CN113588157A

CN113588157A - Pressure sensor erection joint and have its aircraft

Info

Publication number: CN113588157A
Application number: CN202110768516.0A
Authority: CN
Inventors: 姜亮; 宋志强; 高广拓; 丁南竹
Original assignee: Commercial Aircraft Corp of China Ltd
Current assignee: Commercial Aircraft Corp of China Ltd
Priority date: 2021-07-07
Filing date: 2021-07-07
Publication date: 2021-11-02
Anticipated expiration: 2041-07-07
Also published as: CN113588157B

Abstract

The invention relates to a mounting joint for connecting a fuel tank of an aircraft to a pressure sensor, and an aircraft with the mounting joint. The field joint includes an inner connection structure having a line interface, an outer connection structure having a sensor interface in communication with the line interface through an internal passageway, and a mounting structure for mounting the field joint to a tank wall of a fuel tank. In the installed state, the inner connection structure is located in the fuel tank and is intended for connection with a fuel pressure line, and the outer connection structure is located outside the fuel tank and is intended for connection with a pressure sensor. The mounting tabs are integrally constructed as a unitary structure with a central axis of the sensor interface being perpendicular to a central axis of the internal passageway. According to the invention, the number and the types of parts required by the installation of the pressure sensor can be reduced, the installation space is small, the arrangement of the EWIS wire harness is compact and orderly, the installation procedures can be reduced, the weight of an aircraft is reduced, and the manufacturing cost and the maintenance cost of a flight line are reduced.

Description

Pressure sensor erection joint and have its aircraft

Technical Field

The invention relates to the field of civil aviation, in particular to a pressure sensor mounting joint and an aircraft with the same.

Background

Fuel pressure indicating systems are commonly provided in fuel systems of civil aircraft, the function of which is to provide an outlet fuel pressure signal to a fuel system computer for all the fuel pumps on board the aircraft, for indicating to the pilot the operating status of the fuel pumps on board the aircraft. In addition, fuel pressure signals in the pressure filling pipelines of the fuel tanks can be provided, and the opening and closing states of the filling cut-off valves of the fuel tanks can be indicated to crew.

The fuel pump is mounted within an aircraft fuel tank. A fuel pressure-inducing line is usually led out from the fuel pump outlet and connected with one end of a through-frame joint on the aircraft fuel tank structure. And the fuel pressure sensor is arranged at the other end of the through frame joint outside the fuel tank. When the fuel pump switch is pressed, the fuel pump is started, and high-pressure fuel is conducted to the fuel pressure sensor through the fuel pressure guiding pipeline and the frame joint. An elastic reed in the fuel pressure sensor detects high-pressure fuel, outputs a corresponding electric signal to a fuel system computer and indicates a pilot that the current fuel pump is in an open state. On the contrary, after the fuel pump switch is pressed, if the fuel pump is not started due to reasons such as faults and the like, and the fuel pressure sensor detects that the fuel at the outlet of the fuel pump is low pressure, the fuel system computer sends a fuel pump low pressure warning signal to the aircraft cockpit, and meanwhile, a warning lamp corresponding to the fuel pump switch on a control panel at the top of the fuel in the cockpit is also lighted, so that a pilot is reminded that the fuel pump has faults and measures need to be taken according to a flight manual.

Similarly, a fuel pressure line is also typically routed to a fill shut-off valve located within the fuel tank and connected to a pressure sensor via a box connector. When the crew operates the pressure refueling switch to open the refueling stop valve through the refueling and draining control panel, and the fuel pressure sensor connected with the refueling stop valve detects the high pressure of fuel, a signal is sent to the fuel system computer to indicate that the refueling stop valve is in an open state. Otherwise, if the pressure refueling switch is opened, the refueling cut-off valve cannot be opened, and the fuel pressure sensor detects that the outlet of the refueling cut-off valve is low pressure, the fuel system computer sends an alarm signal to the refueling and discharging control panel to prompt the current refueling cut-off valve of the crew member to break down.

Among these, the fuel pressure sensor mounting tabs mounted on the fuel tank structure of an aircraft are important components for connecting the equipment inside the fuel tank (e.g., fuel pump, refueling shutoff valve) with the fuel pressure sensor outside the fuel tank. However, the mounting joint and the connection mounting form of the fuel pressure sensor in the prior art are not enough, and further improvement and optimization are needed.

It is therefore desirable to provide a pressure sensor mount fitting and an aircraft having the same that at least partially address the above-mentioned problems.

Disclosure of Invention

The invention aims to provide an installation joint for connecting a fuel tank of an aircraft and a pressure sensor, and aims to solve the problems that the existing installation joint of the fuel pressure sensor in the civil aircraft has more types of parts and interfaces, is complex to install and maintain, occupies large installation space, and easily triggers a fuel low-pressure alarm signal due to the fact that a measuring port of the fuel pressure sensor is easily blocked by ice blocks, ice crystals or impurities, so that an error indication signal is provided.

According to a first aspect of the invention, there is provided a mounting fitting for effecting a connection between a fuel tank of an aircraft and a pressure sensor, the mounting fitting comprising:

an internal connection structure having a line connection and configured to be disposed inside the fuel tank and to be connected to a fuel pressure line within the fuel tank through the line connection;

an external connection structure provided outside the fuel tank and having a sensor interface communicating with the piping interface through an internal passage, wherein the external connection structure is configured to be connectable with a pressure sensor through the sensor interface; and

a mounting structure for fixedly mounting the mounting fitting to a tank wall of the fuel tank;

wherein the mounting tab is integrally configured as a unitary structure with a central axis of the sensor interface being perpendicular to a central axis of the internal passageway.

According to this scheme, the integral type structure can reduce the quantity and the kind of the required spare part of pressure sensor installation to reduce the installation procedure, alleviate the weight of aircraft, reduce manufacturing cost, can also reduce the stock kind and the quantity of air traffic material spare part in the airline operation, be favorable to reducing the airline maintenance cost. The sensor interface steering arrangement allows the pressure sensor and its signal harness components to be mounted in close proximity to the outer surface of the fuel tank, and can be supported and secured using fewer and shorter structural brackets, helping to reduce the weight of the aircraft and reduce manufacturing costs. Meanwhile, the length of a cantilever formed by the part of the mounting joint extending outwards is shorter, and the mounting joint does not need to occupy larger mounting space, so that the arrangement of the EWIS wire harness is more compact and ordered.

In one embodiment, the internal passage is configured to communicate with the sensor interface by a tapered shape, and is in a horizontal state in a state where the mount fitting is fixedly mounted to a tank wall of the fuel tank.

In one embodiment, the measurement port of the pressure sensor is higher than a low point of a port of the internal passage that communicates with the sensor interface in a state where the pressure sensor is mounted to the mounting joint.

According to the technical scheme, the risk that the measuring port of the pressure sensor is blocked and fails by ice blocks, ice crystals or impurities to trigger the fuel low pressure alarm fault signal can be reduced.

In one embodiment, the external connection comprises a support connection and a steering module, the steering module being connected to the mounting structure via the support connection, the sensor interface being arranged on the steering module.

According to the present solution, the weight of the steering module and the pressure sensor can be supported by the bearing connection section.

In one embodiment, the steering module is provided with a fuse passage for passage of a tie fuse at a location proximate to a port of the sensor interface.

In one embodiment, the cross section of the steering module perpendicular to the central axis of the sensor interface is square, and the included angle formed by the fuse passage and the side line of the square cross section is a predetermined angle

In one embodiment, the number of the fuse paths is set to at least one.

According to the technical scheme, the length of the anti-loosening binding fuse can be shortened, and the risk that the fuse is mistakenly collided and broken is reduced. And the fuse access is integrated, and no additional structural support or fastener is needed to be added for binding and fixing the fuse, so that the weight of the aircraft is reduced.

In one embodiment, the internal connection structure comprises a pipeline connection nozzle and a frame connection section, the pipeline connection nozzle is connected with the mounting structure through the frame connection section, and the pipeline interface is arranged on the pipeline connection nozzle.

According to the scheme, enough length extending into the fuel tank can be provided through the frame connecting section.

In one embodiment, the line connection is designed in the form of a flare.

According to the scheme, the flaring shape can be conveniently butted and sealed with the fuel pressure pipeline in a matching way.

In one embodiment, the outer peripheral surface of the pipe connection nipple is provided with an external thread.

According to the scheme, the pipe nut can be used for realizing the connection of the pipeline connecting nozzle and the fuel oil pressure pipeline.

In one embodiment, the mounting structure is designed as a flange, the side of which facing the fuel tank is provided with a sealing ring groove for receiving a sealing ring.

According to this scheme, the ring flange can realize the firm installation between the tank wall of erection joint and fuel tank, and the sealing washer can realize sealing between the tank wall of erection joint and fuel tank.

In one embodiment, the field joint is made of a metallic material.

According to the scheme, the installation connector can be made of a proper material and is suitable for being made in an integrated machining mode.

In one embodiment, the surface of the field joint is surface treated by a process of surface passivation or cadmium plating.

According to the scheme, the different potential corrosion generated when the mounting connector is attached and contacted with the aluminum structural surface of the fuel tank can be avoided.

According to another aspect of the invention, there is also provided an aircraft equipped with a fuel tank and a pressure sensor connected by a mounting fitting as described above.

Drawings

For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.

FIG. 1 illustrates a fuel pressure sensor mounting connection for an aircraft according to one prior art;

FIG. 2 illustrates a fuel pressure sensor mounting connection for an aircraft according to another prior art;

FIG. 3 illustrates a fuel pressure sensor mounting connection for an aircraft according to yet another prior art;

FIG. 4 illustrates a perspective view of a pressure sensor mount joint according to a preferred embodiment of the present invention;

FIG. 5 shows a cut-away schematic view of the installation joint of FIG. 4;

FIG. 6 shows a schematic view in partial cross-section of the installation joint of FIG. 4;

FIG. 7 shows a schematic view of the mounting adapter of FIG. 4 coupled to a pressure sensor;

FIG. 8 shows an exploded perspective view of the fuel tank and pressure sensor connected using the mounting adapter of FIG. 4; and

FIG. 9 shows a perspective view of the connection of a fuel tank to a pressure sensor using the mounting adapter of FIG. 4.

Detailed Description

Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention.

Fig. 1 shows a fuel pressure sensor mounting connection on an aircraft of some type. The technical scheme has the following defects:

a) according to the technical scheme, the fuel pressure guiding pipe 1a is adopted to connect the fuel pressure guiding pipe in the oil tank with the fuel pressure sensor 2a outside the oil tank, the length of the fuel pressure guiding pipe 1a is long, and the weight of the airplane is increased; and the bending trend forms of the fuel pressure guide pipes 1a are inconsistent, the installation universality is poor, the types and the number of spare parts of the marine materials are increased, and the manufacturing and maintenance cost is increased.

b) The fuel pressure guide pipe 1a runs along the vertical direction, so that a measuring port of the fuel pressure sensor 2a is arranged at the lowest point of the vertical guide pipe; this arrangement is liable to cause deposition and accumulation of moisture and impurities in the fuel oil at the measurement port of the fuel pressure sensor 2 a; in a low-temperature environment, water in oil is frozen or impurities in the oil are deposited after long-time operation, so that a measuring port of the fuel pressure sensor 2a is easily blocked by ice blocks, ice crystals or impurities, a fuel low-pressure warning signal is easily triggered, and an erroneous indicating signal is provided for a pilot.

c) The installation and the fixing of the fuel pressure sensor 2a on the airplane need to additionally use a structural support 3a and a P-type clamp 4a, so that the weight of the airplane is increased, the types and the number of assembled spare and accessory parts are increased, and the installation operation steps and links are increased.

Figure 2 shows a fuel pressure sensor mounting adapter and its connection arrangement on a series of aircraft from boeing, usa. The technical scheme has the following defects:

d) in the technical scheme, the structural form of the fuel pressure sensor mounting joint 1b is a through head form, and a 90-degree vertical angle is formed between the fuel pressure sensor 2b and the wall plate surface 3b of the aircraft fuel tank structure after the fuel pressure sensor 2b is connected with the through head; at the rear of the fuel pressure sensor 2b, an electrical connector 4b (including a harness tail attachment) on the signal cable is connected with an electrical connector at the rear of the fuel pressure sensor 2 b. Under this kind of installation arrangement form, fuel pressure sensor 2b, pencil electric connector 4b and pencil tail annex stack in proper order along the direction of perpendicular to oil tank structure wallboard face 3b, need occupy great installation space.

e) Because the wiring harness electric connector 4b (including the wiring harness tail accessory) is arranged at the tail part of the fuel pressure sensor 2b, is far away from the wall plate surface 3b of the fuel tank structure (the cantilever is longer), and takes the factors of maneuvering flight, vibration and the like of the airplane into consideration, a plurality of structural supports are additionally added to support and fix the wiring harness, and the weight and the manufacturing cost of the airplane are increased.

f) In addition, in this mounting form, since the harness electrical connector 4b (including the harness tail fitting) is far from the tank structure wall surface 3b, the harness length of the signal line needs to be increased, which increases the weight and cost.

Figure 3 shows a fuel pressure sensor mounting adaptor and its connection arrangement on a series of aircraft from european air passenger company. The technical scheme has the following defects:

g) in the technical scheme, when the fuel pressure sensor 2c is assembled with the fuel pressure sensor mounting joint 1c, a plurality of mounting interfaces and mounting links are required; for example, the fuel pressure sensor 2c needs to be assembled and sealed with the sealing valve 3c through the sealing ring 4 c; a plug 5c is required to penetrate through the fuel pressure sensor 2c to be screwed with the sealing valve 3c, and is assembled and sealed with the fuel pressure sensor 2c through another sealing ring 4 c; more interfaces and more links.

h) The number of installation interfaces and installation links is increased, so that the requirement on the reliability of component installation is improved, and the installation difficulty is increased; and meanwhile, the risk points of fuel leakage are increased.

i) Spare and accessory parts that the installation was used are more (including 2 sealing washers, 1 blanking cover and 1 fuse ligature locking washer), have increased the stock kind and the quantity of airline operation in-process avionics spare part, have improved the maintenance cost.

In order to at least partially solve the disadvantages of the solutions described above, the invention provides a mounting joint for making a connection between a fuel tank and a pressure sensor of an aircraft. A preferred embodiment according to the present invention will be described below with reference to fig. 4 to 9.

As shown in fig. 4, the field joint 100 includes an inner connecting structure 1, an outer connecting structure 2, and a mounting structure 3. Wherein the mounting structure 3 is configured for fixedly mounting the mounting nipple 100 to a tank wall 700 of a fuel tank of an aircraft (see fig. 8 and 9). In the state in which the mounting fitting 100 has been fixedly mounted to the tank wall 700 of a fuel tank, the inner connection 1 is located inside the fuel tank for connection with a fuel pressure line inside the fuel tank. The fuel pressure line may in particular be a fuel pressure line leading from a fuel pump and/or a fuel filling shut-off valve. The external connection structure 3 is located outside the fuel tank for connection with a pressure sensor 300 (see fig. 7 to 9) that senses the fuel pressure.

The installation joint 100 according to the present invention may be made of a metal material, such as a stainless steel or alloy steel material, and may be manufactured by using a numerical control machine, so that the installation joint 100 is formed as an integral structure, which is beneficial to reduce the number and types of parts required for installing the pressure sensor 300, thereby reducing the installation process, reducing the weight of the aircraft, reducing the manufacturing cost, reducing the types and numbers of stock of spare parts of aircraft materials in the operation of the airline, and being beneficial to reduce the maintenance cost of the airline.

Additionally, the outer surface of the mounting adapter 100 may be surface treated after machining to prevent corrosion at different potentials when the mounting adapter 100 is in abutting contact with the aluminum structural surface of the fuel tank. Preferably, the surface treatment may be achieved by a process such as surface passivation or cadmium plating.

In the illustrated embodiment, the mounting terminal 100 has an elongated shape as a whole, and the mounting structure 3 is arranged between the inner connecting structure 1 and the outer connecting structure 2 in the longitudinal direction of the mounting terminal 100, which is configured in the shape of a flange. The flange plate is uniformly provided with a plurality of first mounting holes 31 along the circumferential direction. Referring again to fig. 8, a second mounting hole 702 is correspondingly provided in the tank wall 700 of the fuel tank. The field joint 100 can be securely mounted to the tank wall 700 of the fuel tank using fasteners that pass through the second mounting hole 702 and the first mounting hole 31 in sequence. One example of a fastener may be a screw 601 and nut 603 with a washer 602 disposed in mating relation.

It will be understood that the tank wall 700 of the fuel tank is also provided with a through hole 701 for the internal connection 1 to pass through. Also, preferably, as shown in fig. 4, the side of the flange facing the tank wall 700 is provided with a gasket groove 32. When installed, the seal ring 500 may be disposed within the seal ring groove 32 and the seal ring 500 may be sealed around the through hole 701 after installation is completed.

Referring to fig. 4 and 5, the inner joint structure 1 is constructed integrally as a tubular structure extending in the longitudinal direction of the mounting adapter 100, and has one end connected to the mounting structure 3 and the other end provided at the end with a line connection 12 for connection to a fuel pressure line in the fuel tank.

In the illustrated embodiment, the internal connection structure 1 includes two parts, a pipe connection nipple 10 and a through-frame mounting section 20. The over-frame mounting section 20 extends outwardly from the mounting structure 3 for providing sufficient length to extend into the interior of the fuel tank for connection with a fuel pressure line. The pipe connection nozzle 10 is located at the end of the through-frame installation section 20, and the pipe connection port 12 is provided on the pipe connection nozzle 10. Preferably, the line connection 12 is designed as a flared sealing surface in order to be connected in a mating manner to a connection of a fuel pressure line. The outer peripheral surface of the pipeline connecting nozzle 10 is provided with an external thread 11 for matching with a pipe nut. The specification of the external thread 11 and the shape specification parameters of the flared sealing surface of the line interface 12 may be determined according to the specification parameters of the pipe nut connected to the line connection nipple 10 and the line end interface.

The field joint 100 is also provided with an internal passage 101 that communicates between the line connection 12 and the sensor connection 52. The internal passage 101 extends generally in the longitudinal direction of the field joint 100. Thus, the over-frame mounting section 20 is actually a section of hollow thick-walled tubular structure. It will be appreciated that the internal passage 101 extends generally in a direction through the tank wall 700 of the fuel tank to direct fuel pressure from a fuel pressure line within the tank to the outside of the tank. That is, the central axis of the internal passageway 101 is substantially perpendicular to the tank wall 700.

According to the present invention, the mount joint 100 is configured such that the center axis of its internal passageway 101 is substantially perpendicular to the center axis of the sensor interface 52. With this arrangement, the fuel flow passage direction perpendicular to the tank wall 700 of the fuel tank can be changed to the flow passage direction parallel to the tank wall 700 without changing the fuel pressure transmitted, allowing the pressure sensor 300 and the signal harness, harness electrical connector (including harness tail attachment), etc. downstream thereof to be mounted close to the outer surface of the tank wall 700, and allowing fewer and shorter structural brackets to be used for support and fixation, contributing to weight reduction of the aircraft and reduction of the manufacturing cost. Meanwhile, the installation structure enables the length of a cantilever formed by the part of the installation joint 100 extending out of the tank wall 700 of the fuel tank to be shorter, large installation space is not required to be occupied, and the Wiring harness arrangement of an Electrical Wire Interconnection System (EWIS) around the fuel tank of the aircraft can be more compact and ordered.

With continued reference to fig. 4 and 5, in particular, the external connection 2 comprises two parts, a support connection segment 40 and a steering module 50. The sensor interface 52 is disposed within the steering module 50. A sealing ring mounting groove 51 is arranged at the port of the sensor interface 52. As shown in fig. 7, when the pressure sensor 300 is mounted in abutment with the sensor interface 52, the sensor seal 200 may be provided in the seal mounting groove 51 to perform a sealing function.

Preferably, as shown in fig. 6, a through fuse passage 53 is further provided at a port position of the steering module 50 near the sensor interface 52. A fuse 400 (see fig. 8) can be sequentially passed through the pressure sensor 300 and the fuse passage 53 on the steering module 50, so as to perform binding and anti-loosening on the installed pressure sensor 300. Thus, the fuse passage 53 is arranged close to the pressure sensor 300, so that the length of the fuse for preventing the binding from loosening is greatly shortened, and the risk of the fuse being mistakenly collided and broken can be reduced. Moreover, the fuse passage 53 is integrated into the mounting tab 100 without adding additional structural brackets or fasteners for fuse binding, which is beneficial to reducing the weight of the aircraft.

In the illustrated embodiment, the steering module 50 is of a substantially square configuration. In other words, the steering module 50 is square in shape in a cross-section perpendicular to the central axis of the sensor interface 52. The fuse passage 53 forms a predetermined angle, preferably 45 °, with the cross-sectional edge of the steering module 50. Further preferably, the number of the fuse paths 53 may be set to at least one. In the illustrated embodiment, the fuse passages 53 are preferably provided in two, and the angle between the two fuse passages 53 is 90 °.

The support connection segment 40 serves to connect the mounting structure 3 with the steering module 50 and to support the weight of the steering module 50 and the pressure sensor 300. A portion of the internal passageway 101 extends within the support link 40 and communicates with the sensor interface 52.

Preferably, the internal passage 101 is provided to extend in the horizontal direction in a state where the mount fitting 100 has been fixedly mounted to the tank wall 700 of the fuel tank, so that the influence of gravity on the pressure sensing can be eliminated as much as possible. Further preferably, the internal passage 101 is configured to communicate with the sensor interface 52 through a tapered shape. As shown in fig. 5, the internal passage 101 in the support connection section 40 is configured as a tapered portion 102, and communicates with the sensor interface 52 through a small-diameter end of the tapered portion 102. Such a design may position the lowest point within the internal passage 101 away from the sensor interface 52. Moisture and impurity in the fuel oil flow to the lowest position point under the effect of gravity, avoid deposit and gather in the position of pressure sensor 300's measurement port to can prevent that the moisture in the fluid from freezing or the impurity deposit in the long-time operation back fluid under the low temperature environment from leading to pressure sensor 300's measurement port to block up the inefficacy, and then reduce because the measurement port blocks up the risk that the inefficacy triggers fuel low pressure warning fault signal.

In the embodiment shown in fig. 5, only the internal passage 101 in the support connection section 40 is configured as a tapered pipe of a tapered shape, and the internal passage 101 in the through-frame mounting section 20 has a uniform diameter. It is understood, however, that in other embodiments, the internal passageway 101 may also be configured entirely in a shape that tapers toward the sensor interface 52.

Fig. 7 shows a schematic view of the assembly of the pressure sensor 300 with the installation joint 100. It can be seen that in a state where the internal passage 101 extends in the horizontal direction, the measurement port of the pressure sensor 300 is higher than the lowest point of the port of the internal passage 101 that communicates with the sensor interface 52. This prevents moisture and impurities in the oil from being deposited and collected at the position of the measurement port of the pressure sensor 300, thereby ensuring the accuracy of pressure measurement.

The steps of installing the field joint 100 according to the present invention are described below with reference to fig. 8 and 9:

step 1, firstly, a sealing ring 500 is arranged in a sealing ring groove 32 of a flange plate of the mounting joint 100; a sealant for wet-fitting sealing is applied to the outer peripheral surface of the through-frame attachment section 20 of the attachment fitting 100, and the pipe connection nozzle 10 and the through-frame attachment section 20 are inserted through the through-hole in the tank wall 700 of the fuel tank.

Step 2: four sets of fasteners (screw 601, washer 602 and nut 603) are wet mounted with sealant, the screw 601 is passed through the second mounting hole 702 in the tank wall 700 and the first mounting hole 31 in the flange of the field joint 100 from the inside of the fuel tank, respectively, and the nut 603 is tightened to securely mount the field joint 100 to the tank wall 700.

And step 3: the sensor seal 200 is attached to the pressure sensor 300.

And 4, step 4: the pressure sensor 30 is installed in the sensor interface 52 of the field joint 100.

And 5: the installation tab 100 and the pressure sensor 300 are banded anti-loose using a fuse 400 that passes through the fuse passage 53 of the installation tab 100 and the fuse passage of the pressure sensor 300 in sequence.

According to another aspect of the invention, there is also provided an aircraft equipped with a fuel tank and a pressure sensor. Wherein the fuel tank and the pressure sensor are connected by means of a mounting nipple as described above.

Compared with the prior art, the pressure sensor mounting joint provided by the invention can realize the following beneficial effects:

a) compared with a certain type of airplane shown in the figure 1, the pressure sensor in the technical scheme of the invention requires fewer parts for installation and connection (no additional fuel pressure guide pipe and pipe nut are needed), and the pressure sensor installation joint has good consistency and strong universality; meanwhile, the self-supporting mode of the installation joint is adopted, and an additional structural support and a P-shaped clamp are not needed, so that the weight of the airplane is reduced, and the manufacturing cost is reduced; in addition, in the technical scheme of the invention, the measuring port of the pressure sensor is arranged at a high point, so that the phenomenon that the water and impurities in the fuel oil liquid are deposited and gathered at the measuring port of the fuel oil pressure sensor, and the measuring port of the pressure sensor is blocked by ice blocks, ice crystals or impurities can be avoided.

b) Compared with a certain series of airplanes of the Boeing company in America shown in FIG. 2, in the technical scheme of the invention, the pressure sensor, the signal wire harness and the wire harness electric connector (including the wire harness tail accessory) are installed close to the structural wall plate of the oil tank, so that fewer and shorter structural brackets can be adopted for supporting and fixing, and the weight reduction and the manufacturing cost reduction of the airplane are facilitated; the arrangement mode is compact and orderly, and does not need to occupy larger installation space.

c) Compared with a certain series of airplanes of European air passenger company shown in the figure 3, the technical scheme of the invention has the advantages that the number of installation interfaces is reduced, the installation operation steps are reduced, the installation efficiency is improved, and the maintenance time is shortened; meanwhile, the types and the number of spare parts required by the installation of the pressure sensor are reduced (1 sealing ring, 1 installing blanking cover and 1 fuse binding locking washer are reduced), the reduction of the types and the number of the spare parts of the aviation materials in the operation process of the air route is facilitated, and the maintenance cost is reduced; in addition, the number of the interfaces and the installation links are reduced, and the reduction of fuel leakage risk points is facilitated.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims

1. A mounting joint for enabling connection between a fuel tank and a pressure sensor of an aircraft, characterized in that the mounting joint (100) comprises:

an internal connection (1), the internal connection (1) having a line connection (12) and being configured to be arranged in the fuel tank and to be connected to a fuel pressure line in the fuel tank via the line connection (12);

an external connection structure (2) which is arranged outside the fuel tank and has a sensor interface (52), wherein the sensor interface (52) communicates with the line interface (12) via an internal passage (101), wherein the external connection structure (2) is configured to be connectable with a pressure sensor (300) via the sensor interface (52); and

a mounting structure (3), the mounting structure (3) being for fixedly mounting the mounting fitting to a tank wall (700) of the fuel tank;

wherein the mount joint is integrally configured as a unitary structure, and a central axis of the sensor interface (52) is perpendicular to a central axis of the internal passage (101).

2. The field joint according to claim 1, wherein the internal passage (101) is configured to communicate with the sensor interface (52) by a tapered shape, and the internal passage (101) is in a horizontal state in a state where the field joint (100) is fixedly mounted to a tank wall (700) of the fuel tank.

3. The field joint according to claim 2, wherein in a state in which the pressure sensor (300) is mounted to the field joint (100), a measurement port of the pressure sensor (300) is higher than a low point of a port of the internal passage (101) that communicates with the sensor interface (52).

4. The field joint according to claim 1, wherein the external connection structure (2) comprises a support connection section (40) and a steering module (50), the steering module (50) being connected to the mounting structure (3) by the support connection section (40), the sensor interface (52) being provided on the steering module (50).

5. The field joint according to claim 4, wherein the steering module (50) is provided with a fuse passage (53) for passage of a tie fuse (400) at a location close to a port of the sensor interface (52).

6. The field joint according to claim 5, wherein a cross-section of the steering module (50) perpendicular to a central axis of the sensor interface (52) is square, and the fuse path (53) forms an angle of a predetermined angle with a side line of the square cross-section.

7. The field joint according to claim 6, wherein the number of fuse passages (53) is provided as at least one.

8. The field joint according to claim 1, wherein the internal connection structure (1) comprises a pipe connection nozzle (10) and a through frame connection section (20), the pipe connection nozzle (10) being connected with the mounting structure (3) by the through frame connection section (20), the pipe interface (12) being provided on the pipe connection nozzle (10).

9. A field joint according to claim 8, characterised in that the outer peripheral surface of the pipe connection nipple (10) is provided with an external thread (11).

10. The field joint according to claim 1, wherein the pipe interface (12) is configured in a flared shape.

11. The mounting connection according to claim 1, characterized in that the mounting structure (3) is configured as a flange, the side of which facing the fuel tank is provided with a sealing ring groove (32) for receiving a sealing ring.

12. The field joint of claim 1, wherein the field joint (100) is made of a metallic material.

13. The field joint according to claim 1, wherein the surface of the field joint (100) is surface treated by a process of surface passivation or cadmium plating.

14. An aircraft, characterized in that it is equipped with a fuel tank and a pressure sensor (300), which fuel tank and pressure sensor (300) are connected by a mounting joint (100) according to any one of claims 1 to 13.