Aircraft grounding device

Abstract

The present invention relates to the technical field of aircraft anti-static grounding devices, and specifically to an aircraft grounding device, comprising a handle and a grounding plug assembly, the grounding plug assembly comprising a grounding plug, the grounding plug comprising a large diameter section and a small diameter section; a rubber ring, which is sleeved on the small diameter section; an adjusting member, which is threadedly connected to the small diameter section, and is used to make the rubber ring expand by being squeezed when it is screwed forward, and to restore the rubber ring when it is screwed backward; a spring, which is sleeved on the small diameter section, is used to deform by being squeezed when the adjusting member is screwed forward, and to generate a reaction force on the rubber ring so that the rubber ring is elastically squeezed. Beneficial effect: Compared with hard extrusion, the expansion degree of the rubber ring has a variable margin, and the rubber ring will not be excessively expanded, thereby ensuring the service life of the rubber ring. At the same time, after long-term use, when the elasticity of the rubber ring decreases, the reaction force of the spring will further squeeze the rubber ring, ensure the deformation degree of the rubber ring, and then ensure the bonding force between the grounding plug assembly and the aircraft jack, reducing the risk of falling off.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft anti-static grounding devices, and in particular to an aircraft grounding device. Background Art

[0002] When an aircraft is flying at high altitude, static electricity is generated due to friction and static induction. After the aircraft lands, if the static electricity on the body is not effectively released, static electricity may cause fire and electric shock when the body is cleaned, fueled or repaired on the ground, endangering the safety of the aircraft and the staff. Therefore, it is necessary to use an aircraft grounding device to ground the aircraft. Existing aircraft grounding devices generally include a grounding plug. Due to long-term use, the elastic fatigue failure of the internal aircraft socket of the grounding plug causes the grounding plug to fall off easily after being plugged in, and the static electricity cannot be normally conducted. Moreover, it is easy to break when it falls to the ground and cannot be repaired, which cannot ensure the safe and normal conduction of the aircraft static electricity.

[0003] In this regard, the Chinese utility model patent with the authorization announcement number CN208353686U discloses an aircraft grounding device, including a handle and a grounding plug installed on the handle. The grounding plug is in the shape of a stepped shaft, including a large diameter section and a small diameter section. A rubber ring is sleeved on the small diameter section. There are two rubber rings and they are arranged at intervals. A clamping nut is threadedly connected on the small diameter section, and a pressure ring is arranged between the clamping nut and the rubber ring. When in use, after inserting the plug into the body interface (i.e., the aircraft socket), the compression nut is rotated to push the pressure ring to expand the rubber ring, and the expanded rubber ring is squeezed with the aircraft socket, thereby increasing the friction and achieving the purpose of preventing it from falling off.

[0004] The above-mentioned aircraft grounding device increases the friction between the plug and the aircraft socket by squeezing and expanding the rubber ring. During the squeezing and expanding process of the rubber ring, the rubber ring is squeezed hard, and its expansion degree is completely determined by the screw-in amount of the clamping nut. This is difficult to accurately control in actual operation. If you are not careful, the rubber ring will expand excessively and affect its service life. Or after long-term use, the elasticity of the rubber ring decreases, and the bonding force between the rubber ring and the aircraft socket decreases, and there is still a risk of easy falling off. Summary of the invention

[0005] The object of the present invention is to provide an aircraft grounding device to solve the problem that the rubber ring in the existing aircraft grounding device is easily expanded due to hard extrusion, which affects the service life, and the engagement force between the rubber ring and the aircraft socket decreases after long-term use.

[0006] To achieve the above-mentioned purpose, the aircraft grounding device in the present invention adopts the following technical solutions:

[0007] An aircraft grounding device comprises a handle and a grounding plug assembly mounted on the handle, wherein the grounding plug assembly comprises:

[0008] The grounding plug is in the shape of a stepped shaft, including a large diameter section and a small diameter section, and a step surface is provided between the large diameter section and the small diameter section;

[0009] The rubber ring is mounted on the small diameter section;

[0010] The adjusting member is threadedly connected to the small diameter section, and the large diameter section is defined to be located in front of the small diameter section. The adjusting member is used to squeeze and expand the rubber ring when it is screwed forward, and to restore the rubber ring when it is screwed backward;

[0011] The grounding plug assembly also includes:

[0012] The spring is sleeved on the small diameter section and located at the front side of the adjusting member. The spring is used for being squeezed and deformed when the adjusting member is rotated forward, and generating a reaction force on the rubber ring so that the rubber ring is elastically squeezed.

[0013] The beneficial effect of the above technical solution is that: since a spring is sleeved on the small diameter section and the spring is located on the front side of the adjusting member, the spring can be squeezed and deformed when the adjusting member is screwed forward, thereby generating a reaction force on the rubber ring so that the rubber ring is elastically squeezed. Compared with hard squeezing, the expansion degree of the rubber ring has a variable margin, and even if the adjusting member is screwed forward more, the rubber ring will not be excessively expanded, thereby ensuring the service life of the rubber ring. At the same time, after long-term use, when the elasticity of the rubber ring decreases, the reaction force of the spring will further squeeze the rubber ring to ensure the deformation degree of the rubber ring, thereby ensuring the bonding force between the grounding plug assembly and the aircraft jack, and reducing the risk of falling off.

[0014] Furthermore, in order to facilitate the pressing and deformation of the spring and prevent the spring from damaging other components, a retaining ring is sleeved on the small diameter section, and the spring clip is arranged between the retaining ring and the adjusting member.

[0015] Furthermore, in order to protect the rubber ring, a supporting ring is sleeved between the rubber ring and the retaining ring, and between the rubber ring and the step surface on the small diameter section, and the supporting ring is a rubber ring.

[0016] Furthermore, in order to ensure the friction between the grounding plug assembly and the aircraft socket, improve the joint force of the plug-in, and facilitate the deformation of the rubber ring, there are at least two rubber rings, and a gasket is provided between two adjacent rubber rings on the small diameter section.

[0017] Furthermore, in order to ensure the elastic force and reduce the axial length of the grounding plug, the spring is a wave spring.

[0018] Furthermore, in order to facilitate the processing and manufacturing of the adjusting member and the screwing operation, the adjusting member is an adjusting sleeve, the inner hole of the adjusting sleeve is a threaded hole, and knurling is arranged on the outer peripheral surface of the adjusting sleeve.

[0019] Furthermore, in order to prevent the grounding plug assembly from falling off, an annular recess is provided on the outer peripheral surface of the front end of the large diameter section, and the annular recess is used to contact the boss in the aircraft socket.

[0020] Furthermore, in order to facilitate the deformation of the front end of the large diameter section, an axial split groove extending axially along the large diameter section is provided at the front end of the large diameter section, and the positions of the axial split groove and the annular recess correspond to facilitate the deformation of the front end of the large diameter section.

[0021] Furthermore, in order to facilitate use and prevent the grounding plug assembly from being damaged when not in use, a rotating block is installed in the handle, and the rear end of the small diameter section is fixedly connected to the rotating block. The rotating block is installed on the handle through a folding mechanism so that the grounding plug assembly can be popped out of the handle or retracted into the handle through the rotating block.

[0022] Furthermore, in order to facilitate the replacement of parts on the grounding plug assembly, the rear end of the small diameter section is threadedly connected to the rotating block. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is an appearance diagram of the aircraft grounding device of the present invention;

[0024] Figure 2 An exploded view of the aircraft grounding device of the present invention;

[0025] Figure 3 An exploded view of a grounding plug assembly, a rotating block and a folding mechanism of the aircraft grounding device of the present invention;

[0026] Figure 4 for Figure 2 and Figure 3 The inner structure diagram of the middle and upper shell;

[0027] Figure 5 for Figure 2 and Figure 3 The matching structure diagram of the middle and lower housing, the rotating block, the torsion spring and the button;

[0028] Figure 6 for Figure 2 and Figure 5 The structural diagram of the torsion spring;

[0029] Figure 7 A top view of a rotating block of an aircraft grounding device in the present invention;

[0030] Figure 8 A bottom view of the rotating block of the aircraft grounding device of the present invention;

[0031] Fig. 9 for Figure 1~Figure 3 A cross-sectional view of the cooperation between the middle ground plug assembly and the rotating block and folding mechanism (the ground plug assembly is in the state of ejecting the handle);

[0032] Fig.10 for Figure 1~Figure 3 Cross-sectional view of the cooperation between the grounding plug assembly, the rotating block and the folding mechanism (the grounding plug assembly is in the state of being retracted into the handle).

[0033] In the figure: 100-lower handle; 200-upper handle; 300-lower shell; 301-first positioning column; 302-second positioning column; 303-first positioning hole; 304-second positioning hole; 305-lower semicircular groove; 306-first arc-shaped platform; 307-third positioning column; 308-lower guide groove; 400-upper shell; 401-third positioning hole; 402-fourth positioning hole; 403-perforation; 404-second arc-shaped platform; 405-third arc-shaped platform; 406-fourth arc-shaped platform; 407-upper guide groove; 408-upper semicircular groove; 500-rotating block; 501-jack; 502-boss; 503-first through groove; 50 4-second through slot; 505-first blind slot; 506-second blind slot; 507-guide post hole; 508-guide post; 600-button; 601-pressing portion; 602-barrel portion; 603-first boss; 604-second boss; 605-third boss; 606-fourth boss; 700-grounding plug assembly; 701-grounding plug; 7011-annular recess; 7012-axial split groove; 702-supporting ring; 703-rubber ring; 704-washer; 705-retaining ring; 706-wave spring; 707-adjusting sleeve; 800-bolt; 900-torsion spring; 901-tangential extension section; 902-radial extension section. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical scheme and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention, that is, the embodiments described are only part of the embodiments of the present invention, rather than all of the embodiments. The components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0035] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present invention.

[0036] It should be noted that relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0037] The features and performance of the present invention are further described in detail below in conjunction with the embodiments.

[0038] An embodiment of the aircraft grounding device of the present invention is as follows Figure 1 As shown, the invention comprises a handle and a grounding plug assembly 700 mounted on the handle, combined with Figure 2 As shown, the handle includes an upper handle 200 and a lower handle 100, and the upper and lower handles are fixedly connected together by bolts 800. A rotating block 500 is installed between the upper handle 200 and the lower handle 100, and the grounding plug assembly 700 is fixedly connected to the rotating block 500. The rotating block 500 is installed between the upper handle 200 and the lower handle 100 through a folding mechanism, so that the grounding plug assembly 700 can be ejected from the handle or retracted into the handle through the rotating block 500.

[0039] like Figure 2 , Figure 3 , Fig. 9 As shown, the grounding plug assembly 700 includes a grounding plug 701, a supporting ring 702, a rubber ring 703, a washer 704, a retaining ring 705, a wave spring 706 and an adjusting sleeve 707. The grounding plug 701 is in the shape of a stepped shaft, including a large diameter section and a small diameter section. The large diameter section is located at the front side of the small diameter section. There is a step surface between the large diameter section and the small diameter section. The rear part of the small diameter section is processed with a threaded section. The rear end of the small diameter section is threadedly connected with the rotating block 500, which is convenient for replacing damaged parts in the grounding plug assembly. An annular recess 7011 is provided on the outer peripheral surface of the front end of the large diameter section. The annular recess 7011 is used to contact the boss in the aircraft jack to prevent the grounding plug assembly 700 from falling off. To facilitate the deformation of the front end of the large diameter section, the front end of the large diameter section is provided with an axial split groove 7012 extending along the axial direction of the large diameter section. The positions of the axial split groove 7012 and the annular recess 7011 correspond to each other.

[0040] The rubber ring 703 is sleeved on the small diameter section of the grounding plug 701. There are two rubber rings 703 in this embodiment. A gasket 704 is sleeved between two adjacent rubber rings 703 on the small diameter section. The gasket 704 is made of metal to ensure that there is a certain distance between the two rubber rings 703 and facilitate the deformation of the two rubber rings 703.

[0041] The retaining ring 705 and the wave spring 706 are both sleeved on the small diameter section. The wave spring 706 has a large elastic force and can reduce the axial length of the grounding plug 701. The adjusting sleeve 707 is threadedly connected to the small diameter section. The inner hole of the adjusting sleeve 707 is a threaded hole. The outer peripheral surface of the adjusting sleeve 707 is provided with knurling to facilitate the screwing operation. The adjusting sleeve 707 and the retaining ring 705 are both made of metal. The wave spring 706 is sandwiched between the retaining ring 705 and the adjusting sleeve 707 to facilitate the top pressure and deformation of the wave spring 706 and prevent the wave spring 706 from damaging other parts. On the small diameter section, a supporting ring 702 is sleeved between the retaining ring 705 and the rubber ring 703 on the rear side, and between the step surface and the rubber ring 703 on the front side. The supporting ring 702 is a rubber ring that can protect the rubber ring 703.

[0042] When in use, by screwing the adjusting sleeve 707 forward, the wave spring 706 and the rubber ring 703 on the front side can be squeezed and deformed, and the wave spring 706 generates a reaction force on the rubber ring 703, so that the rubber ring 703 is elastically squeezed and expanded. When the adjusting sleeve 707 is screwed backward, the wave spring 706 and the rubber ring 703 can be restored, so the adjusting sleeve 707 plays the role of an adjusting member.

[0043] like Figure 1 , Figure 2 and Figure 3 As shown, the folding mechanism includes an upper shell 400, a lower shell 300, a button 600 and a torsion spring 900. The upper shell 400 and the lower shell 300 are positioned and matched by a first positioning column 301 and a second positioning column 302. The upper shell 400 and the lower shell 300 are fixedly clamped between the upper handle 200 and the lower handle 100, and the rotating block 500 is rotatably installed between the upper shell 400 and the lower shell 300.

[0044] The structure of the rotating block 500 is as follows: Figure 5 , Figure 7 and Figure 8 As shown, the rotating block 500 is provided with a socket 501 for inserting the torsion spring 900, and a boss 502 is provided on the hole wall of the socket 501. The upper and lower ends of the boss 502 are a certain distance away from the upper and lower end surfaces of the rotating block 500, that is, the upper and lower ends of the boss 502 do not extend to the upper and lower end surfaces of the rotating block 500. The boss 502 is provided with a first through slot 503 and a second through slot 504 that penetrate up and down, as shown in FIG. Figure 7As shown, the first through groove 503 and the second through groove 504 are equivalent to dividing the boss 502 into two sections, and the angle between the first through groove 503 and the second through groove 504 is 120 degrees.

[0045] like Figure 8 As shown, a first blind groove 505 and a second blind groove 506 are provided on the other side of the boss 502. The two blind grooves are in the same radial direction, and the angle between the first blind groove 505 and the first through groove 503 and the angle between the first blind groove 505 and the second through groove 504 are both 60 degrees. In addition, a guide post hole 507 is also provided on the rotating block 500, and a guide post 508 is installed in the guide post hole 507. Fig. 9 shown.

[0046] The structure of the button 600 is as follows: Figure 3 and Figure 5 As shown, it includes a pressing portion 601 and a cylindrical portion 602 that are threadedly connected together. Two relatively long first bosses 603 and second bosses 604 are arranged on the outer circumference of the cylindrical portion 602. The length and width of the two bosses are equal and the angle between them is 120 degrees. They are just installed in the first through groove 503 and the second through groove 504 on the rotating block 500. Specifically, the first boss 603 is located in the first through groove 503, and the second boss 604 is located in the second through groove 504.

[0047] Two relatively short third protrusions 605 and fourth protrusions 606 are also provided on the outer circumference of the barrel portion 602. The two protrusions are unequal in length but are located in the radial direction of the barrel portion 602. The angles between the third protrusion 605 and the first protrusion 603 and the second protrusion 604 are all 60 degrees. After installation, the third protrusion 605 is located in the first blind groove 505, and the second protrusion 604 is located in the second blind groove 506, which can prevent the button 600 from escaping upward from the rotating block 500.

[0048] The structure of the lower housing 300 is as follows Figure 3 As shown, the lower shell 300 is provided with a first positioning hole 303 for the first positioning column 301 to pass through, and a second positioning hole 304 for the second positioning column 302 to pass through, and one end of the lower shell 300 is provided with a lower semicircular groove 305, and the second positioning hole 304 is opened on the groove wall of the lower semicircular groove 305. The lower shell 300 is provided with a receiving groove for accommodating half of the rotating block 500, and the first arc-shaped platform 306 and the third positioning column 307 are arranged in the receiving groove. After assembly, the first arc-shaped platform 306 and the third positioning column 307 are located in the insertion hole 501 of the rotating block 500.

[0049] The structure of the torsion spring 900 is as follows: Figure 5 and Figure 6As shown, a tangential extension section 901 is provided at one end of the torsion spring 900, and a radial extension section 902 is provided at the other end. One end of the torsion spring 900 is sleeved outside the third positioning column 307, and the tangential extension section 901 is clamped on the first arc-shaped platform 306 to fix this end of the torsion spring 900. Figure 5 As shown, the pressing portion 601 of the button 600 is stepped, and a split groove is provided on the smallest diameter section thereof. The small diameter section is inserted into the torsion spring 900 , and the split groove just clamps the radial extension section 902 to fix this end of the torsion spring 900 .

[0050] The structure of the upper housing 400 is as follows Figure 3 and Figure 4 As shown, the upper shell 400 and the lower shell 300 are arranged symmetrically, and their structures are substantially the same. The upper shell 400 is provided with a third positioning hole 401 corresponding to the first positioning hole 303 for the first positioning column 301 to pass through, and a fourth positioning hole 402 corresponding to the second positioning hole 304 for the second positioning column 302 to pass through. An upper semicircular groove 408 is provided at one end of the upper shell 400, and the fourth positioning hole 402 is opened on the groove wall of the upper semicircular groove 408. The upper semicircular groove 408 and the lower semicircular groove 305 are matched to form a complete circular hole, which is used to connect the connector of the grounding wire.

[0051] like Figure 4 As shown, the upper shell 400 is provided with a receiving groove for accommodating the other half of the rotating block 500, and the receiving groove is provided with a second arc platform 404, a third arc platform 405, and a fourth arc platform 406. The lengths of the three arc platforms are different, and they are located on the same circumference and arranged at intervals. The intervals between the second arc platform 404 and the third arc platform 405, and the intervals between the third arc platform 405 and the fourth arc platform 406 are equal and relatively small, and the angle between the two intervals is 150 degrees, and the width of each interval is equal to the width of the first convex column 603 or the second convex column 604. The interval between the second arc platform 404 and the fourth arc platform 406 is relatively large.

[0052] The upper shell 400 is provided with a through hole 403, and three arc-shaped stages are provided at the opening of the through hole 403. The through hole 403 allows the barrel portion 602 of the button 600 to pass through. The button 600 is provided to include the pressing portion 601 and the barrel portion 602 for the convenience of installation of the button 600. During installation, the barrel portion 602 can first pass through the through hole 403 from the inner side of the upper shell 400, and then be threadedly connected with the pressing portion 601.

[0053] After the folding mechanism, the rotating block 500 and the grounding plug assembly 700 are assembled, the grounding plug assembly 700 has two states, such as Fig. 9 The state of the eject handle shown and Fig.10In both states, the ground plug assembly 700 is in the locked position.

[0054] Combination Figure 4 , Figure 7 , Figure 8 and Fig. 9 As shown, when the grounding plug assembly 700 is in the state of ejecting the handle, a portion of the first protrusion 603 is located in the first through groove 503, and another portion is located in the larger gap between the second curved platform 404 and the fourth curved platform 406; a portion of the second protrusion 604 is located in the second through groove 504, and another portion is just stuck in the gap formed by the second curved platform 404 and the third curved platform 405, so the rotating block 500 cannot rotate, and the grounding plug assembly 700 is in a locked position.

[0055] When the button 600 is pressed, the torsion spring 900 is axially deformed, and the first protrusion 603 stuck between the second arc-shaped platform 404 and the third arc-shaped platform 405 is pushed out and separated from the arc-shaped platform on the upper shell 400. At this time, the rotating block 500 is unlocked, and the grounding plug assembly 700 can be manually rotated counterclockwise, so that the rotating block 500 rotates counterclockwise 90 degrees. Fig.10 As shown, the torsion spring 900 is deformed circumferentially during this process. Then the button 600 is released, and under the axial elastic force of the torsion spring 900, the button 600 rebounds, and a portion of the first protrusion 603 is just stuck in the gap formed by the third arc-shaped platform 405 and the fourth arc-shaped platform 406, so that the rotating block 500 cannot rotate again, and the grounding plug assembly 700 is in a locked position.

[0056] Of course, when the grounding plug assembly 700 needs to be ejected, the button 600 is pressed again to disengage the first protrusion 603 from the arc-shaped platform on the upper shell 400 . At this time, under the circumferential elastic force of the torsion spring 900 , the grounding plug assembly 700 can be automatically ejected.

[0057] In the process of ejecting and retracting the ground plug assembly 700, in order to limit the rotational travel of the rotating block 500, the corresponding protrusions on the rotating block 500 can be accurately stuck in the corresponding intervals on the upper shell 400 to achieve locking, such as Figure 4 As shown, an upper guide groove 407 is provided on the inner side of the upper shell 400. Figure 3 As shown, a lower guide groove 308 is provided on the inner side surface of the lower shell 300, and both the upper guide groove 407 and the lower guide groove 308 are arc grooves arranged around the rotation center of the rotating block 500, and the two are combined to form a complete guide groove, and the guide column 508 on the rotating block is confined in the guide groove.

[0058] The present invention provides a folding mechanism so that the grounding plug assembly 700 has the functions of ejection and retraction. When retracting, the grounding plug assembly 700 can be prevented from accidental damage and the service life can be improved. When ejected, the aircraft can be grounded. Among them, the grounding plug 701, the upper shell 400, the lower shell 300, the rotating block 500, the first positioning column 301 and the second positioning column 302 are all beryllium bronze, which has high conductivity and high elasticity. The upper handle 200 and the lower handle 100 are made of insulating materials, which are convenient for manual operation and avoid direct manual contact with static electricity.

[0059] When in use, the grounding plug assembly 700 is connected to the aircraft fuselage socket, and the static electricity on the fuselage is guided to the ground through the grounding plug, and then through the ground grounding wire connected in the upper handle and the lower handle, through the grounding clamp. After connecting to the aircraft socket, the adjustment sleeve 707 is screwed forward, and the rubber ring 703 is squeezed through the interaction of the adjustment sleeve 707 and the wave spring 706, so that the rubber ring 703 is squeezed and expanded, and the outer diameter is increased, and it fits tightly with the inner wall of the aircraft socket, increasing the contact area and improving the friction force, so as to prevent the grounding plug from accidentally falling off due to the pulling of the grounding wire or the swing caused by natural factors during use, causing a short circuit caused by static electricity release. After use, the adjustment sleeve 707 is screwed backward to restore the rubber ring 703, so that the grounding plug assembly 700 can be easily pulled out of the aircraft socket.

[0060] The grounding plug assembly of the present invention is provided with a wave spring, so that the rubber ring is elastically squeezed. Compared with hard squeezing, the expansion degree of the rubber ring has a variable margin, and even if the adjustment sleeve is screwed forward more, the rubber ring will not be excessively expanded, thereby ensuring the service life of the rubber ring. At the same time, after long-term use, when the elasticity of the rubber ring decreases, the reaction force of the wave spring will further squeeze the rubber ring, ensuring the deformation degree of the rubber ring, and then ensuring the bonding force between the grounding plug assembly and the aircraft jack, reducing the risk of falling off.

[0061] In other embodiments of the aircraft grounding device, after the rear end of the small diameter section is threadedly connected to the rotating block, sealant may be applied to fix it; or the rear end of the small diameter section may be directly welded to the rotating block.

[0062] In other embodiments of the aircraft grounding device, the grounding plug assembly may not have the folding function, and in this case the grounding plug assembly can be directly installed on the handle.

[0063] In other embodiments of the aircraft grounding device, the front end of the large-diameter section of the grounding plug may not be provided with an axial split groove.

[0064] In other embodiments of the aircraft grounding device, the front end of the large-diameter section of the grounding plug may not be provided with the annular recess.

[0065] In other embodiments of the aircraft grounding device, the adjusting member may also be a nut.

[0066] In other embodiments of the aircraft grounding device, the spring may also be a cylindrical coil spring.

[0067] In other embodiments of the aircraft grounding device, three or more rubber rings may be provided as required, or only one rubber ring may be provided.

[0068] In other embodiments of the aircraft grounding device, the support ring may not be provided, and the rubber ring directly abuts against the step surface or the retaining ring.

[0069] In other embodiments of the aircraft grounding device, the retaining ring may not be provided, and the spring directly abuts against the rubber ring without affecting the deformation of the rubber ring.

[0070] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. The patent protection scope of the present invention shall be based on the claims. All equivalent structural changes made using the contents of the description and drawings of the present invention should also be included in the protection scope of the present invention.

Claims

1. An aircraft grounding device, comprising a handle and a grounding plug assembly mounted on the handle, the grounding plug assembly comprising: The grounding plug is in the shape of a stepped shaft, including a large diameter section and a small diameter section, and a step surface is provided between the large diameter section and the small diameter section; The rubber ring is mounted on the small diameter section; The adjusting member is threadedly connected to the small diameter section, and the large diameter section is defined to be located in front of the small diameter section. The adjusting member is used to squeeze and expand the rubber ring when it is screwed forward, and to restore the rubber ring when it is screwed backward; Characterized in that the grounding plug assembly also includes: The spring is sleeved on the small diameter section and located on the front side of the adjusting member. The spring is used to be squeezed and deformed when the adjusting member is rotated forward, and to generate a reaction force on the rubber ring so that the rubber ring is elastically squeezed; a retaining ring is sleeved on the small diameter section, and the spring is clamped between the retaining ring and the adjusting member; the retaining ring is made of metal.

2. The aircraft grounding device according to claim 1, characterized in that: A supporting ring is sleeved between the rubber ring and the retaining ring, and between the rubber ring and the step surface on the small diameter section, and the supporting ring is a rubber ring.

3. The aircraft grounding device according to claim 1 or 2, characterized in that: There are at least two rubber rings, and a gasket is sleeved between two adjacent rubber rings on the small diameter section.

4. The aircraft grounding device according to claim 1 or 2, characterized in that: The spring is a wave spring.

5. The aircraft grounding device according to claim 1 or 2, characterized in that: The adjusting member is an adjusting sleeve, the inner hole of the adjusting sleeve is a threaded hole, and knurling is arranged on the outer peripheral surface of the adjusting sleeve.

6. The aircraft grounding device according to claim 1 or 2, characterized in that: An annular recess is arranged on the outer peripheral surface of the front end of the large diameter section, and the annular recess is used to contact with the boss in the aircraft plug hole.

7. The aircraft grounding device according to claim 6, characterized in that: The front end of the large diameter section is provided with an axial splitting groove extending along the axial direction of the large diameter section, and the positions of the axial splitting groove and the annular recess correspond to each other to facilitate the deformation of the front end of the large diameter section.

8. The aircraft grounding device according to claim 1 or 2, characterized in that: A rotating block is installed in the handle, and the rear end of the small diameter section is fixedly connected to the rotating block. The rotating block is installed on the handle through a folding mechanism so that the grounding plug assembly can be ejected from the handle or retracted into the handle through the rotating block.

9. The aircraft grounding device according to claim 8, characterized in that: The rear end of the small diameter section is threadedly connected with the rotating block.

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