CN208487309U - The lap device of airplane Hydraulic Tube and fuel tank - Google Patents
The lap device of airplane Hydraulic Tube and fuel tank Download PDFInfo
- Publication number
- CN208487309U CN208487309U CN201820688720.5U CN201820688720U CN208487309U CN 208487309 U CN208487309 U CN 208487309U CN 201820688720 U CN201820688720 U CN 201820688720U CN 208487309 U CN208487309 U CN 208487309U
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- fuel tank
- connector
- hydraulic tube
- lap device
- airplane hydraulic
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Abstract
The utility model describes the lap device of a kind of airplane Hydraulic Tube and fuel tank, comprising: fluid pressure line passes through fuel tank；Connector is used to be tightly bonded together with the exterior panel of fuel tank, seal groove is provided on connector, and have contact surface, center tap is crimped together with fluid pressure line；Sealing element is mounted in the seal groove of connector, for ensuring that fuel sealing, sealing element are nonconducting；Connector is used to for connector being fixed on the exterior panel of fuel tank.The utility model, which can effectively solve the problem that, there is joint looseness when crossing frame overlap joint into the hydraulic system pipeline in fuel tank and the problem of overlap joint falls off, it is significant to reinforce hydraulic pipe bridging arrangement, enter less electric current in fuel tank with the overlap joint of fuel oil box body simultaneously, so that greatly reduce aircraft fuel tank lights probability.
Description
Technical field
The utility model relates to plane hydraulic system fields, relate in particular to plane hydraulic system circuit design, especially
The utility model relates to the lap devices of a kind of airplane Hydraulic Tube and fuel tank.
Background technique
It is well known that plane hydraulic system is to complete using oil liquid as working media on aircraft by oil pressure actuated executing agency
The package unit of particular manipulation movement.To guarantee the hydraulic dynamic of hydraulic system reliable operation, especially raising flight control system
The reliability in power source is referred to as public liquid equipped with two sets (or more covering) mutually independent hydraulic systems mostly on modern aircraft
Pressure system and power-assisted (manipulation) hydraulic system.Public hydraulic system is used for the folding and unfolding of undercarriage, wing flap and flap, Nose Wheel Steering
Manipulation drives windscreen wiper and the hydraulic motor of fuel pump etc.；It is (or complete dynamic flat that it is also used to drive part aileron, elevator simultaneously
Tail) and rudder booster.Assisted hydraulic system is then only used for driving the booster of above-mentioned flight control system and damping rudder
Machine etc., assisted hydraulic system itself also may include two sets of independent hydraulic systems.
The element of hydraulic system includes:
Energy part: hydraulic oil pump
Control section: control valve (such as safety valve, check valve, feather valve, Ground Service Plug)
Execution part: pressurized strut and hydraulic motor and auxiliary device (such as pump oil filter, pressure gauge, fuel tank, accumulator,
Fluid pressure line) etc..
However, the arrangement of some of fluid pressure lines can due to airplane Hydraulic Tube is restricted etc. arrangement space
It can need across fuel tank.But aircraft may suffer from the exceedingly odious weather such as lightning in flight course, thus can produce
Raw electric current.However, fluid pressure line, throughout whole airplane, in this case, fluid pressure line just has to before entering fuel tank
The electric current being attached on fluid pressure line is successfully conducted to fuel oil tank shell, otherwise electric current enters fuel tank with fluid pressure line
Interior, conducting lightning currents or electric spark will touch fuel oil and thus light fuel tank, so as to cause devastating disaster accident.In view of
This, fluid pressure line passes through fuel tank and has to consider the problem that overlap joint is conductive.And involved in the utility model it is exactly aircraft liquid
The lap device on pressure pipe road and fuel tank.
At present it is known that the airplane Hydraulic Tube across fuel tank mostly used bulkhead connector greatly to guarantee the close of fuel tank
Effective overlap joint of envelope and hydraulic pipe and fuel tank surface.Fig. 1 just shows this bulkhead connector excessively being widely adopted at present,
This is crossed bulkhead connector and is designed in the structure for being suitable for sealing compartment.As shown in Figure 1, it includes hydraulic that this, which crosses bulkhead connector mainly,
Pipeline 1 and connector 2.However, in this design, connector 2 and structure contact surface area are small, thus conductive effect is bad, Er Qieyi
Fatigue damage.Further, since fluid pressure line 1 is located at the inside of fuel tank, thus fuel oil can also be to hydraulic pipe and fuel oil tank wall
Plate causes immersion, air oxidation, vibration etc. to adversely affect, and the overlap joint measure so as to cause fluid pressure line and fuel tank surface may
Can degenerate, burn into falls off, thereby result in overlap joint it is bad, finally influence flight safety.Although aviation field is by these measures
It is included in seaworthiness limitation to require, pressure is inspected periodically to ensure that overlap joint measure is effective, but this needs to expend great manpower maintenance
The time of maintenance overhaul in cost and aviation operation, to bring huge economic cost and pressure.
In addition, there is also other a variety of overlap joint measures in the prior art:
US20160244182A1 (date of publication be 2016 on August 25) discloses a kind of aircaft configuration, in conductive material
Between structural member, conducting function is realized by conductive material.
CN103696108 (date of publication is on April 6th, 2016) discloses a kind of for preventing activation from passing from hydraulic connecting
The device of surrounding medium is cast to, which includes pipe fitting, mechanical barrier etc..
US20150091293A1 (date of publication is on April 2nd, 2015) discloses a kind of hydraulic joint device comprising
Hydraulic joint, pipeline, end sealing etc..
US20150096631A1 (date of publication is on April 9th, 2015) discloses a kind of fluid separation member comprising two
Section pipeline section.
EP769115B1 (date of publication is on May 12nd, 1999) discloses a kind of Hydraulic coupling.Such as Figure 12-of the document
Shown in 13, which forms contact seals and is crimped onto taper port with the pipe fluidly connected.The sealing element includes metal-
Metal seal and cross-elasticity sealing, the taper port then include compression ring and crimped loops, the two rings execute metal pair
The contact of metal.
It is taken however, above-mentioned existing technical literature all can not effectively solve the hydraulic system pipeline entered in fuel tank in frame excessively
Occurs joint looseness when connecing and the problem of overlap joint falls off.
Therefore, how to design one kind reinforces hydraulic pipe bridging arrangement, while making less with the overlap joint of fuel oil box body
Electric current enter in fuel tank, to greatly reduce the airplane Hydraulic Tube of lighting probability and fuel tank of aircraft fuel tank
Lap device becomes for technical problem urgently to be resolved.
Utility model content
The utility model is made to solve above-mentioned technical problem, and its purpose is to provide a kind of airplane Hydraulic Tube and fuel oils
The lap device of the lap device of case, the airplane Hydraulic Tube and fuel tank can effectively solve the problem that into the hydraulic pressure system in fuel tank
There is joint looseness when crossing frame overlap joint and the problem of overlap joint falls off in road under the overall leadership, significant to reinforce hydraulic pipe bridging arrangement, simultaneously
Enter less electric current in fuel tank with the overlap joint of fuel oil box body, so that it is general to greatly reduce lighting for aircraft fuel tank
Rate.
In order to solve the above-mentioned technical problem, the utility model provides the overlap joint dress of a kind of airplane Hydraulic Tube and fuel tank
It sets, it is characterized in that, comprising: fluid pressure line, the fluid pressure line pass through fuel tank；Connector, the connector are used for and the combustion
The exterior panel of fuel tank is tightly bonded together, and seal groove is provided on the connector, and have contact surface, wherein institute
Connector is stated to be crimped together with the fluid pressure line；Sealing element, the sealing element are mounted in the seal groove of the connector,
For ensuring that fuel sealing, the sealing element are nonconducting；Connector, the connector are used to the connector being fixed on institute
It states on the exterior panel of fuel tank.
Preferably, connector is multijaw flange in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank
The form of connector, the especially form of three-jaw bump joint.
Preferably, in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank, the connector it is described
Contact surface is subjected to surface coated treatment, can ensure when for ensuring that the contact surface and the surface of the fuel tank contact
Overlap the excellent conduction of electric current.
Preferably, in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank, at the surface covering
Reason includes: polishing priming paint, oxidation processes, assembly and encapsulation process.Wherein, the oxidation processes are preferably A Luoding anode
Oxidation processes.
Preferably, sealing element is using sealing in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank
The form of circle, and be made of insulating material, preferably it is made of rubber.
Preferably, connector uses screw in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank
Or the form of bolt.
Preferably, in the airplane Hydraulic Tube of the utility model and the lap device of fuel tank, the number of the connector
Amount is corresponding with the pawl number of the connector, in particular, the quantity of connector is three when connector is three-jaw bump joint.
By constituting as described above, the lap device of airplane Hydraulic Tube according to the present utility model and fuel tank works as combustion
When having electric current to pass through on the fluid pressure line of fuel tank, which is conducted to rapidly the surface of fuel tank by the contact surface of connector, then
It is connected and is grounded by fuel tank.According in illustrated embodiment, there are three connectors due to setting, thus by these three connector institute shapes
At fixation not only stability is good, guarantee redundancy design, and its probability loosened was greatly lowered for comparing frame connector.And
And according to illustrated embodiment, due to the reason of the larger contact surface of three-jaw bump joint, it is thus possible to ensure to overlap electric current and lead
The general character is excellent, at the same sealing element design and big contact surface also significantly increase the leakproofness of fuel tank and pipeline.
As a result, compared to existing device for, the utility model reduces manpower maintenance cost significantly, shortens aviation
The time of maintenance overhaul in operation, to bring huge economic benefit.
Detailed description of the invention
Fig. 1 is a kind of perspective view for crossing bulkhead connector being widely adopted in the prior art.
Fig. 2 be according to the perspective view of the lap device of the airplane Hydraulic Tube and fuel tank of an embodiment of the present invention,
Wherein fluid pressure line, connector, sealing element and connector have been assembled together.
Fig. 3 be according to the top view of the lap device of the airplane Hydraulic Tube and fuel tank of an embodiment of the present invention,
Wherein fluid pressure line, connector, sealing element and connector have been assembled together.
Fig. 4 is the contact table of the airplane Hydraulic Tube of an embodiment of the present invention with the connector of the lap device of fuel tank
The flow diagram of the surface coating layer treatment method in face.
Specific embodiment
The preferred embodiment of the utility model is described in detail below with reference to attached drawing, to be clearer to understand this reality
With novel objects, features and advantages.It should be understood that embodiment shown in the drawings is not the limit to the scope of the utility model
System, and simply to illustrate that the connotation of technical solutions of the utility model.In attached drawing, identical element is with the same or similar
Appended drawing reference indicates.
Hereinafter, carrying out the lap device of the airplane Hydraulic Tube and fuel tank to an embodiment of the present invention referring to attached drawing
100 composition and assembly are described in detail.
Firstly, referring to Fig. 2 come to the composition of the lap device 100 of the airplane Hydraulic Tube and fuel tank of the utility model into
Row explanation, Fig. 2 be according to the perspective view of the lap device of the airplane Hydraulic Tube and fuel tank of an embodiment of the present invention,
Middle fluid pressure line, connector, sealing element and connector have been assembled together:
As shown in Fig. 2, the airplane Hydraulic Tube of the utility model and the lap device 100 of fuel tank include fluid pressure line
110, connector 120, sealing element 130 and connector 140.
Wherein, connector 120 is used to be tightly bonded together with the exterior panel of fuel tank (not shown).It is worth mentioning herein
Although in the illustrated embodiment, connector 120 is using the form of three-jaw bump joint, it is not limited to that, example
The form of bump joint or two pawls, four paws multijaw bump joint such as can also be used.Seal groove is provided on connector 120
121, and the connector 120 has contact surface 122.The connector 120 has biggish contact surface, and its contact surface
122 carry out coating treatment in advance, thus can ensure to take when the contact surface 122 and the surface of fuel tank (not shown) contact
Connect the excellent conduction of electric current.
Sealing element 130 is mounted in the seal groove 121 of connector 120, for ensuring fuel sealing.It is worth mentioning herein
It is, although in the illustrated embodiment, using the form of sealing ring, it is not limited to that sealing element 130.In addition, by
It is nonconducting in the sealing element 130 of the utility model, thus the sealing element 130 is made of insulating material, such as rubber etc..
Connector 140 is used to for connector 120 being securely fixed in the exterior panel of fuel tank (not shown).Equally, herein
It is noted that although in the illustrated embodiment, using the form of screw, it is not limited to that connector 140,
Such as the form for other fasteners such as bolt can also be used.In addition, since illustrated embodiment shows the bump joint of three-jaw,
Three connectors 140 thus are equipped with, the quantity of the connector and the pawl number of specific used multijaw bump joint are opposite
It answers.
Then, the dress of the lap device 100 to the airplane Hydraulic Tube and fuel tank of the utility model is carried out referring to Fig. 2 and 3
With being illustrated, Fig. 3 is the vertical view according to the lap device of the airplane Hydraulic Tube and fuel tank of an embodiment of the present invention
Figure, wherein fluid pressure line 110, connector 120, sealing element 130 and connector 140 have been assembled together:
After mounting, as shown in Figures 2 and 3, fluid pressure line 110 is crimped together with the mouth that crimps of connector 120.Sealing element
130 are mounted in the seal groove 121 of connector 120.The contact surface 122 and fuel oil of connector 120 after surface coated treatment
The intimate surface contact of case (not shown) forms sealing, and the contact table of connector 120 after thus sealing element 130 is squeezed
Face 122 fits closely the exterior panel of fuel tank, and is fixed on the exterior panel of fuel tank by connector 140, thus fluid pressure line
110 for good and all crimp with the nozzle of connector 120 and are sealed, and ensure that fuel sealing.
When having electric current to pass through on the fluid pressure line of fuel tank, the electric current is connected rapidly the contact surface 122 of connector 120
To the surface of fuel tank, then pass through fuel tank conducting ground connection.According in illustrated embodiment, due to setting there are three connector 140, because
And it is good to be formed by fixed not only stability by these three connectors, guarantees redundancy design, and compares for frame connector it
The probability loosened is greatly lowered.Moreover, according to illustrated embodiment, due to the reason of the larger contact surface of three-jaw bump joint,
It can thus ensure that overlap joint current conduction is excellent, while the design of sealing element 130 and big contact surface also significantly increase combustion
The leakproofness of fuel tank and pipeline.
Finally, carrying out the connector of the lap device 100 to the airplane Hydraulic Tube and fuel tank of the utility model referring to Fig. 4
The surface coated treatment of 120 contact surface 122 is illustrated, and Fig. 4 is the airplane Hydraulic Tube of an embodiment of the present invention
With the flow diagram of the surface coating layer treatment method of the contact surface of the connector of the lap device of fuel tank:
As previously mentioned, in order to ensure that can ensure to overlap when the contact surface 122 of connector 120 and the surface of fuel tank contact
The excellent conduction of electric current will carry out surface coated treatment to the contact surface 122 in advance.
In particular, as shown in figure 4, the surface coating layer treatment method includes following four step:
Step 1 " polishing priming paint ": the lap device 100 of the airplane Hydraulic Tube and fuel tank of the utility model of polishing
The contact surface 122 of connector 120, to remove original priming paint in contact surface；
Step 2 " oxidation processes ": oxidation processes are carried out to the contact surface 122 for the connector 120 polished, preferably
Carry out A Luoding anodized: the immersion coating both ensure that the contact surface 122 and surrounding for the connector 120 polished
The isolation of medium, to play antisepsis；Also ensure that aerolite structural conductive meets connector 120 and fuel oil simultaneously
Conductive requirement when case surface contacts；And combination when improving applying paste again between the A Luoding coating surface
Power, to enhance adhesion effect；
Step 3 " assembly ": as previously mentioned, by the lap device 100 of the airplane Hydraulic Tube of the utility model and fuel tank
Connector 120 be assembled together with fuel tank；
Step 4 " encapsulation process ": connector 120 and fuel tank after to having assembled carry out fillet sealing, preferably right
Contact gap coating sealant between connector 120 and fuel tank, so that it is guaranteed that the leakproofness of fuel tank.At the same time, to spiral shell
Bolt applying paste and carry out package processing, ensure that leakproofness.At this time it should be noted that the link position of bolt needs
Ensure the conductance general character.
The contact surface of the connector 120 of the lap device 100 of airplane Hydraulic Tube and fuel tank in view of the utility model
122 have passed through above-mentioned surface coated treatment, thus realize between the contact surface 122 and the contact surface of fuel tank exterior panel
It is seamless applying, the splendid overlap joint conductance general character thus can not only be obtained, and sealing performance is also fabulous.
The preferred embodiment of the utility model has already been described in detail above, it is understood that having read the utility model
Above-mentioned teaching content after, those skilled in the art will be readily apparent other advantage and modification.Therefore, wider at its
For in general aspect, the utility model is not limited to detail and representative embodiment shown and described herein.
Therefore, those skilled in the art reasonably can be combined the element of above embodiment or be changed, not take off
Premise from the spirit or scope such as the total concept of the invention of the utility model defined by the appended claims and its equivalent
It is lower that various modification can be adapted.
Description of symbols:
1. fluid pressure line 1 in the prior art
2. connector 2 in the prior art
100. the lap device of airplane Hydraulic Tube and fuel tank
110. fluid pressure line
120. connector
121. seal groove
122. contact surface
130. sealing element
140. connector
Claims (13)
1. the lap device (100) of a kind of airplane Hydraulic Tube and fuel tank characterized by comprising
Fluid pressure line (110), the fluid pressure line pass through fuel tank；
Connector (120), the connector is used to be tightly bonded together with the exterior panel of the fuel tank, in the connector
(120) it is provided on seal groove (121), and there are contact surface (122), wherein the connector (120) and the hydraulic tube
Road (110) is crimped together；
Sealing element (130), the sealing element is mounted in the seal groove (121) of the connector (120), for ensuring fuel oil
Sealing, the sealing element (130) is nonconducting；
Connector (140), the connector are used to for the connector (120) being fixed on the exterior panel of the fuel tank.
2. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that described to connect
Head (120) is the form of multijaw bump joint.
3. the lap device (100) of airplane Hydraulic Tube as claimed in claim 2 and fuel tank, which is characterized in that described to connect
Head (120) is the form of three-jaw bump joint.
4. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that described to connect
The contact surface (122) of head (120) is subjected to surface coated treatment, for ensuring the contact surface (122) and the combustion
The excellent conduction of electric current can be ensured to overlap when the surface contact of fuel tank.
5. the lap device (100) of airplane Hydraulic Tube as claimed in claim 4 and fuel tank, which is characterized in that the table
Finishing coat processing includes: polishing priming paint, oxidation processes, assembly and encapsulation process.
6. the lap device (100) of airplane Hydraulic Tube as claimed in claim 5 and fuel tank, which is characterized in that the oxygen
Change processing and is preferably A Luoding anodized.
7. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that described close
Sealing (130) uses the form of sealing ring.
8. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that described close
Sealing (130) is made of insulating material.
9. the lap device (100) of airplane Hydraulic Tube as claimed in claim 8 and fuel tank, which is characterized in that described close
Sealing (130) is made of rubber.
10. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that the company
Fitting (140) uses the form of screw.
11. the lap device (100) of airplane Hydraulic Tube as described in claim 1 and fuel tank, which is characterized in that the company
Fitting (140) uses the form of bolt.
12. the lap device (100) of airplane Hydraulic Tube as claimed in claim 2 and fuel tank, which is characterized in that the company
The quantity of fitting (140) is corresponding with the pawl number of the connector (120).
13. the lap device (100) of airplane Hydraulic Tube as claimed in claim 3 and fuel tank, which is characterized in that described to take
Connection device (100) includes three connectors (140).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820688720.5U CN208487309U (en) | 2018-05-09 | 2018-05-09 | The lap device of airplane Hydraulic Tube and fuel tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820688720.5U CN208487309U (en) | 2018-05-09 | 2018-05-09 | The lap device of airplane Hydraulic Tube and fuel tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208487309U true CN208487309U (en) | 2019-02-12 |
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ID=65253031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820688720.5U Active CN208487309U (en) | 2018-05-09 | 2018-05-09 | The lap device of airplane Hydraulic Tube and fuel tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208487309U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113588157A (en) * | 2021-07-07 | 2021-11-02 | 中国商用飞机有限责任公司 | Pressure sensor erection joint and have its aircraft |
| CN113757471A (en) * | 2021-09-22 | 2021-12-07 | 中国商用飞机有限责任公司 | Frame joint is crossed to fuel double-deck sleeve pipe |
| CN115388248A (en) * | 2022-10-28 | 2022-11-25 | 烟台中宇航空液压有限公司 | Hydraulic pipe connector for aircraft engine |
-
2018
- 2018-05-09 CN CN201820688720.5U patent/CN208487309U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113588157A (en) * | 2021-07-07 | 2021-11-02 | 中国商用飞机有限责任公司 | Pressure sensor erection joint and have its aircraft |
| CN113757471A (en) * | 2021-09-22 | 2021-12-07 | 中国商用飞机有限责任公司 | Frame joint is crossed to fuel double-deck sleeve pipe |
| CN115388248A (en) * | 2022-10-28 | 2022-11-25 | 烟台中宇航空液压有限公司 | Hydraulic pipe connector for aircraft engine |
| CN115388248B (en) * | 2022-10-28 | 2023-01-31 | 烟台中宇航空液压有限公司 | Hydraulic pipe connector for aircraft engine |
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