Airplane pneumatic electromagnetic valve sealing structure and machining method thereof

Abstract

The invention relates to the field of valve sealing structures, and particularly discloses an aircraft pneumatic electromagnetic valve sealing structure and a machining method thereof.The aircraft pneumatic electromagnetic valve sealing structure comprises a sealing structure body, a side wall groove is formed in one end of the sealing structure body, and the sealing structure body comprises any one of a first sealing structure and a second sealing structure; according to the first sealing structure, a plurality of annular bionic grooves which are arranged up and down are formed in the inner circumferential face of the side wall groove, and a plurality of concentrically-distributed annular bionic grooves are formed in the bottom end face of the side wall groove. According to the second sealing structure, a plurality of linear bionic grooves which are distributed in a circumferential array mode are formed in the inner circumferential face of the side wall groove, and a plurality of divergently-distributed linear bionic grooves are formed in the bottom end face of the side wall groove. According to the method, the micro-nano bionic sealing structure is machined on the electromagnetic valve sealing surface through the femtosecond laser micro-nano machining technology, the roughness consistency and the bonding strength of the rubber bonding surface of the pneumatic sealing element are improved, the sealing performance of the pneumatic element is guaranteed, and the reliability of an airplane emergency control system is guaranteed.

Description

TECHNICAL FIELD

[0001] The application relates to a valve sealing structure, in particular to an aircraft pneumatic electromagnetic valve sealing structure and a processing method thereof, and belongs to the field of valve sealing structures. BACKGROUND

[0002] An emergency control system of an aircraft is a key component for ensuring flight safety, and mainly functions to realize control of key components, such as retraction and extension of landing gears, in a pneumatic mode in the case of failure of a hydraulic system. As a core component of the emergency control system, a pneumatic sealing surface is generally sealed by injecting rubber into a specific groove of a part to realize sealing of a matching surface, and the adhesive strength of the rubber and the metal cannot be less than 4.0 MPa. Before coating the rubber, the roughness of the original metal groove is generally improved by sandblasting to improve the bonding force of the rubber. However, it is found in the process of aircraft maintenance that due to the instability of the roughening process such as sandblasting, the adhesive strength of the pneumatic sealing element is not stable enough, and meanwhile, due to the increase in the frequency of rapid climbing and descending of the aircraft in large maneuvers, the cold and hot alternation of the sealing element is intensified, resulting in partial delamination of individual pneumatic sealing elements, a decrease in sealing efficiency, and a serious threat to flight safety. There is an urgent need for new surface technology to improve the roughness and consistency of the rubber bonding surface of the pneumatic sealing element, and to improve the adhesive strength on the basis of the existing technology, so as to adapt to the reliability of the aircraft pneumatic sealing element under the new training outline.

[0003] In order to enhance the adhesive strength of the rubber and the metal of the pneumatic electromagnetic valve, and further improve the pneumatic sealing performance of the emergency control system of the aircraft, based on the non-smooth form and structural features of the inner cavity and outer cavity of an octopus sucker, a bionic functional surface suitable for the pneumatic electromagnetic valve is designed, that is, the surface of the sucker has a series of grooves and protrusions in the form of a linear or annular stripe, and by virtue of the unique characteristics of femtosecond laser ultra-short pulse width and extremely high peak intensity, the electromagnetic valve is ultra-finely processed in sub-micron or even nanometer size, so that the sealing performance of the emergency control system is effectively improved. SUMMARY

[0004] In view of the problems in the prior art, the application provides an aircraft pneumatic electromagnetic valve sealing structure and a processing method thereof. A bionic sealing structure suitable for the pneumatic electromagnetic valve is designed by using a bionic method, and the surface of the electromagnetic valve is ultra-finely processed by using femtosecond laser micro-nano processing technology. The roughness and consistency of the rubber bonding surface of the pneumatic sealing element are improved, and the adhesive strength is improved on the basis of the existing technology, so as to ensure the reliability of the aircraft pneumatic sealing element.

[0005] The purpose of the application can be achieved by the following technical solutions:

[0006] The application discloses an aircraft aerodynamic electromagnetic valve sealing structure, which comprises a sealing structure body, one end of the sealing structure body is provided with a side wall groove, and the sealing structure body comprises any one of a sealing structure one and a sealing structure two; the sealing structure one is provided with a plurality of annular bionic grooves arranged in an up-down direction on an inner circumferential surface of the side wall groove and a plurality of concentric annular bionic grooves on a bottom end surface; and the sealing structure two is provided with a plurality of one-character bionic grooves arranged in a circular array on the inner circumferential surface of the side wall groove and a plurality of one-character bionic grooves arranged in a diverging manner on the bottom end surface.

[0007] Optionally, the side wall groove comprises an inner circumferential surface and a bottom end surface.

[0008] Optionally, in the sealing structure one, the annular bionic groove on the inner circumferential surface has a width of 0.04 mm, a depth of 0.02 mm, and eight annular bionic grooves, and the longitudinal interval distance of each annular bionic groove is 2.5 mm; the annular bionic groove on the bottom end surface has a width of 0.08 mm, a depth of 0.04 mm, and five annular bionic grooves, and the axial interval distance of each annular bionic groove is 2.5 mm.

[0009] Optionally, in the sealing structure two, the one-character bionic groove on the inner circumferential surface has a width of 0.02 mm, a depth of 0.02 mm, and 28 one-character bionic grooves, and the interval of each one-character bionic groove is 1 mm; the one-character bionic groove on the bottom end surface has a width of 0.02 mm, a depth of 0.02 mm, and 28 one-character bionic grooves, and each one-character bionic groove is arranged in a circular array, and the interval of outer end points is 1 mm.

[0010] A processing method of an aircraft aerodynamic electromagnetic valve sealing structure, the processing method is used for processing the sealing structure body, and the processing method further comprises the following steps.

[0011] Based on the constructed three-dimensional structure model of the sealing structure body and a preset laser processing database, a femtosecond laser processing path and process parameters adaptive to the three-dimensional structure model are planned, and a femtosecond laser processing system processes the inside of the side wall groove in the sealing structure body according to the instructions.

[0012] Optionally, the laser processing database stores femtosecond laser processing process parameters corresponding to different material types, and any femtosecond laser processing process parameter comprises laser power, scanning speed, repetition frequency and spot overlap rate.

[0013] Optionally, the laser power of the annular bionic groove during processing is 7.73 W, the scanning speed is 10 mm / s, the repetition frequency is 50 KHz, and the spot overlap rate is 50%; the laser power of the one-character bionic groove during processing is 6.35 W, the scanning speed is 12 mm / s, the repetition frequency is 50 KHz, and the spot overlap rate is 50%.

[0014] The application has the following beneficial effects:

[0015] This invention utilizes femtosecond laser micro-nano fabrication technology to fabricate a micro-nano biomimetic sealing structure on the sealing surface of an electromagnetic valve, thereby improving the roughness consistency and bonding strength of the rubber bonding surface of the pneumatic seal, ensuring the sealing performance of the pneumatic component, and guaranteeing the reliability of the aircraft's emergency control system. Attached Figure Description

[0016] To facilitate understanding by those skilled in the art, the present invention will be further described below with reference to the accompanying drawings.

[0017] Figure 1 This is a schematic diagram of the first sealing structure of the pneumatic solenoid valve in this invention.

[0018] Figure 2 For the present invention Figure 1 Top view.

[0019] Figure 3 This is a schematic diagram of the second sealing structure of the pneumatic solenoid valve in this invention.

[0020] Figure 4 For the present invention Figure 3 Top view.

[0021] In the diagram: 1. Annular bionic groove; 2. Straight bionic groove; 3. Sealing structure body. Detailed Implementation

[0022] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] Please see Figures 1-4 As shown, an aircraft pneumatic electromagnetic valve sealing structure includes a sealing structure body 3. One end of the sealing structure body 3 is provided with a side wall groove. The sealing structure body 3 includes either a sealing structure one or a sealing structure two. The sealing structure one has a plurality of annular bionic grooves 1 arranged vertically on the inner circumferential surface of the side wall groove and a plurality of concentrically distributed annular bionic grooves 2 arranged in a circular array on the inner circumferential surface of the side wall groove and a plurality of divergently distributed linear bionic grooves 2 on the bottom end surface.

[0024] Specifically, the sidewall groove includes an inner circumferential surface and a bottom end surface.

[0025] Specifically, in the sealing structure one, the annular biomimetic groove 1 on the inner circumferential surface has a width of 0.04 mm, a depth of 0.02 mm, and eight in number, and each annular biomimetic groove 1 has a longitudinal interval distance of 2.5 mm; the annular biomimetic groove 1 on the bottom end surface has a width of 0.08 mm, a depth of 0.04 mm, and five in number, and each annular biomimetic groove 1 has an axial interval distance of 2.5 mm.

[0026] Specifically, in the sealing structure two, the one-dimensional biomimetic groove 2 on the inner circumferential surface has a width of 0.02 mm, a depth of 0.02 mm, and 28 in number, and all are vertically arranged, and each one-dimensional biomimetic groove 2 has an interval of 1 mm; the one-dimensional biomimetic groove 2 on the bottom end surface has a width of 0.02 mm, a depth of 0.02 mm, and 28 in number, and each one-dimensional biomimetic groove 2 is distributed in a circumferential array, and the outer end points have an interval of 1 mm.

[0027] The annular biomimetic groove 1 simulates the annular structure of the octopus sucker foot to improve the sealing strength based on the adsorption effect; the one-dimensional biomimetic groove 2 is a one-dimensional linear structure, simulates the micro linear structure on the octopus sucker, and improves the bonding strength. Based on the structural characteristics of the octopus sucker, the above two sealing structures are biomimetically designed.

[0028] Based on the non-smooth morphology and structural characteristics of the inner cavity and the outer cavity surface of the octopus sucker, a biomimetic functional surface suitable for the valve of a pneumatic electromagnetic valve is designed, that is, the surface of the sucker has a series of grooves and protrusions in the form of a one-dimensional or annular stripe, and by virtue of the unique characteristics of femtosecond laser ultra-short pulse width and extremely high peak value, the valve of the electromagnetic valve is ultra-finely processed on the sub-micron or even nanometer size, so that the sealing performance of the emergency control system pneumatic electromagnetic valve is effectively improved.

[0029] The sealing structure realizes the sealing of the fitting surface by coating adhesive to vulcanize and bond the rubber in the biomimetic groove, and the injection rubber is formed in the biomimetic groove.

[0030] A processing method of an aircraft pneumatic electromagnetic valve sealing structure, the processing method is used for processing the sealing structure body, and the processing method further comprises the following steps:

[0031] Based on the three-dimensional structure model of the constructed sealing structure body and the preset laser processing database, a femtosecond laser processing path and process parameters adaptive to the sealing structure body are planned, and a femtosecond laser processing system processes the inside of the side wall groove in the sealing structure body according to the instructions.

[0032] Specifically, the laser processing database stores femtosecond laser processing process parameters corresponding to different material types, and any femtosecond laser processing process parameter includes laser power, scanning speed, repetition frequency and spot overlap rate.

[0033] Specifically, the laser power when the annular biomimetic groove 1 is processed is 7.73 W, the scanning speed is 10 mm / s, the repetition frequency is 50 KHz, and the spot lap rate is 50%; the laser power when the linear biomimetic groove 2 is processed is 6.35 W, the scanning speed is 12 mm / s, the repetition frequency is 50 KHz, and the spot lap rate is 50%.

[0034] Based on the CATIA three-dimensional modeling software, a three-dimensional model of the sealing structure body is constructed, a surface micro-nano sealing structure model is constructed on the bonding interface of the sealing surface of the electromagnetic valve (a sealing structure one or a sealing structure two is constructed in the side wall groove), the three-dimensional model of the designed sealing structure body is imported into the self-developed preset path planning software, the micro-nano sealing structure on the bonding interface of the sealing surface of the electromagnetic valve is sliced, and the laser processing path required by the sealing structure is planned.

[0035] Based on the corresponding femtosecond laser process parameters, the sealing surface is subjected to surface micro-nano structure operation by using a femtosecond laser, and the machining path during the surface micro-nano structure operation is consistent with the planned laser processing path, so as to obtain the preset sealing structure. After laser micro-nano machining, the sealing structure surface is cleaned, and the difference between the size of the micro-nano structure and the target size is measured and compared, so as to ensure the accuracy of the surface micro-nano structure operation.

[0036] After the sealing structure is processed, the rubber vulcanization is bonded to the inside of the biomimetic groove by coating adhesive, the adhesive joint is installed into the side wall groove, and the adhesive performance of the adhesive joint is tested.

[0037] The preferred embodiments disclosed above are only used to help explain the present application. The preferred embodiments do not describe all the details, nor limit the application to the specific embodiments described. Obviously, many modifications and variations can be made according to the content of the present application. The present application selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can well understand and utilize the present application. The present application is limited only by the claims and their entire scope and equivalents.

Claims

1. An aircraft aerodynamic electromagnetic valve seal structure comprising a seal structure body, characterised in that, The sealing structure body is provided with a side wall groove at one end, and the sealing structure body comprises any one of a sealing structure one and a sealing structure two, the sealing structure one is provided with a plurality of annular bionic grooves arranged in an up-down direction on the inner circumferential surface of the side wall groove and a plurality of concentrically distributed annular bionic grooves on the bottom end surface, and the sealing structure two is provided with a plurality of one-character bionic grooves arranged in a circular array on the inner circumferential surface of the side wall groove and a plurality of one-character bionic grooves arranged in a diverging manner on the bottom end surface.

2. An aircraft aerodynamic electromagnetic valve seal structure according to claim 1, wherein, The side wall groove comprises an inner circumferential surface and a bottom end surface.

3. An aircraft aerodynamic electromagnetic valve seal structure as claimed in claim 2, wherein, In the sealing structure one, the annular bionic grooves on the inner circumferential surface have a width of 0.04 mm, a depth of 0.02 mm, and a number of eight, and the longitudinal interval distance of each annular bionic groove is 2.5 mm; the annular bionic grooves on the bottom end surface have a width of 0.08 mm, a depth of 0.04 mm, and a number of five, and the axial interval distance of each annular bionic groove is 2.5 mm.

4. An aircraft aerodynamic electromagnetic valve seal structure as claimed in claim 2, wherein, In the sealing structure two, the one-character bionic grooves on the inner circumferential surface have a width of 0.02 mm, a depth of 0.02 mm, and a number of 28, and the interval of each one-character bionic groove is 1 mm; the one-character bionic grooves on the bottom end surface have a width of 0.02 mm, a depth of 0.02 mm, and a number of 28, and each one-character bionic groove is arranged in a circular array, and the interval of the outer end points is 1 mm.

5. A method of machining an aircraft aerodynamic electromagnetic valve seal structure, characterized in that, The processing method is used for processing the sealing structure body of any one of claims 1-4, and the processing method further comprises the following steps: Based on the constructed three-dimensional structure model of the sealing structure body and the preset laser processing database, a femtosecond laser processing path and process parameters adaptive to the sealing structure body are planned, and a femtosecond laser processing system processes the inside of the side wall groove in the sealing structure body according to the instructions.

6. A method of processing an aircraft aerodynamic electromagnetic valve seal structure according to claim 5, characterized in that, The laser processing database stores femtosecond laser processing parameters corresponding to different material types, and any femtosecond laser processing parameter comprises laser power, scanning speed, repetition frequency, and spot overlap rate.

7. A method of processing an aircraft aerodynamic electromagnetic valve seal structure according to claim 6, characterized in that, The laser power of the annular bionic groove during processing is 7.73 W, the scanning speed is 10 mm / s, the repetition frequency is 50 KHz, and the spot overlap rate is 50%; the laser power of the one-character bionic groove during processing is 6.35 W, the scanning speed is 12 mm / s, the repetition frequency is 50 KHz, and the spot overlap rate is 50%.

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