CN217632713U - Solid rocket engine pressure measurement hole outgoing line sealing connection device - Google Patents
Solid rocket engine pressure measurement hole outgoing line sealing connection device Download PDFInfo
- Publication number
- CN217632713U CN217632713U CN202221691174.3U CN202221691174U CN217632713U CN 217632713 U CN217632713 U CN 217632713U CN 202221691174 U CN202221691174 U CN 202221691174U CN 217632713 U CN217632713 U CN 217632713U
- Authority
- CN
- China
- Prior art keywords
- connecting piece
- aviation
- special connecting
- hole
- solid rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Measuring Temperature Or Quantity Of Heat (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The utility model provides a solid rocket engine pressure measuring hole outgoing line sealing connecting device, which comprises a special connecting piece and an aviation sealing connector; the aviation sealing connector consists of an aviation socket and an aviation plug; the special connecting piece is of a T-shaped structure, and a through hole is formed in the center of the special connecting piece; the first end is in sealing fit with the pressure measuring hole; the second end is matched, sealed and fixedly connected with the end face of the signal output end of the aviation socket; a temperature sensor signal wire arranged on the surface of the explosive column extends into the central through hole from the pressure measuring hole and is in butt joint with the signal output end of the aviation socket; the external signal wire is connected with the aviation plug and is connected into the temperature acquisition system; the aviation plug and the aviation socket are in sealing fit to realize signal transmission. The utility model provides an engine medicine temperature measurement gas tightness problem, avoided the inside gas leakage phenomenon's of combustion chamber emergence in the process of the test, improve temperature sensor installation effectiveness, promoted temperature test process traditional chinese medicine temperature measuring accuracy and reliability by a wide margin.
Description
Technical Field
The utility model relates to a solid rocket engine ground test grain surface temperature measurement pressure measurement hole sealing connection device that is qualified for next round of competitions belongs to the experimental measurement and control technical field of solid rocket engine.
Background
For the explosive column of the combustion chamber of the solid engine for rockets and missiles, the temperature has great influence on the inner ballistic performance, and the temperature change of the explosive column in the storage process is often a common concern for designers and users. Under the condition of field operation, the engine cannot be insulated, so that the change rule of the engine temperature along with the ambient temperature needs to be accurately measured or calculated, the ballistic performance in the engine is accurately predicted, the engine parameters are adjusted, the process flow is further guided to be optimized, and the comprehensive cost of equipment maintenance is reduced.
In order to check and verify the change rule of the solid rocket engine explosive temperature along with the environmental temperature, the temperature sensor is arranged on the surface of the engine explosive column in the process of the ground temperature environmental test of the engine, and the measurement of the solid rocket engine explosive column temperature is carried out. Wherein, the signal line of the temperature sensor is led out from a pressure measuring hole of the engine block cover. In the process of the engine temperature test, a combustion chamber of the engine needs to be inflated and sealed, and the temperature environment test is carried out on the premise of ensuring certain air pressure. When a signal wire of the sensor is led out from a pressure measuring hole of the engine block cover, a lead crosses the pressure measuring hole of the block cover, a sealing measure is adopted, the conduction and the connection of the lead are ensured, and if the sealing is poor, the air leakage of the engine can be directly caused.
In the prior test process, a sensor signal wire is led out through a through hole of an adapter, the sensor signal wire penetrates through the through hole of the adapter, glue is injected into the through hole, the through hole is solidified and sealed, and the adapter is connected to a pressure measuring hole of an engine after solidification is completed, so that the sealing of a wire outlet part in the temperature environment test process is realized, and the figure 1 shows. When the adapter is used, the problem can not be solved by changing the wire core into the enameled wire because the wire core and the outer rubber cover have a hole therebetween, and the air leakage phenomenon can occur in the test process. Meanwhile, in the through hole glue injection process, a gap may exist between the glue and the signal wire, and the sealing of the outgoing line part of the engine cannot be realized. Therefore, the device cannot meet the problem of tightness of the engine outlet hole in the test process.
Disclosure of Invention
Technical problem to be solved
In recent years, in the process of testing the ground temperature environment of the engine, the test task amount of the temperature measurement of the combustion chamber of the engine is increased continuously, and in the test process, a signal wire of a temperature measurement sensor arranged on the inner wall of the combustion chamber of the engine needs to be led out through a pressure measuring hole of the engine and connected to a temperature acquisition system. When a sensor signal wire penetrates through a pressure measuring hole of the engine plug cover to be led out of an engine, if the sealing performance of a wire outlet part is poor, the phenomenon of air leakage is easy to occur, and the internal air pressure value in a combustion chamber of the engine cannot be ensured.
Need carry out medicine temperature measuring's engine at present and all have higher leakproofness requirement, in order to solve the sensor leakproofness problem of being qualified for the next round of competitions, satisfy corresponding experimental leakproofness requirement, ensure that no gas leakage phenomenon takes place among the engine temperature environment process, the utility model discloses a solid rocket engine pressure cell sealing device that is qualified for the next round of competitions improves temperature measurement sensor lead-out wire connected mode to ensure temperature sensor position sealing performance that is qualified for the next round of competitions, promote engine medicine temperature measured data reliability.
The technical scheme of the utility model is that:
a solid rocket engine pressure measuring hole outgoing line sealing connecting device comprises a special connecting piece and an aviation sealing connector; the aviation sealing connector consists of an aviation socket and an aviation plug;
the special connecting piece is of a T-shaped structure, the size of a first end of the special connecting piece is matched with that of a solid rocket engine plugging pressure measuring hole, and the size of a second end of the special connecting piece is matched with that of an aviation socket; a through hole is formed in the center of the special connecting piece and is communicated with the first end and the second end;
the first end of the special connecting piece is inserted into a pressure measuring hole of the solid rocket engine block cover and is in sealing fit with the pressure measuring hole; the second end of the special connecting piece is matched, sealed and fixedly connected with the end face of the signal output end of the aviation socket;
a temperature sensor signal wire arranged on the surface of the grain of the solid rocket engine extends into the central through hole of the special connecting piece from the pressure measuring hole, penetrates through the central through hole of the special connecting piece and then is in butt joint with the aviation socket signal output end; the external signal wire is connected with the aviation plug and is connected into the temperature acquisition system; and the aviation plug is in sealing fit with the aviation socket to realize signal transmission.
Furthermore, the second end face of the special connecting piece is provided with an annular groove, and a rubber gasket is arranged in the groove and is used for being matched with the end face of the signal output end of the aviation socket in a sealing mode.
Furthermore, a semicircular concave cavity is formed in the end face of the second end of the special connecting piece and is used for signal expansion of the temperature sensor signal wire in the semicircular concave cavity to form a plurality of branch wires which are respectively connected with the aviation socket signal output end.
Furthermore, after the temperature sensor signal wire is unfolded into a plurality of branch wires and connected with the aviation socket signal output end, glue is poured into the semicircular cavity to fix the signal wire and seal the central through hole of the special connecting piece.
Furthermore, the first end of the special connecting piece is hermetically connected with the solid rocket engine plugging pressure measuring hole in a threaded and gasket mode.
Advantageous effects
The utility model provides a pressure measurement hole sealing device that is qualified for next round of competitions mainly used solid rocket engine temperature environmental test grain temperature measurement process. When the surface temperature of the engine grain is measured, a temperature sensor signal wire needs to be led out through the capping pressure measuring hole, and the internal air tightness of the engine needs to be kept at the same time, so that the sealing device is provided to solve the problem of sealing the outlet part of the engine pressure measuring hole.
The design is simple and convenient to apply, the installation requirement of the temperature sensor in the combustion chamber of the engine can be met, the problem of air tightness of the engine during chemical temperature measurement is solved, the phenomenon of air leakage in the combustion chamber during the test process is avoided, the installation efficiency of the temperature sensor is improved, and the accuracy and the reliability of the traditional Chinese medicine temperature measurement during the temperature test process are greatly improved.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a schematic diagram of an original transfer method;
FIG. 2 is a schematic view of a sealing device;
FIG. 3 is a view showing a structure of a dedicated connector;
FIG. 4 is a side view of FIG. 3;
wherein: 1. an engine combustion chamber; 2. an adapter; 3. a temperature acquisition system; 4. a temperature sensor; 5. a signal line; 6. injecting glue through holes; 7. a dedicated connection; 8. an aviation socket; 9. an aviation plug; 10. a seal gasket groove; 11. a wire passing hole; 12. the pressure measuring hole is connected with a thread; 13. aviation socket connecting hole.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In the ground temperature environment test process of the solid rocket engine, a temperature measurement sensor signal wire arranged on the inner wall of an engine combustion chamber needs to be led out through an engine pressure measuring hole and connected to a temperature acquisition system. When a sensor signal wire penetrates through a pressure measuring hole of an engine block cover to be led out of an engine, if the sealing performance of a wire outlet part is poor, the phenomenon of air leakage is easy to occur, and the internal air pressure value in a combustion chamber of the engine cannot be ensured.
In order to solve the problem of outgoing line sealing performance of the sensor and ensure that no air leakage phenomenon occurs in the process of the temperature environment of the engine, the embodiment provides the outgoing line sealing and connecting device for the pressure measuring hole of the solid rocket engine.
As shown in fig. 2, the sealing connection device comprises a special connector and an aviation sealing connector; the aviation sealing connector consists of an aviation socket and an aviation plug.
As shown in fig. 3 and 4, the special connecting piece is of a T-shaped structure, the size of a first end is matched with that of a pressure hole of a solid rocket engine blanking cover, and the size of a second end is matched with that of an aviation socket; the center of the special connecting piece is provided with a through hole which is communicated with the first end and the second end.
The first end of the special connecting piece is inserted into the pressure measuring hole of the solid rocket engine blanking cover and is in sealing connection with the pressure measuring hole of the solid rocket engine blanking cover in a threaded and gasket mode. The second end of special connecting piece and aviation socket's signal output part end face seal fixed connection, particularly, the second end terminal surface of special connecting piece is the plane, and second end terminal surface has the annular groove, arranges the rubber packing ring in the recess, and the second end terminal surface all punches and utilizes the screw connection with the four corners of aviation socket's signal output part end face, realizes the second end terminal surface of special connecting piece and aviation socket's signal output part end face seal cooperation.
As shown in fig. 3, a semicircular cavity is formed in the second end face of the special connecting piece, and is used for signal expansion of the temperature sensor signal line into a plurality of branch lines in the semicircular cavity to be respectively connected with the aviation socket signal output end, and after the temperature sensor signal line is expanded into a plurality of branch lines and connected with the aviation socket signal output end, the semicircular cavity is filled with glue to fix the signal line and seal the central through hole of the special connecting piece.
A temperature sensor signal wire arranged on the surface of the grain of the solid rocket engine extends into the central through hole of the special connecting piece from the pressure measuring hole, penetrates through the central through hole of the special connecting piece and then is in butt joint with the signal output end of the aviation socket; the external signal wire is connected with the aviation plug and is connected into the temperature acquisition system; and the aviation plug is in sealing fit with the aviation socket to realize signal transmission. The aviation plug is a sealing plug, so that the reliable transmission of the signal wire in the sealing state of the pressure measuring hole of the combustion chamber is realized by the method. The special connecting piece, the aviation plug and the aviation socket jointly form an outlet wire sealing connecting device of the pressure measuring hole of the engine.
Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the invention, and that those skilled in the art may make variations, modifications, substitutions and alterations herein without departing from the spirit and scope of the invention.
Claims (5)
1. The utility model provides a solid rocket engine pressure cell sealing connection device that is qualified for next round of competitions which characterized in that: comprises a special connecting piece and an aviation sealing connector; the aviation sealing connector consists of an aviation socket and an aviation plug;
the special connecting piece is of a T-shaped structure, the size of a first end is matched with that of a solid rocket engine blanking cover pressure measuring hole, and the size of a second end is matched with that of an aviation socket; a through hole is formed in the center of the special connecting piece and is communicated with the first end and the second end;
the first end of the special connecting piece is inserted into a pressure measuring hole of the solid rocket engine blanking cover and is in sealing fit with the pressure measuring hole; the second end of the special connecting piece is matched, sealed and fixedly connected with the end face of the signal output end of the aviation socket;
a temperature sensor signal wire arranged on the surface of the grain of the solid rocket engine extends into the central through hole of the special connecting piece from the pressure measuring hole, penetrates through the central through hole of the special connecting piece and then is in butt joint with the signal output end of the aviation socket; the external signal wire is connected with the aviation plug and is connected into the temperature acquisition system; and signal transmission is realized through the sealing fit of the aviation plug and the aviation socket.
2. The solid rocket engine pressure tap outlet wire sealing connection device according to claim 1, characterized in that: the second end face of the special connecting piece is provided with an annular groove, and a rubber gasket is arranged in the groove and is used for being in sealing fit with the end face of the signal output end of the aviation socket.
3. The solid rocket engine pressure tap outlet wire sealing connection device according to claim 1, characterized in that: and a semicircular concave cavity is formed in the end face of the second end of the special connecting piece and is used for signal expansion of the temperature sensor signal wire in the semicircular concave cavity to form a plurality of branch wires which are respectively connected with the aviation socket signal output end.
4. The solid rocket engine pressure tap outlet wire sealing connection device according to claim 3, characterized in that: and after the temperature sensor signal wire is unfolded into a plurality of branch wires and connected with the aviation socket signal output end, pouring glue into the semicircular cavity to fix the signal wire and seal the central through hole of the special connecting piece.
5. The solid rocket engine pressure tap outlet wire sealing connection device of claim 1, wherein: the first end of the special connecting piece is hermetically connected with the pressure measuring hole of the solid rocket engine blanking cover through a thread gasket mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221691174.3U CN217632713U (en) | 2022-06-30 | 2022-06-30 | Solid rocket engine pressure measurement hole outgoing line sealing connection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221691174.3U CN217632713U (en) | 2022-06-30 | 2022-06-30 | Solid rocket engine pressure measurement hole outgoing line sealing connection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217632713U true CN217632713U (en) | 2022-10-21 |
Family
ID=83630877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221691174.3U Active CN217632713U (en) | 2022-06-30 | 2022-06-30 | Solid rocket engine pressure measurement hole outgoing line sealing connection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217632713U (en) |
-
2022
- 2022-06-30 CN CN202221691174.3U patent/CN217632713U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201112865Y (en) | Unidirectional high-pressure integrated gas sealing electric connector | |
| US20080216580A1 (en) | Sensor apparatus responsive to pressure and temperature within a vessel | |
| CN202018356U (en) | Integrated fluid pressure sensor system | |
| CN103277091A (en) | High-temperature well temperature and pressure dynamic monitoring system | |
| CN217632713U (en) | Solid rocket engine pressure measurement hole outgoing line sealing connection device | |
| CN101354520A (en) | Method for sealing water-proof CCD camera | |
| CN208902327U (en) | Precision differential pressure sensing device | |
| CN203745129U (en) | Isolation type pressure transmitter | |
| CN209131779U (en) | Device with flame-proof type magnetostrictive liquid level sensor | |
| CN206945215U (en) | A kind of Vehicular pressure sensor assembling shell | |
| CN218412422U (en) | Nitrogen oxygen sensor distribution frock | |
| CN207456431U (en) | High-precision integral type hydrostatic level | |
| CN207280507U (en) | Temperature and pressure compound sensor | |
| CN206945209U (en) | A kind of pressure sensor assembling structure | |
| CN213021994U (en) | EGR temperature sensor connection structure | |
| CN112697671B (en) | Rock mass complex structural surface anisotropic seepage testing machine and testing method under deep-ground environment | |
| CN210499880U (en) | Sealing clamp for airspeed tube | |
| CN210141900U (en) | Sealed ultrasonic transducer | |
| CN202735028U (en) | Mechanical type pipeline safety pressure tapping device | |
| CN206330695U (en) | A kind of pressure test device for battery explosion bulge test | |
| CN203616068U (en) | Helium mass spectrometer leak detection testing apparatus for diaphragm capsule assembly of carrier rocket | |
| CN219573281U (en) | Packaging structure of high-sensitivity temperature sensor | |
| CN2313040Y (en) | Internal-external pressure recording instrument for oil pipe at the moment of being cracked by pressing | |
| CN206330681U (en) | A kind of armoured thermocouple signal output apparatus | |
| CN209102188U (en) | A kind of double-layer sealing structure fuel sensor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |