Solid rocket engine front opening protection tool

Abstract

The utility model relates to the technical field of solid rocket engines, in particular to a solid rocket engine front opening protection tool which comprises a circular ring body, a protection mechanism is arranged above the circular ring body, a groove is formed in the upper end of the circular ring body, and the protection mechanism comprises an outer side buffer ring and a bolt. According to the protection tool for the front opening of the solid rocket engine, through cooperation of the handle and the protection mechanism, an operator rotates the bolt to enable the end of the bolt to be separated from a threaded hole machined in the clamping ring, then the operator pulls the handle upwards, and the clamping ring and the inner side buffering ring are fixedly connected in sequence from outside to inside. The handle moves to drive the outer side buffer ring and the inner side buffer ring to move so as to drive the clamping ring to move upwards, so that when the inner side buffer ring and the outer side buffer ring need to be disassembled, an operator only needs to rotate a plurality of bolts, the operator does not need to consume more physical power, and therefore manual labor is saved.

Description

Technical Field

[0001] The utility model relates to the technical field of solid rocket engines, and particularly relates to a front opening protection tooling for a solid rocket engine. Background Technique

[0002] A solid rocket engine is a chemical rocket engine that uses solid propellant, also known as a solid propellant rocket engine. The front opening end face of the solid rocket engine is higher than the surface of the ignition device top cover. After the top cover installation bolts are installed, the edge of the bolt is very close to the inner side of the front opening aluminum skirt rib frame, leaving a small space for lead sealing operation. When the lead sealing wire is pulled out through the bolt hole, it is easy to touch the aluminum skirt rib frame and cause scratches.

[0003] For example, a front opening protection tooling for a solid rocket engine with the publication number of "CN221299326U" achieves the purpose of protecting the front opening of the engine, solves the quality hidden danger of scratching the product when the lead sealing wire of the connecting bolt at the front opening of the engine is pulled out, solves the irreversible damage and long time-consuming problems of the product caused by the small space for personnel lead sealing operation, improves the production efficiency, installs the tooling on the front opening aluminum skirt rib frame, effectively eliminates the quality hidden danger of the lead sealing wire scratching the product, ensures the appearance quality of the product, and shortens the product delivery cycle. However, for this front opening protection tooling of the solid rocket engine, the inner buffer ring and the outer buffer ring are fixed by injection molding. When it is necessary to disassemble the inner buffer ring and the outer buffer ring, the operator pulls the inner buffer ring and the outer buffer ring away from the circular ring body, which requires the operator to consume a lot of physical strength and pull the inner buffer ring and the outer buffer ring forcefully, thus increasing the labor intensity. Content of the Utility Model

[0004] The purpose of the utility model is to solve the problem that when the inner buffer ring and the outer buffer ring are fixed by injection molding and it is necessary to disassemble the inner buffer ring and the outer buffer ring, the operator needs to consume a lot of physical strength and pull the inner buffer ring and the outer buffer ring forcefully, thus increasing the labor intensity, and a front opening protection tooling for a solid rocket engine is proposed.

[0005] To achieve the above purpose, the utility model provides the following technical solution:

[0006] Design a front opening protection tooling for a solid rocket engine, including a circular ring body, a protection mechanism is arranged above the circular ring body, and a groove is arranged at the upper end of the circular ring body.

[0007] Preferably, the protection mechanism includes an outer buffer ring and a bolt, and a snap ring and an inner buffer ring are fixedly connected to the inner wall of the outer buffer ring in sequence from outside to inside.

[0008] Preferably, the outer wall of the snap ring is inserted into the groove. A plurality of threaded holes are provided at the lower end of the snap ring, and the bolts are respectively threadedly connected to the circular ring body and the threaded holes.

[0009] Preferably, the inner wall of the outer buffer ring is closely attached to the outer wall of the circular ring body, and the outer wall of the inner buffer ring is closely attached to the inner wall of the circular ring body.

[0010] Preferably, the inner wall of the outer buffer ring is slidably connected to the two handles.

[0011] For a front-opening protection tooling of a solid rocket motor proposed by the present utility model, the beneficial effects are as follows: Through the cooperation of the handle and the protection mechanism, the operator rotates the bolt to separate the end of the bolt from the threaded hole machined on the snap ring. Then, the operator pulls the handle upward, and the movement of the handle drives the movement of the outer buffer ring and the inner buffer ring, thereby driving the snap ring to move upward. To achieve the disassembly of the inner buffer ring and the outer buffer ring, the operator only needs to rotate a plurality of bolts. Compared with pulling the outer buffer ring and the inner buffer ring apart, rotating a plurality of bolts requires less force and does not require the operator to consume a lot of physical strength, thus saving labor. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 is a schematic structural diagram of the present utility model;

[0013] Figure 2 is Figure 1 a top view cross-sectional view of the protection mechanism in ;

[0014] Figure 3 is Figure 1 a three-dimensional schematic diagram of the circular ring body in ;

[0015] Figure 4 is Figure 1 a front view cross-sectional view of ;

[0016] Figure 5 is Figure 1 a bottom view of.

[0017] In the figure: 1, circular ring body; 2, handle; 3, protection mechanism; 301, outer buffer ring; 302, inner buffer ring; 303, snap ring; 304, threaded hole; 305, bolt; 4, groove. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0018] The present utility model will be further described below with reference to the accompanying drawings:

[0019] Refer to the attached Figures 1-5: In this embodiment, a front-opening protection tooling for a solid rocket motor includes a toroid 1. A protection mechanism 3 is provided above the toroid 1. A groove 4 is provided at the upper end of the toroid 1, and the shape of the groove 4 is adapted to the shape of the snap ring 303. The protection mechanism 3 includes an outer buffer ring 301 and bolts 305. The inner wall of the outer buffer ring 301 is fixedly connected with a snap ring 303 and an inner buffer ring 302 in sequence from outside to inside. The toroid 1, the outer buffer ring 301 and the inner buffer ring 302 have been disclosed in the publication number "CN221299326U", and will not be elaborated here. The inner buffer ring 302 and the outer buffer ring 301 are made of flexible materials, specifically rubber rings. The outer wall of the snap ring 303 is inserted into the groove 4. A plurality of threaded holes 304 are provided at the lower end of the snap ring 303, and the internal threads machined on the inner wall of the threaded holes 304 are adapted to the external threads machined on the bolts 305. The bolts 305 are threadedly connected to the toroid 1 and the threaded holes 304 respectively. The inner wall of the outer buffer ring 301 is closely attached to the outer wall of the toroid 1, and the outer wall of the inner buffer ring 302 is closely attached to the inner wall of the toroid 1. The inner wall of the outer buffer ring 301 is slidably connected to the two handles 2, and the outer buffer ring 301 can be easily operated by the operator through the handles 2.

[0020] Working principle:

[0021] When using the front-opening protection tooling for a solid rocket motor:

[0022] Installation process of the inner and outer buffer rings:

[0023] First, the operator inserts the snap ring 303 into the groove 4 machined on the toroid 1, and then the operator rotates the bolt 305 to make the end of the bolt 305 cooperate with the threaded hole 304 machined on the snap ring 303. When the upper end of the toroid 1 abuts against the upper part of the inner wall of the outer buffer ring 301, the operator stops rotating the bolt 305, and the fixation of the outer buffer ring 301 is completed, making the toroid 1 located between the outer buffer ring 301 and the inner buffer ring 302.

[0024] Installation process of the toroid:

[0025] Then, the operator puts the ring body 1 with the outer buffer ring 301 and the inner buffer ring 302 installed on the front opening aluminum skirt edge frame of the solid rocket motor, and moves the ring body 1 with the outer buffer ring 301 and the inner buffer ring 302 installed downward. The inner buffer ring 302 and the outer buffer ring 301 are squeezed and deformed. The installation of the front opening aluminum skirt edge frame of the solid rocket motor and the ring body 1 is completed. The deformed inner buffer ring 302 and outer buffer ring 301 are pressed against the inner and outer surface of the front opening aluminum skirt edge frame of the solid rocket motor, and also make the ring body 1 more stably stuck at the end of the front opening aluminum skirt edge frame of the solid rocket motor. The inner buffer ring 302 and the outer buffer ring 301 can prevent the ring body 1 from scratching the surface of the front opening aluminum skirt edge frame of the solid rocket motor during the installation process.

[0026] Disassembly process of the inner and outer buffer rings:

[0027] The operator rotates the bolt 305 to separate the end of the bolt 305 from the threaded hole 304 machined on the snap ring 303. Then, the operator inserts the two handles 2 into the outer buffer ring 301 (the handles 2 will only be inserted into the outer buffer ring 301 when disassembly is required, and the handles 2 are not at the outer buffer ring 301 during normal use), and pulls the handles 2 upward. The movement of the handles 2 drives the movement of the outer buffer ring 301 and the inner buffer ring 302, thus driving the snap ring 303 to move upward. During disassembly, the operator only needs to rotate a plurality of bolts 305, without the operator consuming too much physical strength, thus saving labor.

[0028] Although the present utility model has been illustrated and described by referring to the preferred embodiments, those of ordinary skill in the art should understand that various changes in form and details can be made within the scope of the claims.

Claims

1. A solid rocket engine front opening protection tool, comprising a torus (1), characterized in that: A protective mechanism (3) is provided above the annular body (1), a groove (4) is provided at the upper end of the annular body (1), the protective mechanism (3) comprises an outer buffer ring (301) and a bolt (305), and a clamping ring (303) and an inner buffer ring (302) are fixedly connected to the inner wall of the outer buffer ring (301) in sequence from the outside to the inside.

2. A solid rocket engine front opening protection tooling according to claim 1, characterized in that: The outer wall of the clamping ring (303) is plugged into the groove (4); a plurality of threaded holes (304) are provided at the lower end of the clamping ring (303); and the bolts (305) are respectively connected to the annular body (1) and the threaded holes (304) through threads.

3. A solid rocket engine front opening protection tooling according to claim 2, characterized in that: The inner wall of the outer buffer ring (301) is tightly fitted to the outer wall of the annular body (1), and the outer wall of the inner buffer ring (302) is tightly fitted to the inner wall of the annular body (1).

4. A solid rocket engine front opening protection tooling according to claim 3, characterized in that: The inner wall of the outer buffer ring (301) is slidably connected to the two handles (2).

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