Pressurizing oil tank with pull rope sensor

Abstract

The utility model discloses a pressurizing oil tank with a pull rope sensor, which mainly comprises the pull rope sensor, a shell, an end cover, a supporting ring, a pull rope, a sealing ring, a piston, a spring and the like, the end cover and a valve body are respectively assembled at two axial ends of the shell, the pull rope sensor is arranged on the end cover and is connected with the piston in an inner cavity of the shell through the pull rope, and the piston is arranged in the inner cavity of the shell. And a spring is arranged between the piston and the end cover. The device can be used on an aircraft hydraulic system, the pressurization oil tank is used for storing and providing hydraulic oil with certain pressure, and the pull rope sensor on the pressurization oil tank sends oil tank liquid level signals to an aircraft weapon system in real time. The pressurization oil tank is light in weight, compact in structure and good in maintainability, and has the functions of oil pressurization and stable oil liquid level real-time monitoring at the same time.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of aircraft fuel tank design, especially a pressurized fuel tank with a pull rope sensor. BACKGROUND

[0002] The fuel tank of a conventional aircraft weapon system does not have the ability to pressurize and monitor the liquid level in real time, or the fuel tank has a liquid level monitoring function but the liquid level signal output by the sensor is unstable. In order to solve the above problems, it is urgent to design a pressurized fuel tank that meets the requirements of the aircraft weapon system. SUMMARY

[0003] The utility model aims at a pressurized fuel tank with a pull rope sensor to solve the problem that the fuel tank of a conventional aircraft weapon system does not have the ability to pressurize and monitor the liquid level in real time, or the real-time liquid level monitoring function is unstable.

[0004] To achieve the above-mentioned purpose, the utility model adopts the following technical scheme:

[0005] A pressurized fuel tank with a pull rope sensor, comprising:

[0006] A shell, the axial first end and the axial second end of the shell are open, and the opening of the second end includes an exhaust hole and a mounting hole connected with a valve block;

[0007] An end cover, the end cover is assembled at the axial first end opening of the shell and at least a part of the end cover is located in the inner cavity of the shell, and the outer surface of the part is provided with a first sealing groove, a first sealing ring is installed in the first sealing groove to form a mechanical sealing structure between the end cover and the shell, and a through hole for a pull rope is opened on the end cover;

[0008] A pull rope sensor, the pull rope sensor is installed on the end face of the end cover located outside the shell, the pull rope sensor is connected with the aircraft weapon system through a cable for providing a liquid level signal in the inner cavity of the shell, the pull rope of the pull rope sensor is coaxial with the shell, and the end of the pull rope extends into the inner cavity of the shell through the through hole for the pull rope on the end cover;

[0009] A piston, the piston is slidingly connected in the inner cavity of the shell and connected with the end of the pull rope located in the inner cavity of the shell, the outer surface of the piston is provided with a second sealing groove and a support ring groove, a second sealing ring is installed in the second sealing groove, and a support ring for guiding the piston is installed in the support ring groove;

[0010] A spring, the spring is arranged in the inner cavity of the shell, and the axial first end of the spring is close to the end cover, and the axial second end of the spring is close to the piston.

[0011] As a scheme:

[0012] A plurality of threaded mounting holes are respectively arranged on the outer surfaces of the axial first end and the axial second end of the shell.

[0013] The end cover is connected with the threaded mounting hole on the outer surface of the axial first end of the shell through a twelve-angle screw.

[0014] Further, a threaded hole with a locking wire sleeve is arranged on the outer surface of the shell for connecting with a partition on an airplane.

[0015] Further, a limiting boss is arranged on the inner cavity wall of the shell for preventing the piston from separating from the open axial second end of the shell.

[0016] As a solution, the surface of the shell comprises at least one electrically conductive oxidation treatment layer.

[0017] As a solution, the pull rope sensor is connected with the end cover through a bolt.

[0018] As a solution, the end of the pull rope is connected with the piston through a quick-release joint and a screw with a cylindrical boss in sequence, wherein the cylindrical boss of the screw is inserted into the quick-release joint, and the screw is threadedly connected with the piston.

[0019] As a solution, the surface of the piston comprises at least one anode oxidation layer.

[0020] As a solution, the surface of the spring comprises a cadmium plating layer.

[0021] As a solution, the end cover and the piston have inner holes on the end face of the contact end of the spring, and the outer diameter of the spring is consistent with the inner hole diameters of the end cover and the piston.

[0022] The pressurized oil tank of the utility model mainly comprises a pull rope sensor (i.e. a pull rope displacement sensor), an end cover, a shell, a sealing ring, a spring, a supporting ring and a piston. When a hydraulic pump fills oil into the oil tank (shell), under the action of the spring force, the inner cavity of the oil tank (shell) stores hydraulic oil with a certain pressure, and the pull rope sensor provides a liquid level signal of filling oil into the inner cavity of the oil tank for a weapon system. When the hydraulic pump draws oil from the pressurized oil tank, under the action of the spring force, the pressurized oil tank provides hydraulic oil with a certain pressure for the hydraulic pump, and provides an oil tank oil supply signal for the weapon system.

[0023] Compared with the prior art, the utility model has the following characteristics:

[0024] (1) The pull rope of the pull rope sensor is coaxial with the shell, and the installation position can reflect the piston displacement in the shell in real time, stably and accurately, so as to reflect the oil liquid level in the shell in real time, stably and accurately. The pull rope sensor is provided with a cable, the cable is connected with an airplane weapon system and transmits the liquid level signal in the oil tank to the weapon system in real time.

[0025] (2) The end cover is provided with a sealing groove for mounting the first sealing ring, which forms a sealing structure with the shell and the first sealing ring to prevent impurities or rainwater from entering the inner cavity of the shell;

[0026] (3) The inner cavity of the shell is provided with a limiting boss to ensure the movement stroke of the piston, and an exhaust hole is arranged at the axial second end to discharge the oil gas in the inner cavity of the oil tank to the valve block and finally to the atmosphere;

[0027] (4) The inner cavity of the shell, the piston and the valve block (which is assembled at the axial second end opening of the shell) form an inner cavity, which can ensure the storage of a specified amount of hydraulic oil. The surface of the shell is coated with a white paint layer to improve the "three-proofing" capability of the shell. The two end faces of the shell are subjected to conductive oxidation treatment, which can effectively transfer static electricity to the weapon system;

[0028] (5) The spring provides a certain elastic force to the piston, and under the action of the elastic force, the pressurized oil tank can provide hydraulic oil with a certain pressure to the hydraulic pump. The spring is subjected to cadmium plating surface treatment to improve the "three-proofing" capability;

[0029] (7) The piston is provided with a ring groove for supporting the ring and the second sealing ring, which forms a sealing structure with the second sealing ring and the inner surface of the shell to ensure that the hydraulic oil does not leak. At the same time, the surface of the piston is subjected to anodizing treatment to improve the corrosion resistance and wear resistance of the piston. The support ring can guide the piston to ensure that the piston freely slides in the inner cavity of the shell without piston eccentric wear. The support ring is made of polytetrafluoroethylene, which has a small friction coefficient and can reduce the resistance between the support ring and the shell. At the same time, it can resist various corrosive media. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a sectional view of the pressurized oil tank with a pull rope sensor in a state of providing hydraulic oil to the hydraulic pump;

[0031] Figure 2 is a sectional view of the pressurized oil tank with a pull rope sensor in a state of being filled with hydraulic oil;

[0032] Figure 3 is Figure 1 a three-dimensional exploded view of the pressurized oil tank with a pull rope sensor in

[0033] In the figure: 1. pull rope sensor, 2. end cover, 3. first sealing ring, 4. shell, 5. spring, 6. screw, 7. supporting ring, 8. second sealing ring, 9. piston, 10. twelve-angle screw, 11. pull rope, 12. quick release joint, 13. cylindrical boss, 14. exhaust hole. DETAILED DESCRIPTION

[0034] The utility model will be further explained in connection with the drawings and specific embodiments, but should not be understood as the scope of the subject matter described in the utility model is limited to the following examples, without departing from the above technical thought of the utility model, all kinds of modifications, replacements and changes made according to the ordinary technical knowledge and conventional means in the art are included in the scope of the utility model.

[0035] As Figures 1 to 3 Indicated, it is the pressure tank with pull rope sensor in the embodiment, including pull rope sensor 1, end cover 2, sealing ring 3, shell 4, spring 5, screw 6, supporting ring 7, sealing ring 8 and piston 9.

[0036] The axial first end and the axial second end of the shell 4 are open, and a plurality of threaded mounting holes are arranged on the outer surfaces of the axial first end and the axial second end of the shell 4 (see Figure 3 The left end and the right end of the shell 4 each have four threaded mounting holes), the end cover 2 is connected to the threaded mounting holes on the outer surface of the axial first end of the shell 4 by the twelve-angle screw 10, and the valve block is mounted in the mounting hole at the second end of the shell 4 and is connected to the threaded mounting holes on the outer surface of the axial second end of the shell 4 by the twelve-angle screw 10. The outer surface of the shell 4 is also provided with a threaded hole with a locking steel wire sleeve for connecting with the partition on the aircraft (see Figure 3 The outer surface of the shell 4 near the axial first end has two threaded holes). The inner cavity wall surface of the shell 4 is provided with a limiting boss for preventing the piston 9 from being separated from the open axial second end of the shell 4. The axial second end of the shell 4 is also provided with an exhaust hole 14, and the oil gas in the inner cavity of the tank (shell 4) is discharged to the valve block through the exhaust hole 14 and finally discharged to the atmosphere. The surface of the shell 4 includes at least one conductive oxidation treatment layer.

[0037] The end cover 2 is located at least partly in the inner cavity of the shell 4, and the outer surface of the part is provided with a first sealing groove, and a first sealing ring 3 is installed in the first sealing groove to form a mechanical sealing structure between the end cover 2 and the shell 4, and a through hole for a pull rope is formed in the end cover 2; the pull rope sensor 1 is installed on the end face of the end cover 2 outside the shell 4 and is connected with four threaded holes on the end cover 2 through four bolts. The pull rope sensor 1 is connected with the aircraft weapon system through a cable and is used for providing a liquid level signal in the inner cavity of the shell 4; the pull rope 11 is coaxial with the shell 4, and the end of the pull rope 11 is connected with a piston 9 through a quick release joint 12 and a screw 6 with a cylindrical boss 13 on the surface after passing through the through hole for the pull rope on the end cover 2; the piston 9 is slidingly connected in the inner cavity of the shell 4, and the outer surface of the piston 9 is provided with a second sealing groove and a supporting ring groove, a second sealing ring 8 is installed in the second sealing groove, the second sealing ring 8 is a full fluorine sealing ring, the wear resistance of the sealing ring is improved, various corrosive media can be resisted, and the friction of the piston 9 is reduced. A supporting ring 7 made of polytetrafluoroethylene is installed in the supporting ring groove; a spring 5 is arranged in the inner cavity of the shell 4, and the axial first end of the spring 5 is close to the end cover 2, and the axial second end of the spring 5 is close to the piston 9. The screw 6 is inserted in the quick release joint 12 through the cylindrical boss 13 on the surface. The surface of the piston 9 includes at least one anodic oxidation layer. The surface of the spring 5 includes a chromium plating layer.

[0038] The inner surface of the shell 4, the piston 9 and the valve block form an inner cavity, and the inner cavity can ensure that a specified amount of hydraulic oil is stored. The surface of the shell 4 is sprayed with a white paint layer to improve the "three-proofing" capability of the shell 4. The two end faces of the shell 4 are subjected to conductive oxidation treatment, and can effectively transmit static electricity to the weapon system.

[0039] The spring 5 provides a certain size of elastic force for the piston 9, and under the action of the elastic force, the pressurized oil tank can provide the hydraulic pump port with hydraulic oil with pressure. The spring 5 is subjected to cadmium plating surface treatment and has "three-proofing" capability. The outer diameter of the spring 5 is consistent with the hole diameters of the inner hole of the end cover 2 and the inner hole of the piston 9, and the spring 5 only generates axial compression or elongation.

[0040] When the hydraulic pump charges oil into the shell 4, under the action of the spring 5, the inner cavity of the shell 4 stores hydraulic oil with a certain pressure, and at the same time, the pull rope sensor 1 provides the weapon system with a liquid level signal of charging oil into the inner cavity of the shell 4. When the hydraulic pump pumps oil from the pressurized oil tank, under the action of the spring 5, the pressurized oil tank provides the hydraulic pump with hydraulic oil with a certain pressure, and at the same time, provides the weapon system with a signal that the oil tank supplies oil to the pump.

[0041] The above embodiment is not used to limit the protection scope of the utility model, and any deformation, modification or equivalent replacement made on the basis of the technical scheme of the utility model should fall into the protection scope of the utility model.

Claims

1. A pressurized fuel tank with a pull cord sensor, characterized by, It comprises: a shell (4) with both axial first end and axial second end open, and the open second end includes an exhaust hole (14) and a mounting hole connected with a valve block; an end cover (2) assembled at the open axial first end of the shell (4) and at least a part of which is located in the inner cavity of the shell (4), and the outer surface of the part is provided with a first sealing groove, and a first sealing ring (3) is installed in the first sealing groove to form a mechanical sealing structure between the end cover (2) and the shell (4), and a through hole for a pull rope is also opened on the end cover (2); a pull rope sensor (1) installed on the end surface of the end cover (2) located outside the shell (4), the pull rope sensor (1) is connected with an aircraft weapon system through a cable to provide a liquid level signal in the inner cavity of the shell (4), and a pull rope (11) of the pull rope sensor (1) is coaxial with the shell (4) and the end of the pull rope (11) extends into the inner cavity of the shell (4) through the through hole for the pull rope on the end cover (2); a piston (9) slidingly connected in the inner cavity of the shell (4) and connected with the end of the pull rope (11) located in the inner cavity of the shell (4), and the outer surface of the piston (9) is provided with a second sealing groove and a support ring groove, a second sealing ring (8) is installed in the second sealing groove, and a support ring (7) for guiding the piston (9) is installed in the support ring groove; a spring (5) arranged in the inner cavity of the shell (4), and the axial first end of the spring (5) is close to the end cover (2), and the axial second end of the spring (5) is close to the piston (9).

2. The pressurized oil tank with a pull rope sensor according to claim 1, characterized in that: a plurality of threaded mounting holes are respectively arranged on the outer surfaces of the axial first end and the axial second end of the shell (4); the end cover (2) is connected with the threaded mounting hole on the outer surface of the axial first end of the shell (4) through a twelve-angle screw (10).

3. A pressure tank with a pull cord sensor according to claim 1, characterized in that: a threaded hole with a locking wire sleeve is further arranged on the outer surface of the shell (4) for connecting with a partition on an aircraft.

4. The pressure tank with a pull cord sensor according to claim 1, characterized in that: a limiting boss is arranged on the inner cavity wall surface of the shell (4) to prevent the piston (9) from being separated from the open axial second end of the shell (4).

5. The pressure tank with a pull cord sensor according to claim 1, characterized in that: the surface of the shell (4) comprises at least one conductive oxidation treatment layer.

6. A pressure tank with a pull cord sensor according to claim 1, characterized in that: the pull rope sensor (1) is connected with the end cover (2) through a bolt.

7. The pressure tank with a pull cord sensor according to claim 1, characterized in that: the end of the pull rope (11) is connected with the piston (9) through a quick release joint (12) and a screw (6) with a cylindrical boss (13) in sequence, wherein the cylindrical boss (13) of the screw (6) is inserted into the quick release joint (12), and the screw (6) is threadedly connected with the piston (9).

8. The pressure tank with a pull cord sensor according to claim 1, characterized in that: the surface of the piston (9) comprises at least one anodized layer.

9. The pressure tank with a pull cord sensor according to claim 1, characterized in that: the surface of the spring (5) comprises a cadmium plating layer.

10. The pressure-fed tank with a pull cord sensor of claim 1, wherein: the end surface of the end cover (2) and the piston (9) in contact with the spring (5) has an inner hole, and the outer diameter of the spring (5) is consistent with the hole diameter of the inner hole of the end cover (2) and the inner hole of the piston (9).

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