Portable multi-engine air tightness detection device for solid rocket engine

Abstract

The utility model provides portable multi-engine air tightness detection equipment for solid rocket engines. A pressure reducing valve device is in sealed connection with a self-locking interface through a Teflon pipe; the terminal straight joint is sequentially connected with the three-way connector pipe and the micrometering valve in series through the stainless steel pipe and communicated with the self-locking connector through the stainless steel pipe, and the pressure gauge is connected to the three-way connector pipe. The device can be alternately operated with procedures after air tightness detection, the equipment operation distance can be freely controlled, and the safety risk is greatly improved; and the maximum quantity can be detected simultaneously according to the quantification of the assembly plant.

Description

Technical Field

[0001] The invention relates to the technical field of air tightness detection, and specifically to a portable multi-engine air tightness detection device for an engine. Background Art

[0002] The air tightness test stage of solid rocket engines is completed after the engine is assembled. The engine is a fire-related product. Due to the relevant special characteristics of the product, the existing solid rocket engine air tightness test equipment mainly has fixed processes, fixed positions and single-shot test operations. Among them, the fixed process and fixed position are affected by the equipment structure, which makes the equipment inconvenient to disassemble and move, resulting in poor alternation between the test process and subsequent processes, limited movement and operation distance of the equipment, and low safety index; the air tightness test time for small-caliber solid rockets is required to be 5 minutes, and the air tightness test time for large-caliber solid rockets is required to be at least 2 hours. The low efficiency of single-shot air tightness testing is obvious during mass production. The existing equipment is difficult to meet production needs in terms of operation and efficiency. Summary of the invention

[0003] In order to overcome the deficiencies of the prior art, the present invention provides a portable multi-engine air tightness detection device for solid rocket engines. The present invention mainly solves the following deficiencies of the prior art.

[0004] a. The testing process is fixed and cannot be coordinated or operated alternately with other processes;

[0005] b. The equipment has a limited operating distance, a low safety index and is not easy to move;

[0006] c. Only single-shot detection is possible, and the detection efficiency is low.

[0007] The technical solution adopted by the present invention to solve its technical problem is:

[0008] A portable multi-engine air tightness detection device for a solid rocket engine, comprising a pressure reducing valve device (8), a self-locking interface (6), a fine-adjustment valve (4), a three-way interface pipe (2), a pressure gauge (3), a Teflon tube (7), a stainless steel tube (5) and a terminal straight-through (1);

[0009] The portable multi-engine air tightness detection equipment for solid rocket engines comprises a component 1 and a component 2. Component 1 is a pressure reducing valve device (8) which is sealedly connected to a self-locking interface (6) through a Teflon tube (7); component 2 is a terminal straight-through (1) which is connected in series with a three-way interface tube (2) and a fine-tuning valve (4) through a stainless steel tube (5) in sequence, and is connected to a self-locking interface (6) through the stainless steel tube (5); a pressure gauge (3) is connected to the three-way interface tube (2).

[0010] The connection between component 1 and component 2 is fixed by a self-locking interface (6).

[0011] The number of components in component 2 is increased according to the detection requirements, and they are connected in parallel to the pressure reducing valve device (8).

[0012] The pressure reducing valve device (8) is connected to a gas source.

[0013] The gas source is a nitrogen bottle.

[0014] The beneficial effects of the present invention are:

[0015] a. It can be operated alternately with the process after air tightness test;

[0016] b. The equipment operation distance can be freely controlled, greatly improving safety risks;

[0017] c. According to the assembly plant quantity, the maximum number of simultaneous tests can be met. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of a portable multi-engine air tightness detection device for solid rocket engines of the present invention.

[0019] Figure 2 It is a schematic diagram of a portable multi-engine air tightness detection device for solid rocket engines of the present invention.

[0020] Figure 3 This is a schematic diagram of a portable multi-engine air tightness test device for a certain type of solid rocket engine.

[0021] Among them, 1-terminal straight-through; 2-three-way interface pipe; 3-pressure gauge; 4-fine-tuning valve; 5-stainless steel pipe; 6-self-locking interface; 7-Teflon tube; 8-pressure reducing valve device; 9-gas source. DETAILED DESCRIPTION

[0022] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0023] A portable multi-engine air tightness detection device for a solid rocket engine, comprising a pressure reducing valve device (8), a self-locking interface (6), a fine-adjustment valve (4), a three-way interface pipe (2), a pressure gauge (3), a Teflon tube (7), a stainless steel tube (5) and a terminal straight-through (1);

[0024] The portable multi-engine air tightness detection equipment for solid rocket engines comprises a component 1 and a component 2. Component 1 is a pressure reducing valve device (8) which is sealedly connected to a self-locking interface (6) through a Teflon tube (7); component 2 is a terminal straight-through (1) which is connected in series with a three-way interface tube (2) and a fine-tuning valve (4) through a stainless steel tube (5) in sequence, and is connected to a self-locking interface (6) through the stainless steel tube (5); a pressure gauge (3) is connected to the three-way interface tube (2).

[0025] The connection between component 1 and component 2 is fixed by a self-locking interface (6).

[0026] The number of components in component 2 is increased according to the detection requirements, and they are connected in parallel to the pressure reducing valve device (8).

[0027] The pressure reducing valve device (8) is connected to a gas source.

[0028] The gas source is a nitrogen bottle.

[0029] like Figure 1 As shown, the present invention belongs to a device for air tightness detection of solid rocket engines after assembly. By inputting the air source and combining the relevant components, the air source pressure is safely reduced to the use range, and the operating distance is effectively controlled. For example, during batch production detection, according to Figure 2 Connect in parallel.

[0030] When testing the air tightness of a certain model of 300mm caliber rocket sled engine after assembly, due to the large model and weight of the product, and the fire-related product must have a sufficient operating distance, the present invention can solve the above problems. The specific use example is as follows Figure 3 shown.

Claims

1. A portable multi-engine air tightness detection device for solid rocket engines, comprising a pressure reducing valve device (8), a self-locking interface (6), a fine-adjustment valve (4), a three-way interface pipe (2), a pressure gauge (3), a Teflon tube (7), a stainless steel tube (5) and a terminal straight-through (1), characterized in that: In the portable multi-engine air tightness detection device for solid rocket engines, the portable multi-engine air tightness detection device for solid rocket engines comprises a component 1 and a component 2, wherein the component 1 is a pressure reducing valve device (8) which is sealedly connected to a self-locking interface (6) through a Teflon tube (7); the component 2 is a terminal straight-through (1) which is connected in series with a three-way interface tube (2) and a fine-tuning valve (4) through a stainless steel tube (5) in sequence, and is connected to the self-locking interface (6) through the stainless steel tube (5), and a pressure gauge (3) is connected to the three-way interface tube (2).

2. The portable multi-engine air tightness detection device for solid rocket engines according to claim 1 is characterized in that: The connection between component 1 and component 2 is fixed by a self-locking interface (6).

3. The portable multi-engine air tightness detection equipment for solid rocket engines according to claim 1 is characterized in that: The number of components in component 2 is increased according to the detection requirements, and they are connected in parallel to the pressure reducing valve device (8).

4. The portable multi-engine air tightness detection device for solid rocket engines according to any one of claims 1 to 3, characterized in that: The pressure reducing valve device (8) is connected to a gas source.

5. The portable multi-engine air tightness detection device for solid rocket engines according to claim 4 is characterized in that: The gas source is a nitrogen bottle.

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