Skin microwave focusing repairing device and method for aviation composite material

Abstract

The invention relates to the technical field of skin repairing, in particular to a skin microwave focusing repairing device and method.The skin microwave focusing repairing device comprises a plurality of ultrasonic monitoring mechanisms and a microwave focusing mechanism, a breathable mounting mechanism is mounted on the outer side of the microwave focusing mechanism, and a monitoring mounting mechanism is mounted at the front end of the breathable mounting mechanism; a plurality of ultrasonic monitoring mechanisms are mounted on the inner side of the monitoring mounting mechanism, the microwave focusing mechanism comprises a conical sleeve, and a microwave source, a waveguide tube, a second plano-convex lens and a focusing guide head are sequentially mounted on the inner side of the conical sleeve from back to front; the ultrasonic monitoring mechanism comprises a shielding sleeve, and an electric plug is installed on the inner side of the rear end of the shielding sleeve. According to the method, crack detection can be rapidly carried out on the aviation skin in a flaw detection mode through ultrasonic waves, internal rapid heating is carried out through microwave focusing to achieve repairing, ventilation and heat insulation are carried out, and overheating of the aviation skin and the repairing device is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of skin repair, and in particular to a device and method for repairing the skin of aviation composite materials using microwave focusing. Background Art

[0002] Aircraft skin refers to a dimensional component that surrounds the aircraft skeleton structure and is fixed to the skeleton with adhesives or rivets to form the aircraft's aerodynamic shape. The skin structure formed by the aircraft skin and the skeleton has a large load-bearing capacity and rigidity, but is very light in weight, and plays the role of bearing and transmitting aerodynamic loads. The aircraft skin is repaired through microwave focusing. The principle of microwave focusing is to use the specific frequency and power of microwaves to make the molecules inside the material resonate, thereby generating frictional heat and heating the material. Microwave focusing technology can be used for material processing. Compared with traditional processing methods, microwave focusing technology greatly shortens processing time and improves efficiency.

[0003] When repairing aircraft skin using microwave focusing, the heating of the aircraft skin is uneven, which can easily cause local overheating or overcooling, thereby affecting the repair effect of the aircraft skin and the stability of the repair device; therefore, it does not meet the existing needs. In this regard, we propose a microwave focusing repair device and method for aircraft composite skin. Summary of the Invention

[0004] The purpose of the present invention is to provide a microwave focusing repair device and method for the skin of aviation composite materials, so as to solve the problem raised in the above background technology that when using microwave focusing to repair aviation skin, the heating of the aviation skin is uneven, which easily causes local overheating or overcooling, thereby affecting the repair effect of the aviation skin and the stability of the repair device.

[0005] To achieve the above objectives, the present invention provides the following technical solutions: a microwave focusing repair device for aviation composite skin, comprising multiple ultrasonic monitoring mechanisms and a microwave focusing mechanism, wherein a ventilating mounting mechanism is mounted on the outside of the microwave focusing mechanism, a monitoring mounting mechanism is mounted on the front end of the ventilating mounting mechanism, and multiple ultrasonic monitoring mechanisms are mounted on the inside of the monitoring mounting mechanism, wherein the microwave focusing mechanism comprises a tapered sleeve, on the inside of which a microwave source, a waveguide, a second plano-convex lens, and a focusing guide head are mounted in sequence from back to front;

[0006] The ultrasonic monitoring mechanism includes a shielding sleeve, an electrical plug is installed on the inner side of the rear end of the shielding sleeve, an ultrasonic generating head is installed on the front end face of the electrical plug, a first plano-convex lens is installed in front of the ultrasonic generating head, a second positioning sleeve is installed on the outer side of the first plano-convex lens, a first positioning sleeve is installed on the outer side of the rear end of the second positioning sleeve, a plurality of ultrasonic receiving heads are installed on the inner side of the front end of the second positioning sleeve, and a transparent sealing plate is installed on the front end of the second positioning sleeve.

[0007] Preferably, the microwave focusing mechanism further includes a breathable positioning ring slidably connected to the rear end of the conical sleeve, an isolation positioning plate is fixedly mounted on the front end of the conical sleeve, and a plurality of circumferentially arranged heat conducting plates are fixedly mounted on the outer side of the middle portion of the conical sleeve.

[0008] Preferably, the breathable mounting mechanism includes a mounting box, a breathable disk is fixedly mounted on the rear end face of the mounting box, a fan box is fixedly mounted on the inner side of the mounting box, a first conical cover is fixedly mounted on the inner side of the front end of the mounting box, a handle frame is mounted on the outer side of the middle part of the first conical cover, a locking knob is mounted on the upper end of the handle frame, a power supply cable is mounted on the inner side of the bottom end of the handle frame, and the first conical cover is connected to the conical sleeve through a plurality of limit units.

[0009] Preferably, the plurality of limiting units are arranged in a circle relative to the axis of the first conical cover, and the limiting unit includes a mounting sleeve, a sealing piece is fixedly installed at one end of the mounting sleeve, a support spring is provided on the inner side of the mounting sleeve, and a clamping column is installed on the inner side of the support spring, the first conical cover and the plurality of mounting sleeves are connected by threads, the clamping column is slidably connected to the mounting sleeve and the sealing piece, the clamping column is connected to the mounting sleeve through the support spring, the surface of the conical sleeve is provided with a plurality of protrusions, and the clamping column and the conical sleeve are clamped and installed through the protrusions.

[0010] Preferably, the monitoring installation mechanism includes a second conical cover, the front end of the second conical cover is rollingly connected to a plurality of supporting balls, the inner side of the rear end of the second conical cover is fixedly installed with a shielding cover, the outer side of the rear end of the second conical cover is fixedly installed with a power ring, the front end surface of the power ring is installed with a plurality of conductive sleeves, the rear end of the second conical cover is threadedly connected to the first conical cover, the plurality of supporting balls and conductive sleeves are circumferentially arranged relative to the axis of the second conical cover, the power ring is made of insulating plastic, and the power ring is threadedly connected to the plurality of conductive sleeves.

[0011] Preferably, the first conical cover is fixedly connected to the air-permeable positioning ring, an air-guiding gap is provided between the first conical cover and the conical sleeve, the mounting box and the shielding cover are connected through the air-guiding gap, the bottom end of the locking knob passes through the upper end of the handle frame and is threadedly connected to the first conical cover, and the upper end of the handle frame and the first conical cover are locked and installed by the locking knob.

[0012] Preferably, the upper end of the power supply cable passes through the handle frame and the first conical cover and is electrically connected to the fan box, multiple conductive sleeves and the microwave source. The front end face of the power ring is in contact with multiple shielding sleeves. The rear end of the power plug passes through the shielding sleeve and is plugged into the conductive sleeve. The conductive sleeve is connected to the ultrasonic generator head through the power plug.

[0013] Preferably, the second conical cover is connected to multiple shielding sleeves through threads, the shielding sleeve is connected to the ultrasonic generator head through a first positioning sleeve, the first plano-convex lens is arranged between the first positioning sleeve and the second positioning sleeve, the second positioning sleeve is connected to the shielding sleeve through threads, and the multiple ultrasonic receiving heads are arranged circumferentially relative to the axis of the shielding sleeve, and the ultrasonic generator head, the first plano-convex lens and the second positioning sleeve are coaxial.

[0014] Preferably, the microwave source, waveguide tube and second plano-convex lens are all fixedly connected to the conical sleeve, the front end of the conical sleeve is fixedly connected to the focusing guide head through an isolation positioning plate, the microwave source, waveguide tube, second plano-convex lens and focusing guide head are coaxial, and the installation direction of the second plano-convex lens is opposite to that of the first plano-convex lens.

[0015] A method for using a microwave focused repair device for an aviation composite material skin comprises the following steps:

[0016] S1: The upper end of the power supply cable is passed through the handle frame and the mounting box and electrically connected to the fan box, multiple conductive sleeves, and the microwave source. The power is turned on. The user grasps the handle frame to pick up the entire device. The conical sleeve is inserted into the inner side of the first conical cover so that the air-permeable positioning ring is inserted into the conical sleeve for positioning. At the same time, multiple limiting units clamp the conical sleeve.

[0017] S2: Specifically, the clamping post is connected to the mounting sleeve via a support spring, so that the clamping post can automatically slide and clamp with the conical sleeve under the elastic support of the support spring, thereby facilitating the rapid installation of the microwave focusing mechanism. A plurality of circumferentially arranged support balls are rollingly connected to the front end of the second conical cover, so that the second conical cover contacts the surface of the aircraft skin via the plurality of support balls. The support balls facilitate the sliding of the second conical cover in any direction on the surface of the aircraft skin.

[0018] S3: Connecting multiple shielding sleeves to the second conical cover through threads, so that the shielding sleeves drive the power plug to be plugged into the inner side of the conductive sleeve, thereby facilitating the connection of the ultrasonic generator head to electricity. Ultrasonic waves are emitted by the ultrasonic generator heads in the multiple circumferentially arranged shielding sleeves and the reflected ultrasonic waves are received by the ultrasonic receiving head, thereby enabling all-round ultrasonic detection of the surface of the aircraft skin, thereby facilitating flaw detection operations inside the aircraft skin;

[0019] S4: The ultrasonic wave emitted by the ultrasonic generator can be refracted by the first plano-convex lens, thereby facilitating the maintenance of the ultrasonic wave being perpendicular to the surface of the aircraft skin. When a crack exists inside the aircraft skin, microwaves are emitted by the microwave source and converted into plane waves through the waveguide. The microwaves are then focused into the focusing guide head through the second plano-convex lens. The focusing guide head, supported by the isolation positioning plate, can irradiate the focused microwaves onto the crack inside the aircraft skin, thereby achieving local heating and repair operations on the cracked area.

[0020] S5: An air guide gap is provided between the first conical cover and the conical sleeve, so that the installation box and the shielding cover are connected through the air guide gap, and the external air is extracted through the fan box and transported to the surface of the aviation skin through the air guide gap and the shielding cover, thereby effectively isolating the aviation skin in a heated state from multiple ultrasonic monitoring mechanisms and microwave focusing mechanisms, and preventing multiple ultrasonic monitoring mechanisms and microwave focusing mechanisms from being affected by high temperature.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The present invention uses a breathable positioning ring to position the tapered sleeve. The clamping post can automatically slide and clamp with the tapered sleeve under the elastic support of the support spring, thereby facilitating the rapid installation of the microwave focusing mechanism. The support ball facilitates the sliding of the second tapered cover in any direction on the surface of the aircraft skin. Ultrasonic waves are emitted by ultrasonic generators in multiple circumferentially arranged shielding sleeves and received by ultrasonic receivers. This enables all-round ultrasonic detection of the surface of the aircraft skin, facilitating flaw detection operations inside the aircraft skin.

[0023] 2. The present invention transmits microwaves through a microwave source and converts the microwaves into plane waves through a waveguide tube, and then focuses the microwaves into a focusing guide head through a second plano-convex lens. Then, the focusing guide head, supported by an isolation positioning plate, can irradiate the focused microwaves to the cracks inside the aircraft skin, thereby achieving local heating and repair operations on the cracked parts. External air is extracted through a fan box and transported to the surface of the aircraft skin through an air guide gap and a shielding cover, thereby effectively isolating the heated aircraft skin from multiple ultrasonic monitoring mechanisms and microwave focusing mechanisms, and performing internal rapid heating through microwave focusing to achieve repair, and performing ventilation and heat insulation to prevent the aircraft skin from overheating and multiple ultrasonic monitoring mechanisms and microwave focusing mechanisms from being affected by high temperature. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic structural diagram of the present invention as a whole;

[0025] Figure 2 A rear side view of the present invention as a whole;

[0026] Figure 3 Schematic diagram of the cross-sectional structure of the ventilating installation mechanism of the present invention;

[0027] Figure 4 It is a schematic cross-sectional structure diagram of the present invention as a whole;

[0028] Figure 5 For the present invention Figure 4 Schematic diagram of the cross-sectional structure of area A in the middle;

[0029] Figure 6 For the present invention Figure 4 Schematic diagram of the cross-sectional structure of area B in the middle;

[0030] Figure 7 Schematic diagram of the structure of the microwave focusing mechanism of the present invention;

[0031] Figure 8 It is a schematic cross-sectional structural diagram of the microwave focusing mechanism of the present invention.

[0032] Figure: 1. Ventilation installation mechanism; 101. Installation box; 102. Ventilation plate; 103. Handle frame; 104. Locking knob; 105. First cone cover; 106. Limiting unit; 107. Power supply cable; 108. Fan box; 109. Installation sleeve; 110. Support spring; 111. Clamping column; 112. Blocking piece; 2. Monitoring installation mechanism; 201. Second cone cover; 202. Support ball; 203. Electrical connection ring; 204. Shielding cover; 205. Conductive sleeve; 3. Ultrasonic Acoustic monitoring mechanism; 301, shielding sleeve; 302, transparent sealing plate; 303, power plug; 304, ultrasonic generating head; 305, first positioning sleeve; 306, first plano-convex lens; 307, second positioning sleeve; 308, ultrasonic receiving head; 4, microwave focusing mechanism; 401, conical sleeve; 402, breathable positioning ring; 403, heat conducting plate; 404, isolation positioning plate; 405, microwave source; 406, waveguide tube; 407, second plano-convex lens; 408, focusing guide head. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0034] See also Figures 1 to 4An embodiment of the present invention provides: a microwave focusing repair device for the skin of an aviation composite material, comprising a plurality of ultrasonic monitoring mechanisms 3 and a microwave focusing mechanism 4, a breathable mounting mechanism 1 being installed on the outside of the microwave focusing mechanism 4, the breathable mounting mechanism 1 comprising a mounting box 101, a breathable disk 102 being fixedly installed on the rear end surface of the mounting box 101, a fan box 108 being fixedly installed on the inside of the mounting box 101, a first conical cover 105 being fixedly installed on the inside of the front end of the mounting box 101, a handle frame 103 being installed on the outside of the middle part of the first conical cover 105, a locking knob 104 being installed on the upper end of the handle frame 103, the bottom end of the locking knob 104 passing through the upper end of the handle frame 103 and being threadedly connected to the first conical cover 105, the upper end of the handle frame 103 and the first conical cover 105 being locked and installed by the locking knob 104, a power supply cable 107 being installed on the inside of the bottom end of the handle frame 103, and external air is extracted through the fan box 108 to achieve overall cooling.

[0035] See also Figures 1 to 6 The front end of the breathable mounting mechanism 1 is equipped with a monitoring mounting mechanism 2, and the monitoring mounting mechanism 2 includes a second conical cover 201, and the front end of the second conical cover 201 is rollingly connected with a plurality of supporting balls 202, and a shielding cover 204 is fixedly installed on the inner side of the rear end of the second conical cover 201, and a power ring 203 is fixedly installed on the outer side of the rear end of the second conical cover 201. A plurality of conductive sleeves 205 are installed on the front end surface of the power ring 203, and the rear end of the second conical cover 201 is connected to the first conical cover 105 by a threaded connection, and the plurality of supporting balls 202 and the conductive sleeves 205 are arranged in a circle relative to the axis of the second conical cover 201, and the power ring 203 is made of insulating plastic. The power ring 203 is connected to the plurality of conductive sleeves 205 by a threaded connection, so that the second conical cover 201 is in contact with the surface of the aviation skin through the plurality of supporting balls 202, and the support balls 202 facilitate the second conical cover 201 to slide in any direction on the surface of the aviation skin.

[0036] See also Figure 1 、 Figure 2 and Figure 6 , multiple ultrasonic monitoring mechanisms 3 are installed on the inner side of the monitoring installation mechanism 2, and the ultrasonic monitoring mechanism 3 includes a shielding sleeve 301. The second conical cover 201 is connected to the multiple shielding sleeves 301 through threads. An electrical plug 303 is installed on the inner side of the rear end of the shielding sleeve 301, and an ultrasonic generator 304 is installed on the front end surface of the electrical plug 303. The front end surface of the electrical ring 203 is in contact with the multiple shielding sleeves 301, and the rear end of the electrical plug 303 passes through the shielding sleeve 301 and is plugged into the conductive sleeve 205. The conductive sleeve 205 is connected to the ultrasonic generator 304 through the electrical plug 303. The ultrasonic generator 304 emits ultrasonic waves and receives the reflected ultrasonic waves through the ultrasonic receiving head 308, thereby being able to perform all-round ultrasonic detection on the surface of the aviation skin;

[0037] A first plano-convex lens 306 is installed in front of the ultrasonic generating head 304, and a second positioning sleeve 307 is installed on the outside of the first plano-convex lens 306. The ultrasonic generating head 304, the first plano-convex lens 306 and the second positioning sleeve 307 are coaxial, and the second positioning sleeve 307 is connected to the shielding sleeve 301 through a threaded connection. A first positioning sleeve 305 is installed on the outside of the rear end of the second positioning sleeve 307, and the shielding sleeve 301 is connected to the ultrasonic generating head 304 through the first positioning sleeve 305. The first plano-convex lens 306 is arranged between the first positioning sleeve 305 and the second positioning sleeve 307. A plurality of ultrasonic receiving heads 308 are installed on the inner side of the front end of the second positioning sleeve 307. The plurality of ultrasonic receiving heads 308 are arranged in a circle relative to the axis of the shielding sleeve 301. A transparent sealing plate 302 is installed on the front end of the second positioning sleeve 307. The ultrasonic waves emitted by the ultrasonic generating head 304 can be refracted through the first plano-convex lens 306, thereby facilitating keeping the ultrasonic waves perpendicular to the surface of the aviation skin.

[0038] See also Figure 4 、 Figure 7 and Figure 8 The microwave focusing mechanism 4 includes a conical sleeve 401, an air guide gap is provided between the first conical cover 105 and the conical sleeve 401, the installation box 101 and the shielding cover 204 are connected through the air guide gap, the rear end of the conical sleeve 401 is slidably connected with a breathable positioning ring 402, the first conical cover 105 is fixedly connected to the breathable positioning ring 402, the front end of the conical sleeve 401 is fixedly installed with an isolation positioning plate 404, and a plurality of circumferentially arranged heat conducting plates 403 are fixedly installed on the outer side of the middle part of the conical sleeve 401. The heat is transported to the surface of the aviation skin through the air guide gap and the shielding cover 204, thereby effectively isolating the aviation skin in a heated state from the multiple ultrasonic monitoring mechanisms 3 and the microwave focusing mechanism 4;

[0039] A microwave source 405, a waveguide tube 406, a second plano-convex lens 407 and a focusing guide head 408 are installed on the inner side of the conical sleeve 401 from back to front. The upper end of the power supply cable 107 passes through the handle frame 103 and the first conical cover 105 and is electrically connected to the fan box 108, multiple conductive sleeves 205 and the microwave source 405. The microwave source 405, the waveguide tube 406 and the second plano-convex lens 407 are all fixedly connected to the conical sleeve 401. The front end of the conical sleeve 401 is fixedly connected to the focusing guide head 408 through an isolation positioning plate 404. The microwave source 405, the waveguide tube 406, the second plano-convex lens 407 and the focusing guide head 408 are coaxial. The installation direction of the second plano-convex lens 407 is opposite to that of the first plano-convex lens 306. Microwaves are emitted by the microwave source 405, converted into plane waves by the waveguide tube 406, and then focused by the second plano-convex lens 407.

[0040] See also Figure 4 and Figure 5 The first conical cover 105 is connected to the conical sleeve 401 through a plurality of limiting units 106. The plurality of limiting units 106 are arranged circumferentially relative to the axis of the first conical cover 105. The limiting unit 106 includes a mounting sleeve 109. A blocking piece 112 is fixedly installed at one end of the mounting sleeve 109. A support spring 110 is provided on the inner side of the mounting sleeve 109. A clamping column 111 is installed on the inner side of the support spring 110. The first conical cover 105 and the plurality of mounting sleeves 109 are all connected. Through threaded connection, the clamping column 111 is slidably connected to the mounting sleeve 109 and the sealing piece 112. The clamping column 111 is connected to the mounting sleeve 109 through the support spring 110. The surface of the conical sleeve 401 is provided with multiple protrusions. The clamping column 111 and the conical sleeve 401 are installed by clamping the protrusions, so that the clamping column 111 can automatically slide and clamp with the conical sleeve 401 under the elastic support of the support spring 110, thereby facilitating the rapid installation of the microwave focusing mechanism 4.

[0041] A method for using a microwave focused repair device for an aviation composite material skin comprises the following steps:

[0042] S1: The upper end of the power supply cable 107 is passed through the handle frame 103 and the installation box 101 and electrically connected to the fan box 108, the multiple conductive sleeves 205 and the microwave source 405. The power is turned on. The user grasps the handle frame 103 to pick up the entire device. The conical sleeve 401 is inserted into the inner side of the first conical cover 105 so that the air-permeable positioning ring 402 positions the conical sleeve 401. At the same time, the multiple limiting units 106 clamp the conical sleeve 401.

[0043] S2: Specifically, the clamping post 111 is connected to the mounting sleeve 109 via a support spring 110, so that the clamping post 111 can automatically slide and clamp with the conical sleeve 401 under the elastic support of the support spring 110, thereby facilitating the rapid installation of the microwave focusing mechanism 4. A plurality of circumferentially arranged support balls 202 are rollingly connected to the front end of the second conical cover 201, so that the second conical cover 201 is in contact with the surface of the aviation skin via the plurality of support balls 202. The support balls 202 facilitate the second conical cover 201 to slide in any direction on the surface of the aviation skin.

[0044] S3: Connecting multiple shielding sleeves 301 to the second conical cover 201 through threads, so that the shielding sleeves 301 drive the power plug 303 to be plugged into the inner side of the conductive sleeve 205, thereby facilitating the connection of the ultrasonic generator 304 to the power supply. Ultrasonic waves are emitted by the ultrasonic generators 304 in the multiple circumferentially arranged shielding sleeves 301 and the reflected ultrasonic waves are received by the ultrasonic receiver 308, thereby enabling all-round ultrasonic detection of the surface of the aircraft skin, thereby facilitating flaw detection operations inside the aircraft skin;

[0045] S4: The ultrasonic wave emitted by the ultrasonic generator 304 can be refracted by the first plano-convex lens 306, thereby facilitating the maintenance of the ultrasonic wave being perpendicular to the surface of the aircraft skin. When a crack exists inside the aircraft skin, microwaves are emitted by the microwave source 405 and converted into plane waves through the waveguide 406. The microwaves are then focused into the focusing guide head 408 by the second plano-convex lens 407. The focusing guide head 408, supported by the isolation positioning plate 404, can irradiate the focused microwaves onto the crack inside the aircraft skin, thereby achieving local heating and repair operations on the cracked area.

[0046] S5: An air guide gap is provided between the first conical cover 105 and the conical sleeve 401, so that the installation box 101 and the shielding cover 204 are connected through the air guide gap, and the external air is extracted through the fan box 108 and transported to the surface of the aviation skin through the air guide gap and the shielding cover 204, thereby effectively isolating the aviation skin in a heated state from the multiple ultrasonic monitoring mechanisms 3 and the microwave focusing mechanisms 4, and preventing the multiple ultrasonic monitoring mechanisms 3 and the microwave focusing mechanisms 4 from being affected by high temperature.

[0047] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be included therein. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

Claims

1. A microwave focusing repair device for skin of aviation composite materials, comprising a plurality of ultrasonic monitoring mechanisms (3) and a microwave focusing mechanism (4), characterized in that: A permeable mounting mechanism (1) is installed on the outside of the microwave focusing mechanism (4), a monitoring mounting mechanism (2) is installed at the front end of the permeable mounting mechanism (1), and a plurality of ultrasonic monitoring mechanisms (3) are installed on the inside of the monitoring mounting mechanism (2). The microwave focusing mechanism (4) comprises a conical sleeve (401), and a microwave source (405), a waveguide tube (406), a second plano-convex lens (407), and a focusing guide head (408) are installed on the inside of the conical sleeve (401) in sequence from back to front. The ultrasonic monitoring mechanism (3) comprises a shielding sleeve (301), an electric plug (303) is installed on the inner side of the rear end of the shielding sleeve (301), an ultrasonic generator (304) is installed on the front end of the electric plug (303), a first plano-convex lens (306) is installed in front of the ultrasonic generator (304), a second positioning sleeve (307) is installed on the outer side of the first plano-convex lens (306), a first positioning sleeve (305) is installed on the outer side of the rear end of the second positioning sleeve (307), a plurality of ultrasonic receiving heads (308) are installed on the inner side of the front end of the second positioning sleeve (307), and a transparent blocking plate (302) is installed on the front end of the second positioning sleeve (307).

2. The microwave focused repair device for aviation composite skin according to claim 1, characterized in that: The microwave focusing mechanism (4) further comprises a breathable positioning ring (402) slidably connected to the rear end of the conical sleeve (401); an isolation positioning plate (404) is fixedly mounted on the front end of the conical sleeve (401); and a plurality of circumferentially arranged heat conducting plates (403) are fixedly mounted on the outer side of the middle portion of the conical sleeve (401).

3. The microwave focused repair device for aviation composite skin according to claim 2, characterized in that: The ventilating installation mechanism (1) comprises a mounting box (101), a ventilating plate (102) is fixedly mounted on the rear end surface of the mounting box (101), a fan box (108) is fixedly mounted on the inner side of the mounting box (101), a first conical cover (105) is fixedly mounted on the inner side of the front end of the mounting box (101), a handle frame (103) is mounted on the outer side of the middle part of the first conical cover (105), a locking knob (104) is mounted on the upper end of the handle frame (103), a power supply cable (107) is mounted on the inner side of the bottom end of the handle frame (103), and the first conical cover (105) is connected to the conical sleeve (401) via a plurality of limiting units (106).

4. The microwave focused repair device for aviation composite skin according to claim 3, characterized in that: The plurality of limiting units (106) are arranged in a circle relative to the axis of the first conical cover (105), and the limiting units (106) include a mounting sleeve (109), one end of which is fixedly mounted with a blocking piece (112), the inner side of the mounting sleeve (109) is provided with a support spring (110), the inner side of the support spring (110) is provided with a clamping column (111), the first conical cover (105) and the plurality of mounting sleeves (109) are all connected by threads, the clamping column (111) is slidably connected to the mounting sleeve (109) and the blocking piece (112), the clamping column (111) and the mounting sleeve (109) are connected by the support spring (110), the surface of the conical sleeve (401) is provided with a plurality of protrusions, and the clamping column (111) and the conical sleeve (401) are clamped and mounted by the protrusions.

5. The microwave focused repair device for aviation composite skin according to claim 4, characterized in that: The monitoring installation mechanism (2) comprises a second conical cover (201), a front end of the second conical cover (201) is rollingly connected to a plurality of supporting balls (202), a shielding cover (204) is fixedly installed on the inner side of the rear end of the second conical cover (201), a power ring (203) is fixedly installed on the outer side of the rear end of the second conical cover (201), a front end surface of the power ring (203) is installed with a plurality of conductive sleeves (205), the rear end of the second conical cover (201) is connected to the first conical cover (105) by means of threads, the plurality of supporting balls (202) and the conductive sleeves (205) are arranged in a circle relative to the axis of the second conical cover (201), the material of the power ring (203) is insulating plastic, and the power ring (203) is connected to the plurality of conductive sleeves (205) by means of threads.

6. The microwave focused repair device for aviation composite skin according to claim 5, characterized in that: The first conical cover (105) is fixedly connected to the air-permeable positioning ring (402); an air-guiding gap is provided between the first conical cover (105) and the conical sleeve (401); the installation box (101) and the shielding cover (204) are connected through the air-guiding gap; the bottom end of the locking knob (104) passes through the upper end of the handle frame (103) and is connected to the first conical cover (105) by a thread; the upper end of the handle frame (103) and the first conical cover (105) are locked and installed by the locking knob (104).

7. The microwave focused repair device for aviation composite skin according to claim 6, characterized in that: The upper end of the power supply cable (107) passes through the handle frame (103) and the first conical cover (105) and is electrically connected to the fan box (108), multiple conductive sleeves (205) and the microwave source (405); the front end surface of the power ring (203) is in contact with multiple shielding sleeves (301); the rear end of the power plug (303) passes through the shielding sleeves (301) and is plugged into and installed with the conductive sleeve (205); the conductive sleeve (205) is connected to the ultrasonic generator (304) via the power plug (303).

8. The microwave focused repair device for aviation composite material skin according to claim 7, characterized in that: The second conical cover (201) and the plurality of shielding sleeves (301) are connected by threads, the shielding sleeve (301) and the ultrasonic generating head (304) are connected by a first positioning sleeve (305), the first plano-convex lens (306) is arranged between the first positioning sleeve (305) and the second positioning sleeve (307), the second positioning sleeve (307) and the shielding sleeve (301) are connected by threads, the plurality of ultrasonic receiving heads (308) are arranged in a circle relative to the axis of the shielding sleeve (301), and the ultrasonic generating head (304), the first plano-convex lens (306) and the second positioning sleeve (307) are coaxial.

9. The microwave focused repair device for aviation composite skin according to claim 8, characterized in that: The microwave source (405), the waveguide tube (406) and the second plano-convex lens (407) are all fixedly connected to the conical sleeve (401); the front end of the conical sleeve (401) is fixedly connected to the focusing guide head (408) via an isolation positioning plate (404); the microwave source (405), the waveguide tube (406), the second plano-convex lens (407) and the focusing guide head (408) are coaxial; the second plano-convex lens (407) and the first plano-convex lens (306) are installed in opposite directions.

10. A method for using the microwave focused repair device for aviation composite skin according to any one of claims 1 to 9, characterized in that: The following steps are involved: S1: The upper end of the power supply cable (107) is passed through the handle frame (103) and the installation box (101) and electrically connected to the fan box (108), the plurality of conductive sleeves (205) and the microwave source (405). The power is turned on, and the user grasps the handle frame (103) to pick up the entire device. The conical sleeve (401) is inserted into the inner side of the first conical cover (105), so that the air-permeable positioning ring (402) is positioned on the conical sleeve (401), and the plurality of limiting units (106) are clamped on the conical sleeve (401). S2: Specifically, the clamping column (111) is connected to the mounting sleeve (109) via a support spring (110), so that the clamping column (111) can automatically slide and be clamped with the conical sleeve (401) under the elastic support of the support spring (110), thereby facilitating the rapid installation of the microwave focusing mechanism (4). A plurality of circumferentially arranged supporting balls (202) are rollingly connected to the front end of the second conical cover (201), so that the second conical cover (201) is brought into contact with the surface of the aviation skin via the plurality of supporting balls (202), and the supporting balls (202) facilitate the second conical cover (201) to slide in any direction on the surface of the aviation skin. S3: Connecting a plurality of shielding sleeves (301) to the second conical cover (201) through threads, so that the shielding sleeves (301) drive the power plug (303) to be plugged into the inner side of the conductive sleeve (205), thereby facilitating the connection of the ultrasonic generator (304) with electricity, emitting ultrasonic waves through the ultrasonic generators (304) in the plurality of circumferentially arranged shielding sleeves (301) and receiving the reflected ultrasonic waves through the ultrasonic receiving head (308), thereby enabling all-round ultrasonic detection of the surface of the aviation skin, and facilitating flaw detection operations inside the aviation skin; S4: The ultrasonic wave emitted by the ultrasonic generator (304) can be refracted by the first plano-convex lens (306), thereby facilitating the maintenance of the ultrasonic wave being perpendicular to the surface of the aircraft skin. When a crack exists inside the aircraft skin, microwaves are emitted by the microwave source (405) and converted into plane waves through the waveguide (406). The microwaves are then focused into the focusing guide head (408) through the second plano-convex lens (407). The focusing guide head (408) can then irradiate the focused microwaves onto the crack inside the aircraft skin under the support of the isolation positioning plate (404), thereby achieving local heating and repair operations on the cracked area. S5: An air guide gap is provided between the first conical cover (105) and the conical sleeve (401), so that the installation box (101) and the shielding cover (204) are connected through the air guide gap, and external air is extracted through the fan box (108) and transported to the surface of the aviation skin through the air guide gap and the shielding cover (204), thereby effectively isolating the aviation skin in a heated state from the multiple ultrasonic monitoring mechanisms (3) and the microwave focusing mechanisms (4), thereby preventing the multiple ultrasonic monitoring mechanisms (3) and the microwave focusing mechanisms (4) from being affected by high temperature.

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