Circumferential magnetizing device for connecting frame assembly of main landing gear of aircraft

Abstract

The utility model provides a circumferential magnetizing device for a connecting frame assembly of a main landing gear of an airplane. The two connecting assemblies are used for being connected to the two fork-shaped connecting lugs on the two frame supporting columns respectively. Each connecting assembly comprises a core shaft, a pressing nut, an insulating sleeve and two insulating pads, wherein the core shaft and the pressing nut are made of conductive materials, and the insulating sleeve and the two insulating pads are made of insulating materials. And the insulating sleeve is sleeved on the mandrel and penetrates through the fork-shaped lug hole so as to circumferentially magnetize the connecting frame assembly together with the compression nut. The two insulation pads surround the central spindle on the two sides of the fork-shaped connecting lug and are pressed to the fork-shaped connecting lug under the action of the central spindle and the pressing nut. The two connecting assemblies are connected between the two fork-shaped connecting lugs through a puller nut and a connecting core rod which are made of conductive materials so that the fork-shaped connecting lug holes can be magnetized in the circumferential direction. According to the device, the original four-time electrification magnetization is simplified into two-time magnetization, the part clamping is simple and convenient, and the magnetization efficiency is greatly improved; meanwhile, electrodes of the magnetic powder flaw detector are not in direct contact with the parts, so that the parts can be prevented from being burnt.

Description

Technical Field

[0001] The utility model belongs to the technical field of magnetic powder detection, and in particular relates to a circumferential magnetization device for a connecting frame component of an aircraft main landing gear. Background Art

[0002] Before being put into use, the aircraft main landing gear connecting frame assembly requires circumferential magnetization of all visible surfaces to inspect for longitudinal defects. However, the assembly, consisting of a frame shaft and two frame struts, is complex in shape and heavy. Current circumferential magnetization methods lack any auxiliary tools, and the electrode plates used in magnetic particle inspection machines are two parallel metal plates. To circumferentially magnetize the entire assembly, the two frame struts and the frame shaft must be clamped with the electrode plates three times, followed by three rounds of magnetization. The forked lug holes on the frame struts are then magnetized using the central conductor method, for a total of four rounds of magnetization. The entire magnetization process requires the assembly to be hoisted onto the magnetic inspection machine using a crane, resulting in numerous steps, difficult clamping, and low magnetization efficiency. Furthermore, the arc-shaped clamping area of the frame struts used for circumferential magnetization using the current method has limited contact area with the magnetic particle inspection machine's electrode plates, making it very susceptible to burns. Utility Model Content

[0003] The utility model aims to solve the problems in the prior art of requiring four passes of magnetization when circumferentially magnetizing an aircraft main landing gear connecting frame assembly to inspect for longitudinal defects, resulting in difficult clamping operations, low magnetization efficiency, and the tendency to cause parts burns during magnetization. A circumferential magnetization device for an aircraft main landing gear connecting frame assembly is provided.

[0004] To achieve the above objectives, the technical solutions provided by this utility model are:

[0005] A circumferential magnetization device for a connecting frame assembly of an aircraft main landing gear comprises two connecting assemblies, a tightening nut and a connecting core rod;

[0006] Two connecting assemblies are respectively used to connect to two fork-shaped lugs on two frame struts in an aircraft main landing gear connecting frame assembly. Each connecting assembly includes a core shaft and a compression nut made of a conductive material, an insulating sleeve and two insulating washers made of an insulating material. The core shaft is used to contact an electrode plate of a magnetic particle flaw detector. The insulating sleeve is mounted on the core shaft and coaxially passes through the fork-shaped lug holes of the fork-shaped lugs to circumferentially magnetize the connecting frame assembly together with the compression nut. The two insulating washers are used to prevent current from flowing through the connecting frame when the two fork-shaped lug holes are circumferentially magnetized. The two insulating washers surround the core shaft on both sides of the fork-shaped lug and are compressed to the fork-shaped lugs by the action of the core shaft and the compression nut.

[0007] The tightening nut and the connecting core rod are made of conductive material and are used to connect the two connecting components between the two fork-shaped ears so as to circumferentially magnetize the fork-shaped ear holes of the frame pillars together with the connecting components. The tightening nut is screwed onto one of the two core shafts in the two connecting components, and the two ends of the connecting core rod are respectively connected to the tightening nut and the other of the two core shafts.

[0008] Furthermore, the core shaft is a stepped shaft and includes a large diameter section and a small diameter section. The large diameter section is located outside the fork-shaped lug, and the clamping nut is screwed on the small diameter section inside the fork-shaped lug.

[0009] Furthermore, a first flat-bottomed hole is provided on the end surface of the small-diameter section for receiving a connecting core rod.

[0010] Furthermore, one end of the tightening nut is screwed onto one of the two core shafts, and the other end is provided with a second flat-bottom hole for receiving the connecting core rod.

[0011] Furthermore, the tightening nut is provided with a flange protruding radially outwards to facilitate the screwing of the tightening nut.

[0012] Furthermore, the core shaft, the pressing nut, the tightening nut and the connecting core rod are all made of brass.

[0013] Furthermore, the insulating sleeve and the insulating pad are made of polytetrafluoroethylene.

[0014] The advantages of the utility model are:

[0015] The present invention provides a circumferential magnetization device for an aircraft main landing gear connecting frame assembly. Each of the two frame struts of the aircraft main landing gear connecting frame assembly has a connecting assembly. The mandrel of each mandrel can be inserted through the forked lug holes of the forked lugs on the frame struts. When circumferentially magnetizing a part to inspect for longitudinal defects, only a single clamping operation is required to contact the electrode plates of the magnetic particle detector with the two mandrels. This simple operation allows for a single pass of magnetization of the entire frame assembly. Furthermore, since the magnetic particle detector electrodes do not come into direct contact with the part, part burns are avoided. Furthermore, by tightening the nut, connecting the mandrel, and installing the insulating pad, the central conductor of the forked lug hole of the frame strut can be magnetized. Consequently, the device reduces the original four-pass magnetization to just two, simplifies part clamping, and significantly improves magnetization efficiency.

[0016] 2. The device is provided with an insulating sleeve and an insulating pad made of electrically insulating material. The insulating sleeve can prevent the core shaft from contacting the fork-shaped ear hole, thereby avoiding sparks and burning the inner wall of the hole when power is turned on. In addition, when magnetizing by the central conductor method, the insulating sleeve and the insulating pad can prevent current from flowing through the frame assembly, protecting the parts from being burned. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and / or other features and advantages of the present invention will become more easily understood through the following description with reference to the accompanying drawings, which are not drawn to scale and in which some features are exaggerated or reduced to show details of specific components. In the accompanying drawings:

[0018] Figure 1 It is a schematic three-dimensional diagram of the circumferential magnetization device of the aircraft main landing gear connecting frame assembly of the present invention;

[0019] Figure 2 This is a cross-sectional view of the structure of the device in use. Figure 1 , showing the installation structure of a connection component;

[0020] Figure 3 This is a cross-sectional view of the structure of the device in use. Figure 2 , showing the installation structure of another connection component;

[0021] Figure 4 This is a schematic three-dimensional diagram of the device of the present invention when electromagnetic current is applied;

[0022] Figure 5 It is a schematic three-dimensional diagram of the device of the present invention when performing central conductor method magnetization.

[0023] In the figure: 1-first core shaft, 1A-first flat-bottom hole; 2-first insulating sleeve; 3-first clamping nut; 4-first insulating pad; 5-second core shaft; 6-second insulating sleeve; 7-second clamping nut; 8-second insulating pad; 9-top clamping nut; 10-connecting core rod; 100-part to be inspected, 101-frame support, 102-fork-shaped ear. DETAILED DESCRIPTION

[0024] The present invention will be described in detail below with reference to the accompanying drawings by means of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is only for the purpose of illustration and is not intended to limit the present invention.

[0025] This utility model provides a circumferential magnetization device for an aircraft main landing gear connecting frame assembly, used to clamp components during circumferential magnetization of the aircraft main landing gear connecting frame assembly to inspect for longitudinal defects. The device can complete circumferential magnetization of the aircraft main landing gear connecting frame assembly in one operation. The magnetic particle inspection electrode avoids direct contact with the component, preventing burns. This device also simplifies magnetization of the center conductor of the fork-shaped lug hole, improving production efficiency and work quality.

[0026] Reference Figures 1 to 4As an exemplary embodiment of the present invention, the circumferential magnetization device of the aircraft main landing gear connecting frame assembly may include two connecting assemblies, which are respectively used to connect to two fork-shaped lugs 102 on two frame struts 101 in the test object 100, that is, in the aircraft main landing gear connecting frame assembly.

[0027] Each connection assembly includes a core shaft and a compression nut made of conductive material, and an insulating sleeve and two insulating pads made of insulating material. Figure 2 As shown, one of the two connecting assemblies includes a first core shaft 1, a first insulating sleeve 2, a first pressing nut 3 and two first insulating pads 4. Figure 3 As shown, the other of the two connection assemblies includes a second core shaft 5, a second insulating sleeve 6, a second compression nut 7, and two second insulating washers 8. The first core shaft 1, the first compression nut 3, the second core shaft 5, and the second compression nut 7 are all made of existing conductive materials, particularly brass. The first insulating sleeve 2, the first insulating washer 4, the second insulating sleeve 6, and the second insulating washer 8 are all made of existing electrical insulating materials, particularly polytetrafluoroethylene.

[0028] The first core shaft 1 and the second core shaft 5 are used to contact the two electrode plates of the magnetic particle detector. The first insulating sleeve 2 and the second insulating sleeve 6 can be hollow cylindrical, respectively sleeved on the corresponding core shaft and coaxially passed through the two fork-shaped ear holes of the fork-shaped ear 102, so as to circumferentially magnetize the connection frame assembly together with the two compression nuts, such as Figure 4 The insulating sleeve on the mandrel is used to prevent the mandrel from contacting the fork-shaped lug hole, which could cause sparks and burns to the inner wall of the hole when power is applied. Secondly, when the center conductor is magnetized, the insulating sleeve and insulating pad prevent current from flowing through the frame assembly, thus avoiding burns to parts.

[0029] The first insulating pad 4 and the second insulating pad 8 are used for Figure 5 As shown, the connection frame prevents current from flowing through the forked lug holes when the center conductor method is used to magnetize them. It can be a thin plate with a circular or rectangular cross-section, etc., and wraps around the corresponding core shaft on both sides of the forked lug 102. Two insulating pads are pressed against the forked lug 102 by the corresponding core shaft and the compression nut. For example, in one of the connection components, a first insulating pad 4 is pressed against the outside of the forked lug 102 by the first core shaft 1, while another first insulating pad 4 is pressed against the inside of the forked lug 102 by the first compression nut 3. It should be understood that the insulating pads are deformable. That is, when installed on the core shaft, the insulating pads do not need to be placed on the core shaft from both ends. Instead, once the core shaft is inserted into the forked lug 102, the insulating pads can be deformed by force and wrap around the core shaft.

[0030] In some embodiments, one or both of the first mandrel 1 and the second mandrel 5 can be stepped shafts, each comprising a large-diameter section and a small-diameter section. During use, the large-diameter sections of both mandrels are located outside the forked lug 102, while the first and second compression nuts 3 and 7 are screwed onto the small-diameter sections of the mandrels, respectively, inside the forked lug 102. The end surfaces of the small-diameter sections can be machined with first flat-bottomed holes 1A to facilitate the installation of connecting mandrels 10, and the outer circumferences can be threaded to facilitate connection with the clamping nuts 9, as will be described in detail below.

[0031] The magnetizing device provided by the utility model further comprises a tightening nut 9 and a connecting core rod 10 .

[0032] The tightening nut 9 and the connecting core rod 10 are made of the same conductive material as the core shaft material. Figure 5 As shown, two connecting assemblies are connected between two fork lugs 102 of two frame struts 101 in order to circumferentially magnetize the fork lug holes of the frame struts together with the connecting assemblies.

[0033] The tightening nut 9 is screwed onto one of the two core shafts in the two connecting components, and is shown in the figure as being screwed onto the second core shaft 5. The two ends of the connecting core rod 10 are respectively connected to the tightening nut 9 and the other of the two core shafts (shown as the first core shaft 1).

[0034] To facilitate the installation of the connecting mandrel 10, as Figure 2 It is clear that the end surfaces of the small diameter sections of the two mandrels, in particular the end surface of the small diameter section of the other of the two mandrels, i.e. the first mandrel 1, can be provided with a first flat bottom hole 1A for receiving the connecting mandrel 10. Figure 3 It is clearly seen that one end of the locking nut 9 can be screwed onto the thread on the outer circumference of one of the two core shafts, i.e., the second core shaft 5, and the other end can be provided with a second flat-bottomed hole for receiving the connecting core rod 10. Preferably, the locking nut 9 can be provided with a radially outwardly protruding flange, which can be grasped when the locking nut 9 is screwed to install and fix the connecting core rod 10, thereby facilitating the screwing of the locking nut 9.

[0035] Reference Figure 4 and Figure 5 The following is an example of the method of using the circumferential magnetization device for the aircraft main landing gear connecting frame assembly provided by the present invention:

[0036] The first step, such as Figure 4 As shown, circumferential magnetization of the entire frame assembly is performed, including:

[0037] Step 1: Insert the first core shaft 1 into the first insulating sleeve 2 from the left side of the forked ear hole of the left frame support, and insert the second core shaft 5 into the second insulating sleeve 6 from the right side of the forked ear hole of the right frame support. This will insulate the two core shafts from the inner hole of the frame assembly ear to prevent burns due to contact sparks;

[0038] Step 2: Install the first clamping nut 3 and the second clamping nut 7 on the first core shaft 1 and the second core shaft 5 respectively and tighten them. Close contact can smoothly pass a large current.

[0039] In step 3, the two core shafts mounted on the frame assembly are clamped with two electrode plates of a magnetic particle inspection machine, and then power is applied. The current passes through the frame shaft of the inspected object 100 and the two frame pillars 101 in the direction indicated by arrow I, completing the circumferential magnetization of the entire frame assembly.

[0040] The second step is Figure 5 As shown, the circumferential magnetization of the fork-shaped lug holes of the frame pillar is performed, including:

[0041] Step 1: Loosen the compression nuts on the two core shafts, insert the first insulating pad 4 and the second insulating pad 8 into the two sides of the forked lugs of the two frame pillars, and then tighten the two compression nuts to insulate the entire device from the frame assembly.

[0042] Step 2: Screw the tightening nut 9 into the second core shaft 5 until it stops, insert one end of the connecting core rod 10 into the flat bottom hole on the right side of the first core shaft 1, and the other end into the flat bottom hole on the left side of the tightening nut 9, then unscrew the tightening nut 9 until it is tightened, so that the two core shafts can be connected;

[0043] Step 3: Use two electrode plates of the magnetic particle inspection machine to clamp the two core shafts installed on the frame assembly, and then turn on the power. The current passes through the entire device in the direction indicated by arrow I to complete the circumferential magnetization of the ear hole.

[0044] As described above, the present invention provides a connection assembly for each of the two frame struts of an aircraft main landing gear connecting frame assembly. The mandrel of each mandrel can be passed through the forked lug holes of the forked lugs on the frame struts. When circumferentially magnetizing a part to inspect for longitudinal defects, only one clamping operation is required to bring the electrode plates of the magnetic particle detector into contact with the two mandrels. This simple operation allows for magnetization of the entire frame assembly in one pass. Furthermore, since the magnetic particle detector electrodes do not come into direct contact with the part, part burns are avoided. Furthermore, by tightening the nut, connecting the mandrel, and installing the insulating pad, the center conductor of the forked lug hole of the frame strut can be magnetized. Therefore, the device reduces the original four-pass magnetization to only two passes, simplifies part clamping, and significantly improves magnetization efficiency.

[0045] Finally, it should be noted that the features mentioned and / or illustrated in the above description of the exemplary embodiments of the present invention may be combined in the same or similar manner into one or more other embodiments, and may be combined with or replace the features of other embodiments. The technical solutions obtained by such combination or replacement shall also be deemed to be included in the scope of protection of the present invention.

Claims

1. A circumferential magnetization device for an aircraft main landing gear connecting frame assembly, characterized in that: The invention comprises two connecting components, and also comprises a tightening nut and a connecting core rod; The two connecting assemblies are respectively used to connect to two fork-shaped lugs on two frame struts in the aircraft main landing gear connecting frame assembly. Each connecting assembly includes a core shaft and a compression nut made of a conductive material, and an insulating sleeve and two insulating washers made of an insulating material. The core shaft is used to contact the electrode plate of a magnetic particle flaw detector. The insulating sleeve is sleeved on the core shaft and coaxially passes through the fork-shaped lug hole of the fork-shaped lug to circumferentially magnetize the connecting frame assembly together with the compression nut. The two insulating washers are used to prevent current from flowing through the connecting frame when the two fork-shaped lug holes are circumferentially magnetized. The two insulating washers are surrounded by the core shaft on both sides of the fork-shaped lug and are compressed to the fork-shaped lug under the action of the core shaft and the compression nut. The tightening nut and the connecting core rod are made of conductive material and are used to connect the two connecting components between the two fork-shaped ears so as to circumferentially magnetize the fork-shaped ear holes of the frame pillar together with the connecting components. The tightening nut is screwed onto one of the two core shafts in the two connecting components, and the two ends of the connecting core rod are respectively connected to the tightening nut and the other of the two core shafts.

2. The circumferential magnetization device for the aircraft main landing gear connecting frame assembly according to claim 1, characterized in that: The core shaft is a stepped shaft and includes a large diameter section and a small diameter section. The large diameter section is located outside the fork-shaped lug, and the clamping nut is screwed on the small diameter section inside the fork-shaped lug.

3. The circumferential magnetization device for the aircraft main landing gear connecting frame assembly according to claim 2, characterized in that: A first flat-bottomed hole is provided on the end surface of the small-diameter section for receiving the connecting core rod.

4. The circumferential magnetization device for the aircraft main landing gear connecting frame assembly according to claim 1 or 2, characterized in that: One end of the tightening nut is screwed onto one of the two core shafts, and the other end is provided with a second flat-bottom hole for receiving the connecting core rod.

5. The circumferential magnetization device for the aircraft main landing gear connecting frame assembly according to claim 1 or 2, characterized in that: The tightening nut is provided with a flange protruding radially outwards to facilitate the screwing of the tightening nut.

6. The circumferential magnetization device for the aircraft main landing gear connecting frame assembly according to claim 1 or 2, characterized in that: The core shaft, the pressing nut, the top nut and the connecting core rod are all made of brass.

7. The circumferential magnetization device for an aircraft main landing gear connecting frame assembly according to claim 1 or 2, characterized in that: The insulating sleeve and the insulating pad are made of polytetrafluoroethylene.

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