CN109780355A - A kind of aircraft static pressure system conduit jointing component - Google Patents
A kind of aircraft static pressure system conduit jointing component Download PDFInfo
- Publication number
- CN109780355A CN109780355A CN201711104491.4A CN201711104491A CN109780355A CN 109780355 A CN109780355 A CN 109780355A CN 201711104491 A CN201711104491 A CN 201711104491A CN 109780355 A CN109780355 A CN 109780355A
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- CN
- China
- Prior art keywords
- static pressure
- pressure system
- metal catheter
- aircraft static
- jointing component
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- 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.)
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Abstract
The invention discloses a kind of aircraft static pressure system conduit jointing components.The aircraft static pressure system conduit jointing component includes: metal catheter (1), and one end of the metal catheter (1) is provided with chamfering, and the other end is provided with flaring；One end of flat ozzle (2), the flat ozzle (2) is connect with one end for being provided with flaring of the metal catheter (1)；Cap nut (3), described cap nut (3) one end are connect with the other end of the flat ozzle (2), and the other end is internally provided with internal screw thread.The aircraft static pressure system of the application passes through the cooperation of metal catheter, flat ozzle and cap nut with conduit jointing component, to facilitate the connection of metal catheter Yu two kinds of conduits of fabric hose, and manufacturing cost is low, easily manufactured.
Description
Technical field
The present invention relates to engines to rectify supporting plate technical field, is connected more particularly to a kind of aircraft static pressure system with conduit
Joint assembly.
Background technique
It include the conduit of two kinds of materials of metal catheter and fabric hose in aero pilot-static pressure system.Two kinds of catheter interfaces are different
It causes, needs adapter coupling to transfer when being docked.Bar or plate is mostly used to be turned on machine by machining at present
Connector, but this adapter processing technology is complicated, the process-cycle is long, manufacturing cost is high, affects entire manufacturing cost and life
Produce the period.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
Overcome the purpose of the present invention is to provide a kind of aircraft static pressure system with conduit jointing component or is at least subtracted
At least one drawbacks described above of the light prior art.
To achieve the above object, the present invention provides a kind of aircraft static pressure system conduit jointing component, the aircraft
Static-pressure system conduit jointing component includes: metal catheter, and one end of the metal catheter is provided with chamfering, and the other end is set
It is equipped with flaring；Flat ozzle, one end of the flat ozzle are connect with one end for being provided with flaring of the metal catheter；The flat pipe
Mouth；Cap nut, described cap nut one end are connect with the other end of the flat ozzle, and the other end is internally provided with internal screw thread.
It preferably, is six square toes outside the cap nut.
Preferably, the length of the metal catheter is not less than 50 millimeters.
Preferably, the metal catheter includes the inner layer wall and outer wall being mutually arranged, and the inner layer wall can be opposite
The outer wall stretching motion.
Preferably, micro-camera device is provided between the inner layer wall and the outer wall.
Present invention also provides a kind of engine pack, the engine pack includes anti-icing rectification branch as described above
Plate.
The aircraft static pressure system of the application passes through metal catheter, flat ozzle and cap nut with conduit jointing component
Cooperation, to facilitate the connection of metal catheter Yu two kinds of conduits of fabric hose, and manufacturing cost is low, easily manufactured.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the aircraft static pressure system conduit jointing component of the application first embodiment.
Appended drawing reference:
| 1 | Metal catheter | 3 | Cap nut |
| 2 | Flat ozzle |
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
Fig. 1 is the structural schematic diagram of the aircraft static pressure system conduit jointing component of the application first embodiment.
Aircraft static pressure system conduit jointing component as shown in Figure 1 includes metal catheter 1, flat ozzle 2 and outer
Nut 3 is covered, one end of metal catheter 1 is provided with chamfering, and the other end is provided with flaring；One end of flat ozzle 2 and metal catheter 1
It is provided with one end connection of flaring；3 one end of cap nut is connect with the other end of flat ozzle 2, and the other end is internally provided with interior spiral shell
Line.
The aircraft static pressure system of the application passes through metal catheter, flat ozzle and cap nut with conduit jointing component
Cooperation, to facilitate the connection of metal catheter Yu two kinds of conduits of fabric hose, and manufacturing cost is low, easily manufactured.
It is six square toes outside cap nut 3 in the present embodiment referring to Fig. 1.
Referring to Fig. 1, in the present embodiment, the length of metal catheter 1 is not less than 50 millimeters.
In some alternative embodiments, metal catheter includes the inner layer wall and outer wall being mutually arranged, and inner layer wall can
Opposed outer layer wall stretching motion.In this way, it can according to need the length for further increasing metal catheter.
In some alternative embodiments, micro-camera device is provided between inner layer wall and outer wall.Increase miniature video camera
Device can monitor installation situation in real time in the conduit jointing component of the aircraft static pressure system using the application, according to peace
Dress situation is adjusted.To facilitate alignment to install.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (5)
1. a kind of aircraft static pressure system conduit jointing component, which is characterized in that the aircraft static pressure system is connected with conduit
Connecing joint assembly includes:
One end of metal catheter (1), the metal catheter (1) is provided with chamfering, and the other end is provided with flaring；
One end of flat ozzle (2), the flat ozzle (2) is connect with one end for being provided with flaring of the metal catheter (1)；
Cap nut (3), described cap nut (3) one end are connect with the other end of the flat ozzle (2), setting inside the other end
There is internal screw thread.
2. aircraft static pressure system as described in claim 1 conduit jointing component, which is characterized in that the cap nut
(3) external is six square toes.
3. aircraft static pressure system as claimed in claim 2 conduit jointing component, which is characterized in that the metal catheter
(1) length is not less than 50 millimeters.
4. aircraft static pressure system as described in claim 1 conduit jointing component, which is characterized in that the metal catheter
Including the inner layer wall and outer wall being mutually arranged, the inner layer wall being capable of the relatively described outer wall stretching motion.
5. aircraft static pressure system as claimed in claim 4 conduit jointing component, which is characterized in that the inner layer wall with
Micro-camera device is provided between the outer wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711104491.4A CN109780355A (en) | 2017-11-10 | 2017-11-10 | A kind of aircraft static pressure system conduit jointing component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711104491.4A CN109780355A (en) | 2017-11-10 | 2017-11-10 | A kind of aircraft static pressure system conduit jointing component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109780355A true CN109780355A (en) | 2019-05-21 |
Family
ID=66484842
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711104491.4A Pending CN109780355A (en) | 2017-11-10 | 2017-11-10 | A kind of aircraft static pressure system conduit jointing component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109780355A (en) |
-
2017
- 2017-11-10 CN CN201711104491.4A patent/CN109780355A/en active Pending
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190521 |
|
| WD01 | Invention patent application deemed withdrawn after publication |