CN214666611U - Pressure-resistant shell of aviation LVDT displacement sensor - Google Patents
Pressure-resistant shell of aviation LVDT displacement sensor Download PDFInfo
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- CN214666611U CN214666611U CN202121313909.4U CN202121313909U CN214666611U CN 214666611 U CN214666611 U CN 214666611U CN 202121313909 U CN202121313909 U CN 202121313909U CN 214666611 U CN214666611 U CN 214666611U
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Abstract
The utility model discloses an aviation LVDT displacement sensor's withstand voltage shell, the pressure-bearing inner tube is established inside the pressure-bearing shell, a sealed weld of end that the pressure-bearing inner tube stretched into the pressure-bearing shell has the pressure-bearing end cap passes through between the other end outer wall of pressure-bearing inner tube and the pressure-bearing shell pressure-bearing end cap seal welds, makes aviation LVDT displacement sensor's coil skeleton establish inside the cavity between pressure-bearing inner tube and the pressure-bearing shell, aviation LVDT displacement sensor's iron core connecting rod is established inside the pressure-bearing inner tube. The pressure-resistant shell of the aviation LVDT displacement sensor improves the reliability and stability of the aviation LVDT displacement sensor, and is convenient to realize the purpose of mass production. Not only can improve the convenience of product processing and assembly equipment, alleviateed the weight of whole casing. But also the safety of the product is increased and the manufacturing cost of the housing is low. Most importantly, the housing also may be easily placed within a limited aerospace vehicle.
Description
Technical Field
The utility model relates to a withstand voltage displacement sensor and accurate electronic components field that the aviation field used, concretely relates to aviation LVDT displacement sensor's withstand voltage shell.
Background
The LVDT linear displacement sensor has the characteristics of long service life, high precision, good mechanical strength, low thermal drift and the like, and is widely applied to the measurement of linear displacement in a servo actuating system of military equipment.
For LVDT linear displacement sensors, structural size and weight, withstand voltage requirements, linear measurement range, reliability and stability are key factors for model selection. Due to the requirement of miniaturization, the LVDT displacement sensor with compact structure, high precision and large stroke is more and more favored. In order to obtain a large withstand voltage within a certain structural size, the design of the structure of the housing is critical.
Most of the LVDT linear displacement sensors in China are externally or internally arranged when used on an actuator, but the problem caused by the internally arranged LVDT linear displacement sensors is that the structure is larger, the weight of the actuator is heavier, and the level of the actuator cannot reach the international leading level at present.
In order to realize that the LVDT linear displacement sensor can be applied in an extremely severe environment and is not influenced by oil stain, solution, dust or other pollution, sensitive components are subjected to non-contact measurement, and higher requirements are put on the structure of an electronic chamber, namely a shell of the sensor.
In the prior art, the LVDT linear displacement sensor has a huge structure, is not easy to bear larger pressure, has high manufacturing cost, and cannot meet the requirement of low-cost batch production.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model mainly aims at providing an overall structure is simple, weight reduction is more, can bear the great pressure of design, has improved reliability, the stability of the LVDT displacement sensor of aviation usefulness, and the cost is reduced has conveniently realized mass production's aviation LVDT displacement sensor's withstand voltage shell.
In order to achieve the above purpose, the technical scheme of the utility model is realized like this:
a pressure resistant housing for an airborne LVDT displacement sensor, comprising: the pressure-bearing inner pipe is connected with the pressure-bearing outer shell; the pressure-bearing inner pipe is arranged inside the pressure-bearing shell, one end of the pressure-bearing inner pipe, which extends into the pressure-bearing shell, is hermetically welded with the pressure-bearing plug, the outer wall of the other end of the pressure-bearing inner pipe and the pressure-bearing shell are hermetically welded through the pressure-bearing end cover, so that a coil framework of the aviation LVDT displacement sensor is arranged inside a cavity between the pressure-bearing inner pipe and the pressure-bearing shell, and an iron core connecting rod of the aviation LVDT displacement sensor is arranged inside the pressure-bearing inner pipe.
In a preferred embodiment, one end surface of the pressure-bearing plug is of a conical surface structure, the other end surface of the pressure-bearing plug is of a convex ring structure, the conical surface structure of the pressure-bearing plug extends into the pressure-bearing inner pipe, the end surface of the convex ring structure of the pressure-bearing plug is flush with the end part of the pressure-bearing inner pipe, and the convex ring structure and the end part of the pressure-bearing inner pipe are welded.
In a preferred embodiment, the outer diameter of the convex ring structure of the pressure-bearing plug is in interference fit with the inner diameter of the pressure-bearing inner pipe.
In a preferred embodiment, the end face of the pressure-bearing end cover is provided with a ring groove, so that the end face of the pressure-bearing end cover forms an outer ring and an inner ring; the end face of the outer ring is flush with the end face of the pressure-bearing shell, the outer ring is welded with the end face of the pressure-bearing shell, the end face of the inner ring is flush with the end face of the pressure-bearing inner pipe, and the inner ring is welded with the end face of the pressure-bearing inner pipe.
In a preferred embodiment, one end of the pressure-bearing shell, which is connected with the pressure-bearing end cover, is provided with a connecting groove, and the pressure-bearing end cover is connected inside the connecting groove in an interference manner.
In a preferred embodiment, the inner ring of the pressure-bearing end cover is in interference connection with the outer wall of the pressure-bearing inner pipe.
In a preferred embodiment, the cavity between the pressure-bearing inner pipe and the pressure-bearing outer shell is filled with glue and sealed and fixed.
In a preferred embodiment, laser welding or argon arc welding is used between the pressure-bearing outer shell and the pressure-bearing end cover, between the pressure-bearing inner pipe and the pressure-bearing end cover, and between the pressure-bearing inner pipe and the pressure-bearing plug.
In a preferred embodiment, the pressure-bearing outer shell, the pressure-bearing inner pipe, the pressure-bearing plug and the pressure-bearing end cover are all formed and processed by a machining numerical control center in one step.
In a preferred embodiment, a flange is integrally formed on the outer wall of the pressure-bearing shell, and a connecting groove is formed in the outer wall of one end, far away from the pressure-bearing end cover, of the flange.
The utility model discloses an aviation LVDT displacement sensor's withstand voltage shell has following beneficial effect:
this aviation LVDT displacement sensor's withstand voltage shell includes: the pressure-bearing inner pipe is connected with the pressure-bearing outer shell; the pressure-bearing inner pipe is arranged inside the pressure-bearing shell, one end of the pressure-bearing inner pipe, which extends into the pressure-bearing shell, is hermetically welded with the pressure-bearing plug, the outer wall of the other end of the pressure-bearing inner pipe and the pressure-bearing shell are hermetically welded through the pressure-bearing end cover, so that a coil framework of the aviation LVDT displacement sensor is arranged inside a cavity between the pressure-bearing inner pipe and the pressure-bearing shell, and an iron core connecting rod of the aviation LVDT displacement sensor is arranged inside the pressure-bearing inner pipe.
The problems that the shell of the current aviation LVDT displacement sensor is complex to manufacture, high in production process requirement, high in cost and the like are solved. And the pressure is not easy to bear, the manufacturing cost is high, and the requirement of low-cost batch production cannot be met.
This withstand voltage shell of aviation LVDT displacement sensor, overall structure is simple, weight reduction is more, can bear the great pressure of design, has improved reliability, the stability of the LVDT displacement sensor of aviation usefulness, and the cost is reduced has conveniently realized the mass production purpose. Not only can improve the convenience of product processing and assembly equipment, alleviateed the weight of whole casing. But also increases the safety of the product, and at the same time the housing is very cheap to manufacture and is well suited for mass production, and above all it can be placed easily in limited aeronautical use as a vehicle.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a cross-sectional view of a pressure resistant housing of an airborne LVDT displacement sensor according to one embodiment of the present disclosure;
fig. 2 is a cross-sectional view of a pressure-bearing housing of a pressure-resistant housing of an airborne LVDT displacement sensor according to an embodiment of the present disclosure;
fig. 3 is a cross-sectional view of a pressure-bearing end cap of a pressure housing of an airborne LVDT displacement sensor according to an embodiment of the present disclosure;
fig. 4 is a cross-sectional view of a pressure-bearing inner tube of a pressure-resistant housing of an airborne LVDT displacement sensor according to an embodiment of the present disclosure;
fig. 5 is a cross-sectional view of a pressure-bearing plug of a pressure-resistant housing of an airborne LVDT displacement sensor according to one embodiment of the present disclosure.
[ description of main reference symbols ]
1. A pressure-bearing inner pipe; c1, a plug end; c2, end cap end;
2. a pressure-bearing housing; a1, connecting groove; a2, flange; a3, connecting groove;
3. a pressure-bearing end cover; b1, outer ring; b2, inner ring; b3, a guide groove;
4. a pressure-bearing plug; d1, convex ring structure; d2, tapered surface structure.
Detailed Description
The pressure-resistant housing of the aviation LVDT displacement sensor according to the present invention will be described in further detail with reference to the accompanying drawings and embodiments of the present invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
As shown in fig. 1 to 5, the pressure-resistant housing of the aviation LVDT displacement sensor includes: a pressure-bearing outer shell 2 and a pressure-bearing inner pipe 1 which mainly bear pressure; a pressure-bearing plug 4 and a pressure-bearing end cover 3 which mainly have sealing function. The pressure-bearing inner pipe 1 is arranged inside the pressure-bearing shell 2, one end, extending into the pressure-bearing shell 2, of the pressure-bearing inner pipe 1 is welded with a pressure-bearing plug 4 in a sealing mode, the outer wall of the other end of the pressure-bearing inner pipe 1 is welded with the pressure-bearing shell 2 in a sealing mode through a pressure-bearing end cover 3, a coil framework of the aviation LVDT displacement sensor is arranged inside a cavity between the pressure-bearing inner pipe 1 and the pressure-bearing shell 2, and an iron core connecting rod of the aviation LVDT displacement sensor is arranged inside the pressure-bearing inner pipe 1.
This withstand voltage shell of aviation LVDT displacement sensor, overall structure is simple, weight reduction is more, can bear the great pressure of design, has improved reliability, the stability of the LVDT displacement sensor of aviation usefulness, and the cost is reduced has conveniently realized the mass production purpose.
According to the voltage withstanding requirement of LVDT displacement sensing, 17-4PH stainless steel is selected for voltage withstanding calculation, and design and processing are generally required to be carried out according to 1.5 times of voltage withstanding.
This withstand voltage shell of aviation LVDT displacement sensor not only can improve the convenience of product processing and assembly equipment, has alleviateed the weight of whole casing. But also increases the safety of the product, and at the same time the housing is very cheap to manufacture and is well suited for mass production, and above all it can be placed easily in limited aeronautical use as a vehicle.
In order to facilitate installation, the welding strength between the pressure-bearing plug 4 and the pressure-bearing inner pipe 1 is improved. One end face of the pressure-bearing plug 4 is of a conical surface structure d2, the other end face of the pressure-bearing plug 4 is of a convex ring structure d1, the conical surface structure d2 of the pressure-bearing plug 4 extends into the pressure-bearing inner tube 1, the end face of the convex ring structure d1 of the pressure-bearing plug 4 is flush with the end portion of the pressure-bearing inner tube 1, and the convex ring structure d1 is welded with the end portion of the pressure-bearing inner tube 1. The welding depth and the welding strength are ensured, and the sealing performance and the bearing performance are improved.
As shown in fig. 1, 4 and 5, the pressure-receiving plug 4 is connected to a plug end c1 of the pressure-receiving inner pipe 1. One end of the conical surface structure d2 of the pressure-bearing plug 4 is inserted into the plug end c1 of the pressure-bearing inner pipe 1, so that the maximum diameter of the pressure-bearing plug 4 is closely matched with the inner diameter of the pressure-bearing inner pipe 1 (preferably in interference fit), the end surface of the convex ring structure d1 of the pressure-bearing plug 4 is flush with the inner pipe at the plug end c1 end of the pressure-bearing inner pipe 1, then laser welding or argon arc welding is carried out, and the welding depth conforms to the requirements of drawings.
Preferably, the outer diameter of the convex ring structure d1 of the pressure-bearing plug 4 is in interference fit with the inner diameter of the pressure-bearing inner pipe 1, so that the connection tightness, the sealing strength and the pressure-bearing capacity are ensured.
Preferably, the end face of the pressure-bearing end cover 3 is provided with a ring groove, so that the end face of the pressure-bearing end cover 3 forms an outer ring b1 and an inner ring b 2; the end face of the outer ring b1 is flush with the end face of the pressure-bearing shell 2, the outer ring b1 is welded with the end face of the pressure-bearing shell 2, the end face of the inner ring b2 is flush with the end face of the pressure-bearing inner pipe 1, and the inner ring b2 is welded with the end face of the pressure-bearing inner pipe 1. Before welding, the leveling is ensured, then laser welding or argon arc welding is carried out, the welding depth conforms to the pressure requirement, and the pressure bearing capacity is ensured.
And a guide groove b3 is formed in one end face, far away from the ring groove, of the center of the opening of the pressure-bearing end cover 3, so that the pressure-bearing inner pipe 1 can be conveniently installed.
Preferably, one end of the pressure-bearing shell 2 connected with the pressure-bearing end cover 3 is provided with a connecting groove a1, and the pressure-bearing end cover 3 is connected inside the connecting groove a1 in an interference manner. The connection between the pressure-bearing end cover 3 and the pressure-bearing shell 2 is convenient.
Preferably, the entire housing is connected to other components, for example to actuators for the aircraft, in order to facilitate the connection of the housing to the other components. A flange a2 is integrally formed on the outer wall of the pressure-bearing shell 2, and a connecting groove a3 is formed on the outer wall of one end of the flange a2, which is far away from the pressure-bearing end cover 3.
Preferably, the inner ring b2 of the pressure-bearing end cover 3 is in interference connection with the outer wall of the pressure-bearing inner pipe 1.
As shown in fig. 1, 4 and 5, the inner hole of the inner ring b2 of the pressure-bearing end cover 3 is tightly matched with the outer diameter of the end cover end c2 of the pressure-bearing inner pipe 1, the two are flush before welding, and then laser welding or argon arc welding is carried out, wherein the welding depth is consistent with the requirement of the drawing.
In order to further improve the sealing performance, the cavity between the pressure-bearing inner pipe 1 and the pressure-bearing outer shell 2 is filled with glue for sealing and fixing, and the pressure-resisting strength and the overall reliability of the LVDT displacement sensor are improved.
In order to ensure the welding strength and improve the sealing performance and the bearing performance, laser welding or argon arc welding is adopted between the bearing shell 2 and the bearing end cover 3, between the bearing inner pipe 1 and the bearing end cover 3, and between the bearing inner pipe 1 and the bearing plug 4.
Similarly, in order to improve the strength and the sealing performance, the pressure-bearing shell 2, the pressure-bearing inner pipe 1, the pressure-bearing plug 4 and the pressure-bearing end cover 3 are all formed and processed by a machining numerical control center in one step.
The problems that the shell of the LVDT displacement sensor for aviation is complex to manufacture, the requirement on the production process is high, the cost is high and the like are solved, the reliability and the stability of the LVDT displacement sensor are improved, the cost is reduced, and the purpose of mass production is achieved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention.
Claims (10)
1. A pressure resistant housing for an airborne LVDT displacement sensor, comprising: the pressure-bearing inner pipe comprises a pressure-bearing outer shell (2), a pressure-bearing inner pipe (1), a pressure-bearing plug (4) and a pressure-bearing end cover (3); the pressure-bearing inner pipe (1) is arranged inside the pressure-bearing shell (2), one end, extending into the pressure-bearing shell (2), of the pressure-bearing inner pipe (1) is hermetically welded with the pressure-bearing plug (4), the outer wall of the other end of the pressure-bearing inner pipe (1) and the pressure-bearing shell (2) are hermetically welded through the pressure-bearing end cover (3), a coil framework of the aviation LVDT displacement sensor is arranged inside a cavity between the pressure-bearing inner pipe (1) and the pressure-bearing shell (2), and an iron core connecting rod of the aviation LVDT displacement sensor is arranged inside the pressure-bearing inner pipe (1).
2. The pressure-resistant housing of an aviation LVDT displacement sensor according to claim 1, characterized in that one end surface of the pressure-bearing plug (4) is a conical surface structure (d2), the other end surface of the pressure-bearing plug (4) is a convex ring structure (d1), the conical surface structure (d2) of the pressure-bearing plug (4) extends into the pressure-bearing inner tube (1), the end surface of the convex ring structure (d1) of the pressure-bearing plug (4) is flush with the end of the pressure-bearing inner tube (1), and the convex ring structure (d1) is welded with the end of the pressure-bearing inner tube (1).
3. The pressure casing of an aviation LVDT displacement sensor according to claim 2, characterized in that the outer diameter of the bulge loop structure (d1) of the pressure-bearing choke plug (4) is in interference fit with the inner diameter of the pressure-bearing inner pipe (1).
4. The pressure-resistant housing of an aviation LVDT displacement sensor according to claim 1, characterized in that the end surface of the pressure-bearing end cover (3) is provided with a ring groove, so that the end surface of the pressure-bearing end cover (3) forms an outer ring (b1) and an inner ring (b 2); the end face of the outer ring (b1) is flush with the end face of the pressure-bearing shell (2), the outer ring (b1) is welded with the end face of the pressure-bearing shell (2), the end face of the inner ring (b2) is flush with the end face of the pressure-bearing inner pipe (1), and the inner ring (b2) is welded with the end face of the pressure-bearing inner pipe (1).
5. The pressure-resistant housing of the aviation LVDT displacement sensor according to claim 4, characterized in that a connecting groove (a1) is arranged at one end of the pressure-resistant housing (2) connected with the pressure-resistant end cover (3), and the pressure-resistant end cover (3) is connected in the connecting groove (a1) in an interference manner.
6. The pressure-resistant casing of an aviation LVDT displacement sensor according to claim 4, characterized in that the inner ring (b2) of the pressure-bearing end cover (3) is in interference connection with the outer wall of the pressure-bearing inner pipe (1).
7. The pressure-resistant housing of an aviation LVDT displacement sensor according to claim 1, characterized in that the cavity between the pressure-bearing inner pipe (1) and the pressure-bearing housing (2) is internally filled with glue and sealed and fixed.
8. The pressure-resistant housing of an aviation LVDT displacement sensor according to any one of claims 1-7, characterized in that laser welding or argon arc welding is used between the pressure-bearing housing (2) and the pressure-bearing end cover (3), between the pressure-bearing inner tube (1) and the pressure-bearing end cover (3), and between the pressure-bearing inner tube (1) and the pressure-bearing choke plug (4).
9. The pressure-resistant housing of the aviation LVDT displacement sensor according to any one of claims 1 to 7, characterized in that the pressure-bearing housing (2), the pressure-bearing inner pipe (1), the pressure-bearing plug (4) and the pressure-bearing end cover (3) are all formed and processed by a machining numerical control center in one step.
10. The pressure casing of an aviation LVDT displacement sensor according to any one of claims 1-7, characterized in that the outer wall of the pressure casing (2) is integrally formed with a flange (a2), and the outer wall of one end of the flange (a2) far away from the pressure end cover (3) is provided with a connecting groove (a 3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121313909.4U CN214666611U (en) | 2021-06-13 | 2021-06-13 | Pressure-resistant shell of aviation LVDT displacement sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121313909.4U CN214666611U (en) | 2021-06-13 | 2021-06-13 | Pressure-resistant shell of aviation LVDT displacement sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214666611U true CN214666611U (en) | 2021-11-09 |
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ID=78487176
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121313909.4U Active CN214666611U (en) | 2021-06-13 | 2021-06-13 | Pressure-resistant shell of aviation LVDT displacement sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214666611U (en) |
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2021
- 2021-06-13 CN CN202121313909.4U patent/CN214666611U/en active Active
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