CN218971993U - Mounting and fixing structure for hard pipeline - Google Patents
Mounting and fixing structure for hard pipeline Download PDFInfo
- Publication number
- CN218971993U CN218971993U CN202222821359.8U CN202222821359U CN218971993U CN 218971993 U CN218971993 U CN 218971993U CN 202222821359 U CN202222821359 U CN 202222821359U CN 218971993 U CN218971993 U CN 218971993U
- Authority
- CN
- China
- Prior art keywords
- pipeline
- connecting piece
- machine body
- plate
- connecting plate
- 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
- 238000009434 installation Methods 0.000 claims abstract description 50
- 230000007704 transition Effects 0.000 claims description 20
- 238000001125 extrusion Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 230000013011 mating Effects 0.000 description 9
- 230000007613 environmental effect Effects 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Landscapes
- Supports For Pipes And Cables (AREA)
Abstract
The utility model relates to a mounting and fixing structure for a hard pipeline, relates to the technical field of aircraft ring control system pipelines, and solves the technical problems of complex structure, large occupied space and troublesome mounting of ring control system pipelines of an aircraft in the prior art. The installation fixing structure for the hard pipeline comprises a pipeline connecting part, a machine body structure installing part and a locking connecting piece, wherein the pipeline connecting part is fixedly connected with the hard pipeline, the machine body structure installing part is installed on the machine body structure, and the pipeline connecting part is connected with the machine body structure installing part through the locking connecting piece.
Description
Technical Field
The utility model relates to the technical field of pipelines of aircraft environmental control systems, in particular to a mounting and fixing structure for a hard pipeline.
Background
An aircraft environmental control system, namely an aircraft environmental control system, is one of important onboard systems and is responsible for providing a comfortable air environment for personnel onboard the aircraft. The environmental control system provides a sufficiently comfortable living and working environment for the crew and passengers by controlling the temperature, humidity, flow rate, pressure and other parameters of the air in the cabin.
The aircraft environmental control system provides high-temperature high-pressure bleed air of the engine for a plurality of air source user subsystems such as a downstream refrigeration temperature control system, a ventilation system, a wing anti-icing system, an air preparation system and the like through pipelines.
The loop control system pipeline of the aircraft is used for adjusting the temperature and air quality of the internal environment of the aircraft, and because the length of the loop control system pipeline of the aircraft is longer, the installation form structure is complex, and one of the main stream installation forms is to hoop the pipeline body by virtue of the clamp for installation. The clamp, the mounting bolt and the mounting lug fixed on the machine body are required to be mounted, the mounted clamp accounts for 10% -15% of the weight of the whole system according to the weight statistics of a general system, and the mounted bolt accounts for 30% -45% of the weight of the whole system. The overall weight of the system is greatly increased. The other is to rely on the support on the pipeline and the support on the structure, and the bolts are connected by the bolts, so that the weight of the bolts is heavy. And in addition, the bolts are required to be operated in two mounting modes, so that the mounting and replacement efficiency of the pipeline system is greatly reduced.
Disclosure of Invention
Therefore, the utility model aims to provide a mounting and fixing structure for a hard pipeline, so as to solve the technical problems of complex structure, large occupied space and troublesome mounting of a pipeline of a ring control system of an airplane in the prior art.
In order to achieve the above purpose, the present utility model provides the following technical solutions:
the utility model provides a mounting and fixing structure for a hard pipeline, which comprises a pipeline connecting part, a machine body structure mounting part and a locking connecting piece, wherein:
the pipeline connecting part is fixedly connected with the hard pipeline, the machine body structure installing part is installed on the machine body structure, and the pipeline connecting part is connected with the machine body structure installing part through the locking connecting piece.
As an alternative embodiment of the present utility model, the pipe connection part includes a pipe connection part and a support part, the pipe connection part is connected with the hard pipe, the support part is fixedly connected with the pipe connection part, and the support part is connected with the fuselage structure installation part through the locking connection part.
As an alternative embodiment of the utility model, the pipeline connecting piece is provided with an arc-shaped matching surface which is matched with the shape of the hard pipeline, and the arc-shaped matching surface and the hard pipeline are fixedly connected in a bonding mode.
As an alternative embodiment of the utility model, the support member is in an inverted U shape and comprises a first connecting plate, a second connecting plate and a third connecting plate, wherein the first connecting plate and the second connecting plate are respectively connected to two ends of the pipeline connecting member, the third connecting plate is used for connecting the first connecting plate and the second connecting plate, and the third connecting plate is connected with the installation part of the machine body structure through the locking connecting member.
As an alternative embodiment of the present utility model, an included angle between the first connection plate and the third connection plate is an obtuse angle, an included angle between the second connection plate and the third connection plate is an obtuse angle, and an included angle between the first connection plate and the third connection plate is equal to an included angle between the second connection plate and the third connection plate.
As an alternative embodiment of the present utility model, the connection between the first connection plate and the third connection plate and the connection between the second connection plate and the third connection plate are smooth transitions.
As an alternative embodiment of the utility model, the installation part of the airframe structure is L-shaped and comprises an airframe installation part and a transition connecting part, wherein the airframe installation part is connected with the airframe structure, the airframe installation part is fixedly connected with the transition connecting part, and the transition connecting part is connected with the third connecting plate through the locking connecting part.
As an alternative implementation mode of the utility model, at least two notch holes are formed in the third connecting plate, assembly holes corresponding to the number and the positions of the notch holes are formed in the transition connecting piece, the locking connecting piece can be installed in the notch holes through notches in the notch holes under the action of external force, and the locking connecting piece can be clamped into the assembly holes by pushing the hard pipeline towards the direction close to the transition connecting piece by the external force so as to connect the third connecting plate and the transition connecting piece.
As an alternative embodiment of the present utility model, the locking connection member is formed with a guide section and a mating section, the guide section is connected with the mating section, the guide section is an inclined surface, the locking connection member enters the assembly hole through the guide section, and the mating section can deform under the extrusion action of the hole wall of the assembly hole to enter the assembly hole, so that the locking connection member is connected with the body structure installation part.
As an alternative embodiment of the utility model, the pipeline connecting part and the machine body structure mounting part are both made of metal materials, and the locking connecting piece is made of plastic materials.
The utility model provides an installation and fixation structure for a hard pipeline, which comprises a pipeline connecting part, a machine body structure installation part and a locking connecting piece, wherein the pipeline connecting part is fixedly connected with the hard pipeline, the machine body structure installation part is installed on a machine body structure, and the pipeline connecting part and the machine body structure installation part can be connected through the locking connecting piece. The locking connecting piece can be installed on the pipeline connecting portion through the notch on the notch hole arranged on the pipeline connecting portion under the action of external force, and the locking connecting piece can be clamped into the assembly hole on the installation portion of the machine body structure when the external force pushes the hard pipeline towards the direction close to the installation portion of the machine body structure, so that the pipeline connecting portion is connected with the installation portion of the machine body structure, the hard pipeline is installed on the machine body, the installation fixing structure is simple, the overall dimension specification is small, the weight is light, the use of equipment installation space on the airplane can be effectively reduced, redundant fasteners and installation pieces are not needed, the installation is rapid and convenient, and the reliability is high.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a mounting fixture for a hard pipeline according to an embodiment of the present utility model;
FIG. 2 is a schematic diagram illustrating connection between a fuselage structure and a rigid pipeline according to an embodiment of the present utility model;
FIG. 3 is a schematic view of a pipeline connection part according to an embodiment of the present utility model;
FIG. 4 is a schematic view of a fuselage structure mounting section according to an embodiment of the present utility model;
fig. 5 is a schematic structural view of a locking connector according to an embodiment of the present utility model.
In the figure: 1. a pipeline connecting part; 11. a pipe connection; 12. a support; 121. a first connection plate; 122. a second connecting plate; 123. a third connecting plate; 2. a fuselage structure mounting section; 21. a fuselage mount; 22. a transition piece; 3. a locking connection; 31. a guide section; 32. a mating section; 4. a hard pipeline; 5. a fuselage structure; 6. a notch hole; 7. and (5) assembling holes.
Detailed Description
In order to make the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the utility model. All other embodiments, based on the examples herein, which are within the scope of the utility model as defined by the claims, will be within the scope of the utility model as defined by the claims.
Referring to fig. 1 to 5, the utility model provides a mounting and fixing structure for a hard pipeline 4, which comprises a pipeline connecting part 1, a machine body structure mounting part 2 and a locking connecting piece 3, wherein the pipeline connecting part 1 is fixedly connected with the hard pipeline 4, the machine body structure mounting part 2 is mounted on a machine body structure 5, and the pipeline connecting part 1 and the machine body structure mounting part 2 are connected through the locking connecting piece 3.
As an alternative embodiment of the present utility model, the pipeline connecting part 1 includes a pipeline connecting piece 11 and a supporting piece 12, the pipeline connecting piece 11 is connected with the hard pipeline 4, the supporting piece 12 is fixedly connected with the pipeline connecting piece 11, and the supporting piece 12 is connected with the fuselage structure mounting part 2 through a locking connecting piece 3.
As shown in fig. 3, the pipe connecting piece 11 in this embodiment is formed with an arc-shaped mating surface adapted to the shape of the hard pipe 4, and the arc-shaped mating surface and the hard pipe 4 are fixedly connected by bonding. The support 12 is inverted "U" and includes a first connecting plate 121, a second connecting plate 122 and a third connecting plate 123, where the first connecting plate 121 and the second connecting plate 122 are connected to two ends of the pipeline connecting member 11, respectively, and the third connecting plate 123 is used to connect the first connecting plate 121 and the second connecting plate 122, and the third connecting plate 123 is connected to the fuselage structure installation portion 2 through the locking connecting member 3.
As an alternative embodiment of the present utility model, the included angle between the first connecting plate 121 and the third connecting plate 123 is an obtuse angle, the included angle between the second connecting plate 122 and the third connecting plate 123 is an obtuse angle, and the included angle between the first connecting plate 121 and the third connecting plate 123 is equal to the included angle between the second connecting plate 122 and the third connecting plate 123, so that the stability of the pipeline connecting portion 1 is better.
As an alternative embodiment of the present utility model, the connection between the first connection plate 121 and the third connection plate 123 and the connection between the second connection plate 122 and the third connection plate 123 are smooth transitions, which is beneficial to improving the overall service life. Preferably, the first connecting plate 121, the second connecting plate 122, the third connecting plate 123 and the pipeline connecting piece 11 in this embodiment are integrally formed, and the manufacturing is simple.
In addition, referring to fig. 4, in this embodiment, the fuselage structure installation part 2 is "L" and includes a fuselage installation element 21 and a transition connection element 22, the fuselage installation element 21 is connected with the fuselage structure 5, the fuselage installation element 21 is fixedly connected with the transition connection element 22, preferably, the fuselage installation element 21 and the transition connection element 22 are integrally formed, the processing is simple, and the transition connection element 22 and the third connection plate 123 are connected through the locking connection element 3.
As an alternative embodiment of the present utility model, at least two notch holes 6 are formed on the third connecting plate 123, and assembly holes 7 corresponding to the number and positions of the notch holes 6 are formed on the transitional connecting piece 22, the locking connecting piece 3 can be installed in the notch holes 6 through the notches on the notch holes 6 under the action of external force, and the external force pushes the hard pipeline 4 towards the direction approaching to the transitional connecting piece 22, so that the locking connecting piece 3 can be clamped into the assembly holes 7 to connect the third connecting plate 123 and the transitional connecting piece 22.
As shown in fig. 5, the locking connector 3 is formed with a guide section 31 and a mating section 32, the guide section 31 is connected with the mating section 32, the guide section 31 is an inclined surface, the locking connector 3 enters the assembly hole 7 through the guide section 31, and the mating section 32 can deform under the extrusion action of the wall of the assembly hole 7 to enter the assembly hole 7, so that the locking connector 3 is connected with the fuselage structure installation part 2. Thereby link up pipeline connecting portion 1 and fuselage structure installation department 2, and then can install stereoplasm pipeline 4 on the fuselage, this installation fixed knot constructs simply, does not need unnecessary fastener and installed part, and the installation is swift convenient, and the reliability is high.
As an alternative embodiment of the utility model, the pipeline connecting part 1 and the machine body structure mounting part 2 are both made of metal materials, and the locking connecting piece 3 is made of plastic materials.
A pipeline connecting part 1 is arranged on a single-piece hard pipeline 4 of a pipeline of an environmental control system, a fuselage structure installation part 2 is arranged on a fuselage, and a notch hole 6 and an assembly hole 7 are reserved on the pipeline connecting part 1 and the fuselage structure installation part 2 respectively. During installation, the locking connector 3 is installed in the notch hole 6 on the pipeline connecting part 1, the locking connector 3 is aligned with the assembly hole 7 on the fuselage structure installation part 2, and the hard pipeline 4 is pushed to load the locking connector 3 into the assembly hole 7 on the fuselage structure installation part 2.
The installation and fixation structure for the hard pipeline 4 is simple, no redundant fasteners and installation parts are needed, the reliability is high, the overall dimension specification is small, the weight is light, and the weight is reduced by 60 percent compared with the weight of a metal clamp and a bolt which are conventionally used. And the installation space that this installation fixed knot constructs uses is little, can effectually reduce the use of fuselage equipment installation space, simple to operate is swift.
The foregoing is merely illustrative embodiments of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art can easily think about variations or substitutions within the technical scope of the present utility model, and the utility model should be covered. Therefore, the protection scope of the utility model is subject to the protection scope of the claims.
Claims (5)
1. A installation fixed knot constructs for stereoplasm pipeline, its characterized in that includes pipeline connecting portion, fuselage structure installation department and locking connecting piece, wherein:
the pipeline connecting part is fixedly connected with the hard pipeline, the machine body structure mounting part is arranged on the machine body structure, and the pipeline connecting part and the machine body structure mounting part are connected through the locking connecting piece;
the pipeline connecting part comprises a pipeline connecting piece and a supporting piece, the pipeline connecting piece is connected with the hard pipeline, the supporting piece is fixedly connected with the pipeline connecting piece, and the supporting piece is connected with the machine body structure mounting part through the locking connecting piece; the support piece is of an inverted U shape and comprises a first connecting plate, a second connecting plate and a third connecting plate, the first connecting plate and the second connecting plate are respectively connected to two ends of the pipeline connecting piece, the third connecting plate is used for connecting the first connecting plate and the second connecting plate, and the third connecting plate is connected with the installation part of the machine body structure through the locking connecting piece; the machine body structure installation part is L-shaped and comprises a machine body installation part and a transition connecting piece, wherein the machine body installation part is connected with the machine body structure, the machine body installation part is fixedly connected with the transition connecting piece, and the transition connecting piece is connected with the third connecting plate through the locking connecting piece; the third connecting plate is provided with at least two notch holes, the transition connecting piece is provided with assembly holes corresponding to the notch holes in number and positions, the locking connecting piece can be installed in the notch holes through the notches in the notch holes under the action of external force, and the external force pushes the hard pipeline towards the direction close to the transition connecting piece so that the locking connecting piece can be clamped into the assembly holes to connect the third connecting plate and the transition connecting piece; the locking connecting piece is characterized in that a guide section and a matching section are formed on the locking connecting piece, the guide section is connected with the matching section, the guide section is an inclined surface, the locking connecting piece enters the assembly hole through the guide section, and the matching section can deform under the extrusion action of the hole wall of the assembly hole to enter the assembly hole, so that the locking connecting piece is connected with the installation part of the machine body structure.
2. The mounting and fixing structure for a hard pipeline according to claim 1, wherein the pipeline connecting piece is provided with an arc-shaped matching surface which is matched with the shape of the hard pipeline, and the arc-shaped matching surface and the hard pipeline form a fixed connection in a bonding mode.
3. The mounting and fixing structure for a hard pipeline according to claim 1, wherein an included angle between the first connection plate and the third connection plate is an obtuse angle, an included angle between the second connection plate and the third connection plate is an obtuse angle, and an included angle between the first connection plate and the third connection plate is equal to an included angle between the second connection plate and the third connection plate.
4. The mounting and fixing structure for a hard pipeline according to claim 1, wherein the connection of the first connecting plate and the third connecting plate and the connection of the second connecting plate and the third connecting plate are both smooth transitions.
5. The mounting and fixing structure for a hard pipeline according to claim 1, wherein the pipeline connecting portion and the fuselage structure mounting portion are both made of metal materials, and the locking connecting piece is made of plastic materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222821359.8U CN218971993U (en) | 2022-10-25 | 2022-10-25 | Mounting and fixing structure for hard pipeline |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222821359.8U CN218971993U (en) | 2022-10-25 | 2022-10-25 | Mounting and fixing structure for hard pipeline |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218971993U true CN218971993U (en) | 2023-05-05 |
Family
ID=86161620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222821359.8U Active CN218971993U (en) | 2022-10-25 | 2022-10-25 | Mounting and fixing structure for hard pipeline |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218971993U (en) |
-
2022
- 2022-10-25 CN CN202222821359.8U patent/CN218971993U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101506035B (en) | Frame element, aircraft air-conditioning system and method for the installation of a frame element in an aircraft | |
| US6607165B1 (en) | Aircraft engine mount with single thrust link | |
| US10145256B2 (en) | Aircraft propulsion system seal assembly with spring seal element and compliant seal element | |
| EP3052381B1 (en) | Stowage bin systems | |
| US7526921B2 (en) | Auxiliary power unit with integral firebox | |
| US8366038B2 (en) | Device for fastening a turbojet engine to an aircraft fixing strut | |
| CN218971993U (en) | Mounting and fixing structure for hard pipeline | |
| US20090078907A1 (en) | Composite valve assembly for aircraft environmental control systems | |
| US7093618B2 (en) | Lounge valve mounting housing and assembly | |
| CN109808870A (en) | A quick disassembly structure for vertical tail connection of unmanned aerial vehicle | |
| US11674540B2 (en) | Track beam with composite lug | |
| CN104254481B (en) | There is the turbojet engine nacelle of tract | |
| CN213862694U (en) | Elastic ventilation cooling device for airplane | |
| CN203248870U (en) | Metal ring seal clamp flange connection structure with shoulder | |
| CN109502047B (en) | Compensation method for single-side connection unqualified bolt hole of airplane structure | |
| US10046851B2 (en) | Landing gear noise abatement devices | |
| CN216429684U (en) | Blade and installation component of intermediary cartridge receiver and contain its aeroengine | |
| CN222254144U (en) | Turbine cooling air entraining device | |
| EP3470694A1 (en) | Strut assembly and method of forming | |
| CN215523515U (en) | Mount that outer machine of heating and ventilating equipment was used | |
| CN218972084U (en) | Pipeline connection spherical compensation structure and environmental control system pipeline | |
| CN210897599U (en) | Basin-shaped antenna mounting base | |
| CN219159785U (en) | Air duct connecting device | |
| CN219545077U (en) | Easy dismounting's of aircraft wing point stroboscopic lamp shade after losing device that passes | |
| CN222727803U (en) | Assembly structure of radiator and intercooler and vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |