws penetrate through an assembly hole 3 and a second through hole 4, then the screws are locked by nuts, the upper connecting surface 111, the lower connecting surface 121 and each arc plate 1 are further locked, a plurality of arc plates 1 form a circular ring, and finally the locating pin is removed.

One of them, a plurality of assembly holes 3 (the assembly holes 3 are counter bores) are arranged on the lower connecting surface 121, and a second through hole 4 is arranged on the upper connecting surface 111 corresponding to the assembly holes 3; wherein a first positioning pin hole 13 is provided between two adjacent assembly holes 3.

As shown in fig. 4, as an alternative embodiment, the arc plate 1 is provided with second positioning pin holes 14 in the thickness direction, and the second positioning pin holes 14 are distributed along the circumference of the arc plate 1 and are located between adjacent first through holes 2. Before the assembly holes 3 of all parts of the rocket engine are machined, positioning pins penetrate through positioning pin holes to be fixed on the parts or a machining tool or a die, the tooling plate is pre-fixed, the tooling plate is further fixed on the parts or the machining tool or the die through bolts or other modes, and then the assembly holes 3 of the parts are machined.

As an alternative embodiment, the arc plate 1 is made of stainless steel or the like.

As an alternative embodiment, the radius of the inner arc edge of the arc plate 1 is 1700mm, and the radius of the outer arc edge is 1800mm.

As an alternative embodiment, the diameter of the first through holes 2 is 21mm, and the radius of the connecting line of the centers of the plurality of first through holes 2 is 1750mm.

In the description of the present specification, the terms "connected," "mounted," "secured," and the like are to be construed broadly, and for example, "connected" may be a fixed connection, a removable connection, or an integral connection; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

In the description of the present specification, the terms "one embodiment," "some embodiments," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above is only a preferred embodiment of the present application, and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A tooling plate for a rocket engine, comprising:

A plurality of arc plates (1), wherein the thickness of the arc plates (1) is the same, and the adjacent arc plates (1) are connected with each other to form a circular ring;

A plurality of first through holes (2) are formed in the arc plate (1) along the thickness direction of the arc plate, and the first through holes (2) are distributed along the circumferential direction of the arc plate (1).

2. Tooling plate for rocket engines according to claim 1, characterized in that the arc plate (1) has an upper surface (11) and a lower surface (12), the upper surface (11) of one end of the arc plate (1) extending in its centerline direction forming an upper connection face (111), the lower surface (12) of the other end of the arc plate (1) extending in its centerline direction forming a lower connection face (121); the sum of the thickness of the upper connection surface (111) and the thickness of the lower connection surface (121) is equal to the thickness of the arc plate (1).

3. Tooling plate for rocket engines according to claim 2, characterized in that said upper (111) or lower (121) connection face is provided with a plurality of assembly holes (3), said lower (121) or upper (111) connection face being provided with second through holes (4) in correspondence of said assembly holes (3).

4. A tooling plate for rocket engines according to claim 3, characterized in that the assembly holes (3) are counter bores.

5. A tooling plate for a rocket engine according to claim 3, characterized in that a first positioning pin hole (13) is provided between two adjacent assembly holes (3), the first positioning pin hole (13) penetrating the upper (111) or lower (121) connection face.

6. Tooling plate for rocket engines according to claim 1, characterized in that said arc plate (1) is provided with second dowel holes (14) in the thickness direction, said second dowel holes (14) being distributed circumferentially along said arc plate (1), between adjacent said first through holes (2).

7. Tooling plate for rocket engines according to claim 1, characterized in that the arc plate (1) is of stainless steel.

8. Tooling plate for rocket engines according to claim 1, characterized in that the inner radius of the arc plate (1) is 1700mm and the outer radius is 1800mm.

9. Tooling plate for rocket engines according to claim 1, characterized in that the diameter of the first through holes (2) is 21mm and the radius of the line connecting the centers of the plurality of first through holes (2) is 1750mm.