Solid rocket engine ignition test thrust transmission tool

Abstract

The utility model discloses a solid rocket engine ignition test thrust transmission tool, which relates to the technical field of solid rocket engines and comprises a peripheral wall and a mounting plate. At least one window is arranged on the peripheral wall; wherein one end of the peripheral wall is connected with the mounting plate, and the other end of the peripheral wall is detachably connected with the engine; and one side, far away from the peripheral wall, of the mounting plate is detachably connected with the thrust sensor. The device can be suitable for ground ignition tests of various types of solid rocket engines, is simple in structure and convenient to assemble and disassemble, and improves the ignition test efficiency.

Description

Technical Field

[0001] This application relates to the technical field of solid rocket engines, and particularly to a thrust transfer tooling for solid rocket engine ignition tests. Background Art

[0002] The ground ignition test of a solid rocket engine, also known as the ground static test, fixes the engine to a test bench through test tooling. The engine ignites and operates, and data such as the thrust, pressure, temperature, and strain of the engine are measured. During the entire ignition process, the engine remains stationary relative to the test bench. The ground ignition test is an important means to evaluate the working reliability and matching of each component of the engine, the internal ballistic performance of the engine, and the structural reliability during the development of a solid rocket engine.

[0003] However, the existing ground ignition test tooling has the disadvantages of being inapplicable to ground ignition tests of various types of solid rocket engines, having a relatively complex structure, inconvenient loading and unloading, and low ignition test efficiency. Utility Model Content

[0004] The purpose of this application is to provide a thrust transfer tooling for solid rocket engine ignition tests, which can be applicable to ground ignition tests of various types of solid rocket engines, has a simple structure, is convenient for loading and unloading, and improves the ignition test efficiency.

[0005] To achieve the above objective, this application provides a thrust transfer tooling for solid rocket engine ignition tests, including: a surrounding wall and a mounting plate; at least one window is provided on the surrounding wall; wherein, one end of the surrounding wall is connected to the mounting plate, and the other end of the surrounding wall is detachably connected to the engine; the side of the mounting plate away from the surrounding wall is detachably connected to a thrust sensor.

[0006] As above, wherein, the surrounding wall is a hollow cylinder; the mounting plate is a circular plate.

[0007] As above, wherein, there are three windows.

[0008] As above, wherein, the three windows are arranged at equal intervals in a circumferential direction around the central axis of the surrounding wall.

[0009] As above, wherein, at least one first threaded hole is provided on the mounting plate, and it is connected to the thrust sensor through the first threaded hole.

[0010] As above, wherein, there is one first threaded hole, and the first threaded hole is arranged in the middle of the mounting plate.

[0011] As above, wherein, a plurality of second threaded holes are provided at the other end of the surrounding wall, and it is connected to the engine through the second threaded holes.

[0012] As above, wherein, there are six second threaded holes.

[0013] As described above, the second threaded hole is connected to the engine by an M8 screw.

[0014] As described above, the diameter of the peripheral wall is greater than the diameter of the engine, and the outer diameter of the engine and the inner diameter of the other end of the peripheral wall are in shaft-hole fit.

[0015] The thrust transfer tooling for the solid rocket engine ignition test of the present application can be applied to the ground ignition tests of various types of solid rocket engines. It has the characteristics of simple structure, wide application range and simple loading and unloading, and can greatly improve the efficiency of the ground ignition test of solid rocket engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments recorded in the present application. For those of ordinary skill in the art, other drawings can also be obtained according to these drawings.

[0017] Figure 1 FIG. is a schematic structural diagram of an embodiment of the thrust transfer tooling for the solid rocket engine ignition test;

[0018] Figure 2 FIG. is a schematic structural diagram of another embodiment of the thrust transfer tooling for the solid rocket engine ignition test, wherein Figure 2 in (a) is the front view of the thrust transfer tooling for the solid rocket engine ignition test, Figure 2 in (b) is Figure 2 the A-A sectional view of (a) in Figure 2 in (c) is Figure 2 the B-B sectional view of (a) in

[0019] Figure 3 FIG. is a perspective view of an embodiment of the thrust transfer tooling for the solid rocket engine ignition test. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0020] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0021] As Figures 1-3As shown in the figure, the present application provides a thrust transfer tooling 1 for a solid rocket engine ignition test, including: a surrounding wall 11 and a mounting plate 12; at least one window 111 is provided on the surrounding wall 11; wherein, one end of the surrounding wall 11 is connected to the mounting plate 12, and the other end of the surrounding wall 11 is detachably connected to the engine 2; the side of the mounting plate 12 away from the surrounding wall 11 is detachably connected to the thrust sensor.

[0022] Specifically, as an embodiment, the surrounding wall 11 and the mounting plate 12 are of an integral structure.

[0023] As another embodiment, the surrounding wall 11 and the mounting plate 12 are of a separable structure.

[0024] When the surrounding wall 11 and the mounting plate 12 are of a separable structure, one end of the surrounding wall 11 is welded to the mounting plate 12, but not limited to welding.

[0025] Further, the engine 2 is a solid rocket engine, but not limited to a solid rocket engine. The present application preferably uses a solid rocket engine.

[0026] Further, the specific shape of the surrounding wall 11 is set according to the actual situation. The present application preferably uses a cylindrical body with a through middle.

[0027] Further, the specific shape of the mounting plate 12 is set according to the actual situation. The present application preferably uses a circular plate.

[0028] Further, the specific number of the windows 111 is set according to the actual situation. The present application preferably uses three.

[0029] Further, the three windows 111 are arranged at equal intervals in a circumferential direction around the central axis of the surrounding wall 11, but not limited to being arranged at equal intervals in a circumferential direction around the central axis of the surrounding wall 11.

[0030] Further, the windows 111 are located in the middle section of the surrounding wall 11.

[0031] Specifically, opening three windows 111 in the middle section of the thrust transfer tooling 1 for the solid rocket engine ignition test can minimize the weight while ensuring the strength and stiffness of the tooling, ensuring the convenience of use of the tooling.

[0032] In addition, the windows 111 located in the middle section of the surrounding wall 11 are also used to connect the engine head pressure sensor pipeline and the ignition cable.

[0033] Further, at least one first threaded hole 121 is provided on the mounting plate 12, and it is connected to the thrust sensor through the first threaded hole 121.

[0034] Specifically, the specific number of the first threaded holes 121 is set according to the actual situation. During the engine test, the thrust sensor is installed at the first threaded holes 121.

[0035] Furthermore, the first threaded hole 121 is a threaded hole with M20×1.5 and a length of 18 mm, but it is not limited to the threaded hole with M20×1.5 and a length of 18 mm. This application preferably uses a threaded hole with M20×1.5 and a length of 18 mm.

[0036] Furthermore, there is one first threaded hole 121, and the first threaded hole 121 is arranged in the middle of the mounting plate 12.

[0037] Furthermore, a plurality of second threaded holes 112 are arranged at the other end of the peripheral wall 11, and the engine is connected through the second threaded holes 112.

[0038] Furthermore, the specific number of the second threaded holes 112 is set according to the actual situation, and this application preferably uses six.

[0039] Furthermore, the six second threaded holes 112 are arranged at circumferentially uniform intervals around the central axis of the peripheral wall 11, but it is not limited to being arranged at circumferentially uniform intervals around the central axis of the peripheral wall 11.

[0040] Furthermore, the second threaded holes 112 and the engine are connected by M8 screws 3, but it is not limited to M8 screws 3. This application preferably uses M8 screws 3.

[0041] Furthermore, the diameter of the peripheral wall 11 is larger than the diameter of the engine, and the outer diameter of the engine and the inner diameter of the other end of the peripheral wall 11 are in shaft-hole fit.

[0042] Specifically, the right end of the thrust transfer tooling 1 for solid rocket engine ignition test is connected and fixed to the engine. The outer diameter of the engine and the inner diameter of the other end of the peripheral wall 11 are designed to be in shaft-hole fit relationship, and the end face is the tightening face. Six M8 threaded holes are arranged in the radial direction of the other end of the peripheral wall 11, which is convenient for installation and fixation.

[0043] The working principle of the thrust transfer tooling 1 for solid rocket engine ignition test in this application is specifically as follows: When in use, the solid rocket engine is docked with one side of the thrust transfer tooling 1 for solid rocket engine ignition test. After docking, six M8 screws are radially installed to ensure reliable fixation with the thrust transfer tooling 1 for solid rocket engine ignition test during the engine test. The pipeline of the pressure sensor at the head of the engine and the ignition cable are led out from the window 111 in the middle section of the thrust transfer tooling 1 for solid rocket engine ignition test. The other side of the thrust transfer tooling 1 for solid rocket engine ignition test is connected to the thrust sensor, and then the entire thrust transfer tooling 1 for solid rocket engine ignition test and the engine are placed on the test bench for ignition test.

[0044] The thrust transfer tooling for the ignition test of the solid rocket motor of the present application can be applicable to the ground ignition tests of various types of solid rocket motors, and has the characteristics of simple structure, wide application range and simple loading and unloading, and can greatly improve the efficiency of the ground ignition test of the solid rocket motor.

[0045] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications to these embodiments once they learn the basic creative concept. Therefore, the protection scope of the present application is intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application. Obviously, those skilled in the art can make various changes and variations to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the protection of the present application and its equivalent technologies, the present application also intends to include these modifications and variations.

Claims

1. A thrust transfer tool for a solid rocket engine ignition test, characterized in that: include: surrounding walls and mounting plates; At least one window is arranged on the surrounding walls; One end of the surrounding wall is connected to the mounting plate, and the other end of the surrounding wall is detachably connected to the engine; The side of the mounting plate away from the surrounding walls is detachably connected to the thrust sensor.

2. The solid rocket engine ignition test thrust transmission tooling according to claim 1, characterized in that: The surrounding walls are cylindrical and through; the mounting plate is a circular plate.

3. The solid rocket engine ignition test thrust transmission tooling according to claim 2, characterized in that: There are three windows.

4. The solid rocket engine ignition test thrust transmission tooling according to claim 3, characterized in that: The three windows are evenly spaced around the central axis of the surrounding walls.

5. The solid rocket engine ignition test thrust transmission tooling according to claim 1, characterized in that: The mounting plate is provided with at least one first threaded hole, and is connected to the thrust sensor through the first threaded hole.

6. The solid rocket engine ignition test thrust transmission tooling according to claim 5, characterized in that: There is one first threaded hole, and the first threaded hole is arranged in the middle of the mounting plate.

7. The solid rocket engine ignition test thrust transmission tooling according to claim 1, characterized in that: The other end of the surrounding wall is provided with a plurality of second threaded holes, and is connected to the engine through the second threaded holes.

8. The solid rocket engine ignition test thrust transmission tooling according to claim 7, characterized in that: The number of the second threaded holes is six.

9. The solid rocket engine ignition test thrust transmission tooling according to claim 7, characterized in that: Connect the second threaded hole to the engine using an M8 screw.

10. The solid rocket engine ignition test thrust transmission tooling according to claim 7, characterized in that: The diameter of the surrounding wall is larger than the diameter of the engine, and the outer diameter of the engine and the inner diameter of the other end of the surrounding wall are matched with the shaft hole.

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