An aircraft grounding monitoring device and a monitoring method

Abstract

The present application provides an aircraft grounding monitoring device and a monitoring method. The grounding monitoring device includes a support installed on a refueling vehicle and electrically connected to the refueling vehicle. The grounding cable includes a connecting wire and a detection wire, grounding clips provided at the free ends of the connecting wire and the detection wire, and a monitoring component provided on the support. The monitoring component further includes a resistance detection module electrically connected to the refueling vehicle, the support, the fixed ends of the connecting wire and the detection wire and forming a resistance measurement path. The grounding monitoring device of the present invention is not only compact in structure and convenient to operate, but also can monitor the installation firmness, aircraft grounding connection and grounding clip return status in real time, etc., and can effectively improve the safety level during the aircraft fuel filling process.

Description

Technical Field

[0001] The present application relates to the technical field of grounding monitoring, and in particular to an aircraft grounding monitoring device and a monitoring method. Background Art

[0002] A large amount of static electricity is generated during the refueling process of an aircraft. To prevent static electricity accumulation and accidents, the aircraft needs to connect the grounding wire of the grounding reel installed on the refueling truck to the aircraft's static conductive pile before refueling; after the refueling operation is completed, the grounding wire needs to be recovered to the grounding reel. Currently, refueling trucks for aircraft usually use mechanical grounding reels to achieve the grounding connection between the aircraft and the refueling truck during the refueling process. The grounding connection between the refueling truck and the aircraft relies on the experience and judgment of the personnel, and it is impossible to effectively verify the reliability of the grounding connection during the aircraft refueling process.

[0003] In addition, long-term bumpy driving of the refueling truck may cause the grounding reel to loosen, which may lead to failure of the grounding connection between the refueling truck and the aircraft. At present, the mechanical grounding reel equipped with the refueling truck can only rely on regular inspection to detect potential loose installation failures, which is time-consuming and labor-intensive, and cannot effectively detect installation failures in a timely manner. Summary of the invention

[0004] In order to solve the above problems existing in the prior art, the purpose of the present invention is to provide an aircraft grounding monitoring device and a monitoring method, which can not only accurately and efficiently monitor the grounding connection status of the aircraft and the refueling truck, but also monitor the installation fault of the device itself in real time.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] An aircraft ground monitoring device, comprising:

[0007] A support, mounted on the refueling truck and electrically connected to the refueling truck;

[0008] The grounding cable comprises a connecting wire and a detection wire, wherein the connecting wire comprises a connecting wire free end and a connecting wire fixed end, and the detection wire comprises a detection wire free end and a detection wire fixed end;

[0009] A grounding clamp, comprising a grounding electrode electrically connected to a free end of the connection line and a detection electrode electrically connected to a free end of the detection line;

[0010] The monitoring component is arranged on the support, and the monitoring component includes a resistance detection module, which is electrically connected to the refueling vehicle, the support, the fixed end of the connecting line and the fixed end of the detection line to form a resistance measurement path.

[0011] Furthermore, the grounding monitoring device also includes a return conductor for detachably clamping the grounding clamp, the return conductor is insulated and arranged on the refueling truck or the support, and the grounding monitoring device also includes a return cable, and the resistance detection module is electrically connected to the return conductor through the return cable to form another resistance measurement path.

[0012] Furthermore, the grounding monitoring device comprises:

[0013] A mandrel is fixed on the support and has a hollow structure inside;

[0014] The winding drum is mounted on the spindle and can rotate around the spindle; the grounding cable is wound on the winding drum;

[0015] The rotating electrical connection mechanism is arranged in the spindle, and the fixed end of the connecting wire and the fixed end of the detection wire are electrically connected to the resistance detection module through the rotating electrical connection mechanism.

[0016] Furthermore, the rotating electrical connection mechanism includes a stator fixedly arranged relative to the spindle and a rotor rotatably arranged relative to the stator, the stator is electrically connected to the rotor, the rotor is connected to the fixed end of the connecting line and the fixed end of the detection line, and the stator is electrically connected to the resistance detection module.

[0017] Furthermore, the grounding monitoring device also includes a manual wire return assembly and / or an automatic wire return assembly for reeling the grounding cable.

[0018] Furthermore, the manual rewind assembly is a folding handle arranged on the winding drum, and the automatic rewind assembly is a combination of a clockwork spring and a ratchet mechanism, wherein the clockwork spring is arranged inside the winding drum, one end of the clockwork spring is connected to the spindle, and the other end of the clockwork spring is connected to the winding drum; the ratchet mechanism includes a ratchet and a pawl, the ratchet is sleeved on the spindle and fixedly connected to the spindle, the pawl is fixed to the winding drum and engages or disengages with the ratchet as the winding drum rotates, thereby realizing the positioning or recovery of the grounding cable.

[0019] Furthermore, the aircraft ground monitoring device also includes a wire frame arranged on the support and a wire stopper ball arranged on the grounding cable, and the size of the wire stopper ball is matched with the wire frame to limit the wire stopper ball from passing through the wire frame.

[0020] Furthermore, the monitoring component also includes an alarm module, a control module and a power module, and the alarm module, the control module and the power module are respectively connected to the resistance detection module.

[0021] The aircraft grounding monitoring method provided by the present invention can be applied to the aircraft grounding monitoring device, and comprises the following steps:

[0022] Step 1: Detect the first resistance between the support and the refueling truck. If the first resistance does not exceed the first resistance threshold, it is determined that the grounding monitoring device and the refueling truck are firmly installed; otherwise, it is determined that the grounding monitoring device and the refueling truck are loosely installed;

[0023] Step 2: After determining that the grounding monitoring device is firmly installed, further detect the second resistance between the grounding electrode and the detection electrode of the grounding clamp. If the second resistance does not exceed the second resistance threshold, it is determined that the grounding clamp is connected to a conductive object; otherwise, it is determined that the grounding clamp is not connected to a conductive object.

[0024] Step 3: After determining that the grounding clamp is connected to a conductive object, further detect the third resistance between the refueling truck and the detection electrode of the grounding clamp. If the third resistance does not exceed the third resistance threshold, it is determined that the aircraft and the refueling truck are grounded. Otherwise, it is determined that the aircraft and the refueling truck are not grounded.

[0025] Furthermore, step 2 also includes the following steps:

[0026] Step 2a: After determining that the grounding clamp is connected to a conductive object, further detect the fourth resistance between the return conductor and the refueling truck; if the fourth resistance does not exceed the fourth resistance threshold, determine that the grounding clamp is in the return state; otherwise, determine that the grounding clamp is in the non-return state.

[0027] Furthermore, step 2 also includes the following steps:

[0028] Step 2b: After determining that the grounding clamp is not connected to a conductive object, further detect the fourth resistance between the homing conductor and the refueling truck. If the fourth resistance does not exceed the fourth resistance threshold, it is determined that the homing conductor and the refueling truck or the support are in an insulation state; otherwise, it is determined that the insulation between the homing conductor and the refueling truck or the support is abnormal.

[0029] Furthermore, the value range of the first, second, third or fourth resistance threshold is 10-100Ω.

[0030] Compared with the prior art, the aircraft grounding monitoring device provided by the present application is not only compact in structure and easy to operate, but also has the following technical effects:

[0031] (1) The installation firmness between the grounding monitoring device and the refueling truck can be monitored in real time, solving the problem of poor timeliness and heavy workload of regular inspection of mechanical grounding reels.

[0032] (2) The ground connection status between the aircraft and the refueling truck can be accurately and efficiently determined, thereby improving the safety level of the aircraft refueling process.

[0033] (3) The return status of the grounding clamp and the insulation status of the return conductor can be monitored in real time, which can effectively prevent the grounding monitoring device or aircraft from being damaged due to the fuel truck driving away without the grounding clamp returned to its original position. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0035] Figure 1 The figure shows a schematic diagram of the connection between a refueling truck and an aircraft according to an embodiment of the present application;

[0036] Figure 2 The figure shows a three-dimensional schematic diagram of an aircraft ground monitoring device according to an embodiment of the present application;

[0037] Figure 3 Shown Figure 1 A three-dimensional schematic diagram of a grounding clamp of an aircraft grounding monitoring device is shown;

[0038] Figure 4 Shown Figure 1 A longitudinal section of the aircraft touchdown monitoring device shown;

[0039] Figure 5 Shown is a flow chart of an aircraft grounding monitoring method according to an embodiment of the present application;

[0040] Figure 6 Shown is a flow chart of an aircraft grounding monitoring method according to another embodiment of the present application;

[0041] Figure 7 Shown is a flow chart of an aircraft touchdown monitoring method according to yet another embodiment of the present application. DETAILED DESCRIPTION

[0042] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The implementations described in the following exemplary embodiments do not represent all implementations consistent with the present application. Instead, they are merely examples of devices and methods consistent with some aspects of the present application as detailed in the appended claims.

[0043] The terms used in this application are only for the purpose of describing specific embodiments and are not intended to limit this application. Unless otherwise defined, the technical terms or scientific terms used in this application should be understood by people with ordinary skills in the field to which this application belongs. The words "first", "second" and similar words used in the specification and claims of this application do not indicate any order, quantity or importance, but are only used to distinguish different components. Similarly, words such as "one" or "one" do not indicate a quantitative limit, but indicate that there is at least one. "Multiple" or "several" means two or more. Unless otherwise specified, words such as "front", "rear", "lower" and / or "upper" are only for the convenience of explanation and are not limited to one position or one spatial orientation. Words such as "include" or "comprise" mean that the elements or objects appearing in front of "include" or "comprise" include the elements or objects listed after "include" or "comprise" and their equivalents, and do not exclude other elements or objects. Words such as "connect" or "connected" are not limited to physical or mechanical connections, and can include electrical connections, whether direct or indirect.

[0044] The terms used in this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The singular forms of "a", "a", "an" and "the" used in this application and the appended claims are also intended to include plural forms unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used in this article refers to and includes any or all possible combinations of one or more associated listed items.

[0045] Figure 1 The figure shows a connection diagram of a refueling truck 10 and an aircraft 11 according to an embodiment of the present application. The refueling truck 10 is used to refuel the aircraft 11. In the present application, the refueling truck 10 may generally refer to a device for refueling or pumping oil from the aircraft 11, including but not limited to various refueling trucks, such as pipeline trucks, tank refueling trucks, and various devices, such as carts, skid-mounted devices, etc. Figure 1 As shown, the aircraft 11 is connected to the refueling truck 10 at an equipotential ground via the ground monitoring device 12 to prevent static electricity from accumulating and discharging during the refueling process, thereby ensuring the safety of the refueling process of the aircraft 11.

[0046] In the related art, the refueling truck 10 and the aircraft 11 are usually connected through a mechanical grounding reel, one end of the grounding wire wound in the mechanical grounding reel is connected to the refueling truck 10 through the grounding reel support, and the other end of the grounding wire is clamped to the static conductive pile of the aircraft 11 through a grounding clamp. The staff can only check from the surface whether the grounding clamp is in contact with the static conductive pile, and cannot effectively judge the reliability of the grounding connection between the refueling truck 10 and the aircraft 11, which brings safety hazards to the refueling of the aircraft 11.

[0047] In order to monitor the reliability of the ground connection between the refueling truck 10 and the aircraft 11 , the present application provides an aircraft ground monitoring device 12 . Figure 2 FIG. 1 is a perspective schematic diagram of an aircraft touchdown monitoring device 12 according to an embodiment of the present application. Figure 3 Shown Figure 1 FIG. 1 is a perspective schematic diagram of a grounding clamp 22 of an aircraft grounding monitoring device 12 . Figure 4 Shown Figure 2 A longitudinal sectional view of the aircraft ground monitoring device 12 is shown. Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the aircraft grounding monitoring device 12 includes a support 13 , a grounding cable 21 , a grounding clamp 22 and a monitoring component 14 .

[0048] The support 13 is installed on the refueling truck 10 and electrically connected to the refueling truck 10. The monitoring component 14, the grounding cable 21 and the grounding clamp 22 are arranged on the refueling truck 10 through the support 13. The support 13 can be installed on the refueling truck 10 by bolts and can be electrically connected to the refueling truck 10 by bolts.

[0049] The grounding cable 21 includes a connecting wire and a detection wire, wherein the connecting wire includes a connecting wire fixed end 211 and a connecting wire free end 213, and the detection wire includes a detection wire fixed end 212 and a detection wire free end 214. The connecting wire and the detection wire may be two wire cores of the grounding cable 21, and the connecting wire and the detection wire are insulated from each other, but the connecting wire and the detection wire share a cable protective sheath. The grounding cable 21 is preferably a flexible cable, and the cable protective sheath is wear-resistant and stretch-resistant.

[0050] Please refer to Figure 3 The grounding clamp 22 includes a first clamp body 221 and a second clamp body 222. The first clamp body 221 and the second clamp body 222 are rotatably connected through a pin shaft 223 for clamping objects. The end of the first clamp body 221 is provided with a grounding electrode 23 electrically connected to the free end 213 of the connecting line and a detection electrode 24 electrically connected to the free end 214 of the detection line.

[0051] A through hole is provided at the tail of the first clamp 221 for the grounding cable 21 to pass through and enter the first clamp 221. After entering the first clamp 221, the grounding cable 21 extends along the length direction of the first clamp 221 and is connected to the vicinity of the grounding electrode 23 and the detection electrode 24. The free end 213 of the connecting wire and the free end 214 of the detection wire in the grounding cable 21 are electrically connected to the grounding electrode 23 and the detection electrode 24 respectively; the grounding electrode 23 and the detection electrode 24 are arranged side by side in the width direction of the end of the first clamp 221, which helps to reduce the routing interference between the free end 213 of the connecting wire and the free end 214 of the detection wire; a partition 224 is arranged between the grounding electrode 23 and the detection electrode 24 to separate the grounding electrode 23 and the detection electrode 24, so as to avoid the grounding electrode 23 and the detection electrode 24 being electrically connected when the conductive object is not clamped.

[0052] When the grounding clamp 22 clamps a conductive object, the grounding electrode 23 and the detection electrode 24 of the grounding clamp 22 are electrically connected. When the grounding clamp 22 does not clamp a conductive object, the grounding electrode 23 and the detection electrode 24 of the grounding clamp 22 are not electrically connected. The grounding clamp 22 is used to clamp the electrostatic conductive pile of the aircraft 11 during refueling.

[0053] The monitoring component 14 is disposed on the support 13 , and includes a resistance detection module 18 , which is electrically connected to the refueling vehicle 10 , the support 13 , the connection line fixed end 211 and the detection line fixed end 212 , respectively. The support 13 is electrically connected to the connection line fixed end 211 .

[0054] like Figure 1 , Figure 2 As shown, the resistance detection module 18 is electrically connected to the refueling vehicle 10 through a vehicle connecting cable 19. One end of the vehicle connecting cable 19 has a metal terminal 20, which can be an O-type metal terminal. One end of the vehicle connecting cable 19 is electrically connected to the refueling vehicle 10 through the metal terminal 20, and the other end is connected to the measurement terminal a of the resistance detection module 18.

[0055] The measuring terminal b and the measuring terminal c of the resistance detection module 18 are electrically connected to the ground cable connection line fixed end 211 and the detection line fixed end 212 respectively, and the measuring terminal b is electrically connected to the support 13 at the same time.

[0056] The resistance detection module 18 can be used to detect the first resistance R between the support 13 and the refueling vehicle 10 ab If the first resistance does not exceed the first resistance threshold, it indicates that the support 13 and the refueling truck 10 are electrically connected, and it is determined that the grounding monitoring device 12 is firmly and reliably installed on the refueling truck 10; otherwise, it is determined that the grounding monitoring device 12 and the refueling truck 10 are loosely installed. Through fault self-detection, installation faults can be discovered in a timely and effective manner before the aircraft is refueled, thereby preventing the risk of grounding failure caused by them.

[0057] The resistance detection module 18 can also be used to detect a second resistance R between the grounding electrode 23 and the detection electrode 24 of the grounding clamp 22. bc If the second resistance does not exceed the second resistance threshold, it indicates that the grounding electrode 23 of the grounding clamp 22 is electrically connected to the detection electrode 24, and it is determined that the grounding clamp 22 is connected to a conductive object; otherwise, it is determined that the grounding clamp 22 is not connected to a conductive object.

[0058] After determining that the grounding clamp 22 is connected to a conductive object, the third resistor R between the refueling truck 10 and the detection electrode 24 of the grounding clamp 22 is further detected. ac If the third resistance does not exceed the third resistance threshold, it indicates that the fuel truck 10 is electrically connected to the grounding clamp 22, and the aircraft 11 is determined to be grounded to the fuel truck 10. Otherwise, it is determined that the aircraft 11 is not grounded to the fuel truck 10. By monitoring the grounding connection status of the aircraft, the safety risks caused by the grounding clamp 22 not being connected to the aircraft 11 or being falsely connected during the fuel filling process can be effectively avoided.

[0059] Main references Figure 1 , Figure 2 and Figure 3 As shown, in another embodiment, the aircraft ground monitoring device 12 further includes a homing component 25, and the homing component 25 includes a homing conductor 27 and a homing cable 26. The homing conductor 27 is used for the detachable clamping connection of the grounding clamp 22, and can be insulated and arranged on the refueling truck 10 or the support 13 according to the convenience of operation, preferably arranged on the support 13, so that the installation is more convenient. The homing conductor 27 is electrically connected to the measuring terminal d of the resistance detection module 18 through the homing cable 26. The grounding clamp 22 is clamped on the homing conductor 27 when not in operation. When in operation, the grounding clamp 22 removes the static conductive pile clamped on the aircraft 11 from the homing conductor 27, and returns to the homing conductor 27 again after the operation is completed.

[0060] In this embodiment, the resistance detection module 18 can also be used to detect a fourth resistance R between the homing conductor 27 and the refueling vehicle 10. ad .

[0061] When the grounding clamp is connected to a conductive object, if the fourth resistance is further detected to be less than the fourth resistance threshold, it means that the homing conductor 27 is electrically connected to the refueling truck 10 through the grounding clamp 22, and then the grounding clamp 22 is determined to be connected to the homing conductor 27 in the homing state; otherwise, the grounding clamp 22 is determined to be in a non-homing state. By detecting the homing state, it is possible to prevent the refueling truck 10 from driving away from the aircraft 11 when the grounding clamp 22 is not detached from the aircraft 11, thereby preventing the grounding monitoring device 12 or the aircraft 11 from being damaged.

[0062] When the grounding clamp is not connected to a conductive object, if the fourth resistance is further detected to be less than the fourth resistance threshold, it means that the homing conductor 27 is not electrically connected to the refueling truck 10, and the homing conductor 27 is determined to be in an insulation state; otherwise, the homing conductor 27 is determined to be in an insulation abnormal state. By detecting the insulation state of the homing conductor 27, the grounding monitoring device 12 can be prevented from making a homing misjudgment.

[0063] Please refer to Figure 2 , Figure 4 In one embodiment, the aircraft ground monitoring device 12 also includes a spindle 35, a winding drum 15, and a rotating electrical connection mechanism 36. The spindle 35 is fixed on the support 13. The spindle 35 has a hollow structure to facilitate the setting of the rotating electrical connection mechanism 36 and to accommodate the connecting wire fixed end 211 and the detection wire fixed end 212.

[0064] The winding drum 15 is sleeved on the spindle 35 and can rotate around the spindle 35. In one embodiment, the winding drum 15 is arranged on one side of the support 13, and the monitoring component 14 and the homing component 25 are arranged on the other side of the support 13. Such a layout is reasonable and the structure is more compact.

[0065] The grounding cable 21 is wound on the winding drum 15, and the winding drum 15 rotates to realize the retraction and extension of the grounding cable 21. In one embodiment, the winding drum 15 includes a cylinder 28 for winding the grounding cable 21, and a right baffle 29 and a left baffle 30 connected to opposite sides of the cylinder 28. In the radial direction of the cylinder 28, the size of the cylinder 28 is smaller than the size of the right baffle 29 or the left baffle 30. In this way, the grounding cable 21 can be better wound and prevented from escaping from the winding drum 15.

[0066] The rotating electrical connection mechanism 36 is arranged in the spindle 35 at one end close to the winding drum 15, and the connecting wire fixed end 211 and the detection wire fixed end 212 are electrically connected to the resistance detection module 18 through the rotating electrical connection mechanism 36. The rotating electrical connection mechanism 36 includes a stator 38 fixedly arranged relative to the spindle 35 and a rotor 39 rotatably arranged relative to the stator 38, the stator 38 is electrically connected to the rotor 39, the rotor 39 is connected to the connecting wire fixed end 211 and the detection wire fixed end 212, and the stator 38 is electrically connected to the resistance detection module 18 through the connecting cable 37. In this way, when the winding drum 15 rotates to realize the process of retracting and releasing the grounding cable 21, the connecting wire fixed end 211 and the detection wire fixed end 212 can always be kept reliably electrically connected to the resistance detection module 18.

[0067] In one embodiment, the aircraft grounding monitoring device 12 further includes a manual wire reel assembly 16 and / or an automatic wire reel assembly 41 for reeling the grounding cable 21. The manual wire reel assembly 16 is a folding handle 40 provided on the wire reel 15. When in use, the folding handle 40 is opened, and the wire reel 15 is manually cranked to reel the grounding cable 21. After the wire reeling is completed, the folding handle 40 can be folded. Such a configuration is convenient for operation and has a more compact structure.

[0068] In one embodiment, the automatic rewind assembly 41 is a combination of a spring 42 and a ratchet mechanism 43. The spring 42 is disposed inside the winding drum 15, one end of the spring 42 is connected to the spindle 35, and the other end of the spring 42 is connected to the winding drum 15. The spring 42 is used to provide a force for the winding drum 15 to rotate in the direction of recovering the grounding cable 21. The ratchet mechanism 43 includes a ratchet 44 and a pawl 45. The ratchet 44 is sleeved on the spindle 35 and fixedly connected to the spindle 35. The pawl 45 is fixed to the winding drum 15 and is engaged or disengaged with the ratchet 44 as the winding drum 15 rotates, thereby realizing the positioning or recovery of the grounding cable 21.

[0069] When the operator pulls out the grounding cable 21 from the winding drum 15, the winding drum 15 rotates, and the spring spring 42 is tightened to store energy until the ratchet 44 and the pawl 45 engage to position the grounding cable 21 to the desired position; when the operator recycles the grounding cable 21, the grounding cable 21 is slightly stretched to disengage the ratchet 44 and the pawl 45, and the spring spring 42 drives the winding drum 15 to rotate in the opposite direction, thereby realizing the automatic recycle of the grounding cable 21. This is convenient to operate and can reduce the workload of the operator.

[0070] In one embodiment, the aircraft ground monitoring device 12 further includes a wire frame 17 disposed on the support 13 and a wire stopper ball 31 disposed on the ground cable 21, the size of the wire stopper ball 31 being matched with the wire frame 17, that is, the diameter of the wire stopper ball 31 is larger than the inner frame size of the wire frame 17, and the wire stopper ball 31 is restricted from passing through the wire frame 17. The ground cable 21 passes through the wire frame 17, and the wire stopper ball is located between the wire frame 17 and the ground clamp 22.

[0071] In one embodiment, the monitoring component 14 further includes an alarm module 32 , a control module 33 and a power module 34 .

[0072] The alarm module 32 is used for fault or alarm prompts. The alarm module 32 can be, but is not limited to, an indicator light, a buzzer, or other components that can be used to prompt operators. For example, the alarm module 32 can distinguish between loose installation faults, aircraft failure to ground, grounding clamp failure to return to position, and insulation abnormalities of the return conductor in the ground monitoring device through lights of different colors or buzzers of different sounds, and is used for fault or alarm prompts. This arrangement makes it easier for operators to find problems in a timely manner.

[0073] The control module 33 is used to implement interlocking protection of the refueling truck 10. For example, when the grounding clamp 22 is not returned to its original position, the refueling truck 10 is kept in a braking state; when the aircraft 11 is not grounded to the refueling truck 10, the refueling valve is closed to stop refueling.

[0074] The power module 34 is used to supply power to the monitoring component 14 , including but not limited to a vehicle power supply, mains power or a battery.

[0075] refer to Figure 5 The aircraft grounding monitoring method provided by the present invention comprises the following steps:

[0076] Step 1: Detect the first resistance R between the support 13 and the refueling vehicle 10 ab If the first resistance does not exceed the first resistance threshold, it indicates that the support 13 is electrically connected to the refueling truck 10, and it is determined that the grounding monitoring device 12 is firmly and reliably installed on the refueling truck 10; otherwise, it is determined that the grounding monitoring device 12 and the refueling truck 10 are loosely installed.

[0077] Step 2: After determining that the grounding monitoring device 12 is firmly installed, further detect the second resistance R between the grounding electrode 23 of the grounding clamp 22 and the detection electrode 24 bc If the second resistance does not exceed the second resistance threshold, it means that the grounding electrode 23 of the grounding clamp 22 is electrically connected to the detection electrode 24, and it is determined that the grounding clamp 22 is connected to a conductive object; otherwise, it is determined that the grounding clamp 22 is not connected to a conductive object.

[0078] Step 3: After determining that the grounding clamp is connected to a conductive object, further detect the third resistance R between the refueling truck 10 and the detection electrode 24 of the grounding clamp 22 ac If the third resistance does not exceed the third resistance threshold, it indicates that the fuel truck 10 is electrically connected to the ground clamp 22, and it is determined that the aircraft 11 and the fuel truck 10 are grounded. Otherwise, it is determined that the aircraft 11 and the fuel truck 10 are not grounded.

[0079] refer to Figure 6 In the aircraft grounding monitoring method provided by the present invention, step 2 further comprises the following steps:

[0080] Step 2a: After determining that the grounding clamp is connected to a conductive object, further detect the fourth resistance between the return conductor and the refueling truck. If the fourth resistance does not exceed the fourth resistance threshold, it is determined that the grounding clamp is in the return state; if the fourth resistance exceeds the fourth resistance threshold, it is determined that the grounding clamp is not in the return state.

[0081] refer to Figure 7 In the aircraft grounding monitoring method provided by the present invention, step 2 further comprises the following steps:

[0082] Step 2b: After determining that the grounding clamp is not connected to a conductive object, further detect the fourth resistance between the homing conductor and the refueling truck. If the fourth resistance does not exceed the fourth resistance threshold, it is determined that the homing conductor and the refueling truck or the support are in an insulation state; otherwise, it is determined that the insulation between the homing conductor and the refueling truck or the support is abnormal.

[0083] It should be noted that the first, second, third or fourth resistance thresholds can be set according to actual conditions, and can be the same or different. In practical applications, the resistance threshold can be set within the range of 10Ω to 100Ω, and is preferably set to 50Ω in consideration of the resistance of the grounding cable 21 itself and measurement errors.

[0084] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the application disclosed herein. The present application is intended to cover any variations, uses or adaptations of the present application, which follow the general principles of the present application and include common knowledge or customary techniques in the art that are not disclosed in the present application. The specification and examples are intended to be exemplary only, and the true scope and spirit of the present application are indicated by the following claims.

[0085] It should be understood that the present application is not limited to the precise structures that have been described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. An aircraft grounding monitoring device, characterized in that, it includes: A support installed on the refueling vehicle and electrically connected to the refueling vehicle; A grounding cable, including a connecting wire and a detection wire. The connecting wire includes a free end of the connecting wire and a fixed end of the connecting wire. The detection wire includes a free end of the detection wire and a fixed end of the detection wire; A grounding clip, having a grounding electrode electrically connected to the free end of the connecting wire and a detection electrode electrically connected to the free end of the detection wire; A monitoring component arranged on the support. The monitoring component includes a resistance detection module, and the resistance detection module is electrically connected to the refueling vehicle, the support, the fixed end of the connecting wire and the fixed end of the detection wire to form a resistance measurement path.

2. The aircraft grounding monitoring device according to claim 1, characterized in that, The grounding monitoring device further includes a return conductor for detachably clamping the grounding clip. The return conductor is insulated and arranged on the refueling vehicle or the support. The grounding monitoring device further includes a return cable. The resistance detection module is electrically connected to the return conductor through the return cable to form a resistance measurement path.

3. The aircraft grounding monitoring device according to claim 1, characterized in that, The grounding monitoring device includes: A mandrel fixed on the support, and the mandrel has a hollow structure inside; A winding disc sleeved on the mandrel and rotatable around the mandrel; the grounding cable is wound on the winding disc; A rotary electrical connection mechanism arranged inside the mandrel. The fixed ends of the connecting wire and the detection wire are electrically connected to the resistance detection module through the rotary electrical connection mechanism.

4. The aircraft grounding monitoring device according to claim 3, characterized in that, The rotary electrical connection mechanism includes a stator fixedly arranged relative to the mandrel and a rotor rotatably arranged relative to the stator. The stator is electrically connected to the rotor. The rotor is connected to the fixed ends of the connecting wire and the detection wire. The stator is electrically connected to the resistance detection module.

5. The aircraft grounding monitoring device according to claim 3 or 4, characterized in that, The grounding monitoring device further includes a manual cable rewinding component and / or an automatic cable rewinding component for rewinding the grounding cable by the winding disc.

6. The aircraft grounding monitoring device according to claim 5, characterized in that, The manual cable rewinding component is a folding handle arranged on the winding disc. The automatic cable rewinding component is a combination of a clockwork spring and a ratchet mechanism. The clockwork spring is arranged inside the winding disc. One end of the clockwork spring is connected to the mandrel, and the other end of the clockwork spring is connected to the winding disc; the ratchet mechanism includes a ratchet and a pawl. The ratchet is sleeved on the mandrel and fixedly connected to the mandrel. The pawl is fixed on the winding disc and rotates with the winding disc to engage or disengage with the ratchet to realize the positioning or recovery of the grounding cable.

7. An aircraft grounding monitoring method, including the following steps: Step 1: Detect the first resistance between the support and the refueling vehicle. If the first resistance does not exceed the first resistance threshold, it is determined that the grounding monitoring device is firmly installed on the refueling vehicle; otherwise, it is determined that the grounding monitoring device is loosely installed on the refueling vehicle. Step 2: After determining that the grounding monitoring device is firmly installed, further detect the second resistance between the grounding electrode and the detection electrode of the grounding clamp. If the second resistance does not exceed the second resistance threshold, it is determined that the grounding clamp is connected to a conductive object. Otherwise, it is determined that the grounding clamp is not connected to a conductive object. Step 3: After determining that the grounding clamp is connected to a conductive object, further detect the third resistance between the refueling vehicle and the detection electrode of the grounding clamp. If the third resistance does not exceed the third resistance threshold, it is determined that the aircraft is grounded to the refueling vehicle; otherwise, it is determined that the aircraft is not grounded to the refueling vehicle.

8. The aircraft grounding monitoring method according to claim 7, wherein, Step 2 further includes the following steps: Step 2a: After determining that the grounding clamp is connected to a conductive object, further detect the fourth resistance between the return conductor and the refueling vehicle. If the fourth resistance does not exceed the fourth resistance threshold, it is determined that the grounding clamp is in the retracted state; if the fourth resistance exceeds the fourth resistance threshold, it is determined that the grounding clamp is in the non-retracted state.

9. The aircraft grounding monitoring method according to claim 8, wherein, Step 2 further includes the following steps: Step 2b: After determining that the grounding clamp is not connected to a conductive object, further detect the fourth resistance between the return conductor and the refueling vehicle. If the fourth resistance does not exceed the fourth resistance threshold, it is determined that the return conductor is insulated from the refueling vehicle or the support; otherwise, it is determined that there is an insulation abnormality between the return conductor and the refueling vehicle or the support.

10. The aircraft grounding monitoring method according to claim 8 or 9, wherein, The range of the first, second, third, or fourth resistance threshold is 10 - 100 Ω.

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