Airplane grounding wire containing self-returning gear
By introducing self-returning gears and automatic rotation mechanisms into the aircraft grounding wire, the problem of manual recycling of existing grounding wires is solved, automatic winding is achieved, and operating efficiency and safety are improved.
Patent Information
- Application Number
- CN202420286779.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-02-06
- Publication Date
- 2025-02-25
- Estimated Expiration
- 2034-02-06
AI Technical Summary
The existing aircraft grounding wire needs to be manually recycled when not in use, which is cumbersome and inconvenient for operation.
An aircraft grounding wire containing a self-returning gear is designed. Through the coordination of the fixed rod, winding barrel, bearing and scroll spring, the automatic rotation of the winding barrel and the automatic winding of the wire are realized.
The automatic winding of the ground wire is realized, reducing the complexity and time of manual operation, and improving the efficiency and safety of use.
Smart Images
Figure CN222530823U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of grounding wires, in particular to an aircraft grounding wire with a self-returning gear. Background Art
[0002] The grounding wire is a wire directly connected to the earth, also known as a safety return line. It transfers high voltage directly to the earth in case of danger. Some equipment will have a certain amount of static electricity on its casing due to poor insulation performance or humid operating environment, which may cause electric shock accidents in serious cases. In order to avoid accidents, you can connect a wire to the metal casing and connect the other end of the wire to the ground. Once leakage occurs, the grounding wire will bring static electricity to the ground and release it.
[0003] When the aircraft is refueling, in order to prevent safety accidents caused by static electricity, both the aircraft and the refueling truck must be grounded using a grounding wire. Current aircraft grounding wires have a grounding clamp installed at one end of the wire and a power clamp installed at the other end. Because there is no wire reeling structure, the wire needs to be manually wound up when it is not in use, which makes recovery very troublesome.
[0004] For this purpose, we design an aircraft grounding wire with a self-returning gear. Utility Model Content
[0005] The utility model aims to provide an aircraft grounding wire with a self-returning gear to solve the problems raised in the background technology in view of the shortcomings of the prior art.
[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aircraft grounding wire containing a self-returning gear, comprising an outer shell, the outer shell is approximately cylindrical in shape and has a cavity therein, a fixed shaft is fixedly connected between the two inner side walls of the outer shell, a winding structure is rotatably installed on the fixed shaft, a self-returning gear is installed on one side of the winding structure, a lock buckle is rotatably installed on the inner side wall of the outer shell via a rotating shaft, the lock buckle is located near the self-returning gear, and the left end of the lock buckle can be against the gear teeth of the self-returning gear, a sliding groove is provided on the right side of the side wall of the lock buckle, the bottom end of the connecting rod is transmission-connected to the sliding groove of the lock buckle via a slider, a button is installed on the top of the connecting rod, a limit plate is installed in the middle of the connecting rod, the limit plate is located in the cavity, a compression spring is sleeved on the outside of the connecting rod, and the compression spring is located between the button and the outer shell.
[0007] Preferably, the winding structure includes a bearing, a conductive slip ring and a vortex spring installed on a fixed shaft, the vortex spring is located between the bearing and the conductive slip ring, a winding barrel is installed on the outside of the bearing, the conductive slip ring and the vortex spring, the inner ring of the bearing and the conductive slip ring, and the inner connecting end of the vortex spring are all fixedly installed on the fixed shaft, the outer ring of the bearing and the conductive slip ring, and the outer connecting end of the vortex spring are all fixedly installed on the inner side wall of the winding barrel, the inner ring of the bearing and the conductive slip ring can rotate on the outer ring, and the self-return gear is fixedly installed on the side of the winding barrel away from the conductive slip ring.
[0008] Preferably, the output end of the inner ring of the conductive slip ring is connected to one end of the first wire, the other end of the first wire is connected to the grounding clamp, a through hole is opened on the barrel wall of the winding barrel, one end of the second wire passes through the through hole and is connected to the input end of the outer ring of the conductive slip ring, the second wire is wound on the winding barrel, and the other end of the second wire is connected to the grounding clamp, and a through hole is opened on the side wall of the shell for the first wire and the second wire to pass through.
[0009] Preferably, the grounding clamp includes a C-shaped clamp, a threaded hole is opened on the C-shaped clamp and a threaded rod is provided, a rotating handle is installed on the top of the threaded rod, a clamp is rotatably installed on the bottom of the threaded rod, a first connecting buckle is installed at the tail of the C-shaped clamp, the first connecting buckle is connected to the first wire, and the grounding clamp is located outside the outer shell.
[0010] Preferably, the power connection clip comprises a metal conductive clip, a tail of the metal conductive clip is covered with an insulating sleeve, a second connecting buckle is installed on one side of the metal conductive clip, the second connecting buckle is connected to one end of the second wire, and the power connection clip is located outside the housing.
[0011] Preferably, the portion of the first wire located in the cavity of the shell is fixed to the inner wall of the shell by a fixing buckle.
[0012] Preferably, a carrying handle is installed on the outer side of the shell.
[0013] Compared with the prior art, the utility model provides an aircraft grounding wire with a self-returning gear, which has the following beneficial effects:
[0014] 1. The aircraft grounding wire with self-returning gear can make the winding barrel rotate through the cooperation of the fixing rod, winding barrel, bearing and vortex spring, so as to automatically reel in the wire;
[0015] 2. The aircraft grounding wire with a self-returning gear can control whether the winding barrel rotates through the cooperation of the lock and the self-returning gear to prevent the grounding wire from automatically retracting when in use. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 This is a schematic diagram of the overall external structure of the utility model;
[0017] Figure 2This is a schematic diagram of the internal structure of the housing of the utility model;
[0018] Figure 3 This is a schematic diagram of the partial structure inside the shell of the utility model;
[0019] Figure 4 This is a schematic diagram of the winding structure of the utility model;
[0020] Figure 5 This is a schematic diagram of fixing the first wire of the utility model;
[0021] Figure 6 This is a schematic diagram of the structure of the grounding clamp of the utility model;
[0022] Figure 7 This is a schematic diagram of the structure of the power connection clamp of the utility model.
[0023] Figure numerals: 1, housing, 2, fixed shaft; 3, self-return gear; 4, rotating shaft; 5, lock; 6, connecting rod; 7, button; 8, compression spring; 9, winding structure; 91, winding barrel; 92, bearing; 93, conductive slip ring; 94, vortex spring; 95, first wire; 96, second wire; 10, grounding clamp; 101, C-shaped clamp; 102, threaded rod; 103, clamp; 104, rotating handle; 105, first connecting buckle; 11, power connecting clamp; 111, metal conductive clamp; 112, second connecting buckle; 113, insulating sleeve; 12, limit plate; 13, fixing buckle; 14, carrying handle. DETAILED DESCRIPTION
[0024] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0025] See also Figure 1-6In this embodiment: an aircraft grounding wire containing a self-returning gear comprises a shell 1, characterized in that: the shell 1 is approximately cylindrical in shape and has a cavity inside, a carrying handle 14 is installed on the outer side of the shell 1, a fixed shaft 2 is fixedly connected between the two inner side walls of the shell 1, a winding structure 9 is rotatably installed on the fixed shaft 2, a self-returning gear 3 is installed on one side of the winding structure 9, a lock buckle 5 is rotatably installed on the inner side wall of the shell 1 through a rotating shaft 4, the lock buckle 5 is located near the self-returning gear 3, and the left end of the lock buckle 5 can be against the gear teeth of the self-returning gear 3, a slide groove is opened on the right side wall of the lock buckle 5, the bottom end of the connecting rod 6 is transmission-connected to the slide groove of the lock buckle 5 through a slider, and a button 7 is installed on the top of the connecting rod 6, and the connecting rod 6 is connected to the bottom end of the connecting rod 6. A limit plate 12 is installed in the middle of the connecting rod 6, and the limit plate 12 is located in the cavity. A compression spring 8 is sleeved on the outside of the connecting rod 6, and the compression spring 8 is located between the button 7 and the shell 1. The carrying handle 14 is installed on the outside of the shell 1 to facilitate the staff to hold the grounding wire. The lock buckle 5 is used to limit the rotation of the self-return gear 3. The connecting rod 6 is used to press the right end of the lock buckle 5. Through the cooperation of the rotating shaft 4, the lock buckle 5, the connecting rod 6 and the button 7, the left end of the lock buckle 5 can be controlled to lift, thereby releasing the restriction on the self-return gear 3. The compression spring 8 can ensure that the lock buckle 5 always limits the rotation of the self-return gear 3 when the button 7 is not pressed by external force. The limit plate 12 is used to prevent the lock buckle 5 from failing in the restriction function due to excessive rotation angle.
[0026] See also Figure 4 The winding structure 9 includes a bearing 92, a conductive slip ring 93 and a vortex spring 94 installed on the fixed shaft 2, the vortex spring 94 is located between the bearing 92 and the conductive slip ring 93, a winding barrel 91 is installed outside the bearing 92, the conductive slip ring 93 and the vortex spring 94, the inner rings of the bearing 92 and the conductive slip ring 93, and the inner connecting end of the vortex spring 94 are all fixedly installed on the fixed shaft 2, the outer rings of the bearing 92 and the conductive slip ring 93, and the outer connecting end of the vortex spring 94 are all fixedly installed on the inner side wall of the winding barrel 91, the inner rings of the bearing 92 and the conductive slip ring 93 can rotate on the outer ring, and the automatic gear 3 is fixedly installed on the side of the winding barrel 91 away from the conductive slip ring 93, wherein the bearing 92 and the conductive slip ring 93 both have the function of rotating the winding barrel 91 on the fixed shaft 2, and the vortex spring 94 is used to control the rotation of the winding barrel 91.
[0027] See also Figure 4 and 5The output end of the inner ring of the conductive slip ring 93 is connected to one end of the first wire 95, and the other end of the first wire 95 is connected to the grounding clamp 10. The part of the first wire 95 located in the cavity of the shell 1 is fixed to the inner wall of the shell 1 through the fixing buckle 13. A through hole is opened on the barrel wall of the winding barrel 91. One end of the second wire 96 passes through the through hole and is connected to the input end of the outer ring of the conductive slip ring 93. The second wire 96 is wound on the winding barrel 91, and the other end of the second wire 96 is connected to the power connection clamp 11. The side wall of the shell 1 is opened. The through hole allows the first wire 95 and the second wire 96 to pass through, wherein the winding barrel 91 is used to wind the second wire 96, and the first wire 95 and the second wire 96 are connected by a conductive slip ring 93, which can prevent the first wire 95 from breaking due to continuous twisting when the second wire 96 is wound. The first wire 95 is fixed to the inner wall of the shell 1 with a fixing buckle 13 to prevent the first wire 95 from being wound into the winding barrel 91 when the winding barrel 91 rotates. The grounding clamp 10 is connected to the ground wire, and the power clamp 11 is connected to the shell of the aircraft.
[0028] See also Figure 6 The grounding clamp 10 includes a C-shaped clamp 101, a threaded hole is opened on the C-shaped clamp 101 and a threaded rod 102 is provided. A rotating handle 104 is installed on the top of the threaded rod 102, and a clamp plate 103 is rotatably installed on the bottom of the threaded rod 102. A first connecting buckle 105 is installed at the tail of the C-shaped clamp 101, and the first connecting buckle 105 is connected to the first wire 95. The grounding clamp 10 is located outside the housing 1, wherein the rotating handle 104 is used to rotate the threaded rod 102. The cooperation of the C-shaped clamp 101, the threaded rod 102 and the clamp plate 103 can make the grounding clamp 10 more firmly clamped on the ground wire.
[0029] See also Figure 7 The power connection clip 11 includes a metal conductive clip 111, the tail of the metal conductive clip 111 is covered with an insulating sleeve 113, a second connecting buckle 112 is installed on one side of the metal conductive clip 111, and the second connecting buckle 112 is connected to one end of the second wire 96. The power connection clip 11 is located outside the shell 1, wherein the metal conductive clip 111 is used to connect to the aircraft shell, and the insulating sleeve 113 can prevent the staff from electric shock.
[0030] The use process of the utility model is as follows: before refueling the aircraft, the staff first clamps the ground wire with the grounding clamp 10, then pulls out the second wire 96 through the power clamp 11, connects the power clamp 11 to the aircraft shell, and starts refueling the aircraft after confirming that both sides of the ground wire are connected. After refueling, first remove the power clamp 11, then remove the grounding clamp 10, and press the button 7 to retract the second wire 96.
[0031] Finally, it should be noted that the above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions recorded in the above embodiments or replace some of the technical features therein with equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.
Claims
1. An aircraft grounding wire with a self-returning gear, comprising a housing (1), characterized in that: The shell (1) is approximately cylindrical in shape and has a cavity therein. A fixed shaft (2) is fixedly connected between two inner side walls of the shell (1). A winding structure (9) is rotatably mounted on the fixed shaft (2). A self-returning gear (3) is mounted on one side of the winding structure (9). A lock buckle (5) is rotatably mounted on the inner side wall of the shell (1) via a rotating shaft (4). The lock buckle (5) is located near the self-returning gear (3), and the left end of the lock buckle (5) can be pressed against the gear teeth of the self-returning gear (3). A sliding groove is provided on the right side of the side wall of the lock buckle (5). The bottom end of the connecting rod (6) is transmission-connected to the sliding groove of the lock buckle (5) via a slider. A button (7) is mounted on the top of the connecting rod (6). A limit plate (12) is mounted in the middle of the connecting rod (6). The limit plate (12) is located in the cavity. A compression spring (8) is sleeved on the outer side of the connecting rod (6). The compression spring (8) is located between the button (7) and the shell (1).
2. The aircraft grounding wire with a self-returning gear according to claim 1, characterized in that: The winding structure (9) comprises a bearing (92), a conductive slip ring (93) and a vortex spring (94) mounted on a fixed shaft (2); the vortex spring (94) is located between the bearing (92) and the conductive slip ring (93); a winding barrel (91) is mounted outside the bearing (92), the conductive slip ring (93) and the vortex spring (94); the inner rings of the bearing (92) and the conductive slip ring (93) and the inner connecting end of the vortex spring (94) are all fixedly mounted on the fixed shaft (2); the outer rings of the bearing (92) and the conductive slip ring (93) and the outer connecting end of the vortex spring (94) are all fixedly mounted on the inner side wall of the winding barrel (91); the inner rings of the bearing (92) and the conductive slip ring (93) can rotate on the outer ring; and the self-returning gear (3) is fixedly mounted on the winding barrel (91) on a side away from the conductive slip ring (93).
3. The aircraft grounding wire with a self-returning gear according to claim 2, characterized in that: The output end of the inner ring of the conductive slip ring (93) is connected to one end of a first wire (95), the other end of the first wire (95) is connected to a grounding clamp (10), a through hole is formed on the barrel wall of the winding barrel (91), one end of a second wire (96) passes through the through hole and is connected to the input end of the outer ring of the conductive slip ring (93), the second wire (96) is wound on the winding barrel (91), and the other end of the second wire (96) is connected to the grounding clamp (11), and a through hole is formed on the side wall of the housing (1) through which the first wire (95) and the second wire (96) pass.
4. The aircraft grounding wire with a self-returning gear according to claim 3, characterized in that: The grounding clamp (10) comprises a C-shaped clamp (101), a threaded hole is formed on the C-shaped clamp (101) and a threaded rod (102) is provided, a rotating handle (104) is installed at the top end of the threaded rod (102), a clamping plate (103) is rotatably installed at the bottom end of the threaded rod (102), a first connecting buckle (105) is installed at the tail end of the C-shaped clamp (101), and the first connecting buckle (105) is connected to the first wire (95), and the grounding clamp (100) is located outside the housing (1).
5. The aircraft grounding wire with a self-returning gear according to claim 3, characterized in that: The power connection clip (11) comprises a metal conductive clip (111), the tail of the metal conductive clip (111) is covered with an insulating sleeve (113), a second connection buckle (112) is installed on one side of the metal conductive clip (111), the second connection buckle (112) is connected to one end of the second wire (96), and the power connection clip (11) is located outside the housing (1).
6. The aircraft grounding wire with a self-returning gear according to claim 3, characterized in that: The portion of the first conductive wire (95) located in the cavity of the housing (1) is fixed to the inner wall of the housing (1) via a fixing buckle (13).
7. The aircraft grounding wire with a self-returning gear according to claim 1, characterized in that: A carrying handle (14) is installed on the outer side of the housing (1).