Control single machine assembling and positioning tool for turbojet engine

Abstract

The utility model discloses a turbojet engine oriented control single machine assembling and positioning tool which comprises an annular structural body, a groove-shaped structure is arranged on the annular structural body, the upper surface of the groove-shaped structure is flush with the upper surface of the annular structural body, a suspension supporting lug of a turbojet engine servo mechanism can be sleeved with the interior of the groove-shaped structure, and the upper surface of the groove-shaped structure is flush with the upper surface of the annular structural body. The annular structural body is attached to the annular plane of the turbojet engine; a positioning structure is arranged on the edge of the outer side of the annular structural body, the positioning structure is provided with a positioning plane, and the positioning plane is a plane formed in the axial direction of the annular structural body and the direction perpendicular to the tangential direction of the annular structural body and is used for positioning the control single-machine mounting plate. According to the tool, one-time accurate positioning can be achieved when a control single machine of the turbojet engine is assembled, the production efficiency and the production quality are improved, and good portability is achieved.

Description

Technical Field

[0001] The utility model relates to the field of assembly tooling design, in particular to an assembly positioning tooling for a control unit facing a turbojet engine. Background Technique

[0002] Rotary turbojet engines are usually applied in fields such as ships, model aircraft, and aircraft. The control of the jet direction is realized by an external servo structure, and its control unit usually needs to be installed on the surface of the rotary turbojet engine through a structure to drive the servo structure and realize the control of the power direction of the whole product. During the assembly process of such products, the transmission effect of the servo structure has extremely high requirements for the assembly coaxiality, and the assembly position of the control unit directly affects the transmission relationship between the servo structures. Therefore, the assembly accuracy and consistency of the control unit on the surface of the rotary turbojet engine are crucial.

[0003] Since the surface of the rotary turbojet engine is a rotationally symmetric structure without a positioning structure as a reference, in the traditional production process, operators need to achieve the guarantee of the assembly accuracy and consistency of the control unit on the surface of the rotary turbojet engine through successive adjustments and comparisons. There are many problems such as complicated operation procedures, low test efficiency, and insufficient assembly consistency, which hinder the response of product performance. There is an urgent need for a structural part positioning method that can meet the assembly requirements of the control unit on the surface of the rotary turbojet engine to ensure its assembly accuracy and consistency and promote the optimization of product performance and quality improvement. Summary of the Utility Model

[0004] The technical problem solved by the utility model is: overcoming the deficiencies of the prior art, providing an assembly positioning tooling for a control unit facing a turbojet engine, ensuring the equipment accuracy and consistency when the control unit is installed on the turbojet engine, and improving the installation efficiency.

[0005] The technical solution of the utility model is: providing an assembly positioning tooling for a control unit facing a turbojet engine. The turbojet engine is a columnar body, and the outer surface of the turbojet engine has an annular groove and an annular plane below. The annular groove is used for installing a hoop structure combination and a control unit mounting plate, and the annular plane is used for installing a suspension ear. The control unit assembly positioning tooling includes an annular structure body, on which a groove-shaped structure is provided, and a suspension ear is sleeved inside the groove-shaped structure to make the annular structure body fit with the annular plane of the turbojet engine; a positioning structure is provided on the outer edge of the annular structure body, and the positioning structure has a positioning plane, and the positioning plane is a plane formed along the axial direction of the annular structure body and perpendicular to the tangent direction of the annular structure body, and is used for positioning the control unit mounting plate.

[0006] Furthermore, the positioning structure is a cuboid structure with variable thickness, including a first-thickness cuboid and a second-thickness cuboid formed integrally. The side surface of the first-thickness cuboid is fixed to the outer edge of the annular structure body, and the thickness of the first-thickness cuboid is less than that of the second-thickness cuboid.

[0007] Furthermore, the area of the positioning plane is larger than that of the control single-machine mounting plate.

[0008] Furthermore, two groove-like structures are symmetrically arranged on the annular structure body. The upper surface of the groove-like structure is flush with the upper surface of the annular structure body, and the groove body extends to one side; the lower surface of the positioning structure is flush with the lower surface of the annular structure body, and the positioning plane extends to the other side.

[0009] Furthermore, both of the two groove-like structures are rectangular grooves.

[0010] Furthermore, the internal space of the groove-like structure is the same size as that of the suspension lug.

[0011] Furthermore, the annular structure body, the groove structure, and the positioning structure are integrally formed.

[0012] Furthermore, the annular structure body, the groove structure, and the positioning structure are all made of aluminum metal.

[0013] The advantages of the present utility model compared with the prior art are as follows:

[0014] A control single-machine assembly positioning tooling is designed for the surface of a rotary-body turbojet engine without a positioning structure, which guarantees the accuracy and consistency of the control single-machine assembly on the surface of the rotary-body turbojet engine. It can achieve one-time precise positioning of the control single-machine assembly position on the surface of the rotary-body turbojet engine, reduce the number of rework iterations, and improve production efficiency and production quality. At the same time, this assembly positioning tooling has good portability and can well adapt to the installation requirements in various environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic structural diagram of the assembly positioning tooling of the present utility model;

[0016] Figure 2 is a three-dimensional model diagram of the P400Pro turbojet engine in the embodiment of the present utility model;

[0017] Figure 3 is a three-dimensional model diagram of the P400Pro turbojet engine after assembly in the embodiment of the present utility model;

[0018] Figure 4 is a schematic diagram of the thickness of the assembly positioning tooling of the present utility model. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] To better understand the technical solution of the present utility model, the embodiments of the present utility model will be specifically described below in conjunction with the accompanying drawings.

[0020] The assembly positioning tooling of this embodiment is as Figure 1 shown, and mainly includes a groove structure part 1, an annular structure part 2, and a positioning structure part 3. The overall tooling is integrally processed.

[0021] Among them, the groove structure part 1 is used to complete the relative positioning between the tooling and the engine; the annular structure part 2 is used to butt and support the bottom annular plane 5 of the engine; the positioning structure part 3 is used to position and control the fixed position of the single control unit installation plate, so as to ensure the installation accuracy of the single control unit.

[0022] Taking the P400Pro turbojet engine as an example, as a typical use object of this assembly positioning tooling, the usage method of the tooling will be described:

[0023] The three-dimensional model of the P400Pro turbojet engine is as Figure 2 shown. The overall engine is a rotary body structure, and there is a surface groove 4 on its side surface for installing the hoop structure assembly 6 and the single control unit installation plate 7 (a component of the engine's own servo structure); there is a bottom annular plane 5 in the lower half for installing the suspension ear 8 (a component of the engine's own servo structure). The specific installation process is as follows:

[0024] First, install the suspension ear 8 on the bottom annular plane 5 of the P400Pro turbojet engine, and install the hoop structure assembly 6 and the single control unit installation plate 7 in the surface groove 4 of the P400Pro turbojet engine, as Figure 3 shown. Among them, the fastening screws connecting the hoop structure assembly 6 and the single control unit installation plate 7 are not fully tightened, ensuring that the hoop structure assembly 6 and the single control unit installation plate 7 can rotate in the surface groove 4 of the P400Pro turbojet engine and will not fall off from the surface groove 4 of the P400Pro turbojet engine.

[0025] Then, align and sleeved the groove structure part 1 of the assembly positioning tooling with the suspension ear 8 already installed under the P400Pro turbojet engine, and make the annular structure part 2 of the assembly positioning tooling closely adhere to the bottom annular plane 5 of the P400Pro turbojet engine, realizing the installation of the assembly positioning tooling and the P400Pro turbojet engine. At this time, the positioning structure part 3 of the assembly positioning tooling is located outside the rotary body surface of the P400Pro turbojet engine.

[0026] Next, by rotating the hoop structure assembly 6 and the control unit mounting plate 7 within the surface groove 4 of the P400Pro turbojet engine, the control unit mounting plate 7 is made to fit against the positioning surface (the larger plane in the figure) of the positioning structure part 3 of the assembly positioning tooling. At this time, the fastening screws connecting the hoop structure assembly 6 and the control unit mounting plate 7 are tightened, causing the hoop structure assembly 6 and the control unit mounting plate 7 to hold tightly and be fixed within the surface groove 4 of the P400Pro turbojet engine.

[0027] Finally, the assembly positioning tooling is removed from beneath the P400Pro turbojet engine, and it is restored to the state where the P400Pro turbojet engine, the hoop structure assembly 6, the control unit mounting plate 7, and the suspension lugs 8 are installed, as Figure 3 shown. At this time, the relative positions of the control unit mounting plate 7 and the P400Pro turbojet engine have been fixed, so that when the control unit is subsequently installed on the control unit mounting plate 7 by screws, it is possible to achieve one-time precise positioning of the assembly position of the control unit.

[0028] During the design process of the assembly positioning tooling, through the dimensional chain transfer calculation of the three-dimensional models of the P400Pro turbojet engine, the hoop structure assembly, the control unit mounting plate, and the control unit, the thickness of the positioning structure part 3 ( Figure 4 d1, d2 in the figure) is determined. To avoid installation interference, d1 < d2; after physical assembly, the three-coordinate measurement of the installation position of the control unit is used to further fine-tune the thickness of the positioning structure part to improve the positioning accuracy of the control unit.

[0029] During the machining process of the assembly positioning tooling, a numerically controlled machine tool with a machining accuracy better than 0.1 mm is used to ensure the machining accuracy of the tooling structure, and to achieve the control and guarantee of the assembly position accuracy and consistency of the control unit on the surface of the rotary body turbojet engine.

[0030] Preferably, the assembly positioning tooling is made of 5A06 aluminum rod, with appropriate dimensions and an overall weight not exceeding 2 kg to ensure its portability.

[0031] It can be understood that the present utility model is described through embodiments. As is known to those skilled in the art, without departing from the spirit and scope of the present utility model, various changes or equivalent replacements can be made to these features and embodiments. Additionally, under the teachings of the present utility model, these features and embodiments can be modified to adapt to specific situations without departing from the spirit and scope of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed herein, and embodiments that can fall within the scope of the claims of this application all belong to the scope protected by the present utility model.

[0032] The content not described in detail in the specification of the present utility model belongs to the well-known technology of those skilled in the art.

Claims

1. A control unit assembly and positioning tool for a turbojet engine, the turbojet engine is a columnar body, the outer surface of the turbojet engine has an annular groove, and the lower part has an annular plane, the annular groove is used to install the hoop structure combination and the control unit installation plate, and the annular plane is used to install the suspension lug, characterized in that: The control unit assembly positioning tooling includes an annular structure, on which a groove structure is provided, and a suspension lug is inserted into the groove structure so that the annular structure fits the annular plane of the turbojet engine; a positioning structure is provided on the outer edge of the annular structure, and the positioning structure has a positioning plane, which is a plane formed along the axial direction of the annular structure and perpendicular to the tangent direction of the annular structure, and is used to position the control unit mounting plate.

2. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: The positioning structure is a rectangular structure with variable thickness, including an integrally formed first thickness rectangular block and a second thickness rectangular block. The side of the first thickness rectangular block is fixed to the outer edge of the annular structure, and the thickness of the first thickness rectangular block is less than that of the second thickness rectangular block.

3. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: The area of ​​the positioning plane is larger than the area of ​​the control stand-alone mounting plate.

4. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: Two groove structures are symmetrically arranged on the annular structure, the upper surface of the groove structure is flush with the upper surface of the annular structure, and the groove body extends to one side; the lower surface of the positioning structure is flush with the lower surface of the annular structure, and the positioning plane extends to the other side.

5. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: Both groove-like structures are rectangular grooves.

6. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: The internal space of the groove structure is consistent with the size of the suspension lug.

7. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: The annular structure, the groove structure and the positioning structure are integrally formed.

8. The control unit assembly and positioning tool for a turbojet engine according to claim 1, characterized in that: The annular structure, the groove structure and the positioning structure are all made of metal aluminum.

Images