Solid rocket engine multi-station airtight test device and use method

Abstract

The invention discloses a solid rocket engine multi-station airtight test device and a use method. The test device is characterized by comprising a gas exhaust shunting assembly, an airtight assembly and a ball valve, the gas exhaust shunting assembly is used for an engine gas tightness experiment; and the airtight assembly is used for connecting and fixing an engine and is connected with the gas exhaust shunting assembly through a ball valve. The invention further discloses a using method of the testing device. Compared with the prior art, through the airtight assembly, multiple solid rocket engines can be subjected to airtight test at the same time, and the efficiency of the engines in the airtight test process is effectively improved; through the boss interface of the base, the time consumed by thread screwing is reduced, and the butt joint disassembly and assembly efficiency is improved; axial limiting in the airtight process of the engine can be achieved through the base and the clamping cover, fast disassembly and assembly can be achieved, the base does not need to be replaced or adjusted when multiple products are subjected to airtight detection in sequence, safety is guaranteed, and the overall efficiency in the airtight test of the multiple engines is remarkably improved.

Description

Technical Field

[0001] The present invention belongs to the field of solid rocket engines, and particularly relates to a multi-station airtight test device for solid rocket engines and a usage method thereof. Background Art

[0002] The process of solid rocket engines is complex and the flow is cumbersome. To ensure production safety requirements and product quality, strict and detailed airtightness detection should be carried out before the solid rocket engines leave the factory, during storage, and before launch. Since the number of solid rocket engines that need to be subjected to airtightness tests in each batch is large, the airtightness test for a single solid rocket engine takes a long time, has a high labor intensity, and the production efficiency is low.

[0003] Patent document CN113155372A, "A Rocket Engine Airtightness Detection System and Detection Method", provides a rocket engine airtightness detection system and detection method, including components such as a low frame, a connecting frame, a cross beam, and a pressing screw. This invention realizes the airtightness test installation of the engine through screw pressing, and can realize the function of simultaneously testing the airtightness of multiple engines by setting multiple sets of pressing components and detection components. However, the disassembly and assembly of the screw pressing method require screwing the screw multiple times, and the time taken to lift and press through the thread is similar to the time taken to directly connect the airtight nozzle with the thread structure, resulting in low efficiency. Summary of the Invention

[0004] To solve the above problems, the present invention provides a multi-station airtight test device for solid rocket engines, which includes an air exhaust shunt component, an airtight component, and a ball valve; the air exhaust shunt component is used for the airtightness experiment of the engine; the airtight component is used to connect and fix the engine and is connected to the air exhaust shunt component through a ball valve.

[0005] Furthermore, the air exhaust shunt component is provided with a ball valve, an external ball valve, an air exhaust shunt, and a plug; the ball valve is fixed on the upper part of the air exhaust shunt; the external ball valve is fixed on the side of the air exhaust shunt for connecting the air source; the plug is fixed at the end of the air exhaust shunt; the air exhaust shunt realizes sealing through the ball valve and the plug.

[0006] Furthermore, there are six ball valves.

[0007] Furthermore, the ball valve is threadedly and tightly connected to the base.

[0008] Furthermore, the ball valve is threadedly connected to the air exhaust shunt.

[0009] Furthermore, the airtight component includes a base and a clamping cover; the base is used to place the engine and perform axial limitation on the engine; the clamping cover is used to press and fix the engine, and the engine is pressed and fixed by screwing the clamping cover.

[0010] Furthermore, the base and the card cover adopt a snap - fit assembly form, with upper - lower butt - joint assembly, and the axial limit of the card cover can be realized by screwing the card cover.

[0011] Furthermore, the base is provided with a docking boss for connecting the engine head interface.

[0012] The present invention also provides a usage method of the above - mentioned multi - station airtight test device for solid rocket engines, which is characterized by including the following steps:

[0013] S1: Remove the card cover from the base, put an O - ring on each inner interface of the base; place the engine into the base, and realize the axial seal of the product through the O - ring and the sealing groove at the engine interface; assemble the card cover with the base through the snap - fit to realize the axial limit of the engine.

[0014] S2: Connect the gas source pipeline led out from the airtight test bench with the external ball valve on the gas exhaust shunt assembly; adjust the opening and closing of the external ball valve and the ball valve to realize the sealing of the gas exhaust shunt and the gas source shunt, so as to conduct airtight tests on single or multiple engines.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] (1) The present invention realizes the simultaneous airtight tests of multiple solid rocket engines through the airtight assembly, effectively improving the efficiency of the engine during the airtight test process.

[0017] (2) Through the boss interface of the base, the engine does not need to use a threaded interface every time during the airtight test, reducing the time consumed by screwing the threads and improving the docking disassembly efficiency.

[0018] (3) Through the base and the card cover, the axial limit of the engine during the airtight process can be realized, and it can be quickly disassembled and assembled. When multiple products are sequentially subjected to airtightness detection, the base does not need to be replaced or adjusted, and can always be grounded, which not only ensures safety but also significantly improves the overall efficiency during the airtight test of multiple engines. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following - described drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0020] Figure 1 It is a three - dimensional schematic diagram of a multi - station airtight test device for solid rocket engines of the present invention;

[0021] Figure 2It is a two-dimensional schematic diagram of a multi-station airtight test device for a solid rocket engine of the present invention;

[0022] Figure 3 It is a structural schematic diagram of the air discharge and shunt assembly of the present invention;

[0023] Figure 4 It is a structural schematic diagram of the airtight assembly of the present invention.

[0024] In the figure: 10 is the air discharge and shunt assembly; 101 is the ball valve; 102 is the external ball valve; 103 is the air discharge shunt; 104 is the plug; 20 is the airtight assembly; 201 is the base; 202 is the clamping cover. Specific embodiments

[0025] The following uses specific specific examples to illustrate the implementation manners of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.

[0026] It should be noted that the diagrams provided in the following embodiments only illustrate the basic concept of the present invention in a schematic manner. Therefore, only the components related to the present invention are shown in the diagrams, rather than being drawn according to the number, shape, and size of the components during actual implementation. The types, quantities, and ratios of the components during actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0027] As Figure 1 and Figure 2 shown, a multi-station airtight test device for a solid rocket engine of the present invention includes an air discharge and shunt assembly 10, an airtight assembly 20, and a ball valve 101; the air discharge and shunt assembly 10 is used for the airtightness test of the engine; the airtight assembly 20 is used to connect and fix the engine and is connected to the air discharge and shunt assembly 10 through the ball valve 101.

[0028] As Figure 3 shown, the air discharge and shunt assembly 10 is provided with a ball valve 101, an external ball valve 102, an air discharge shunt 103, and a plug 104; the ball valve 101 is fixed on the upper part of the air discharge shunt 103; the external ball valve 102 is fixed on the side of the air discharge shunt 103 and is used to connect the air source; the plug 104 is fixed at the end of the air discharge shunt 103; the air discharge shunt 103 is sealed through the ball valve 101 and the plug 104.

[0029] There are six ball valves 101. The ball valve 101 is threadedly fastened to the base 201. The ball valve 101 is threadedly connected to the air discharge shunt 103.

[0030] The airtight assembly 20 includes a base 201 and a clamping cover 202; the base 201 is used to place the engine and axially limit the engine; the clamping cover 202 is used to tightly fix the engine, and the engine is tightly fixed by screwing the clamping cover 202.

[0031] As Figure 4 shown, the base 201 and the clamping cover 202 adopt a snap-fit assembly form, are butted and assembled up and down, and the axial limit of the clamping cover 202 can be realized by screwing the clamping cover 202. The base 201 is provided with a docking boss for connecting the engine head interface.

[0032] The specific steps of the usage method of the multi-station airtight test device for solid rocket engines of the present invention are as follows:

[0033] S1: Remove the clamping cover 202 from the base 201, and put an O-ring on the inner interface of each base 201; place the engine into the base 201, and realize the axial seal of the product through the O-ring and the seal groove at the engine interface; assemble the clamping cover 202 with the base 201 through a snap-fastener to realize the axial limit of the engine.

[0034] S2: Connect the gas source pipeline led out by the airtight test bench to the external ball valve 102 on the gas discharge shunt assembly 10; adjust the opening and closing of the external ball valve 102 and the ball valve 101 to realize the sealing and gas source shunting of the gas discharge shunt 103, so as to conduct airtight tests on single or multiple engines.

[0035] Compared with the prior art, the present invention realizes the simultaneous airtight test of multiple solid rocket engines through the airtight assembly, effectively improving the efficiency of the engine during the airtight test; through the boss interface of the base, the time-consuming of thread screwing is reduced, and the docking disassembly and assembly efficiency is improved; the axial limit of the engine during the airtight process can be realized through the base and the clamping cover, and it can be quickly disassembled and assembled. When multiple products are sequentially subjected to airtightness detection, the base does not need to be replaced or adjusted, which not only ensures safety but also significantly improves the overall efficiency during the airtight test of multiple engines.

[0036] The embodiments of the present invention described above are only used to help explain the present invention. These embodiments are selected and specifically described in order to better explain the principle and practical application of the present invention, so that those skilled in the relevant technical field can understand and utilize the present invention well. The embodiments do not elaborate on all the details, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and variations can be made according to the content of this specification, and these all belong to the protection scope of the present invention.

Claims

1. A multi-station airtight test device for a solid rocket motor, characterized in that It includes an air exhaust shunt component (10), an airtight component (20) and a ball valve (101); The air exhaust shunt component (10) is used for the airtightness test of the engine; The airtight component (20) is used to connect and fix the engine and is connected to the air exhaust shunt component (10) through the ball valve (101).

2. The multi-station airtight test device for a solid rocket motor according to claim 1, characterized in that, The air exhaust shunt component (10) is provided with a ball valve (101), an external ball valve (102), an air exhaust shunt (103), and a plug (104); The ball valve (101) is fixed on the upper part of the air exhaust shunt (103); The external ball valve (102) is fixed on the side of the air exhaust shunt (103) and is used to connect the air source; The plug (104) is fixed at the end of the air exhaust shunt (103); The air exhaust shunt (103) is sealed through the ball valve (101) and the plug (104).

3. The multi-station airtight test device for a solid rocket motor according to claim 2, characterized in that, There are six ball valves (101).

4. The multi-station airtight test device for solid rocket motors according to claim 2, characterized in that, The ball valve (101) is threadedly and firmly connected to the base (201).

5. The multi-station airtight test device for a solid rocket motor according to claim 2, characterized in that, The ball valve (101) is threadedly connected to the air exhaust shunt (103).

6. The multi-station airtight test device for a solid rocket motor according to claim 1, characterized in that, The airtight component (20) includes a base (201) and a clamping cover (202); The base (201) is used to place the engine and axially limit the engine; The clamping cover (202) is used to press and fix the engine, and the engine is pressed and fixed by screwing the clamping cover (202).

7. The multi-station airtight test device for a solid rocket motor according to claim 6, wherein, The base (201) and the clamping cover (202) are assembled in a snap-fit form, with upper and lower butt-joint assembly. The axial limit of the clamping cover (202) can be achieved by screwing the clamping cover (202).

8. The multi-station airtight test device for solid rocket motors according to claim 6, characterized in that, The base (201) is provided with a docking boss for connecting the engine head interface.

9. The usage method of the multi-station airtight test device for a solid rocket motor according to claim 1, characterized in that, It includes the following steps: S1: Remove the clamping cover (202) from the base (201), and put an O-ring on the inner interface of each base (201); place the engine in the base (201), and achieve the axial seal of the product through the O-ring and the sealing groove at the engine interface; assemble the clamping cover (202) with the base (201) through the snap-fit to achieve the axial limit of the engine. S2: Connect the air source pipeline led out from the airtight test bench to the external ball valve (102) on the air exhaust shunt component (10); adjust the opening and closing of the external ball valve (102) and the ball valve (101) to achieve the sealing and air source shunt of the air exhaust shunt (103), so as to conduct the airtightness test on a single or multiple engines.

Images