Onboard antenna defect detection device

Abstract

The present disclosure relates to an airborne antenna defect detection device, which comprises a first antenna straightening mechanism, a defect detection module and a second antenna straightening mechanism arranged in sequence along a first direction; the first antenna straightening mechanism and the second antenna straightening mechanism each comprise an acting force applying assembly and H rubber wheel groups arranged in sequence along the first direction; each rubber wheel group comprises a first rubber wheel and a second rubber wheel; the groove on the antenna contact surface of the first rubber wheel and the groove on the antenna contact surface of the second rubber wheel are combined to form an antenna moving channel; the acting force applying assembly is used to apply acting force to the first rubber wheel and the second rubber wheel in each rubber wheel group to control the size of the antenna moving channel and limit the distance between two rubber wheel groups arranged adjacently. It can detect the full length of the antenna on line, in real time and accurately, and sufficiently reduce the damage probability of the antenna. In addition, it has a small volume and is convenient to use on the airplane.

Description

Technical Field

[0001] This disclosure relates to the field of nondestructive testing technology, and in particular to an airborne antenna defect detection device. Background Technology

[0002] To enable aircraft-to-submarine communication, deep-sea communication systems, including very low frequency (VLF) dual towed antennas, are typically deployed on aircraft. These systems can radiate electromagnetic signals to signal receiving devices in the deep sea to meet communication needs and possess the capability to maintain communication even after suffering significant damage, making them a primary means of survivable anti-submarine communication.

[0003] Very low frequency (VLF) dual-towed antennas are typically formed by stranding multiple steel-clad metal antenna strands. They are generally small in diameter, usually a few millimeters, and several kilometers long, with no protective layer on the outer surface. During antenna deployment and retrieval, the high-speed feed of the winch can cause pressure and friction damage to the VLF dual-towed antenna. Surface damage or broken wires will severely affect its electromagnetic radiation performance, leading to communication failure. Furthermore, the flight conditions of airborne VLF dual-towed antennas are particularly complex, subject to loads such as tension, shearing force, and frictional resistance, which may result in serious failure modes such as antenna breakage, ultimately leading to catastrophic consequences. In other words, every deployment, retrieval, and use of the antenna has the potential to cause damage. Therefore, how to detect defects in VLF dual-towed antennas while minimizing the probability of antenna damage is a pressing problem that needs to be solved. Summary of the Invention

[0004] In order to solve the above-mentioned technical problems, or at least partially solve the above-mentioned technical problems, this disclosure provides an airborne antenna defect detection device.

[0005] This disclosure provides an airborne antenna defect detection device for use on an aircraft. The device includes: a first antenna straightening mechanism, a defect detection module, and a second antenna straightening mechanism arranged sequentially along a first direction; the first direction is the same as or opposite to the movement direction of the antenna.

[0006] Both the first antenna straightening mechanism and the second antenna straightening mechanism include a force application component and H rubber wheel sets arranged sequentially along the first direction; H is a positive integer greater than or equal to 2;

[0007] Each of the rubber wheel sets includes a first rubber wheel and a second rubber wheel; the antenna contact surface of the first rubber wheel and the antenna contact surface of the second rubber wheel are both provided with grooves; the first rubber wheel and the second rubber wheel are opposite each other, and the grooves on the antenna contact surface of the first rubber wheel and the grooves on the antenna contact surface of the second rubber wheel are joined together to form an antenna movement channel;

[0008] The force application component is used to apply force to the first rubber wheel and the second rubber wheel in each of the rubber wheel sets to control the size of the antenna movement channel and to limit the distance between two adjacent rubber wheel sets;

[0009] The defect detection module includes a magnetization unit and a magnetic field detection unit; the magnetization unit is distributed circumferentially along the antenna; the magnetization unit is used to form a saturation magnetization circuit, so that the antenna is saturated magnetized within the detection range; the magnetic field detection unit is distributed circumferentially along the antenna, and its relative position to the magnetization unit is fixed; the magnetic field detection unit is used to detect the magnetic induction intensity value of the leakage magnetic field of the antenna; wherein, both the magnetization unit and the magnetic field detection unit have an air gap with the antenna.

[0010] Furthermore, both the first antenna straightening mechanism and the second antenna straightening mechanism include three rubber wheel sets arranged sequentially along the first direction;

[0011] The force application assembly includes a first force application assembly and a second force application assembly;

[0012] The first force application assembly includes a first rotating shaft, a first spring, a second spring, a first support rod, a second support rod, a third support rod, and a first locking component;

[0013] The first support rod is provided with a first groove extending along the length direction of the first support rod; the first rotating shaft is disposed in the first groove and can slide along the extension direction of the first groove; the first end of the second support rod and the first end of the third support rod are both fixed on the first rotating shaft and can rotate around the first rotating shaft; one end of the first spring is connected to the first support rod and the other end is connected to the second support rod; one end of the second spring is connected to the first support rod and the other end is connected to the third support rod; the second end of the first support rod is fixed to the axis of the first rubber wheel in the second rubber wheel group counting from the first direction; the second end of the second support rod is fixed to the axis of the first rubber wheel in the first rubber wheel group counting from the first direction; the second end of the third support rod is fixed to the axis of the first rubber wheel in the third rubber wheel group counting from the first direction; the first locking component is fixed to the first support rod and is used to limit the position of the first rotating shaft relative to the first support rod;

[0014] The second force application assembly includes a second rotating shaft, a third spring, a fourth spring, a fourth support rod, a fifth support rod, a sixth support rod, and a second locking component;

[0015] The fourth support rod is provided with a second sliding groove extending along the length direction of the fourth support rod; the second rotating shaft is disposed in the second sliding groove and can slide along the extension direction of the second sliding groove; the first end of the fifth support rod and the first end of the sixth support rod are both fixed on the second rotating shaft and can rotate around the second rotating shaft; one end of the third spring is connected to the fourth support rod and the other end is connected to the fifth support rod; one end of the fourth spring is connected to the fourth support rod and the other end is connected to the sixth support rod; the second end of the fourth support rod is fixed to the axis of the second rubber wheel in the second rubber wheel group counting from the first direction; the second end of the fifth support rod is fixed to the axis of the second rubber wheel in the first rubber wheel group counting from the first direction; the second end of the sixth support rod is fixed to the axis of the second rubber wheel in the third rubber wheel group counting from the first direction; the second locking component is fixed to the fourth support rod and is used to limit the position of the second rotating shaft relative to the fourth support rod.

[0016] Furthermore, along the first direction, the distance between any two adjacent rubber wheel sets is greater than or equal to 1 times the antenna pitch and less than or equal to 1.5 times the antenna pitch.

[0017] Furthermore, the defect detection module includes N magnetization units; each magnetization unit includes two permanent magnets and an iron yoke; the two permanent magnets are fixed to the same side of the iron yoke at a predetermined distance along the first direction, and the magnetization directions of the two permanent magnets are opposite; the included angle between two adjacent magnetization units is... N is a positive integer greater than or equal to 2;

[0018] The defect detection module further includes a fixing unit; the fixing unit includes a first clamp, a second clamp, and a base plate;

[0019] The first clamp and the second clamp are fixed to the base plate opposite to each other. The surface of the first clamp near the second clamp is provided with N first limiting grooves and a first hole for the antenna to pass through. The N first limiting grooves are symmetrically arranged with respect to the first hole. The surface of the second clamp near the first clamp is provided with N second limiting grooves and a second hole for the antenna to pass through. The N second limiting grooves are symmetrically arranged with respect to the second hole. The first limiting grooves and the second limiting grooves are one-to-one corresponding and are used to cooperate to fix one of the magnetizing units. The first hole and the second hole are used to pass through the antenna. The permanent magnet is located on the side of the yoke near the antenna.

[0020] Furthermore, the air gap between the permanent magnet and the antenna is greater than or equal to 2 mm and less than or equal to 10 mm.

[0021] Furthermore, the magnetic field detection unit includes P sensor mounting plates arranged sequentially along the first direction, the plurality of sensor mounting plates being located between the first clamp and the second clamp; P is a positive integer greater than or equal to 1;

[0022] Each of the sensor mounting plates is provided with a third hole through which the antenna passes; Q magnetic field detection sensors are arranged along the edge of the third hole, and the included angle between two adjacent magnetic field detection sensors is equal to The projections of the magnetic field detection sensors in any two of the sensor mounting plates onto the standard plane do not coincide, the standard plane is perpendicular to the first direction, and Q is a positive integer greater than or equal to 2.

[0023] Furthermore, the inner diameters of the first hole, the second hole, and the third hole are larger than the diameter of the antenna; during use, the antenna does not contact the inner walls of the first hole, the second hole, and the third hole.

[0024] Furthermore, it also includes a computing module and a coding speedometer;

[0025] The coded speed measuring device is disposed in the first antenna straightening mechanism and / or the second antenna straightening mechanism, and is used to detect the moving speed of the antenna;

[0026] The computing module is communicatively connected to the magnetic field detection sensor and the coded velocimeter, and is used to determine the location of the defect in the antenna based on the detection results of the magnetic field detection sensor and the detection results of the coded velocimeter.

[0027] Furthermore, it also includes electromagnetic shielding mesh;

[0028] The defect detection module is located within the shielding area of ​​the electromagnetic shielding mesh.

[0029] The technical solution provided in this disclosure has the following advantages compared with the prior art:

[0030] The technical solution provided in this disclosure allows for defect detection during aircraft flight, specifically during the VLF dual-towed antenna release phase before aircraft-to-submarine communication and during the VLF dual-towed antenna retrieval phase after aircraft-to-submarine communication. This setup does not increase the number of antenna releases or retrievals required for defect detection; instead, it integrates defect detection of the antenna under test with the antenna's operational process, enabling online, real-time, and accurate detection of the entire antenna length, significantly reducing the probability of antenna damage. Furthermore, the technical solution provided in this disclosure integrates vibration reduction, speed measurement, and antenna straightening functions into one unit, greatly reducing the size of the airborne antenna defect detection device and facilitating its use on aircraft. Attached Figure Description

[0031] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure.

[0032] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0033] Figure 1 A schematic diagram of the structure of an airborne antenna defect detection device provided in this application;

[0034] Figure 2 and Figure 3 A schematic diagram of the structure of a first antenna straightening mechanism under different states provided in the embodiments of this disclosure;

[0035] Figure 4 For along Figure 2 Cross-sectional view of A1-A2;

[0036] Figure 5 For along Figure 3 Cross-sectional view of B1-B2;

[0037] Figure 6 This is a schematic diagram of the structure of a defect detection module provided in an embodiment of the present disclosure;

[0038] Figure 7 This is a schematic diagram of the orientation of the defect detection module provided in an embodiment of this disclosure;

[0039] Figure 8 A schematic diagram of the saturation magnetization circuit of an antenna with a defect-free surface provided in an embodiment of this disclosure;

[0040] Figure 9 A schematic diagram of a saturation magnetization circuit for an antenna with surface defects provided in an embodiment of this disclosure;

[0041] Figure 10 This is a schematic diagram of the structure of a defect detection module provided in an embodiment of the present disclosure;

[0042] Figure 11 for Figure 10 A schematic diagram of the structure of the first fixture in the middle;

[0043] Figure 12 and Figure 13 Schematic diagrams of two sensor mounting plates provided in embodiments of this disclosure;

[0044] Figure 14 To be Figure 12 and Figure 13 A schematic diagram of projections onto the same plane. Detailed Implementation

[0045] To better understand the above-mentioned objectives, features, and advantages of this disclosure, the solutions disclosed herein will be further described below. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0046] Numerous specific details are set forth in the following description in order to provide a full understanding of this disclosure, but this disclosure may also be implemented in other ways different from those described herein; obviously, the embodiments in the specification are only some, and not all, of the embodiments of this disclosure.

[0047] Figure 1 A schematic diagram of the structure of an airborne antenna defect detection device provided in this application. See also... Figure 1 This airborne antenna defect detection device is used for installation on an aircraft. The airborne antenna defect detection device includes: along a first direction (e.g., ... Figure 1 The first antenna straightening mechanism 1, the defect detection module 2, and the second antenna straightening mechanism 3 are sequentially arranged in the C direction; the first direction (e.g., Figure 1 The direction C in the antenna 4 is the same as or opposite to the direction of movement of the antenna 4 during the antenna 4 retraction and extension phase.

[0048] Among them, antenna 4 can be a very low frequency dual towed antenna used to realize aircraft-to-submarine communication.

[0049] The first antenna straightening mechanism and the second antenna straightening mechanism have the same structure. Specifically, both the first antenna straightening mechanism and the second antenna straightening mechanism include a force application component and H rubber wheel groups arranged sequentially along a first direction; H is a positive integer greater than or equal to 2; each rubber wheel group includes a first rubber wheel and a second rubber wheel; grooves are provided on the antenna contact surfaces of the first rubber wheel and the second rubber wheel; the first rubber wheel and the second rubber wheel are opposite each other, and the grooves on the antenna contact surfaces of the first rubber wheel and the second rubber wheel are joined together to form an antenna movement channel; the force application component is used to apply force to the first rubber wheel and the second rubber wheel in each rubber wheel group to control the size of the antenna movement channel and limit the distance between two adjacent rubber wheel groups.

[0050] Figure 2 and Figure 3 This is a schematic diagram of the structure of a first antenna straightening mechanism under different states, provided in an embodiment of this disclosure. Figure 4 For along Figure 2 Cross-sectional view of A1-A2. Figure 5 For along Figure 3 Cross-sectional view of section B1-B2. Among them, Figure 2 and Figure 4 In the middle, the first antenna straightening mechanism is in a non-operating state. In the non-operating state, the antenna is neither released nor retracted. Therefore, Figure 2 and Figure 4 In the middle, there is no antenna in the antenna moving channel. Figure 3 and Figure 5 In the middle, the first antenna straightening mechanism is in the working state. In the working state, the antenna is released or retracted. Therefore, Figure 3 and Figure 5 In the middle, there is an antenna in the antenna moving channel.

[0051] See Figures 2-5 The first antenna straightening mechanism 1 includes a force application component 11 and three rubber wheel sets 12 arranged sequentially along a first direction. Each rubber wheel set 12 includes a first rubber wheel 121 and a second rubber wheel 122. A first groove is provided on the antenna contact surface 1211 of each first rubber wheel 121. A second groove is provided on the antenna contact surface 1221 of each second rubber wheel 122. The first rubber wheel 121 and the second rubber wheel 122 are opposite each other, and the first groove and the second groove are joined together to form an antenna movement channel 123.

[0052] Since airborne antennas are generally small in diameter, only about 5mm, and their deployment and retraction speeds are relatively fast, reaching 1-2m / s, a first groove is provided on the antenna contact surface 1211 of each first rubber wheel 121, and a second groove is provided on the antenna contact surface 1221 of each second rubber wheel 122. This confines the antenna 4 within the movement channel 123, preventing it from detaching. Simultaneously, the first and second rubber wheels 121 and 122 apply a clamping force to the antenna 4, while all springs are under tension. During the clamping process, the first and second rubber wheels 121 and 122 will not cause secondary damage to the antenna 4.

[0053] The principle behind the straightening mechanism described above for straightening the antenna is as follows: if the antenna bends and deforms, the contact points between the first and second rubber wheels and the antenna will no longer overlap, resulting in axial displacement. Under the action of the spring force, the pressure exerted by the first and second rubber wheels on the antenna will generate a bending moment opposite to the direction of the antenna's bending, which will straighten the antenna.

[0054] When the antenna needs to be released or retrieved, the force application component applies force to the first and second rubber wheels in each rubber wheel assembly to control the size of the antenna movement channel and to define the distance between two adjacent rubber wheel assemblies.

[0055] Those skilled in the art will understand that by controlling the size of the antenna movement channel and limiting the distance between two adjacent rubber wheel sets, the antenna can be straightened under the action of friction.

[0056] There are various ways to configure the force-applying component, and this application does not limit this. For example, see... Figure 2 and Figure 3 The first antenna straightening mechanism includes three rubber wheel sets 12 arranged sequentially along a first direction; the force application assembly includes a first force application assembly 111 and a second force application assembly 112; the first force application assembly 111 includes a first rotating shaft 1111, a first spring 1112, a second spring 1113, a first support rod 1114, a second support rod 1115, a third support rod 1116, and a first locking component 1117. A first sliding groove extending along the length direction of the first support rod 1114 is provided on the first support rod 1114. Figure 2 (Not shown in the image); the first rotating shaft 1111 is disposed in the first sliding groove and can slide along the extension direction of the first sliding groove; the first end of the second support rod 1115 and the first end of the third support rod 1116 are both fixed on the first rotating shaft 1111 and can rotate around the first rotating shaft 1111; one end of the first spring 1112 is connected to the first support rod 1114 and the other end is connected to the second support rod 1115; one end of the second spring 1113 is connected to the first support rod 1114 and the other end is connected to the third support rod 1116; the second end of the first support rod 1114 is connected to the third support rod 1116 along the first direction (i.e., along the first sliding groove); Figure 2 The first rubber wheel 121 in the second rubber wheel set 12 (measured from the C-axis direction) is fixed to the axis; the second end of the second support rod 1115 is fixed to the axis of the first rubber wheel 121 in the first rubber wheel set 12 (measured from the first direction); the second end of the third support rod 1116 is fixed to the axis of the first rubber wheel 121 in the third rubber wheel set 12 (measured from the first direction). The first locking component 1117 is fixed to the first support rod 1114 to limit the position of the first rotating shaft 1111 relative to the first support rod 1114.

[0057] Similarly, see also Figure 2 The second force application assembly 112 includes a second rotating shaft 1121, a third spring 1122, a fourth spring 1123, a fourth support rod 1124, a fifth support rod 1125, a sixth support rod 1126, and a second locking component 1127; the fourth support rod 1124 is provided with a second sliding groove extending along the length direction of the fourth support rod 1124. Figure 2(Not shown in the image); the second rotating shaft 1121 is disposed in the second sliding groove and can slide along the extension direction of the second sliding groove; the first end of the fifth support rod 1125 and the first end of the sixth support rod 1126 are both fixed on the second rotating shaft 1121 and can rotate around the second rotating shaft 1121; one end of the third spring 1122 is connected to the fourth support rod 1124 and the other end is connected to the fifth support rod 1125; one end of the fourth spring 1123 is connected to the fourth support rod 1124 and the other end is connected to the sixth support rod 1126; the fourth support rod 1125... The second end of 124 is fixed to the axis of the second rubber wheel 122 in the second rubber wheel set 12 along the first direction; the second end of the fifth support rod 1125 is fixed to the axis of the second rubber wheel 122 in the first rubber wheel set 12 along the first direction; the second end of the sixth support rod 1126 is fixed to the axis of the second rubber wheel 122 in the third rubber wheel set 12 along the first direction; the second locking component 1127 is fixed on the fourth support rod 1124 to limit the position of the second rotating shaft 1121 relative to the fourth support rod 1124.

[0058] Optionally, the second antenna straightening mechanism and the first antenna straightening mechanism have the same structure, that is, the second antenna straightening mechanism includes three rubber wheel sets arranged sequentially along the first direction; the force application component in the second antenna straightening mechanism is exactly the same as the force application component in the first antenna straightening mechanism.

[0059] This design allows for a simple, compact structure for both the first and second antenna straightening mechanisms, making them easy to carry and install. Aircraft cabin space is limited, and there are specific requirements for weight and balance. The first and second antenna straightening mechanisms provided in this application are particularly suitable for use in aircraft cabins.

[0060] Optionally, along the first direction, the distance between any two adjacent rubber wheel sets is greater than or equal to 1 times the antenna pitch and less than or equal to 1.5 times the antenna pitch. Since the antenna is formed by twisting together multiple strands of steel-clad metal antenna wire, the antenna pitch refers to the distance the antenna travels axially when a single strand of steel-clad metal antenna wire rotates one revolution. This arrangement allows the first and second antenna straightening mechanisms to achieve better straightening effects.

[0061] Figure 6 This is a schematic diagram of the structure of a defect detection module provided in an embodiment of this disclosure. See also... Figure 6The defect detection module includes a magnetization unit 21 and a magnetic field detection unit 22. The magnetization unit 21 is distributed along the circumference of the antenna 4. The magnetization unit 21 is used to form a saturation magnetization circuit so that the antenna 4 is saturated magnetized within the detection range. The magnetic field detection unit 22 is distributed along the circumference of the antenna 4 and its relative position to the magnetization unit 21 is fixed. The magnetic field detection unit 22 is used to detect the magnetic induction intensity value of the leakage magnetic field of the antenna 4. Both the magnetization unit 21 and the magnetic field detection unit 22 have air gaps with the antenna 4.

[0062] Figure 7 This is a schematic diagram showing the orientation of the defect detection module provided in an embodiment of this disclosure. See also... Figure 7 The direction along a straight line parallel to or coinciding with antenna 1 is the axial direction, i.e. Figure 7 In this context, the z-axis direction is the axial direction, which is the direction of antenna movement during the deployment and take-off phases. Within a plane perpendicular to the axial direction, the direction of any straight line passing through the center of a circle in that plane is radial, corresponding to the direction of r in cylindrical coordinates. Figure 7 The plane perpendicular to the axial direction, defined by the first direction x and the second direction y, is the polar coordinate plane. The origin of this polar coordinate plane can be the corresponding point of antenna 4 on this plane. Any straight line passing through the origin is radial, and the direction around the axial direction of antenna 4 is circumferential, corresponding to θ. Figure 7 The circle formed by the four intermediate antennas is circumferential. Figure 7 In the equation, the distance between point M and the z-axis is r, the distance between point M and the polar coordinate plane is z, and the angle between the line connecting the projection of point M onto the origin and the x-axis is θ. Then the coordinates of point M can be represented as M(r,θ,z).

[0063] Figure 8 This is a schematic diagram of the saturation magnetization circuit of an antenna with a defect-free surface, provided as an embodiment of this disclosure. Figure 9 This is a schematic diagram of a saturation magnetization circuit for an antenna with surface defects, provided in an embodiment of this disclosure. The magnetization unit 21 saturates the antenna 4 within the detection range, forming a saturation magnetization circuit. After forming the saturation magnetization circuit, the magnetic field detection unit 22 can detect the magnetic induction intensity value of the leakage magnetic field of the antenna 4. When there are no defects on the antenna surface, after the antenna 4 is magnetized, see [reference needed]. Figure 8 The magnetic field lines are all confined within antenna 4, with almost none escaping from the surface of antenna 4. The surface of antenna 4 within the detection range can be considered to contain only the background magnetic field. The magnetic flux density of the leakage magnetic field detected by magnetic field detection unit 22 should be within a certain range. (See also...) Figure 9If there are defects on the surface of antenna 4, these defects will cause changes in the magnetic permeability (magnetization reflects the degree of magnetization of a material in response to an applied magnetic field). Since the permeability at the defect is extremely low, the path of the magnetic field lines will change. Some lines will pass directly through the defect or bypass it inside antenna 4, while others will leave the surface of antenna 4, bypass the defect through the air, and re-enter antenna 4, creating a leakage magnetic field at the defect. This manifests as an abnormal magnetic flux density in the leakage magnetic field, and the magnetic flux density detected by the magnetic field detection unit 22 will change.

[0064] Optionally, the air gap between the permanent magnet and the antenna is greater than or equal to 2 mm and less than or equal to 10 mm. The purpose of this setting is to make the magnetic field lines in the air gap perpendicular to the interface between the permanent magnet and the air gap, and perpendicular to the interface between the antenna 1 and the air gap.

[0065] The yoke can be made of carbon steel or other highly magnetically permeable materials. This design ensures that the permanent magnet and antenna form a magnetization circuit while reducing the background magnetic field, thereby improving the defect detection sensitivity of the defect detection module.

[0066] In practice, there are various methods for arranging magnetization units, and this application does not limit this. Exemplarily, the defect detection module includes N magnetization units. Exemplarily, in... Figure 6 In this module, the defect detection module includes four magnetization units. See also... Figure 6 or Figure 8 Each magnetization unit 21 includes two permanent magnets 211 and an iron yoke 212; the two permanent magnets 211 are fixed on the same side of the iron yoke 212 at a predetermined distance along a first direction, and the magnetization directions of the two permanent magnets 211 are opposite; the included angle between two adjacent magnetization units 21 is equal to N is a positive integer greater than or equal to 2.

[0067] Furthermore, the defect detection module also includes a fixing unit; the fixing unit is used to fix the magnetization unit so that the relative position of the magnetization unit and the cabin is fixed.

[0068] There are various methods for setting up the fixed unit, and this application does not limit this. For example, Figure 10 This is a schematic diagram of the structure of a defect detection module provided in an embodiment of this disclosure. See also... Figure 10 The fixing unit 23 includes a first clamp 231, a second clamp 232 and a base plate 233; the first clamp 231 and the second clamp 232 are fixed to the base plate 233 opposite to each other.

[0069] Figure 11 for Figure 10 A schematic diagram of the first fixture. (See attached diagram.) Figure 10and Figure 11 The first clamp 231 has N first limiting slots 2311 and a first hole 2312 for the antenna to pass through on its surface near the second clamp 232. The N first limiting slots 2311 are symmetrically arranged relative to the first hole 2312. The second clamp has N second limiting slots and a second hole for the antenna to pass through on its surface near the first clamp; the N second limiting slots are symmetrically arranged relative to the second hole. The first limiting slots 2311 and the second limiting slots correspond one-to-one, and the corresponding first limiting slots 2311 and the second limiting slots are used to cooperate to fix a magnetizing unit 21; the first hole 2312 and the second hole are used for the antenna to pass through; the permanent magnet 211 is located on the side of the yoke 212 near the antenna 4.

[0070] This configuration keeps the magnetizing unit in a fixed position within the naval cabin, preventing fluctuations in the air gap between the magnetizing unit and the antenna, which could lead to inaccurate antenna defect detection. It also avoids contact between the magnetizing unit and the antenna, preventing damage and wear.

[0071] In practice, there are various specific arrangements for the magnetic field detection unit, and this application does not limit this. The magnetic field detection unit includes P sensor mounting plates arranged sequentially along a first direction, with multiple sensor mounting plates located between a first clamp and a second clamp; P is a positive integer greater than or equal to 1; each sensor mounting plate is provided with a third hole for the antenna to pass through; Q magnetic field detection sensors are arranged at the edge of the third hole, and the included angle between two adjacent magnetic field detection sensors is equal to... The projections of the magnetic field detection sensors in any two sensor mounting plates onto the standard plane are non-coincident, and the standard plane is perpendicular to the first direction. Optionally, P is a positive integer greater than or equal to 2;

[0072] Figure 12 and Figure 13 This is a schematic diagram of two sensor mounting plates provided in embodiments of this disclosure. It is assumed that the magnetic field detection unit includes two sensor mounting plates arranged sequentially along a first direction. See also... Figure 12 and Figure 13 Both sensor mounting plates have a third hole 241. In each sensor mounting plate, four magnetic field detection sensors 242 are installed along the edge of the third hole 241. The included angle between any two adjacent magnetic field detection sensors 242 on the same sensor mounting plate is 90°. Figure 14 To be Figure 12 and Figure 13 A schematic diagram projected onto the same plane. Figure 14 In this configuration, magnetic field detection sensors 242, filled with the same pattern, are located on the same sensor mounting plate. Figure 14It can be seen that no two magnetic field detection sensors 242 overlap.

[0073] In practice, if the number of magnetic field detection sensors is small, the detection range cannot cover all surfaces of the antenna. If the number of magnetic field detection sensors is large, due to the small antenna diameter (usually around 5mm), it is impossible to arrange all the magnetic field detection sensors on the same sensor mounting plate. By setting the magnetic field detection unit to include P sensor mounting plates, the P magnetic field detection sensors are essentially distributed across multiple sensor mounting plates to achieve the goal of covering all surfaces of the antenna.

[0074] Optionally, the inner diameters of the first, second, and third holes are larger than the diameter of the antenna; during use, the antenna does not come into contact with the inner walls of the first, second, and third holes. This design aims to prevent the antenna from rubbing against the inner walls of the first, second, or third holes during use, thus avoiding damage to the antenna surface.

[0075] Based on the above technical solutions, optionally, the airborne antenna defect detection device further includes a calculation module and an coded velocimeter; the coded velocimeter is disposed in the first antenna straightening mechanism and / or the second antenna straightening mechanism, and is used to detect the moving speed of the antenna; the calculation module is communicatively connected to the magnetic field detection sensor and the coded velocimeter, and is used to determine the location of the defect in the antenna based on the detection results of the magnetic field detection sensor and the detection results of the coded velocimeter. For example, Figures 2-5 In the first antenna straightening mechanism, an coded velocimeter 5 is installed.

[0076] Optionally, the calculation module can specifically be a computer. Specifically, the calculation module can determine the location of the defect in the antenna based on the following formula:

[0077]

[0078] Where v(t) is the moving speed of the antenna, Δt is the time interval of the feedback speed of the encoder velocimeter, and s is the distance between the defect position and the initial detection position, that is, the axial coordinate of the defect position.

[0079] Based on the above technical solutions, optionally, the airborne antenna defect detection device also includes an electromagnetic shielding mesh; the defect detection module is located within the shielding area of ​​the electromagnetic shielding mesh. Since the complex electromagnetic environment inside the aircraft may cause electromagnetic interference, by placing the defect detection module within the shielding area of ​​the electromagnetic shielding mesh, the influence of the complex electromagnetic environment inside the aircraft on the defect detection results can be suppressed using the electromagnetic shielding mesh.

[0080] Optionally, to further reduce possible clutter interference in the same frequency band, linear locally weighted linear regression smoothing or bandpass filtering algorithms may be considered when the calculation module determines the location of the defect in the antenna.

[0081] Optionally, the detection result of the magnetic field sensor is a magnetic flux density value. After obtaining the magnetic flux density value collected by the magnetic field sensor, the calculation module performs online moving average filtering on the magnetic flux density value. Online moving average filtering refers to smoothing the magnetic flux density signal during the detection process using a moving average filter. When performing online moving average filtering, weighted linear least squares or a first-order polynomial model can be used for local weighted linear regression smoothing.

[0082] In practice, the magnetic flux density value collected by the magnetic field detection sensor in this application varies with the antenna's feed distance. Those skilled in the art will understand that, using the airborne antenna defect detection device provided in this application, with distance as the independent variable and magnetic flux density as the dependent variable, a graph showing the relationship between magnetic flux density and antenna distance can be plotted. In this graph, the relationship between the magnetic flux density value and the antenna's feed distance is represented as a curve in a two-dimensional coordinate system. The online moving average filtering process is applied to this curve along the independent variable. Taking coordinate point x as an example, the smoothing formula used in this system is the following 2N+1-point locally weighted linear regression smoothing:

[0083]

[0084] Among them, B s B(x) represents the smoothed magnetic field strength, B(x) represents the original magnetic field measurement data of the magnetic field detection sensor, and Δx represents the axial displacement resolution of the antenna.

[0085] The airborne antenna defect detection device provided by the above technical solution can perform defect detection during aircraft flight, before aircraft-to-submarine communication (VLCC) is established, during the VLCC dual-towed antenna deployment phase, and after aircraft-to-submarine communication is established, during the VLCC dual-towed antenna retrieval phase. This setup does not increase the number of antenna deployments or retrievals required for defect detection; instead, it integrates defect detection of the antenna under test with the antenna's operational process, achieving online, real-time, and accurate detection along the entire antenna length, thus significantly reducing the probability of antenna damage. Furthermore, the airborne antenna defect detection device provided by the above technical solution integrates vibration reduction, speed measurement, and antenna straightening functions into one unit, greatly reducing the size of the airborne antenna defect detection device and facilitating its use on aircraft.

[0086] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0087] The above description is merely a specific embodiment of this disclosure, enabling those skilled in the art to understand or implement it. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not to be limited to the embodiments described herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An airborne antenna defect detection device, characterized in that, The airborne antenna defect detection device is configured on an aircraft. The device includes: a first antenna straightening mechanism, a defect detection module, and a second antenna straightening mechanism arranged sequentially along a first direction; the first direction is the same as or opposite to the movement direction of the antenna. Both the first antenna straightening mechanism and the second antenna straightening mechanism include a force application component and H rubber wheel sets arranged sequentially along the first direction; H is a positive integer greater than or equal to 2; Each of the rubber wheel sets includes a first rubber wheel and a second rubber wheel; the antenna contact surface of the first rubber wheel and the antenna contact surface of the second rubber wheel are both provided with grooves; the first rubber wheel and the second rubber wheel are opposite each other, and the grooves on the antenna contact surface of the first rubber wheel and the grooves on the antenna contact surface of the second rubber wheel are joined together to form an antenna movement channel; The force application component is used to apply force to the first rubber wheel and the second rubber wheel in each of the rubber wheel sets to control the size of the antenna movement channel and to limit the distance between two adjacent rubber wheel sets; The defect detection module includes a magnetization unit and a magnetic field detection unit; the magnetization unit is distributed circumferentially along the antenna; the magnetization unit is used to form a saturation magnetization circuit, so that the antenna is saturated magnetized within the detection range; the magnetic field detection unit is distributed circumferentially along the antenna, and its relative position to the magnetization unit is fixed; the magnetic field detection unit is used to detect the magnetic induction intensity value of the leakage magnetic field of the antenna; wherein, both the magnetization unit and the magnetic field detection unit have an air gap with the antenna.

2. The apparatus according to claim 1, characterized in that, Both the first antenna straightening mechanism and the second antenna straightening mechanism include three sets of rubber wheels arranged sequentially along the first direction; The force application assembly includes a first force application assembly and a second force application assembly; The first force application assembly includes a first rotating shaft, a first spring, a second spring, a first support rod, a second support rod, a third support rod, and a first locking component; The first support rod is provided with a first groove extending along the length direction of the first support rod; the first rotating shaft is disposed in the first groove and can slide along the extension direction of the first groove; the first end of the second support rod and the first end of the third support rod are both fixed on the first rotating shaft and can rotate around the first rotating shaft; one end of the first spring is connected to the first support rod and the other end is connected to the second support rod; one end of the second spring is connected to the first support rod and the other end is connected to the third support rod; the second end of the first support rod is fixed to the axis of the first rubber wheel in the second rubber wheel group counting from the first direction; the second end of the second support rod is fixed to the axis of the first rubber wheel in the first rubber wheel group counting from the first direction; the second end of the third support rod is fixed to the axis of the first rubber wheel in the third rubber wheel group counting from the first direction; the first locking component is fixed to the first support rod and is used to limit the position of the first rotating shaft relative to the first support rod; The second force application assembly includes a second rotating shaft, a third spring, a fourth spring, a fourth support rod, a fifth support rod, a sixth support rod, and a second locking component; The fourth support rod is provided with a second sliding groove extending along the length direction of the fourth support rod; the second rotating shaft is disposed in the second sliding groove and can slide along the extension direction of the second sliding groove; the first end of the fifth support rod and the first end of the sixth support rod are both fixed on the second rotating shaft and can rotate around the second rotating shaft; one end of the third spring is connected to the fourth support rod and the other end is connected to the fifth support rod; one end of the fourth spring is connected to the fourth support rod and the other end is connected to the sixth support rod; the second end of the fourth support rod is fixed to the axis of the second rubber wheel in the second rubber wheel group counting from the first direction; the second end of the fifth support rod is fixed to the axis of the second rubber wheel in the first rubber wheel group counting from the first direction; the second end of the sixth support rod is fixed to the axis of the second rubber wheel in the third rubber wheel group counting from the first direction; the second locking component is fixed to the fourth support rod and is used to limit the position of the second rotating shaft relative to the fourth support rod.

3. The apparatus according to claim 2, characterized in that, Along the first direction, the distance between any two adjacent rubber wheel sets is greater than or equal to 1 times the antenna pitch and less than or equal to 1.5 times the antenna pitch.

4. The apparatus according to claim 1, characterized in that, The defect detection module includes N magnetization units; each magnetization unit includes two permanent magnets and an iron yoke; the two permanent magnets are fixed to the same side of the iron yoke at a predetermined distance along the first direction, and the magnetization directions of the two permanent magnets are opposite; the included angle between two adjacent magnetization units is... N is a positive integer greater than or equal to 2; The defect detection module further includes a fixing unit; the fixing unit includes a first clamp, a second clamp, and a base plate; The first clamp and the second clamp are fixed to the base plate opposite to each other. The surface of the first clamp near the second clamp is provided with N first limiting grooves and a first hole for the antenna to pass through. The N first limiting grooves are symmetrically arranged with respect to the first hole. The surface of the second clamp near the first clamp is provided with N second limiting grooves and a second hole for the antenna to pass through. The N second limiting grooves are symmetrically arranged with respect to the second hole. The first limiting grooves and the second limiting grooves are one-to-one corresponding and are used to cooperate to fix one of the magnetizing units. The first hole and the second hole are used to pass through the antenna. The permanent magnet is located on the side of the yoke near the antenna.

5. The apparatus according to claim 4, characterized in that, The air gap between the permanent magnet and the antenna is greater than or equal to 2 mm and less than or equal to 10 mm.

6. The apparatus according to claim 4, characterized in that, The magnetic field detection unit includes P sensor mounting plates arranged sequentially along the first direction, with the P sensor mounting plates located between the first clamp and the second clamp; P is a positive integer greater than or equal to 1; Each of the sensor mounting plates is provided with a third hole through which the antenna passes; Q magnetic field detection sensors are arranged along the edge of the third hole, and the included angle between two adjacent magnetic field detection sensors is equal to The projections of the magnetic field detection sensors in any two of the sensor mounting plates onto the standard plane do not coincide, the standard plane is perpendicular to the first direction, and Q is a positive integer greater than or equal to 2.

7. The apparatus according to claim 6, characterized in that, The inner diameters of the first hole, the second hole, and the third hole are larger than the diameter of the antenna; during use, the antenna does not contact the inner walls of the first hole, the second hole, and the third hole.

8. The apparatus according to claim 6, characterized in that, It also includes a computing module and an encoding speed meter; The coded speed measuring device is disposed in the first antenna straightening mechanism and / or the second antenna straightening mechanism, and is used to detect the moving speed of the antenna; The computing module is communicatively connected to the magnetic field detection sensor and the coded velocimeter, and is used to determine the location of the defect in the antenna based on the detection results of the magnetic field detection sensor and the detection results of the coded velocimeter.

9. The apparatus according to claim 1, characterized in that, It also includes electromagnetic shielding mesh; The defect detection module is located within the shielding area of ​​the electromagnetic shielding mesh.

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